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NASA Contract Report 177_89
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https://ntrs.nasa.gov/search.jsp?R=19880004720 2020-07-28T10:18:17+00:00Z
TABLE OF CONTENTS
PART 2APPENDICES
APPENDIX A:
APPENDIX B:
APPENDIX C:
APPENDIX D:
APPENDIX E:
DAST ARW-2 AERODYNAMIC, INERTIA AND THRUST DATA
DAST ARW-2 OUTBOARD AILERON SERVOVALVE RELOCATIONSTUDY
DAST ARW-2 FINAL FLUTTER SUPPRESSION SYSTEMPERFORMANCEDATA
DAST ARW-2 SENSITIVITY ANALYSIS DATA
DAST ARW-2 AUTOMATIC CONTROL SYSTEM (ACS) ANDAUTOMATIC FLIGHT CONTROL SYSTEM (AFCS) ROOT LOCl
17
55
101
136
176
LIST OF FIGURES
FIGURE
1
2
3
8
.
10
11
12
13
14
15
16
17
LONGITUDINAL STABILITY DERIVATIVES AND TRIM COEFFICIENTS
LATERAL-DIRECTIONAL STABILITY DERIVATIVES
LIFT COEFFICIENT VERSUS ANGLE OF ATTACK,LAUNCH CONDITION
PITCHING MOMENT COEFFICIENT VERSUS ANGLE OF ATTACKpLAUNCH CONDITION
LIFT COEFFICIENT VERSUS ANGLE OF ATTACK,MLA TEST CONDITION
PITCHING MOMENT COEFFICIENT VERSUS ANGLE OF ATTACK,MLA TEST CONDITION
LIFT COEFFICIENT VERSUS ANGLE OF ATTACK,MLA DESIGN CONDITION
PITCHING MOMENTCOEFFICIENT VERSUS ANGLE OF ATTACK,MLA DESIGN CONDITION
LIFT COEFFICIENT VERSUS ANGLE OF ATTACK,GLA TEST CONDITION
PITCHING MOMENTCOEFFICIENT VERSUS ANGLE OF ATTACK,GLA TEST CONDITION
LIFT COEFFICIENT VERSUS ANGLE OF ATTACKpGLA DESIGN CONDITION
PITCHING MOMENT COEFFICIENT VERSUS ANGLE OF ATTACK,GLA DESIGN CONDITION
LIFT COEFFICIENT VERSUS ANGLE OF ATTACK,HIGH ALTITUDE CONDITION
PITCHING MOMENTCOEFFICIENT VERSUS ANGLE OF ATTACK,HIGH ALTITUDE CONDITION
LIFT COEFFICIENT VERSUS ANGLE OF ATTACK,CRUISE CONDITION
PITCHING MOMENTCOEFFICIENT VERSUS ANGLE OF ATTACK,CRUISE CONDITION
LIFT COEFFICIENT VERSUS ANGLE OF ATTACK,MAXIMUM DYNAMIC PRESSURE CONDITION
18
19
2O
21
22
2.3
24
25
26
27
28
29
3O
31
32
33
34
FIGURE
18
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21
22
23
24
25
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32
33
34
35
36
LIST OF FIGURES (CONTINUED)
PITCHING MOMENT COEFFICIEICT VERSUS ANGLE OF AI-FACK,MAXIMUM DYNAMIC PRESSURE CONDITION
MOMENT OF INERTIA
DRAG COEFFICIENT VERSUS ANGLE OF AI-FACK AT
MACH: 0.60, WITH SPEEDBRAKES
DRAG COEFFICIENT VERSUS ANGLE OF ATTACK AT
MACH: 0.70, WITH SPEEDBRAKES
DRAG COEFFICIENT VERSUS ANGLE OF AI-I'ACKAT
MACH: 0.80, WITH SPEEDBRAKES
DRAG COEFFICIENT VERSUS ANGLE OF ATTACK AT
MACH: 0.90, WITH SPEEDBRAKES
LIFT COEFFICIENT VERSUS ANGLE OF ATTACK AT
MACH: 0.60, WITH SPEEDBRAKES
LIFT COEFFICIENT VERSUS ANGLE OF AI-I'ACKAT
MACH: 0.70, WITH SPEEDBRAKES
LIFT COEFFICIENT VERSUS ANGLE OF ATTACK AT
MACH: 0.80, WITH SPEEDBRAKES
LIFT COEFFICIENT VERSUS ANGLE OF ATTACK AT
MACH: 0.90, WITH SPEEDBRAKES
PITCHING MOMENT COEFFICIENT VERSUS ANGLE OF ATTACK
AT MACH: 0.60, WITH SPEEDBRAKES
PITCHING MOMENT COEFFICIENT VERSUS ANGLE OF AI-I'ACK
AT MACH: 0.70, WITH SPEEDBRAKES
PITCHING MOMENT COEFFICIENT VERSUS ANGLE OF AI-rACK
AT MACH: 0.80, WITH SPEEDBRAKES
PITCHING MOMENT COEFFICIENT VERSUS ANGLE OF ATTACK
AT MACH: 0.90, WITH SPEEDBRAKES
THRUST DATA FOR 80 PERCENT ENGINE RPM
THRUST DATA FOR 85 PERCENT ENGINE RPM
THRUST DATA FOR 90 PERCENT ENGINE RPM
THRUST DATA FOR 95 PERCENT ENGINE RPM
THRUST DATA FOR 100 PERCENT ENGINE RPM
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4O
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42
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5O
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52
53
FIGURE
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4O
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51
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53
LIST OF FIGURES (C(]NTINUED)
DAST ARW-2 OUTBOARD AILERON SERVOVALVE RELOCATION STUDY
SYMMETRIC ELASTIC MODE
MACH: 0.80, ALTITUDE:
SYMMEIIRIC ELASTIC MODE
MACH: 0.83, ALTITUDE:
SYMMETRIC ELASTIC MODE
MACH: 0.86, ALTITUDE:
SYMMETRIC ELASTIC MODE
MACH: 0.83, ALTITUDE:
SYMMETRI C ELASTIC MODE
MACH: 0.86, ALTITUDE:
SYMMETRIC ELASTIC MODEMACH: 0.91, ALTIIIJDE:
DAMPING AND FREQUENCY,
2,000 FEET, UNSCALED EOM
DAMPING AND FREQUENCY,3,000 FEET, UNSCALED EOM
DAMPING AND FREQUENCY,
4,500 FEET, UNSCALED EOM
DAMPING AND FREQUENCY,
12,000 FEET, UNSCALED EOM
DAMPING AND FREQUENCY,
15,000 FEET, UNSCALED EOM
DAMPING AND FREQUENCY,8,000 FEET, UNSCALED EOM
ANTISYMMETRIC ELASTIC MODE DAMPING AND FREQUENCY
WITH PARAIVETER SCHEDULING, MACH: 0.86,
ALTITUDE: 4,250 FEET, UNSCALED EOM
ANTISYMMETRIC ELASTIC MODE DAMPING AND FREQUENCY
WITH PARAMETER SCHEDULING, MACH: 0.83,
ALTITUDE: 12,000 FEET, UNSCALED EOM
ANTISYMMETRIC ELASTIC MODE DAMPING AND FREQUENCY
WITH PARAMETER SCHEDULING, MACH: 0.86,
ALTITUDE: 15,000 FEET, UNSCALED EOM
ANTISYMMETRI C ELASTIC MODE DAMPING AND FREQUENCY
WITH PAPjMVETER SCHEDULING, MACH: 0.91,
ALTITUDE: 8,000 FEET,
SYMMETRIC FLLFFTER MODE 0.80
SYMMETRIC FLUTTER MODE 0.83
SYMMETRIC FLUT'IIERMODE 0.86
SYMMETRIC FLLFFTER MODE 0.91
ANTISYMMETRIC FLUTTER MODE DAMPING, MACH:
ANI ISYMMETIRIC FLUTTER MODE DAMPING, MACH:
UNSCALED EOM
DAMPING, MACH:
DAMPING, MACH:
DAMPING, MACH:
DAMPING, MACH:
0.80
0.83
56
102
103
104
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FIGURE
54
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LIST OF FIGURES (CONTINUED)
ANTISYMMETRIC FLUTTER MODE DAMPING, MACH:
ANTISYMMETRIC FLUTTER MODE DAMPING, MACH:
SYMMETRIC FLUTTER MODE DAMPING, ALTITUDE:
0.86
0.91
15,000 FEET
ANTISYMMETRIC FLUTTER MODE DAMPING, ALTITUDE: 15,000 FEET
SYMMETRIC FLUTTER MODE DAMPING, ALTITUDE: 12,000 FEET
ANTISYMMETRIC FLUTTER MODE DAMPING, ALTITUDE= 12,000 FEET
PHASE-GAIN ROOT LOCUS OF SYMMETRIC FSS, NOMINAL SYSTEM,
MACH: 0.80, ALTITUDE= 2,000 FEET 124
PHASE-GAIN ROOT LOCUS OF SYMMETRIC FSS, NOMINAL SYSTEM,MACH: 0.83, ALTITUDE: 3,000 FEET 125
PHASE-GAIN ROOT LOCUS OF SYMMETRIC FSS, NOMINAL SYSTEM,
MACH: 0.83, ALTITUDE: 12,OO0 FEET 126
PHASE-GAIN ROOT LOCUS OF SYMMETRIC FSS, NOMINAL SYSTEM,MACH: 0.86, ALTITUDE: 4,250 FEET 127
PHASE-GAIN ROOT LOCUS OF SYMMETRIC FSS, NOMINAL SYSTEM,MACH: 0.86, ALTITUDE: 15,000 FEET 128
PHASE-GAIN ROOT LOCUS OF SYMMETRIC FSS, NOMINAL SYSTEM,MACH: 0.91, ALTITUDE: 8,000 FEET 129
PHASE-GAIN ROOT LOCUS OF ANTISYMMETRIC FSS, NOMINAL SYSTEM,MACH: 0.80, ALTITUDE: 2,000 FEET 130
PHASE-GAIN ROOT LOCUS OF ANTISYMMETRIC FSS, NOMINAL SYSTEM,
MACH: 0.83, ALTITUDE: 3,000 FEET 131
PHASE-GAIN ROOT LOCUS OF ANTISYMMETRIC FSS, NOMINAL SYSTEM,
MACH: 0.83, ALTITUDE: 12,000 FEET 132
PBASE-GAIN ROOT LOCUS OF ANTISYMMETRIC FSS, NOMINAL SYSTEM,
MACH: 0.86, ALTITUDE: 4,250 FEET 133
PHASE-GAIN ROOT LOCUS OF ANTISYMMETRIC FSS, NOMINAL SYSTEM,MACH: 0.86, ALTITUDE: 15,000 FEET 134
PHASE-GAIN ROOT LOCUS OF ANTISYMMETRIC FSS, NOMINAL SYSTEM,MACH: 0.91, ALTITUDE: 8,000 FEET 135
118
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120
121
122
123
FIGURE
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8O
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89
LIST OF FIGURES (CONTINUED)
SYMMETRIC SENSOR LOCATION SENSITIVITY 138
ANTISYMMETRIC SENSOR LOCATION SENSITIVITY .141
NOTCH FILTER TRANSFER FUNCTION FOR SENSITIVITY STUDIES 144
SYMMETRIC NOTCH FILTER SENSITIVITY TO NOTCH FREQUENCY,85 RAD. NOTCH 145
SYMMETRIC NOTCH FILTER SENSITIVITY TO NOTCH FREQUENCY,170 RAD. NOTCH 146
SYMMETRIC NOTCH FILTER SENSITIVITY TO NOTCH MAGNITUDE,85 RAD. NOTCH 147
SYMMETRIC NOTCH FILTER SENSITIVITY TO NOTCH MAGNITUDE,170 RAD. NOTCH 148
AN'I'ISYMIVETRIC NOTCH FILTER SENSITIVITY TO NOTCH FREQUENCY,110 RAD. NOTCH 149
ANTISYMMETRIC NOTCH FILTER SENSITIVITY TO NOTCH FREQUENCY,230 RAD. NOTCH 150
ANTISYMMETRIC NOTCH FILTER SENSITIVITY TO NOTCH MAGNITUDE,110 RAD. NOTCH 151
ANTISYMMETRIC NOTCH FILTER SENSITIVITY TO NOTCH MAGNITUDE,230 RAD. NOTCH 152
PHASE-GAIN ROOT LOCUS OF SYMMETRIC FSS, NOMINAL SYSTEM 153
PHASE-GAIN ROOT.LOCUS OF SYMMETRIC FSS WITH AR-25SERMOVALVE 154
ROOT LOCUS OF SYMMETRIC AND ANTISYMMETRIC FSS WITHSERIES 30 SERVOVALVE 155
PHASE-GAIN ROOT LOCUS OF ANTISYMMETRIC FSS, NOMINAL SYSTEM 156
PHASE-GAIN ROOT LOCUS OF ANTISYMMETRIC FSS WITH AR-25SERVOVALVE 157
PHASE-GAIN ROOT LOCUS OF SYMMETRIC FSS, EFFECTS OFUNCOMPENSATING ACTUATOR 158
PHASE-GAIN ROOT LOCUS OF ANT ISYMMETRIC FSS, EFFECTS OFUNCOMPENSATINGACTUATOR 159
FIGURE
90
91
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98
99
100
101
102
103
104
105
106
LIST OF FIGURES (CONTINUED)
SYMMETRIC FSS SENSITIVITY TO SURFACE-ACTUATOR MODE
CHANGES
PHASE-GAIN ROOT LOCUS OF SYMMETRIC FSS, EFFECTS OF A 20%
SURFACE-ACTUATOR MODE FREQUENCY INCREASE
PHASE'GAIN ROOT LOCUS OF SYMMETRIC FSS, EFFECTS OF A 20%
SURFACE-ACTUATOR MODE FREQUENCY DECREASE
SYMMETRIC FSS SENSITIVITY TO PRESSURE FEEDBACK GAIN
REDUCTION
PHASE-GAIN ROOT LOCUS OF SYMMETRIC FSS, EFFECTS OF A 30%
PRESSURE FEEDBACK MODE FREQUENCY REDUCTION
ANTISYMMETRIC FSS SENSITIVITY TO PRESSURE FEEDBACK GAIN
REDUCTI ON
PHASE-GAIN ROOT LOCUS OF ANTISYMMETRIC FSS WITH A 30
PERCENT PRESSURE FEEDBACK GAIN REDUCTION
HINGE MOMENT SENSITIVITY, OUTBOARD SERVOACTUATORGAIN AND PHASE RESPONSE @ 23.8 HZ
EFFECT OF HINGE MOMENT ON OUTBOARD SERVOACTUATOR
AMPLITUDE FREQUENCY RESPONSE
EFFECT OF HINGE MOMENT ON OUTBOARD SERVOACTUATOR
PHASE FREQUENCY RESPONSE
EFFECT OF MAXIMUM AIDING HINGE MOMENT ON OUTBOARDSERVOACTUATOR
EFFECT OF HINGE MOMENT ON SYMMETRIC FSS
PHASE-GAIN ROOT LOCUS OF SYMMETRIC FSS, MAXIMUMHINGE MOMENT AIDING (230 IN-LBS)
EFFECT OF HINGE MOMENT ON ANTISYMMETRIC FSS,UNCOMPENSATED ACTUATOR
PHASE-GAIN ROOT LOCUS OF ANTISYMMETRIC FSS,MAXIMUM HINGE MOMENT AIDING (230 IN-LBS)
EFFECT OF ACS ON FUSELAGE MODE SYMMETRIC AIRPLANE
ROOT LOCI FIGURE IDENTIFICATION
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FIGURE
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L IST OF F IGURES (CONTINUED)
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASICAIRPLANE FOR FOI:_/ARDC.G. MLA TEST CONDITION
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH
PCS CLOSED FOR FOI:_/ARDC.G. MLA TEST CONDITION
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS
AND GLA CLOSED FOR FORWARD C.G. MLA TEST CONDITION
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCSCLOSED FOR FORWARD C.G. MLA TEST CONDITION
DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSED
FOR FORWARD C.G. MLA TEST CONDITION
DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA
CLOSED FOR FORWARD C.G. MLA TEST CONDITION
DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS
CLOSED FOR FORWARD C.G. MLA TEST CONDITION
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASICAIRPLANE FOR AFT C.G. MLA TEST CONDITION
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS
CLOSED FOR AFT C.G. MLA TEST CONDITION
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCSAND GLA CLOSED FOR AFT C.G. MLA TEST CONDITION
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS
CLOSED FOR AFT C.G. MLA TEST CONDITION
DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSED
FOR AFT C.G. MLA TEST CONDITION
DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA
CLOSED FOR AFT C.G. MLA TEST CONDITION
DAST ARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCI WITH
RSS, PCS AND GLA STABILIZER LOOPS CLOSED FOR AFT C.G.MLA TEST CONDITION
DAST ARW-2 GLA STABILIZER LOOP GAIN/PHASE ROOT LOCI
WITH RSS, PCS AND GLA AILERON LOOPS CLOSED FOR AFTC.G. MLA TEST CONDITION
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207
FIGURE
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123
124
125
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133
134
135
136
LIST OF FIGURES (CONTINUED)
DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS
CLOSED FOR AFT C.G. MLA TEST CONDITION
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC
AIRPLANE FOR FORWARD C.G. GLA TEST CONDITION
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCSCLOSED FOR FORWARD C.G. GLA TEST CONDITION
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCSAND GLA CLOSED FOR FORWARD C.G. GLA TEST CONDITION
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS
CLOSED FOR FORWARD C.G. GLA TEST CONDITION
DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSEDFOR FORWARD C.G. GLA TEST CONDITION
DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA
CLOSED FOR FORWARD C.G. GLA "rEST CONDITION
DAST ARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCI WITH
RSS, PCS AND GLA STABILIZER LOOPS CLOSED FOR FORWARDC.G. GLA TEST CONDITION
DAST ARW-2 GLA STABILIZER LOOP GAIN/PHASE ROOT LOCI
WITH RSS, PCS AND GLA AILERON LOOPS CLOSED FORFORWARD C.G. GLA TEST CONDITION
DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS
CLOSED FOR FORWARD C.G. GLA TEST CONDITION
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASICAIRPLANE FOR AFT C.G. GLA TEST CONDITION
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCSCLOSED FOR AFT C.G. GLA TEST CONDITION
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS
AND GLA CLOSED FOR AFT C.G. GLA TEST CONDITION
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCSCLOSED FOR AFT C.G. GLA TEST CONDITION
DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSEDFOR AFT C.G. GLA TEST CONDITION
210
212
214
216
218
220
222
224
227
230
232
234
236
238
240
FIGURE
137
138
139
140
141
142
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144
145
146
147
148
149
150
151
LIST OF FIGURES (CONTINUED)-
DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLACLOSED FOR AFT C.G. GLA TEST CONDITION
DAST ARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCI WITH
RSS, PCS AND GLA STABILIZER LOOPS CLOSED FOR AFT C.G.GLA TEST CONDITION
DAST ARW-2 GLA STABILIZER LOOP GAIN/PHASE ROOT LOCI
WITH RSS, PCS AND GLA AILERON LOOPS CLOSED FOR AFTC.G. GLA TEST CONDITION
DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS
CLOSED FOR AFT C.G. GLA TEST CONDITION
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC
AIRPLANE FOR FORWARD C.G. LAUNCH CONDITION
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCSCLOSED FOR FORWARD C.G. LAUNCH CONDITION
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS
AND GLA CLOSED FOR FORWARD C.G. LAUNCH CONDITION
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS
CLOSED FOR FORWARD C.G. LAUNCH CONDITION
DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSEDFOR FORWARD C.G. LAUNCH CONDITION
DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLACLOSED FOR FORWARD C.G. LAUNCH CONDITION
DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS
CLOSED FOR FORWARD C.G. LAUNCH CONDITION
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASICAIRPLANE FOR AFT C.G. LAUNCH CONDITION
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCSCLOSED FOR AFT C.G. LAUNCH CONDITION
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS
AND GLA CLOSED FOR AFT C.G. LAUNCH CONDITION
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS
CLOSED FOR AFT C.G. LAUNCH CONDITION
242
244
247
250
252
254
256
258
260
262
264
266
268
270
272
I0
FIGURE
152
153
154
155
156
157
158
159
160
161
162
163
164
165
166
LIST ON FIGURES (CONTINUED)
DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSEDFOR AFT C.G. LAUNCH CONDITION
DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLACLOSED FOR AFT C.G. LAUNCH CONDITION
DAST ARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCI WITH
RSS, PCS AND GLA STABILIZER LOOPS CLOSED FOR AFT C.G.LAUNCH CONDITION
DAST ARW-2 GLA STABILIZER LOOP GAIN/PHASE ROOT LOCI
WITH RSS, PCS AND GLA AILERON LOOPS CLOSED FOR AFTC.G. LAUNCH CONDITION
DAST ARW-2 I_3S SYSTEM GAIN/PHASE ROOT LOCI WITH RSSCLOSED FOR AFT C.G. LAUNCH CONDITION
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASICAIRPLANE FOR FORWARD C.G. HIGH ALTITUDE CONDITION
DAST ARW'2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS
CLOSED FOR FORWARD C.G. HIGH ALTITUDE CONDITION
DASTARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCSAND GLA CLOSED FOR FORWARD C.G. HIGH ALTITUDE
CONDITION
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCSCLOSED FOR FORWARD C.G. HIGH ALTITUDE CONDITION
DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSEDFOR FORWARD C.G. HIGH ALTITUDE CONDITION
DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA
CLOSED FOR FORWARD C.G. HIGH ALTITUDE CONDITION
DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSSCLOSED FOR FORWARD C.G. HIGH ALTITUDE CONDITION
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC
AIRPLANE FOR AFT C.G. HIGH ALTITUDE CONDITION
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCSCLOSED FOR AFT C.G. HIGH ALTITUDE CONDITION
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCSAND GLA CLOSED FOR AFT C.G. HIGH ALTITUDE CONDITION
274
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281
284
286
288
290
292
294
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298
300
302
304
II
FIGURE
167
168
169
170
171
172
173
174
175
176
177
178
179
180
181
LIST OF FIGURES (CONTINUED)
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS
CLOSED FOR AFT C.G. HIGH ALTITUDE CONDITION
DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSED
FOR AFT C.G. HIGH ALTITUDE CONDITION
DAST ARW-2 PCS GAIN/PHASE RooT LOCI WITH RSS AND GLACLOSED FOR AFT C.G. HIGH ALTITUDE CONDITION
DAST
RSS,HIGH
ARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCI WITHPCS AND GLA STABILIZER LOOPS CLOSED FOR AFT C.G.
ALTITUDE CONDITION
DAST
WITH
C.G.
ARW-2 GLA STABILIZER LOOP GAIN/PHASE ROOT LOCI
RSS, PCS AND GLA AILERON LOOPS CLOSED FOR AFTHIGH ALTITUDE CONDITION
DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCl WITH RSSCLOSED FOR AFT C.G. HIGH ALTITUDE CONDITION
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC
AIRPLAI_Z FOR FORWARD C.G. CRUISE CONDITION
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS
CLOSED FOR FORWARD C.G. CRUISE CONDITION
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCSAND GLA CLOSED FOR FORWARD C.G. CRUISE CONDITION
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS
CLOSED FOR FORWARD C.G. CRUISE CONDITION
DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSED
FOR FORWARD C.G. CRUISE CONDITION
DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLACLOSED FOR FORWARD C.G. CRUISE CONDITION
DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS
CLOSED FOR FORWARD C.G. CRUISE CONDITION
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC
AIRPLANZ FOR AFT C.G. CRUISE CONDITION
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCSCLOSED FOR AFT C.G. CRUISE CONDITION
306
308
310
312
315
318
320
322
324
326
328
330
332
334
336
12
FIGURE
182
183
184
185
186
187
188
189
190
191
192
193
194
LIST OF FIGURES (CONTINUED)
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCSAND GLA CLOSED FOR AFT C.G. CRUISE CONDITION
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS
CLOSED FOR AFT C.G. CRUISE CONDITION
DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSEDFOR AF-F C.G. CRUISE CONDITION
DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLACLOSED FOR AFT C.G. CRUISE CONDITION
DAST ARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCI WITH
RSS, PCS AND GLA STABILIZER LOOPS CLOSED FOR AFT C.G.CRUISE CONDITION
DASTW ITH
C.G.
ARW-2 GLA STABILIZER LOOP GAIN/PHASE ROOT LOCI
RSS, PCS AND GLA AILERON LOOPS CLOSED FOR AFTCRUISE CONDITION
DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS
CLOSED FOR AFT C.G. CRUISE CONDITION
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC
AIRPLANE FOR FORWARD C.G. MAXIMUM DYNAMIC PRESSURECONDITION
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCSCLOSED FOR FORWARD C.G. MAXIMUM DYNAMIC PRESSURE
CONDITION
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCSAND GLA CLOSED FOR FORWARD C.G. MAXIMUM DYNAMIC
PRESSURE CONDITION
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS
CLOSED FOR FORWARD C.G. MAXIMUM DYNAMIC PRESSURECONDITION
DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSED
FORFORWARD C.G. MAXIMUM DYNAMIC PRESSURE CONDITION
DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLACLOSED FOR FORWARD C.G. MAXIMUM DYNAMIC PRESSURE
CONDITION
338
340
342
344
346
349
352
354
356
358
360
362
364
13
FIGURE
195
196
197
198
199
200
201
202
203
204
LIST OF FIGURES (CONCLUDED)
DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS
CLOSED FOR FORWARD C.G. MAXIMUM DYNAMIC PRESSURE
CONDITION
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC
AIRPLAI_E FOR AFT C.G. MAXIMUM DYNAMIC PRESSURE
CONDITION
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS
CLOSED FOR AFT C.G. MAXIMUM DYNAMIC PRESSURE CONDITION
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS
AND GLA CLOSED FOR AFT C.G. MAXIMUM DYNAMIC PRESSURE
CONDITION
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS
CLOSED FOR AFT C.G. MAXIMUM DYNAMIC PRESSURE CONDITION
DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSED
FOR AFT C.G. MAXIMUM DYNAMIC PRESSURE CONDITION
DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA
CLOSED FOR AFT C.G. MAXIMUM DYNAMIC PRESSURE CONDITION
DAST ARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCI WITH
RSS, PCS AND GLA STABILIZER LOOPS CLOSED FOR AFT C.G.MAXIMUM DYNAMIC PRESSURE CONDITION
DAST
W ITH
C.G.
ARW-2 GLA STABILIZER LOOP GAIN/PHASE ROOT LOCI
RSS, PCS AND GLA AILERON LOOPS CLOSED FOR AFTMAXIMUM DYNAMIC PRESSURE CONDITION
DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS
CLOSED FOR AFT C.G. MAXIMUM DYNAMIC PRESSURE CONDITION
366
368
370
372
374
376
378
38O
383
386
14
INTRODUCTION
This volume contains the appendices for Boeing document D500-I0897-I,"Design Verification and Fabrication of Active Control Systems for theDAST ARW-2 High Aspect Ratio Wing", the final report summarizing the workaccomplished under Contract NASI-16010.
Appendix A contains data defining the aerodynamics and inertias used inthe airplane and control systems linear analyses and nonlinear simulation.A study is presented in Appendix B that compares servoactuator bench testresults to analysis and investigates various factors that affect actuatorperformance and stability. Appendix C contains data which summarizes theairplane stability and performance with the final flutter suppressionsystem. The data contained in Appendix D shows stability and performancesensitivity to variation in the dynamics and location of the control systemcomponents. Appendix E contains data that shows the relative gain andphase stability margins of each individual ACS and AFCS feedback loop andthe compatibility of the combined loops.
15
(This page intentionally left blank)
16
APPENDIX A
DAST ARW-2 AERODYNAMIC, INERTIA AND THRUST DATA
This appendix containsthe aerodynamic and inertia data used in airplane andcontrol systems linear analyses and non-linear simulation. It also containsspeed brake and thrust data used in the determination of speed brake require-ments.
List of data included:
• Longitudinal derivatives
25 percent MAC C.G.8 flight conditions
• Lateral-directional derivatives
25 percent MAC C.G.8 flight conditions
• Non-linear CL and CM versus alpha
8 flight conditions
• Moments of inertia
3 weight-C.G, combinations, body axis
• Plots of CD versus alpha with speed brakes
• Plots of thrust versus altitude for constant Mach numbers and percentRPM
PRECEDING PAGE BLANK NOT FILM_
pR]_C_DI_G PAGE BLANK NOT FILMED
APPENDIX A
18
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•
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I
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'$" ,,..-I II0"
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• _ _ _ ......"I I I ! I I I I
Oh _,O 0") O'_ (3*', ,--4 _0 GO GO _ _ IY) _ C) Q ('%1 _ 0 _) C) 0e_J C_ O') Q C) _ 0'_ C) C) 0 C_ O _ 0 0
I I I I I I I I I
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19
APPENDIX A
• MACH: 0.40e ALTITUDE: 15,000 FEET• STABILIZER: 0.0
;, ,; , . l ..... , ,1..;-_ .L .: .:-',:: .... _'" _ .... : : _ " : _ _4_'_---_'_
- i t ; .... : t: ; ]"
T:: : :.......... :.-t---:-:-:-] ........ : -I .... _--,_:"-:: 't-:-::-:--:t.:..-1:--,:./-:: - t ..... :...... , -
r-"T _'::-__ ! t ' _ I ; t ! r' ' i ....• l I • ] : :t : I..:/" I : I. i ' r :li i ' : :
" : ' " ' : '"''I......... r ::,:: ........ :l "':'"I:"::: ; , : : " " "_F:: ..... 17_I:........ : -:i '' _ ": :
, , . _ : : , .... • .: ; ' • . . ,, : :
- : :: :T-T:/ ::::::-::r::::: ....
...........r- / .....i ......:::__:.......:._LI_ET.._:._:.G..6_ : _ _. ..........................__
COEFFICIENT: " I . : :/-_ : . : . ;• ::-i:! .....F-::::: .... :.:-"9:: .......:.....".... r :_ .... i ...... :
:;::;: ::4i::::::::::::::::::::::........:::::::
-: : .:_._.,::____0_.._ : : :......_ : ,,-:.......
.................:......; ....:-..:......._:_.:....:.......:_......:-:--
......:-_- i-: '---0_2-- ', ; - ; : , ;--_ _ ' --_---; I : ::' : :.: .-:. I : " : . :
.......... J i-_:_:-_--: .... ,--:.!:--:-:--::--:=:::.::-:-..:-:--÷:--.:-:-_.--:-_..
, !/: : .:-:: , I. _ : .: • : , r-...........f "':....! "::m" ":....I.......:": ..............r" : "':.......:"':" , :...._-
.:.-l.::.---..--..i....P:::-:.I:-:l::-i}-_:l=-::.{--:.::--::-.4-+--i--::-::-::-:: ! q : : : -' .': 1 .,. .I::: '. " ' i " _. ; i " ,
• , I .... t ........ _ ;
FIGURE 3
LIFT COEFFICIENT VERSUS ANGLE OF ATTACK, LAUNCH CONDITION
2O
_G_NAL PAGE 15
_OR QUAL[_
APPENDIX A ORIGINAL PAGE IS
POOR QUALITY
• MACH: 0.40
• ALTITUDE: 15,000 FEET• STABILIZER: 0.0
t + : : L
: _ i ., ! :+"
+
• : + _ + !
............ i-o! • +,
}..... :........ +....... :_. +I . :
-8 :.6 -+ .-2 ........ i+::+.i+__4+} "
FIGURE 4
PITCHING MOMENT COEFFICIENT VERSUS ANGLE OF ATTACK, LAUNCH CONDITION
21
APPENDIX A
• MACH: 0.42
• ALTITUDE: 10,000 FEET
• STABILIZER: 0.0
t
I _::__ _ i___ ::_I_" i__ _-!" -if:I-.L__ i ii-iI :i-I - -h:.i.__-_ _ 4"----i......
.......' : -_ ;-_, ._' I ! .I _ I: I : ! ' '...._..... .....:---;=--r--'.:--;--".-: T
I .....•"__:I _I ....:_:I.....:_I::i_:Y:_::b._I._:_ .
- -_ " -=_ " -_-_t--t--_
--!'--_m_-_-_d_N_-_"'-'--iLIF_:___ _I_____:::...._.....'--i,................., :........ ;.....".....I -----:_--I _-:--:.... - -
_ " _ . : ' -- ._; : i: :1! : i, :_ I ' i ; :
i _ _ ;..: ..I....:--I-.$_ ..........._ ......;.........: "....
i: _ . ._ " ...... , ".....:t._...._ .. . :!......./....:..:....._......_--...._..... _....;.............:..-
- :i-.:-_.'/ : i---! ; ,! --_------=...........; : i "UF : : i:: " _ , _ •
' : --/-; • : ' i :_i..: .......'.... _ _:-_": "-:-'_........_ !-i: "_-::' ,
-8. -6._.-4/.,'-Z-. : ...... :2. i..g ...... 6 .... 8 .:i.10. 12
.....i.....', =/'_ _ANC___O£_ATI,_.X,_.I_EGI_EES1____._
.....___/_ _,_-,, .. :. ....,.... . .....: J i :..I. :.... . ._ . ..:.._......_....._.
....... _" "_,_.... I " -t::"! ............"" t ". .... _""I ' ": .... ' _ '
• _I . ! V _ ; ." :. : : i .....
• :::::' ': _ I ," I : ! i__ i, :: " ; I :i _ " i ' '
• _ L._! ....... I.... ::..__:... :. ,: ......... _......... ,i ..:..:_; .......'i ...... : _ i" : " I : I ' ] _ : i " ' "
......... _-----G .... L_O.6! : : !
FIGURE 5
LIFT COEFFICIENT VERSUSANGLE OF ATTACK, MLA TEST CONDITION
22//
!
APPENDIX A
• MACH: 0°42
• ALTITUDE: 10,000 FEET• STABILIZER: 0.0
I[. ,
' _ ' _ i i ._0.08-.i ........{._.:_.M:...
-- E • ; " -f- ........:..........
_ii i!....i....i i _ i _ i __
...!-.-'-;--;MOMEtCT--->_I.:._t4- - , ........
.----4]_-:--.L-_ -._----L _ " ---._.4'..... :----
/i ........... ;........ :]............... , .......
-=-o .-, -= . i:i_'_ = ,2-i
• • ." i . _ _ • i , i _ '" ! :. 0.02' : i !---_.'! i ,--_ ' "......] .....i.-:] ....i......[......_.,ii i ....
FIGURE 6
PITCHING MOMENT COEFFICIENT VERSUS ANGLE OF ATTACK, MLA TEST CONDITION
23
APPENDIX A
• MACH: 0.35
• ALTITUDE: SEA LEVEL
• STABILIZER: 0.0
" :.... ;-i .........:t-''•F_p ...... -! ........{.... T.... :.:-T!t ....... 7-: .......... :-::t : . ; " /: '; i J , : _ - ; :
.....,.......--/........--e-._-t- i ii--_ .i..........._--:......"!.....' /_ .....: ....I:--_....÷.......i....---',,......i.....i.....;_..i. if _.i._L t : { _,:. I __i _ _. i ....._-_I: i- ' .:i-- _: I : _ : __
...._ _:._._ ,:i::,_4 ._ _I! _ ;:i i- ,i:i,i i_.__
i i !. i i_::_ , ;!;ii : I- _; I _:-i_, i" 7.:!....f i-_;i •:::77t!!7:77-7!7-7:...:77:!_]--77-:t::: :77-F-::7t771!7:i---7-:i-
" r: _',w# i I,_ ........... < : 'f ............ I . t .....
FIGURE 7
LIFT COEFFICIENT VERSUS ANGLE OF ATTACK, MLA DESIGN CONDITION
24
APPENDIX AORIGINAL P[_ JS
OF POOR QUALrrY
• MACH: 0.35
• ALTITUDE: SEA LEVEL
• STABILIZER: 0.0
: \; : _ ° i .... . : _ l : t i ' ! I
i. :! \i _:_:F': _ !-i _ i ! \ i ! :,
____.z._NTZ_____ - :.........____..,-..___: ; _ .,'........: ._.......
--.I:COEFFICIENT-_-:..................._.....:--4..............._-.._...........J......!
_........:-!....._:!'!:_-_X)q_.-!_.....!:........:I-_".'1f-tl;...._....___.._____ .___..____., : ?...! .T_/----_-
................ l " [ .......................
-8...-6 ..-;4.:::-2:.-..._.i:...21..i:.-i!::!.:.._...:.:8_._.]0. 12,
" ' i
FIGURE 8
PITCHING MOMENT COEFFICIENT VERSUS ANGLE OF ATTACK, MLA DESIGN CONDITION
25
APPENDIX A
i MACH: 0,70
e ALTITUDE: 15,000 FEET
• STABILIZER: 0.0
L
I I• , t: _ I i
, . ; . i t . > , t: +. : : ; " + !
; " : .... ;" . I , ...... t t ; ....
_i_:._.jL!FT_L --L--dM-_.+.........4--
i COEFFI]CIENT ! "___L::_; ' _ _
•_ _..::.i/....i":.t _ _ i : ! ."_ " + ", .... T < _ ..... i •
_-B :-_6 _. ......... 2. _ 4...... 6.... B...... io 12
:....._ii: ,.....!............._ : :-..j-.:-.:•........._-:! :--,-.¸•.¸i¸•....___7_ i•: • _ : i..... _e:.e_ .... : :. ."-i: ' , : "_......
! I ._ ; 1 ; : ; !
-I" _t ......!....:'+T-:-......._.............._-_:._t .........!::.-:,: ......:] t: , ! .... ' :. : : "
..... : { : ........_:::_:-7,;;7:7::j:_:::7!-::....:--,.7:............:!::-::i-
FIGURE 9
LIFT COEFFICIENT VERSUS ANGLE OF ATTACK, GLA TEST CONDITION
26
APPENDIX AORIGIN;_L __c
OF POOR QUALITY
• MACH: 0.70
• ALTITUDE: 15,000 FEET• STABILIZER: 0.0
- I ...... c;....... _r._ ;. , _., --:'-,-
.... z....... [PI;TCHtNG i--:.
.... _ ! MO_M]ZNT.COEFFI_IEN! i
.o ...................... ,.........
i....._2.....
I _ I : |
-:.................- -0-,04-
............ i ....................
.!
-_- i:! I t _, 7---:_ _ t-_ i _ ! _I̧ ¸ i"'7"1:'T:I" _ T....... Z .... ?.... I" - '/" :........
° i t _. ;i ; i :: ]
,__: .......... ; -: .... : .... ; ........ ..... _...... ; ..
, .
............. f ' _.
} :
....T ............................! ; : ; , ! i i
• i " I + " -....
_-8...-.'6..:_,iI.:i.;2,.i!...(J.L_i:i._i.;i..,41,!.::gi..;_..8.::;::.7jLO::,12_.
_._ _,, N.GLE_Q . t_C____E_S_L4_;,_: i i. !..: _.i ......: _.i.-.i.#:_i :. I :.:i..:I T . .J:. I ; -
FIGURE 10
PITCHING MOMENT COEFFICIENT VERSUS ANGLE OF ATTACK, GLA TEST CONDITION
27
APPENDIX A
I MACH: 0.60• ALTITUDE: 7,000 FEET• STABILIZER: 0.0
......... i
< i'_ .... i---_-:. . ! ! : i , ! . _ -
: i i-'-i-,_ i I i_.L i:I i_ . _ • T-- o
.... i I --_-_,_: i.--iI ! !-:? !._ ! L____L......
, ; _ .... ! ] ' ! i I : _ i _
' " ; ' : ...........'_!-il :!/IZ i:::1:i'!_-I-r ......... i. ......T....+: _ !' T: "
#
.z ............. iCOEFFIClIENT ......... ,......... :_ . ,.... .................
:__"1=-=r-!-7--T:":!.....i ::]57.7;;.Z_.
.............__!/_i [___A,_,E_.,._.<_(._s_____i .........
...................--- .'-_,:.2-
i / .......,
, . ,
_..,I i " " : :i " '. ; i
! ....
i " i . IUI_
..t 1_..!.......... _ . _
7 ; 7 i i i' : i......f--r •.........._ , _ :........ ! '"; .I '-_
: i ; i
;! i ' i I ......i
I
. ] Il
( : i, i
FIGURE 11
LIFT COEFFICIENT VERSUS ANGLE OF ATTACK, GLA DESIGN CONDITION
28
APPENDIX A
OF' POOR QUALITy
• MACH: 0.60
• ALTITUDE: 7,000 FEET• STABILIZER: 0.0
' ' , ........... _ ...... i .... i 1 ....... i
: ; i i _ . i ,i .: t ! _ ,i: i _ ! :: F!I i
_ "i_d " " i ..... _k:_ ...._ .... _.... _.... i
i
\
-i ...... hITCIilNG;;i' :..................... MOMENTr................... L..................... \
i .....::.ii:].... ;' \........................................... i........ T.......... i ......... { ............... 2
..i!-::]'"_......!-.-:-.i........._.....L,,.
................... ---- .......0-.-02-- .... _ " ' -- _[
" " ;.......!.......................:..I .. : ......i
_-.L ] ' " ............
I
........ I ..........
.......i__ ,__ A_T___.._._(_1±._________......
FIGURE 12
PITCHING MOMENT COEFFICIENT VERSUS ANGLE OF ATTACK, GLA DESIGN CONDITION
29
APPENDIX A
• MACH: 0o70• ALTITUDE: 50,000 FEETe STABILIZER: 0.0
........... _ " " _ ...... T " "T ...... _ 71 -'-$ "
._--T----T-.---_-_T-_._-IT'__ k_._._.... .,._-.
--_-_. _ _o_q--__--_ _--,
,.:_.........._. LI.E'3"...... ; • : ..:_...i __.
COEFFICIENT ___ ;;..: _ _,
!, _; _ i i-I-.- : I _, I _ _
4 ---+/-_----_'I _ i . i ,,-_ ..... --:---
. ._ ....... _ ...... _ ...... .'.......... i....... _. .
A_AIIIACJL_I !DeGI_ES)_ .....
.... T--T_O:; : _ : . : : :. .. : • ,,
i_ni_ .; : i : ! :• :. ........... : .............. ! ............... L_" ...... !_.__. ! .:L.;. .........
FIGURE 13
LIFT COEFFICIENT VERSUS ANGLE OF ATTACK, HIGH ALTITUDE CONDITION
30
APPENDIX A
............. MOME_-ICOEFF_-IOIE
FIGURE 14
PITCHING MOMENT COEFFICIENT VERSUS ANGLE OF ATTACK, HIGH ALTITUDE CONDITION
31
APPENDIX A
• MACH: 0.80
• ALTITUDE: 46,800 FEET
• STABILIZER: 0.0
i i.L - " .........
" i
FIGURE 15'
LIFT COEFFICIENT VERSUS ANGLE OF ATTACK, CRUISE CONDITION
32
APPENDIX A
• MACH: 0°80
• ALTITUDE: 46,800 FEET• STABILIZER: 0.0
..... i
OF' POOR QUAL/Ty
I : I 1
K I .... :" -'T-
!
FIGURE 16
PITCHING MOMENT COEFFICIENT VERSUS ANGLE OF ATTACK, CRUISE CONDITION
33
APPENDIX A
• MACH: 0.86
• ALTITUDE: 15,000 FEET
,I STABILIZER: 0.0
!
FIGURE 17
LIFT COEFFICIENT VERSUS ANGLE OF ATTACK, MAXIMUM DYNAMIC PRESSURE CONDITION
34
APPENDIXA
• MACH: 0.86o ALTITUDE: 15,000 FEET• STABILIZER: 0.0
! . i : !: _ i .:-/ X.F" i::::i!._i!_i : i :_ !, --!......_..!-..÷--:-.--i.-+_l-._L_i:.- !---i-:--:_.---÷-_......_------ -:-.-
..........._-_........,....-7........:-._......,_........i-.\!.-i.........!-......-_--',_ ! _,.._ i,,t_,,_:-i-:!" ' .f . i t..':i _ _ : ;
._ ..........._#__,_----r_.; t-_--_..-_--_--: ...,........_......._.................................................._...._.,............,........._.
, : , _ _ " t _I : : _: " _-:": t :1i_i' i..: ;
....... " " "...... : " , t" :...."r ....... : " "
..........r..................io-. ..... .............PITCHING:,:; ........'....'............--T" I" " ; ] I
'. t. I .... _ ! ,
...._......COEFF-IIOIENel....i......:--i:T!.......::-:l"-:;-::i......!, *.......'T " _ ;" I " 'I ...... < ..... !......._- " -'--_---_06;-:: ! : " : -
.........I.:_....__...z......._....7-;TT;;I7 i
I !
i ; 2 i
.................. : ....... _l: "_" i_'-:...." ......
! i!............: '. ":" "'T';......
..... ' } : i " '-_-04-' _-_ _ ...... ,.............
i{ I i
I ! : i, I .... ' .... / , " . " .....
.:Z..::..,.7¢..._..:'_i...L._i_.._iID 12..
ANGItF!CiF A_TTACK_(D.F_:-, . , _ES]____._.
-::"-I....: I: .....I::""I........!II.......
ORIGINAL _''.... ""
OF POOR QUALITY
FIGURE 18
PITCHING MOMENTCOEFFICIENT VERSUS ANGLE OF ATTACK,MAXIMUM DYNAMIC PRESSURE CONDITION
35
APPENDIX A
GROSS
WEIGHT
(LBS)
C.G.
(%MAC)
*MOMENT OF INERTIA (SLUG-FT 2)
IXX Iyy IZZ IXZ
2500 19.93 163.5 2802.0 2286.3 20.25
2350 27.40 163.3 2173.8 2236.4 22.54
2200 32.75 163.1 2146.4 2210.5 24.16
*BODY AXIS
FIGURE 19
MOMENTS OF INERTIA
36
APPENDIX A
ORIGIN,'%L F_,_.,_ {3
OF POOR Q_ALITY
°"22I...:.:,jS'_Ei_I_I3R-A'K,_S........_::J_:_-_::_-_i_--/--_:!-!_-!::- ............---__ _ 4:---__-- _..:.:..........I_2o o........ -_!-_i_-:_._-_:.:-:_?i--_---.........o.2o 400.... _i_ci!:-i"::;:.,-__;.i171_::
500
0.18
0.16
- _ 600 ...... -_"z:..-_- _ __7-:
0.12
DRAGCOEFFICIENT
0.10
0.08
0.06
0.04
0.02
I
1 2 3 4 5 6 7 8
ANGLE OF ATTACK (DEGREES)
FIGURE 20
DRAG COEFFICIENT VERSUS ANGLE OF ATTACK AT MACH: 0.60, WITH SPEEDBRAKES
37
APPENDIX A
ORJG£NAE PAGE IS
DR I_)OR QUALITY
DRAG•COEFFICIENT
0.10
ANGLE OF ATTACK (DEGREES)
FIGURE 21
DRAG COEFFICIENT VERSUS ANGLE OF ATTACK AT MACH: 0.70, WITH SPEEDBRAKES
38
APPENDIX A
ORIGINAL PAGE IS
OF POOR QUALITY
0.22
0.20
0.18
0.16
0.14
0.04
............ :.-: -: :: _.-
5 6 7 8
ANGLE OF ATTACK (DEGREES)
FIGURE 22
DRAG COEFFICIENT VERSUS ANGLE OF ATTACK AT MACH: 0.80, WITH SPEEDBRAKES
39
APPENDIX A
0.22
0.2C
0.18
0.16
0.14
0.12 .........
DRAG "
COEFFICIENT _.0.I0 " : ...........I
0.08
0.06
0.04
0.02
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ANGLEOF ATTACK(DEGREES)
FIGURE 23
DRAG COEFFICIENT VERSUS ANGLE OF ATTACK AT MACH: 0,90, WITH SPEEDBRAKES
4O
ORIGI'NAL PAGE IS
OF POOR QUALITY.
APPENDIX A
ORIGINAL PAGE I_
OF POOR QUALITY
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LIFTCOEFFICIENT
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::_:-=================================00 I 2 6 7 83 4 5
ANGLE OF ATTACK (DEGREES)
FIGURE 24
LIFT COEFFICIENT VERSUS ANGLE OF ATTACK AT MACH: 0°60, WITH SPEEDBRAKES
41
APPENDIX A
ORIGINAL PAGE IS
OF.. POOR QUALITY
0,8 ........................................
0.4 ........
I 2 3 4 5 6 7
ANGLE OF ATTACK (DEGREES)
FIGURE 25
LIFT COEFFICIENT VERSUS ANGLE OF ATTACK AT MACH: 0.70, WITH SPEEDBRAKES
42
APPENDIX A
ORIG!NAL PAGE IS
OF POOR QUALm.
LIFTCOEFFICIENT
ANGLE OF ATTACK (DEGREES)
FIGURE 26
LIFT COEFFICIENT VERSUS ANGLE OF ATTACK AT MACH: 0.80, WITH SPEEDBRAKES
43
APPEND I X A
" " - : ........ T": ...............
FIGURE 27
LIFT COEFFICIENT VERSUS ANGLE OF ATTACK AT MACH: 0.90, WITH SPEEDBRAKES
44
APPENDI X A
ORIGINAL PAGE ISOF POOR QUALITY
:: : _:--- SPEEDBRAKES0.3
:- .._- oo20 °
400
500
I:=,: .........
- .... ::':-i 600
PITCHING
MOMENT 0
FIGURE 28
PITCHING MOMENT COEFFICIENT VERSUS ANGLE OF ATTACK AT MACH:
WITH SPEEDBRAKES
0.60,
45
APPENDIX A
o!dGLNAL PAGE IS
l )OR QUA.U'r
o.3!
0.2
0.1
PITCHING
MOMENT 0
COEFFICIENT
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FIGURE 29
PITCHING MOMENT COEFFICIENT VERSUS ANGLE OF ATTACK AT MACH:
WITH SPEEDBRAKES
0.70,
46
APPENDIX A
• . _. ,_ ,.J
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PITCHINGMOMENT
COEFFICIENT
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FIGURE 30
PITCHING MOMENT COEFFICIENT VERSUS ANGLE OF ATTACK AT MACH: 0.80,
WITH SPEEDBRAKES
47
APPENDIX A
"'"'""-"_AL PAGE IS
OF POOR QUALITy
O. l--;L:÷:-:::iL;!:_:;_:_-i-- I-i_-_-:-__-'-;:;_---E:::----;:=-_-_;:::':SPEEDBRAKEs ......
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FIGURE 31
PITCHING MOMENT COEFFICIENT VERSUS ANGLE OF ATTACK AT MACH:
WITH SPEEDBRAKES
0.90,
48
APPENDIX A
OE I?OOR QUAJAT:_
THRUST(LBS.)
800
700
400
300
200'
0 o 10 20 30 40 50
ALTITUDE (I000 FEET}
FIGURE 32
THRUST DATA FOR 80 PERCENT ENGINE RPM
49
APPENDIX A
THRUST
(LBS.)
_-MACH i 0.0 ....
:-_.!__'_-_-_.:=_:-_ii:.!___ _.__ MACH: O. 8 _..
...... --=._T:=-_:----_ ..... =F:'=-=:-:_ MACH: 1.O ....
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600 _-::- _:_-]_=:"{:==-
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3OO
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ALTITUDE (lOOO FEE-r)
FIGURE 33
THRUST DATA FOR 85 PERCENT ENGINE RPM
5O
APPENDIX A
ORIGINAL PAGE IS
OF POOR QUALITY
MACH: 1.0
THRUST(LBS.)
400 -
3O0
10 20 30 40 50
ALTITUDE (1000 FEET)
FIGURE 34
THRUST DATA FOR 90 PERCENT ENGINE RPM
51
oRIGINAL pAGE IS.
OF pOOR QU_
APPENDIX A
1000
900
IMACH: 0.'0.....CH: 0.4 --
........ 0.8---MACH: 1.0....
800iii .......
THRUST
(LBS.)
700
600
5OO
400 .....
300
200
100
___
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10 20 30 40 50
ALTITUDE (fOOD FEET)
FIGURE 35
THRUST DATA FOR 95 PERCENT ENGINE RPM
52
'.ORIGINAl;p_:GE I_
OF pOOR QUALITY
APPENDIX A
160
1200
THRUST(LBS.) 80( ::_-_.:-::::::-:..
600
200
..7: "1 :-" : : - d:'--':.:": .:£::_:::.:-:::i::::._: "- -..- : .::..:- :.
iO 20 30 40 50ALTITUDE (fOOD FEET)
FIGURE 36
THRUST DATA FOR 100 PERCENT ENGINE RPM
53
(This page intentionally left blank)
54
APPENDIX B
DAST ARW-2 OUTBOARD AILERON SERVOVALVE RELOCATION STUDY
This appendix contains a study (see Figure 37) initiated when data obtainedduring bench testing of the servoactuator of DAST ARW-I did not comparefavorably with the model used for analysis.
The testing was conducted to determine if the DAST ARW-2 outboard aileronservovalves should be moved outboard closer to the actuators. Line lengths,load variations and position feedback gain variations were investigated.
__EDiN6 PAGE BLANK NOT FILMED
PP_CED/_G PAGE E_A,_ ,"_.OT F_
55
APPENDIX B
COORDINATION SHEET
TO Gary HodgesNO. 3-75610-79-015
DATE 31 October 1979MODEL DAST ARW-2
GROUP INDEX Flight Controls Analysis
SUBJECT DAST ARW-2 Outboard Aileron Servovalve Relocation Study
1.0 INTRODUCTION AND SUMMARY
The DAST ARW-I outboard aileron servoactuators installed in the test vehiclehave about 84 inches of 3/16-inch outside diameter steel tubing between theservovalves mounted in the center wing section and the actuators mounted outin the wing at the inboard edges of the ailerons. Ground testing on the testvehicle shows higher frequency servoactuator modes, at about I12, 155 and380 hertz, which cause servoactuator instability at the desired feedback
gains. In addition, a lower frequency dominant mode with peak at 50-60hertz has been shown by analysis to couple adversely with wing structuralelastic modes with the flutter suppression systems engaged. The higher frequency
modes required addition of notch filters to reduce actuator gain at the modefrequencies. The lower frequency dominant mode will also require additionalcompensation to provide satisfactory performance from the flutter suppressionsystem on the test vehicle.
As part of the subject study, testing was accomplished on a breadboard of theDAST ARW-I outboard aileron servoactuator to establish the effects of line
length between Lhe servovaive and actuator and load inertia variations onthe servoactuator dynamic performance. The testing was conducted to determineif the DAST ARW-2 outboard aileron servovalves should be moved outboard closerto,the actuators and, if so, how much to alleviate the difficulties encounteredwith the DAST ARW-I servoactuator:
The test results show that tileservoactuator bandpass does not improvesignificantly as the length of the lines between the servoactuator and servo-valve is shortened. In general, damping of the dominant, low frequency hydraulicfluid-actuator coupled mode increases as line length is shortened and as controlsurface inertia Is decreased. But, the frequency of this mode, with position
and pressure feedback gains constant, does not vary significantly with linelength or load inertia variations.
The dominant mode, which appears to be a coupled hydraulic fluid-actuator mode,does not vary significantly in frequency or damping with changes in positionfeedback loop gain. The general trend is to decrease frequency and dampingas position feedback gain increases. Pressure feedback increases the dampingon this mode, but decreases damping on higher frequency fluid modes.
The two higher frequency fluid modes increase in frequency as the servovalveis moved closer to the actuator. With fuIl length (84-inch) lines, the modesare at 160 and 380 hertz, but with lines reduced by half, the lower frequencymode is at 230 hertz and the other above 500 hertz.
FIGURE 37
DAST ARW-2 OUTBOARD AILERON SERVOVALVE RELOCATION STUDY
56
APPENDIX B
C/S 3-75610-7g-015Page 2
The test results show that improved performance can be attained with shorterlines and reduced control surface inertia. The DAST ARW-2 outboard aileron
servovalve should be moved farther outboard in the wing and the control surfaceinertia should be reduced. While this should improve the servoactuatorperformance, additional electronic compensation may be required to providesatisfactory performance from the flutter suppression system.
2.0 TEST RESULTS
The tests were conducted on a breadboard of the DAST ARW-I outboard aileronservoactuator set up in the Hydraulics Laboratory. Position and load pressurefeedback loops were closed on an EAI TR-48 analog co_uter. A 741 operationalamplifier with current feedback was used to drive the electrohydraulicservovalve. Hydraulic power"was provided by a portable hydraulic power unitcapable of about 5 gallons per minute. The test set up with long linesbetween the servovalve and actuator was identical to the servoactuator functionaltest set up in August 1978.
The simulated load inertia used in the functional test was cut in half witha long bolt added so testing could be accomplished with full or half inertia,or with no inertia by removing the inertia from the actuator shaft. The linesbetween the servovaive and actuator used for the functional test were used for
the full length lines tests. Another pair of lines were made up for the shorterlines tests.
Three groups of tests were accomplished. The first serieswere frequencyresponse tests with variations in line length and simulated control surfaceinertia. The second series of tests were all with full line length to determinemore exactly the nature of the dynamic response. In the third set, dynamicresponses were obtained with full and lO-inch lines with position feedbackgain variations.
Each time a change in the lines was made, the lines were bled and the actuator
oscillated 4 or 5 degrees amplitude at I0 hz for about 5 minutes to precludeair being trapped in the lines and actuator.
2.1 Line Length and Load Inertia Variations
The servoactuator was first set up with the full length lines (84 inches)and frequency responses obtained for actuator shaft displacement due to displace-ment command for full (0.004 in-lb-sec2), half and no load inertia. Then, theline length was shortened to three-quarter (63 inches), half (42 inches), one-quarter (21 inches) and the shortest practical lines (I0 inches), consecutively,and the same frequency responses obtained. The resulting plots are shown onFigures l through 15. These frequency responses were all run with the nominalposition and pressure feedback loop gains, 329.6 rad/sec and 0.5678 rad/sec,respectively. Different notch filters were required as the lines were shortened,because the higher frequency fluid modes increased in frequency.
The notch filters implemented in the servoactuator feedforward path for eachof the line lengths are tabulated below.
FIGURE 37 (CONTINUED)
DAST ARW-2 OUTBOARD AILERON SERVOVALVE RELOCATION STUDY
57
APPENDI X B
C/S 3-75610-79-015Page 3
LINE LENGTH NOTCH FILTER(S)
Full 380 Hz
Three-Quarter 160, 380
Half ]60, 240
One-Quarter 160, 240
]O-inch 160, 430
The frequency responses all show a first order ro]]-off followed by a dominantmode peak in the 50-60 hertz range. Table I shows a summary of the frequencyresponses. In general, for a given line length, reducing the load inertiaincreased damping of the dominant mode (reduced peak magnitude), but changingline length did not affect this mode significantly in either damping orfrequency. The dominant mode appears to be the coupled hydraulic fluid-actuator mode. With full load inertia, the actuator-surface mode is at ]]O-l]5hertz.
With full length lines, higher frequency fluid modes are evident at 160 and380 hertz (a notch filter was required at 380 hertz to reach the nominalfeedback gains). With the lines reduced to 63 inches, these modes are atabout 185 and 460 hertz. At half line length, the lower frequency mode hasmoved up to 230 hertz and the other is.above 500 hertz. Thus, the two higherfrequency fluid modes increase in frequency as the lines are shortened. The230 hertz mode evident in the frequency responses with ]O-inch lines is theservovalve. The servovalve mode is notapparent in the other frequency responses.
The dominant mode appears to change in damping and Frequency with time. Figure16 shows the frequency response of actuator position obtained in the functionaltests in September 1978, with full length lines, full inertia and the sameposition and pressure feedback gains and notch filter as the response shownon Figure I. The functional test frequency response shows the dominant modepeak at 72 hertz with amplitude about 2.27 degrees for the one degree amplitudecommand. Figure I shows the peak at 60 hertz with amplitude of about2.03 degrees. The frequency response obtained during the functional testwas run for 0.1 to I00 hertz frequency rangep so the higher frequency modescannot be compared. The 380 hertz mode was present and a notch filter at 380hertz was required to attain the desired feedback gains. The difference inthis mode would tend to suggest air was entrapped in the lines during thecurrent test, but efforts were made to eliminate trapped air before any data
was taken.
2.2 Dominant Mode Tests
After completion of the line length variation tests, the servoactuator bread-board was reassembled with the full length lines. Figures 17, 18 and ]9 showfrequency responses obtained at this time for full, half and no load inertia,respectively. A comparison of these plots with responses obtained initially,
FIGURE 37 (CONTINUED)
DAST ARW-2 OUTBOARD AILERON SERVOVALVE RELOCATION STUDY
58
APPENDIX B
C/S 3-75610-79-015Page 4
Figures I, 2 and 3, show the dominant mode to be lighter damped and atlower frequency. This response is more like that obtained on the servo-actuators installed in the DAST ARW-I vehicle. Throughout the remainderof the testing on the breadboard setup, the response changed some from dayto day, but essentially was the same.
A frequency response with the load inertia removed and low position feedbackgain (90.91 rad/sec) only was run to compare with a response obtained duringthe DAST ARW-I functional tests. The two responses are plotted on Figure20. The dominant mode frequency is at I00 hertz for both responses. Thelower frequency differences in the responses are probably due to actuatorfriction, with the friction less now than a year ago. However, the measuredphase angles agree very well throughout the frequency range tested.
The hydraulic fluid mode at 160 hertz also changed some in nature. A notchfilter had to be added when the breadboard was revised to return to fulllength lines. This notch was not required during the functional tests orwhen the breadboard was first assembled for the current tests.
A frequency response of the valve drive amplifier output voltage, shown onFigure 21, was run for a one degree actuator command, to determine ifamplifier saturation was occurring. Near the dominant mode peak frequency,around 60 hertz, the voltage peaks at about 2.70 volts, with the maximumpeak at 500 hertz of about 15.2 volts. Thus, the dominant mode is not beingcaused by nonlinear effects due to valve drive amplifier saturation.
Figure 22 shows the servoactuator frequency response obtained with thehydraulic supply pressure increased to 2000 psi. The dominant mode peak occursat 62 hertz, slightly higher than obtained with 1500 psi supply pressure shownon Fi.gure17. Supply pressure does not affect the servoactuator dynamicresponse significantly.
2.3 Position Feedback Gain Variations
The final set of data run on the DAST ARW-I outboard aileron servoactdator
breadboard consisted of frequency responses for actuator displacement andload pressure for four low position loop gains and no pressure feedback ornotch filters. Figures 23 through 26 show the actuator responses for thefull length lines, and Figures 27 through 30 show the corresponding loadpressure frequency responses. The actuator responses for lO-inch lines areshown on Figures 31 through 34 and Figures 35 through 38 show load pressureresponses. The responses were obtained to determine if the dominant modewas affected by position feedback for the full length and lO-inch lines.
The four gains run were Ig.18, 38.36, 76.72 and I15.08 rad/sec. The firsttwo were obtained using a 2 degree command because the response was so smallat the higher frequency fluid mode frequencies.
FIGURE 37 (CONTINUED)
DAST ARW-2 OUTBOARD AILERON SERVOVALVE RELOCATION STUDY
59
APPENDIX B
ClS 3-75610-79-015
Page 5
The dominant mode frequency, with full length lines, show only a weak dep-endence on position feedback gain. The peak frequency varies from about85 hertz at 19.18 rad/sec down to about 80 hertz at II5.08 rad/sec. Thehigher frequency fluid modes are more apparent in the load pressure frequencyresponses.
The responses with lO-inch lines show little effect on the dominant mode
frequency by the position loop gain. The peak occurs at about 85 hertz,except for the highest gain, I15.08 rad/sec, when it drops to about 82 hertz.With lO-inch lines, positon feedback gain could be raised to higher loopgain without driving the dominant mode unstable than with full length lines.
In general, results of these tests show little dependence of the dominant
mode on position feedback gain, in either frequency or damping, Mode dampingis hard to assess because as position loop gain is increased the first orderactuator mode moves farther out on the real axis, resulting in increasedresponse at the dominant mode frequency.
3.0 CONCLUSIONS AND RECO_ENDATIONS
The test results discussed in Section 2, above, show that the dominant modein the DAST ARW-I outboard aileron response limits, the dynamic performancecapability of the servoactuator. Because the DAST ARW-2 outboard aileronservoactuator is similar in structure and actuator size, it will also havea dominant fluid-actuator mode of similar frequency and damping whichwill limit its capability.
This mode is not a strong function of line length (between the servovaIveand actuator) or position feedback gain. The nature of the response doesvary some with time, probably due to actuator and servovalve wear-in. The
higher frequency modes increase in frequency as the line length is shortened,with the higher frequency mode above 500 hertz for 42-inch and shorter lines.
The dominant mode damping increased with a decrease in the simulated control
surface inertia, butthe inertia had no effect on the higher frequency fluidmodes.
While the test results are not totally conclusive, the general trend showsthat better dynamic performance can be attained with shorter lines betweenthe servovalve and actuator and with lower control surface inertia. There-fore, it is recommended that the DAST ARW-2 outboard aileron servovalve be moved
outboard in the wing from that shown on the design drawings to no more than40-45 inches from the actuator between the wing spars. Also, the inertiaof the outboard aileron should be reduced to the lowest value consistentwith maintaining structural strength.
FIGURE 37 (CONTINUED)
DAST ARW-2 OUTBOARD AILERON SERVOVALVE RELOCATION STUDY
60
APPENDIX B
C/S 3-75610-79-015
Page 6
A more accurate mathematical representation of the outboard aileron servo-actuator should be developed to permit analytical exploration for additionalelectrical compensation to improve the actuator response. The data generatedin this series of tests should aid in the mathematical formulation.
Other tests could be run on the breadboard test setup, such as other compensationand line diameter variations. Changing line diameter would require a change
in the feedback potentiometermounting to provide clearance for larger tubefittings at the actuator ports.
F. Sevart
CC: J. Arnold
FIGURE 37 (CONTINUED)
DAST ARW-2 OUTBOARD AILERON SERVOVALVE RELOCATION STUDY
61
APPENDIX B
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62
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DAST ARW-2 OUTBOARD AILERON SERVOVALVE RELOCATION STUDY
63
APPENDIX B
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APPENDIX C
DAST ARW-2 FINAL FLUTTER SUPPRESSION SYSTEM PERFORMANCEDATA
This appendix contains data which summarizes the airplane stability andperformance withthe final flutter suppression system.
Figures 38 through 47 show the symmetric and antisymmetric mode dampingratios and frequencies for the critical flight Conditions determined fromanalysis. This data yerifies that the FSS meets the requirements to provideflutter mode stability and not reduce mode damping ratio below 0.01 ordegrade damping of modes with damping ratios below 0.01.
Figures 48 through 59 show the improvement in flutter mode damping with theFSS operating. Damping ratio data is presented as a function of altitudeand Mach number.
Figures 60 through 71 present root loci showing structural mode stabilityfor flight conditions within the specified flight envelope. Figures 66,67, 69 and 71 show the requirement for FSS antisymmetric filter gain sched-uling and with gain scheduling, the FSS meets the specifications containedin the final report.
101
APPENDIX C
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APPENDIX D
DAST ARW-2 SENSITIVITY ANALYSIS DATA
This appendix contains data which summarizes the sensitivity of structuralmode stability to variations in dynamics and locations of control systemcomponents. For the most part the sensitivity analysis was not repeatedfor the final FSS filters, however sensitivity to changes shown in thisdata and the root loci analysis performed using the latest filters indicatethat results of this study are valid.
Figures 72 and 73 compare structural mode damping ratios for various accel-erometer wing locations. The optimal sensor locations were selected byzero root locus as presented in the final report for sensors moved alongfront and rear spars. Thesensor locations were varied inboard and out-board of the optimal up to two inches. The symmetric gain margin was notreduced below plus or minus 6 dB but the phase margin was reduced to 20degrees when the sensors were separated by six inches. The antisymmetricgain and phase margins were reduced significantly when the sensors wereseparated by four inches.
The recommended installation of the symmetric accelerometers was plus orminus one inch of the wing station 82 on front spar and 84 on rear spar.The recommended installation of the antisymmetric accelerometers was plusor minus 0.5 inch of wing station 92 on both front and rear spars. Thevertical accelerometer recommended location was at body station 265 plusor minus 2.5 inches.
Notch filters are used both in the FSS filter and servoactuator compensa-tion. Sensitivity to notch filter parameter changes was analyzed. Figure74 shows the transfer functions of the notch filters used in the symmetricand antisymmetric compensation. The final filters did not include the 170and 230 radian notch filters, however the sensitivity analysis is presentedhere for future reference.
The summary of the notch filter sensitivity analysis is shown on Figures74 through 82. The capacitors and resistors of the notch filters have veryclose tolerances and small sensitivity to temperature changes, thereforethe parameter changes from nominal is expected to be small over the flightenvelope. The damping ratio and frequency of the notch filters were variedplus and minus five percent and the damping ratio of the actual modes changedless than eight percent.
Several servovalves were evaluated in an effort to extend the servoactuatorbandwidth. A Moog Series 31 servovalve was initially selected for theactuator model and later bench tested. The Series 31 servovalve has a wide
bandwidth and improved FSS performance but was expensive and required com-plicated closed loop circuitry. A Hydraulic Research Model AR-25 servovalvewas selected because it was a direct replacement for the Series 30 used forthe ARW-I servoactuator but had a wider bandwidth. The structural mode
136
APPENDIXD
stability results of the three servovalves are shownon Figures 83 through88. Figure 85 showsthat a plus 6 dB gain margin cannot be achieved withthe Series 30 servovalves. Although the AR-25 servovalve did not increasethe servoactuator bandwidth, the increased servovalve bandwidth providedincreased performance and 6 dB of gain margin was achieved.
Figures 88 and 89 whencomparedwith Figures 83 and 86 respectively verifythat the compensating actuator filter which cancels the surface-actuatormodeis required. Figures 90 through 92 summarizethe sensitivity analysisperformed by varying the frequency of the surface-actuator modewith respectto the compensating filter frequency.
The results of this sensitivity study indicated that when the compensatingfilter was removedthe symmetric airplane modeswere destabilized and weredifficult to stabilize and the antisymmetric filter modelead phase marginwas decreased to 40 degrees. The FSSwas relatively insensitive to a plusor minus 20 percent frequency change in the surface-actuator mode.
Servoactuator pressure feedback gain was reduced to determine the effect onairplane stability. Figures 93 through 96 summarizethis analysis. A reduc-tion of 30 percent in pressure feedback gain did not reduce symmetricstability below specifications and the antisymmetric lag phase margin wasreduced only to 40 degrees.
A hinge momentsensitivity analysis was performed to determine stabilityeffects. Figure 97 shows the servoactuator gain and phase response to ahinge momentchangeat the filter frequency. The maximumaiding (surfacetrailing edge up) to the maximumresisting (trailing edge down) hinge momentcauses approximately 45 degrees of phase lag and 4 dB loss in gain. Figures98 through 104 summarizethe hinge momentsensitivity analysis. Changesinhinge momentmay require servoactuator gain scheduling. This should beevaluated further by ground and flight testing.
Other sensitivity studies showedthat the airplane is relatively insensitiveto small changes in stability derivatives and the active control systemstend to increase frequency and dampingof the fuselage modeas shownonFigure 105.
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APPENDIX E
ACS/AFCS SYSTEMS ROOT LOCl
Gain and phase stability margins of each individual ACS and AFCS feedbackloop, except the flutter system, are shown on the figures of this section.The stability margins of each loop were determined with each combinationof systems that may be closed during some phase of flight testing. Themargins were determined at various flight conditions spanning the totalflight range. The root loci plots are identified in Figure 106 and shownon Figures 107 through 204. The stability margins were evaluated usingQSE equations of motion. Each system loop was evaluated by +4.5 dB gainand +30 degrees phase margin criteria. Refer to Figure 106 as a guide toread-gain and phase information.
176
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APPENDIX E
• MLA TEST• RSS
• MACH: 0.42
• ALTITUDE: 10,000 FT.• GROSS WEIGHT= 2500 LBS.• C.G.: 20_ MAC
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FIGURE 107
DAST AKW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC AIRPLANE FOR...... FORWARDC.GoMLA TEST CONDITION _
APPENDIX E
• MLA TEST• RSS• MACH: 0.42• ALTITUDE: 10,000 FT.• GROSS WEIGHT= 2500 LBS.• C.G.: 205 MAC
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DAST ARW-2 RSS SYSTEM C_AIN/PHASE ROOT LOCl WITH BASIC AIRPLANE FORFORWARD C,G. MLA TEST CONDITION
179
DO 6000 2145 REV 9182
APPENDIX E
• MLA TEST• RSS WITH PCS CLOSED• MACH: 0.42• ALTITUDE: 10,000 FT.• GROSS WEIGHT= 2500 LBS.• C.G.: 20_ MAC
N@, GRIN.5 0
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180
FIGURE 108
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS CLOSED FOR..... FORWARDC,G. MLA TEST CONDITION
APPENDIX E
• MLATEST• RSS WITH PCS CLOSED• MACH: 0.42• ALTITUDE: 10,000 FT.• GROSS WEIGHT: 2500 LBS.• C.G.: 20% MAC
CJ:IN I ' _X_.X, _ I
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DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS CLOSED FOR.... FORWARDC.G. MLA TESTCONDITION
181
APPENDIX E
• MLA TEST• RSS WITH PCS AND GLA CLOSED• MACH: 0.42• ALTITUDE: 10,000 FT.• GROSS WEIGHT= 2500 LBSo• C.G.: 20% MAC
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]82
FIGURE 109
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS AND GLA CLOSED FOR....... FORWARDC°G. MLATEST CONDITION
APPENDIX E
e. MLA TEST
• RSS WITH PCS AND GLA CLOSED
• MACH= 0.42• ALTITUDE: 10,000 FT.• GROSS WEIGHT: 2500 LBS.• C.G.: 20_ MAC
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DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS AND GLA CLOSED FORFORWARD C.G. NLATEST CONDITION
183
APPENDIX E
• MLA TEST• RSS WITH BCS CLOSED• MACH: 0.42• ALTITUDE: 10,000 FT.• GROSS WEIGHT: 2500 LBS.• C.G.: 20_ MAC
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184
FIGURE 110
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS CLOSED FORFORWARD C,G. MLATEST CONDITION
APPENDIX E
• MLA TEST• RSS WITH BCS CLOSED• MACH= 0.42• ALTITUDE= 10,000 FT'.• GROSS WEIGHT= 2500 LBS.• C.G.= 20% MAC
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NO. GRINI .59502 I.O00
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DAST ARW-2 RSS SYSTEM GAI N/PHASE ROOT LOOI WITH BCS CLOSED FOR.... FORWARDC.G. MLA TESTCONDITION
185
DO 6000 2145 REV 9/82
APPENDI X E
• MLA lEST• PCS WITH RSS CLOSED• MACH: 0,42• ALTITUDE: 10,000 FT,• GROSS WEIGHT: 2500 LBS,• C,G,: 205 MAC
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FIGURE 111
DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR' FORWARDC.G. MLA TEST CONDITION •
APPENDIXE
• MLA TEST• PCS WITH RSS CLOSED• MACH: 0.42• ALTITUDE: 10,000 FTo• GROSS WEIGHT: 2500 LBS.• C.G.= 20_ MAC
NO. GRIN1 .5950
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DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR• ' FORWARDC.G, MLA TEST CONDITION _ "
187
APPENDIX E
• MLA TEST• PCS WITH RSS AND GLA CLOSED• MACH: 0.42• ALTITUDE: 10,000 FT.• GROSS WEIGHT= 2500 LBS.• C.G.: 20_ MAC
NO. GRIN1 .5950
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FIGURE 112
DASTARW-2 PCS GAIN/PHASE ROOT LOOI WITH RSS AND GLA CLOSED FOR.... FORWARDC.G. MLATEST CONDITION
APPENDIX E
• MLA TEST• PCS wI'rH RSS AND GLA CLOSED• MACH: 0.42• ALTITUDE= 10,000 FT.• GROSS WEIGHT: 2500 LBSo• C.G.: 20_ MAC
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DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA CLOSED FOR.... FORWARD'C.Go MLA TEST CONDITION "
189
APPENDIXE
• MLA .rEST• BCS WITH RSS CLOSED• MACH: 0.42• ALTITUDE: 10,000 FT.• GROSS WEIGHT: 2500 LBS.• C.G.: 20% MAC
NO. GRIN
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190
FIGURE 113
DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR.... FORWARDC,G. MLA TEST CONDITION
APPENDIXE
• MLA TEST• BCS WITH RSS CLOSED• MACH: 0.42• ALTITUDE: 10,000 FT.• GROSS WEIGHT: 2500 LBS.• C.G.: 20_ MAC
lNO. GRIN1 .5950
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DAS'r ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR• FORWARDC.G. MLA TEST CONDITION
Igl
APPENDIX E
• MLA TEST• RSS• MACH: 0.42• ALTITUDE= 10,000 FT.• GROSS WEIGHT= 2200 LBS.• C.G.: 33_ MAC
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192
FIGURE 114
DAS"FARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC AIRPLANE FOR....... AFT C,G. MLA TEST CONDITION
APPENDIX E
• MLA TEST• RSS• MACH: 0.42• ALTITUDE: 10,000 FT.• GROSS WEIGHT: 2200 LBS.• C.G.: 33% MAC
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DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC AIRPLANE FOR........ AFTC.G. MLA TESTCONDITION
193
APPEND IX E
• MLA TEST• RSS WITH PCS CLOSED• MACH: 0.42• ALTITUDE: 10,000 FT.• GROSS WEIGHT: 2200 LBS.• C.G.: 33_ MAC
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DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS CLOSED FOR..... AFT C.G, MLA TEST CONDITION
194
APPENDI X E
• MLA TEST• RSS WITH PCS CLOSED• MACH: 0.42• ALTITUDE: 10,000 FT.• GROSS WEIGHT: 2200 LBS.• C.G,: 33_ MAC
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DAST ARW-2 RSS SYSTEH GAIN/PHASE ROOT LOCI WITH PCS CLOSED FOR.... AFT C.G.HLA TEST CONDITION
195
APPENDIX E
• MLA TEST• RSS WITH PCS AND GLA CLOSED• MACH: 0.42• ALTITUDE: 10,000 FT.• GROSS WEIGHT: 2200 LBS.• C.G,: 33_ MAC
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FIGURE 116
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS AND GLA CLOSED FOR
....... AF-rC.G. MLA TEST CONDITION
APPENDI X E
• MLA TEST• RSS WITH PCS AND GLA CLOSED• MACH= 0.42• ALTITUDE= 10,000 FT.• GROSS WEIGHT= 2200 LBS.• C.G;: 33_ MAC
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° .E)
O
0.eb
FIGURE 116 (CONCLUDED)
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS AND GLA CLOSED FOR....... AFT C.G. MLA TEST CONDITION
]97
APPENDIXE
• MLA TEST• RSS WITH BCS CLOSED• MACH: 0.42• ALTITUDE: 10,000 FT.• GROSS WEIGHT: 2200 LBS.• C.G.: 33_ MAC
t
-20. O0
I I I I I
i.ooot. 680
1
/
/
. // /
• ( /
/'1
I- 16. O0 - 12. O0 -8. O0 -q, O0 O. O0
//
///
(RAD/SEC)
_
/
/'
I
o
=;
L)
£:) (./)
IiTM
rt,-
.,-,,j
c;
C3
C3
FIGURE 117
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS CLOSED FORAFT C.G. MLATEST CONDITION
198
APPENDIX E
t
-| .60
• MLA TEST
• RSS WITH BCS CLOSED• MACH: 0.42
• ALTITUDE: I0,000 FT.• GROSS WEIGHT: 2200 LBS.
i C.G,: 33% MACI I I
NO. GRIN• 59S0
! .0001,6eo
-I. 20 -0.80 -0.qO O.O0 O.qo
t_
o_D
'oJ
c_(_
c_0o
(_(RAD/SEC)
c_c_
c__o
c;
c_o.ob
c.)
r-.,
OC
3..--_
FIGURE 117 (CONCLUDED)
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS CLOSED FORAFT C.G. MLA TEST CONDITION
199
APPENDIXE
• MLA TEST• PCS WITH RSS CLOSED• MACH: 0.42• ALTITUDE: 10,000 FT.• GROSS WEIGHT: 2200 LBS.• C.G;: 33% MAC
NS.!23
I I I tGRIN•5950I.O001.680
I I I
0
c_El
C_
1,1C/)
fY
3.--j
I
-20. O0 - 16. O0 - 12. O0 -8. O0 -q,. O0 O. O0
¢:D
_ob
o (RAD/SEC)
200
FIGURE 118
DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR.... AFT C.G. MLA TEST CONDITION _
APPENDIX E
• MLA TEST• PCS WITH RSS CLOSED• MACH: 0.42• ALTITUDE: 10,,000 FT.• GROSSWEIGHT: 2200 LBS.• C.G,: 335_ MAC
I
i
J
I I I,GRIN
.S950
1.680
I I 4'
-1.60 -i.20 _ -0.80 -O.qO 0.00 o.qo
(RAD/SEC)
oJ
L,O
n,-
3
C:D
¢D(%1
C_
o.sb
FIGURE 118 (CONCLUDED)
DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR' " AFT C.G. MLA TEST CONDITION ....
201
APPENDIX E
• MLA TEST• PCS WITH RSS AND GLA CLOSED• MACH: 0.42• ALTITUDE: 10,000 FT.• GROSS WEIGHT: 2200 LBS.• C.G,: 33_ MAC
GRIN.5950
t.O001.680
t I I t
oo
oo
/o0
C3
t..Ucrj
j E)
/ °r,,-3
I I I I
(:3E3
-(-,;
0
-2o.oo -_B.O0 -_2.00 -B.O0 -4.00 mOO _.ob
(_ (RAD/SEC)t
FIGURE 119
DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA CLOSED FORAFT C.G. MLA TEST CONDITION
202
APPENDIXE
• MLA TEST• PCS WITH RSS AND GLA CLOSED• MACH: 0.42• ALTITUDE: 10,000 FT.• GROSS WEIGHT: 2200 LBS.• C.G.: 33% MAC
I I I
NO. GRINI .5950Z 1.0003 i.680
i
tII
4
I , , i I ,z6o -z2o -o.8o -o.,m o.oo o qo
(RAD/SEC)
C_¢D
o,;
CD
o;
C,G:I
• °
LIJ
::3"
3
C3
=;
C_
c;o,eb
FIGURE 119 (CONCLUDED)
DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA CLOSED FORAFT C.G. MLA TEST CONDITION
203
APPENDIX E
• MLA TEST
• GLA AILERON WITH RSS, PCS ANDGLA STAB IL IZER CLOSED
• MACH: 0.42
• ALTITUDE: 10,000 FT.• GROSS WEIGHT: 2200 LBS.
• C.G.: 33% MAC
I I I I
I D J IO.O0 -16.00 -12.00 -8.00 -tt. O0 0.00
(_(RAD/SEC)
(_
C:)
4
(Z)
L_
3
°"'JC)
(_C_
oo
_.0b
204
FIGURE 120
DAST ARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLA'' •STABILIZER LOOPS CLOSEDFOR AFT C,G. MLA TEST CONDITION
-125.00 -100.00 -75.00
APPENDI X E
• MLATEST• GLA AILERON WITH RSS, PCS AND
GLA STABILIZER CLOSED• MACH: 0.42• ALTITUDE: 10,000 FT.• GROSS WEIGHT: 2200 LB$.
• C.G.: 33% I_C
I I
-50. O0 -25. O0
(RAD/SEC)
u_p-
FIGURE 120 (CONTINUED)
DAST ARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLASTABILIZER LOOPS CLOSED FOR AFT C.G. MLA TEST CONDITION
205
APPENDIXE• MLA TEST
• GLA AILERON WITH RSS, PCS ANDGLA STAB I L IZER CLOSED
• MACH: 0.42• ALTITUDE: 10,000 FT.• GROSS WEIGHT: 2200 LBS°• C.G.: 33% MAC
I I
O. O0 O. 40
0 (RAD/SEC)
0(M
(:D
(3ILlU1
3
c_(:3
C_tD
'c;
o(M
(3
Ic;o_sb
206
FIGURE 120 (CONCLUDED)
DAST ARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLASTABILIZER LOOPS CLOSED FOR AFT CoG. MLA TEST CONDITION
APPENDIX E
• MLA TEST• GLA STABILIZER WITH RSSp PCS
AND GLA AILERON CLOSED• MACH: 0.42• ALTITUDE- lOpO00 FT.• GROSS WEIGHT= 2200 LBS.• C.G.. 33_ MAC
t I I "f ',
//
/
-20.00 -16.00 -12.00 -B. O0 -u,. O0 0.00
(_(RAD/SEC)
"5
0C)
.,,G
FIGURE 121
DAST"ARW-2 GLA STABILIZER LOOP GAIN/PHASE ROOT LOCI WITH RSS,, PCS AND GLAA I LERON LOOPS CLOSED FOR AFT C.G. "MLA TEST CONDIT ION•
207
APPENDIX E
• MLA TEST• GLA STABILIZER WITH RSS, PCS
AND GLA AILERON CLOSEDm MACH: 0.42
• ALTITIlDE: I0,000 FT.• GROSS WEIGHT: 2200 LBS.
• C.G.: 33% MAC
I I I I I
t \
r_
• °
_8
Ac.)uJc_
ti"3
cr (RAD/SEC)
FIGURE 121 (CONTINUED)
DAST ARW-2 GLA STABILIZER LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLA• AILERON LOOPS CLOSED FOR AFT C.G. MLA TEST CONDITION
2O8
APPENDIX E
• MLA TEST
• GLA STABILIZER WITH RSS, PCS ANDGLA AILERON CLOSED
• MACH- 0.42
• ALTITUDE: I0,000 FT.• GROSS WEIGHT: 2200 LBS.
• C.G,: 33% MAC
I I I
I
I I _ I
-_.6o -1.20 -o.Bo -0.40 o.oo 0.40
(_(PAD/SEC )
_4
,-d
o(._
ooo
:.o
o
(,o
c)(._
c)
018b
uJ
OC
3
FIGURE 121 (CONCLUDED}
DAS'r ARW-2 GLA STABILIZER LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLAAILERON LOOPS CLOSED FOR AFT C.G. MLA TEST CONDITION
209
APPENDIX E
• MLA TEST• BCS WITH RSS CLOSED• MACH: 0.42• ALTITUDE: 10,000 FT.• GROSS WEIGHT: 2200 LBS.• C.G.: 335 MAC
3
li
I
I I I IG_IIN
• 59S0I. 0001.680
\\
\
\\
\
\\
_\ \.,
\. /
-16.00
• I
i I-12.00 -8.00 -I_.O0 0.00
c_(RAD/SEC)
c_o
C3C_
e,;c_
C3
_ao
A
ILl
3..-.,_
C_
(:3
"o;
C:.
o;_ob
FIGURE 122
DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS CLOSED FORAFT CoG. MLATEST CONDITION
210
APPENDIX E
• MLA TEST• BCS WITH RSS CLOSED• MACH: 0.42• ALTITUDE: 10,000 FT.• GROSS WEIGHT: 2200 LBS.• C.G.: 33% MAC
+
I
I I
- L. 60 - 1.20 -0.80 -0. q,o O. O0 O. qO
cr (RAD/SEC)
FIGURE 122 (CONCLUDED)
DAST ARW-2 BCS SYSTEN GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR.... AFT C.G, NLA TEST CONDITION .....
211
APPENDIX E
• GLA TEST• RSS• HACH: 0.70• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2500 LBS.• C.G,: 20_ MAC
I I I
°d
....
20.00 tO.DO 12.00 8 O0 q.O0 0.00 _ UU
(RAD/SEC)
¢.)uJ(v3
(::3 •
3o--._
FIGURE 123
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC AIRPLANE FOR...... FORWARDC.G. GLATEST CONDITION
212
APPENDIX E
• GLA .3lEST• RSS• MACH= 0.70• ALTITUDE: _ 15,000 FT.• GROSS WEIGHT= 2500 LBS.• C.G.= 20% MAC
I I
I
I I I _ I
1. G(J [, 20 O. 80 D. 40 O. O0 O. qO
o" (RAD/SEC)
0UD
C)_J
C_CO
0w
(:3 --_1' r_ •
3°--,j
00
0
FIGURE 123 (CONCLUDED)
DAS'i"ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC AIRPLANE FOR...... FORWARDC.G.GLATESTCONDITION '
213
APPENDI X E
• GLA TEST• RSS Wll_! PCS CLOSED• MACH: 0.70• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2500 LBS.• C.G.: 20_ MAC
N_j"
I I I
I
I
i IgO. O0 tG. O0 12. O0 6. O0 q. O0 O. O0
o (I_a.D/SEC)
FIGURE 124
DAS'FARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS CLOSED FOR..... FORWARDC.G. GLATEST CONDITION
214
APPENDI X E
• GLA TEST• RSS WITH PCS CLOSED• MACH: 0.70• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2500 LBS.• C.G,: 20_ MAC
"i
f
I
I I I
I
l o I I It.6o z .zo o.so o.qo o.oo o.qo
o (RAD/SEC)
C_
f.o
6
',_H
°
LU
S
FIGURE 124 (CONCLUDED)
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS CLOSED FOR..... FORWARDC.G. GLA TEST CONDITION
215
APPENDIX E
• GLA TEST• RSS WITH PCS AND GLA CLOSED• MACH: 0.70• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2500 LBS.• C.G.: 20_ MAC
I I I I
1 °020.00 16.00 12.00 e. O0 4.0D 0.00 4.0b
(RAD/SEC)
FIGURE 125
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOOI WITH PCS AND GLA CLOSED FOR........ FORWARDC.G. GLA TEST CONDITION
216
APPENDIX E
• GLA TEST• RSS WITH PCS AND GLA CLOSED• NIACH: 0.70• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2500 LBS.• C.G.: 20'_ MAC
I I I
I
, , I ,t.6o -1.2o o,eo o.4o o.oo o.qo
o (RAD/SEC)
_D
C'o
r,;
CI¢o
A
(.t")
:=" r'_
...; .<n,"
3°--)
C)C_
"...:
C)cJo
04
,.,H
0
0
oisb
FIGURE 125 (CONCLUDED)
DAST ARW-2 RSS SYSTEN GAIN/PHASE ROOT LOCI WITH PCS AND GLA CLOSED FOR..... FORWARDC. G. GLA TEST CONDI TI ON
217
APPENDIX E
• GLA TEST• RSS WITH BCS CLOSED• MACH: 0.7U• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2500 LBS.• C.G.: 20_ MAC
I I I
0C;,
20. O0 16. O0 -12. O0 6. O0 4. O0 O. O0
o (RAD/SEC)
218
FIGURE 126
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS CLOSED FOR.... FORWARDC.G. GLA TEST CONDITION
APPENDIXE
• GLA TEST• RSS WITH BCS CLOSED• MACH: 0.7U• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2500 LBS.• C.G.: 20_ MAC
INO. GRIN
isN
ZI I
T
I i_ _ _ -
I I ; I I1.60 1.20 0.80 O.qO 0.00 o.qo
o (RAD/SEC)
IJD
0OJ
0CO
0
(DlID
c;
0
o.8b
A
(.)u.I
r_
3
FIGURE 126 (CONCLUDED)
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS CLOSED FOR..... FORWARDC,G. GLA TEST CONDITION
219
APPENDIX E
• GLA lEST• PCS WITH RSS CLOSED• MAC'H: 0.70• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2500 LBS.• C.G.: 20% MAC
I N(_.
l
TEh
J
I
+
I I I t
GRIN.59S0
l.O001.680
I I I
c_
/ °C3
/
/
, *,
j- - Z3"
/ .// f i
s
0
÷_, .ob
CO
C_
"=C
r_"v
3.-,-}
-20.O0 -_e.oo -_2.oo -a.oo -q.oo o.oo
o (I:_ISEC)
FIGURE 127
DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR' ' ' FORWARDC.G. GLA lEST CX)NDITION ' "
220
APPENDIX E
• GLA TEST• PCS WITH RSS CLOSED• MACH: O.7U• ALTITUDE, 15,000 FT.• GROSSWEIGHT: 2500 LBS.• C.G.: 20_ MAC
NO. GRIN
.5950.000
F
!F)
t
Q
-1,60
I I I
I
- I. 20 -0.80 -0. LIO O. O0 O. qO
o (RAD/SEC)
,==
u_
v
...=_
(:3
c3(,13
(:3
c3L'u
o.Bb
FIGURE 127 (CONCLUDED)
DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSED FORFORWARDC.G. GLA TEST CONDITION
221
APPENDIXE
• GLA TEST
• PCS WITH RSS AND GLA CLOSED
• MACH: 0.70
• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2500 LBS.
• C.G.: 20_ MAC
P
NO. GRINl .59502 l. O003 I. 680
fi
J
I
I I I
-20. O0 - 16. O0 -12. O0 -8. O0
C,
,-h
C_
- e_i_- a- -_
-4. oo o. oo 4_ob
(RAD/SEC)
FIGURE 128
DAST'ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA CLOSED FOR' FORWARDC.G. GLATEST CONDITION
222
APPENDIX E
• GLA "lEST• PCS WITH RSS AND GLA CLOSED• MACH: 0.70• ALTITUDE= 15,000 F'l'.• GROSS WEIGHT: 2500 LBS.• C.G.: 20_ MAC
1
+
3 t. 680
I I I
I I I
I
I
to
,0
oco
0
03
v
3
• •
"c;
oJ
¢;
Od
¢;0.sb-_.6o -_.2o -o.ao -o._o o.oo o.qo
0"(RAD/SEC)
FIGURE 128 (CONCLUDED)
DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA CLOSED FOR• • FORWARD C.G. GLATEST CONDITION " • '
223
APPEND IX E
• GLA TEST• GLA AILERON WITH RSS, PCS AND
GLA STABILIZERCLOSED• MACH: 0.70• ALTITUDE: 15,000 FT.
• GROSS WEIGHT: 2500 LBS.
• C.G.: 20_ MAC
I I I
-20. O0 - 16. O0 - 12. O0 -8. O0 -q,. O0 O. O0
O"(RAO/SEC)
0
00
,o,;
(:::)0
0LI,J
oo o0
c_
3.,,.,_
0
0
0,i_.ob
224
FIGURE 129
DAST ARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLASTABILIZER LOOPS CLOSED FOR FORWARDC.G. GLA TEST CONDITION
APPENDIX E
• GLA TEST• GLA AILERON WITH RSS, PCS AND
GLA STAB I L I ZER CLOSED• MACH: 0.70• ALTITUDE= 15,000 FT.• GROSSWEIGHT: 2500 LBS.• C.G.:. 20% MAC
NO. _9_N \ I
3 t.680 \ I o
1\ _ I Io
I \ \ ,I
-_2s.oo -_oo.oo -_s.oo -_o.oo -_s.oo "o'.oo '. o
c_(RAD/SEC)
3:;3
F I GURE 129 (C1:)NTI NUED)
DAS'I" ARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLA.. STABILIZER LOOPS CLOSED FOR FORWARDCoGo GLA TEST CONDITION
225
........................... ........
APPEND IX E
• GLA TEST• GLA AILERON WITH RSS, PCS AND
GLA STABI L IZER CLOSED• MACH: 0.70
• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2500 LBS.
• C.G.: 20% MAC
I I I
0
0co
3
0
l.60 -1.20 -0.80 0 0 0 0 0 8b
o' (RAD/SEC)
226
FIGURE 129 (CONCLUDED)
DAST ARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLA• STABILIZER LOOPS CLOSED FOR FORWARDC.G. GLA TEST CONDITION
APPENDIXE
• GLATEST• GLA STABILIZER WITH RSS, PCS
AND GL.A AILERON CLOSED•• MACH: 0.70• ALTITUDE= 15,000 FT.• GROSS WEIGHT: 2500 LBS.• C.G.: 20_ P,ff_C
C3
('U
C3
C3C3
.=;
A
r..3
r'_
• c:_
c3
i I i I-20.00 -16.00 -12.00 -B.O0 -_.00 0.00 _0_
(RAD/SEC)
FIGURE 130
DAST ARW-2 GLA STABILIZER LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLAAILERON LOOPS CLOSED FOR FORWARDC.G. GLA TEST CONDITION
227
APPENDI X E
• GLA TEST• GLA STABILIZER WITH RSSp PCS
AND GLA AILERON CLOSED• MACH: 0.70
• ALTITUDE: 15,000 FT.• GROSS WEIGHT.- 2500 LBS.
• C.G..- 20_ MAC _
I I I I !NO. GRIN I
3 t:seo II co
-tO0.O0 I .50, O0 0
o u'}
Io3°...._
C)
- 125. O0 -75. O0 -25. O0
(RAD/SEC)
FIGURE 130 (CONTINUED)
DAbT ARW-2 GLA STABILIZER LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLA'' AILERON LOOPS CLOSED FORFORWARD C.Go GLA TEST CONDITION
228
I
GRIN.5950
APPEND I X E
• GLA TEST
• GLA STABILIZER WITH RSS, PCS ANDGLA AILERON CLOSED "
• MACH: 0.70• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2500 LBS.• C.G;: 20_ MAC
I I I c,i
C3
C3('_
0_33
LI.IU3--...
v
3
C3
=;
J
-1.60 -2.2o -0.80 -0. _0 o. oo o. qo o. 8b
_r (RAD/SEC)
FIGURE 1)0 (CONCLUDED)
DAST ARW-2 GLA STABILIZER LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLA• AILERON LOOPS CLOSED FORFORWARD C.G. GLA "lEST CONDITION
229
APPENDIX E
• GLA TEST• BCS WITH RSS CLOSED• MAC'H: 0.70• ALTITUDE: 1.5•000 FT,• GROSS WEIGHT: 2.500 LBS,• C.G.: 20_ MAC
• 5950
2"_\ t. 000l. 680
\,
'\
\
I
!
\\,
l I I I
,\
\\
\,
\\
\,,
'\
<
I I I
-20. O0 - 16. O0 - 12. O0 -8. O0 -LI. O0 O. O0
(RAD/SEC)
C_(:3
C_(::3
3.-,,_
C_C3
C3
0
_:ob
FIGURE 131
DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR.... FORWARDC,Go GLA TEST CONDITION ....
230
APPENDIX E
• GLA TEST• BCS WITH RSS CLOSED• MAC'H: 0.70• ALTITUDE= 15,000 FT.• GROSS WEIGHT= 2500 LBSo• C.G,: .20_ MAC
t'"7-_ 11-°°°'_9s°='"'._,o* / '
j_ \
\
'.N
-I. 60 -I. 20 -0.80 -0, _0
/
O. O0
/
//
//
C_)LU
I oO
rr
3o-==j
(:3oo
o (RAD/SEC)
C3
(:3C_
Io. o
FIGURE 131 (CONCLUDED)
DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR• FORWARD C.G. GLA TEST CONDITION •
231
APPENDI X E
• GLA TEST• RSS• MACI-I: 0.70• ALTITUDE: 15,000 FT.• GROSS WEIGHT= 2200LBSo• . C.G,= 33% MAC
-20. O0 -I 6. O0
I I !
cr (RAD/SEC)
FIGURE 132
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC AIRPLANE FOR....... AFT" C.G, GLA TEST CONDITION
232
APPENDIX E
• GLATEST• RSS• MACH: 0.70• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2200 LBS.• C,G.: 33_ MAC
I I
FIGURE 132 (CONCLUOED)
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC AIRPLANE FORAFT C.G. GLA TEST CONDITION
233
APPENDIX E
• GLA TEST• RSS WITH PCS CLOSED• I_,CH: 0.70• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2200 LBS.• C.G,= 33% MAC
I I I INO. GRIN
.59501.0003 I. 680
It I
-4. O0 O. O0
/
0o
C_
(RAD/SEC)
I,I
0_.
3°--,,,j
FIGURE 133
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOOI WITH PCS CLOSED FOR
...... AFF C.G. GLA TEST CONDITION
234
APPENDIX E
• GLA TEST• RSS WITH PCS CLOSED• MACH: 0.70• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2200 _LBS,• C.G,; 33_ MAC
NO,
1
GAIN.5950t.O00t .680
I I I I I
II I I I I
C;I¢0
C_
(:3
0¢,O
"(5
(:3(M
(3
ic:;08b
L_03
n"
3
-l. 60 -1.20 -0.80 -0. qo O. O0 O. qo
(RAD/SEC)
FIGURE 133 (CONCLUDED)
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS CLOSED FOR....... AFT C.G, GLA TEST CONDITION
235
APPENDIX E
• GLA TEST• RSS WITH PCS AND GLA CLOSED• MACH: 0.70• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2200 LBS.• C.G.: 33% MAC
I I I I ! / _NO. GRIN / [1 .sgso ' / ]3 t. 680
/ , /iI o
t _2
E3
-20.00 -t6.oo -z2.oo -e.oo -q.oo o.oo q:ob
cr (RAD/SEC)
FIGURE 134
DASTARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS AND GLA CLOSED FOR....... AFTC.G.GLATEST CONDITION ' ' _
236
APPENDIX E
• GLA TEST• RSS WITH PCS AND GLA CLOSED• MACH: 0.70• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2200 LBSo• C.G.: 33% MAC
NO. GR N
.$9 o3 1:8 8
I I I
I
l i j I i• 60 -l. 20 -0.80 -0. u,o O. O0
(RAD/SEC)
0.40
0_
o
c,J
o
LUc_ 03
. • r_
r_
o
o_o
"c;
o
o,sb
FIGURE 134 (CONCLUDED)
DASTARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS AND GLA CLOSED FOR
....... AFT C.G.GLA TEST CONDITION '
237
APPENDIX E
• GLA TEST• RSS WITH BCS CLOSED• MACH: 0.70• ALTITUDE: 15•000 FT.• GROSS WEIGHT: 2200 •LBS.• C.G,: 33_ MAC
I I I
/
/
/!
//
/
FIGURE 135
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS CLOSED FOR
.... AFT C.G, GLATESTCONDITION
238
APPENDIX E
• GLA TEST• RSS WITH BCS CLOSED• MACH: 0.70• ALTITUDE: 15,000 FT.• GROSSWEIGHT= 2200 LBS.• C.G,: 33_ MAC
NO.I
C)(D
0
ED(;0
A
L4J
TM
r_
r_v
3
o(23
0_D
0(_
I o
-l. 60 -t. 20 -0.80 -0. qo O. O0 O. qo O.
(RAD/SEC)
FIGURE 135 (CONCLUDED)
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS CLOSED FOR
....... AFT C.G. GLATEST CONDITION " ' •
239
APPENDIX E
• GLA TEST• PCS WITH RSS CLOSED• MACH: 0.70
• ALTITUDE= 15,000 FT.• GROSS WEIGHT: 2200 LBS.• C.G,: 33_ MAC
I ! 1 I (:3
0
¢;
LIJ
-20. O0
I
I I I I
- 16. O0 - t 2. O0 -8. O0 -U,. O0 O. O0
(RAD/SEC)
FIGURE 136
DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR.... AFT C.G. GLATEST CONDITION
240
APPENDIX E
• GLA TEST• PCS WITH RSS CLOSED• MACH: 0.70 '• ALTITUDE: 15,000 FT.• GROSSWEIGHT: 2200LBS.• C.G;: 33% MAC
I I I
| I
'o-i
0_o
0o,,I
GO. °
A
LI.I
o,--,_
. °C_
0I
0 I-i. 60 -t.2o -0.80 -0.40 0.00 0.40 o: 8b
(RAD/SEC)
FIGURE 136 (CONCLUDED)
DAST ARW-2 PCS GAIN/PHASE ROOT LOOI WITH RSS CLOSED FOR.... AFT C,G. GLA TEST CONDITION '
241
APPENDIX E
• GLA TEST• PCS WITH RSS AND GLA CLOSED• MACH: 0.70• ALTITUDE: 1.5,000 FT.• GROSS WEIGHT: 2200 •LBSo• C.G.: 33_ MAC
I I I I
15950
00
c_J
..j.1 3°_
-20.00 -16.00 -12.00 -8.00 -tLO0 0.00
(RAD/SEC)
E3(:3
C:)
u,.ob
FIGURE 137
DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA CLOSED FOR. . •AFT C.G_ GLA TEST CONDITION '
242
APF_ND I X E
• GLA TEST• PCS WITH RSS AND GLA CLOSED• MACH= 0.70• ALTITUDE: 15,000 FT.• GROSSWEIGHT: 2200LBS.• C.G.: 33% MAC
.
I I I
I
, 4 I I 0-1.60 -_. 20 -0. BO -o.'m o.oo o. 4o
ar (RAD/SEC)
o.;
C)10
"e3
UJ¢.,'3
=" n,"
3
'..3
o.sb
FIGURE 137 (CONCLUDED)
DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA CLOSED FORAF'r CoG. GLA TEST CONDITION
243
APPEND IX E
• GLA TEST• GLA AILERON WITH RSS, PCS AND
GLA STAB I L I ZER CLOSED• MACH: 0.70• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2200 LBS,
• C.G,: 33% MAC
I I I Y / I/,/
//',/
//
._.._t.O001.680
_-_ ...__....._ _tJ"
-i I I
/ / /
) /
, //[
I
0
.
0
-20. O0 -16. O0 -I 2, O0 -8. O0 -4. O0 O, O0
(RAD/SEC)
T_
i¢;
c_o
00
_.ob
A
FIGURE 138
DAST ARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLASTABILIZER LOOPS CLOSED FOR AFT C.G. GLA TEST CONDITION
244
APPENDIX E
• GLA TEST• GLA AILERON WITH RSS, PCS AND
GLA STAB I L I ZER CLOSED• MACH: 0.70• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2200 LBS.• C.G,: 33_ MAC
iN@. GRIN
isgso
L,
\ °
\
4-
\
I I I I
-125.00
D_RIGINAL PAGE rg
_'00R QUALITY
oo.If)
CDO
c;c-j.4
I °t_in 3
T_
dF . -OJ
-I00.00 -TS.O0 -S0.O0 -2S.O0 O.00 2s.bo
cI(RAD/SEC)
FIGURE 138 (CONTINUED)
DAST ARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLASTABILIZER LOOPS CLOSEDFOR AFT C.G. GLA TEST CONDITION
245
APPENDIX E
• GLA TEST• GLA AILERON WITH RSS, PCS AND
GLA STABILIZER CLOSED• MACH= 0.70• ALTITUDE= 15,000 FT.• GROSS WEIGHT= 2200 LBS.• C.G.= )3% MAC
GRINNO. .5950
2 I. 0003 I. 680
p-
II
4-
fJ+
÷
+
IIt
I
- .60
I I I
-I. 20
I I I
-0.80 -0.40 0.00 0. q0
c_oD
A
C.DLUo0
0C
3,-=)
c3c_
c_t_
c_
o
c5
(RAD/SEC)
oc,J
o.ob
246
FIGURE 138 (CONCLUDED)
DAST ARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLASTAB I L IZER LOOPS CLOSED FOR AFT C. Go GLA TEST CONDI T I ON
APPENDIX E
• GLA TEST• GLA STABILIZER WITH RSS, PCS
AND GLA AILERON CLOSED• MACH; 0.70• ALTITUDE: 15,000 FT.• GROSSWEIGHT: 2200 LBS.• C.G, = 33_ MAC
ORIGINAL PAGE IS
DE POOR QUALITY
t \
, I-20. O0 - 16. O0 - 12. O0 -8. O0 -q. O0 O. O0
c_(RAD/SEC)
FIGURE 139
DAST ARW-2 GLA STABILIZER LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLA
AILERON LOOPS CLOSED FOR AFT C.G. GLA TEST CONDITION
247
N?. GRIN
595i.o(_
3 !. 680
tl
iX
APPENDIX E
• GLA TEST
• GLA STABILIZER WITH RSS, PCSAND GLA AILERON CLOSED
• MACI_: 0.70
• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2200 LBS.
• O.G,: 33% MAC
I I I I
0
,.i- ed
t
t
"\,,
i ",s
lJ
_\ i \'
//_L../ ,-125.00 -100.00 -75.00
c_
6C_
LLJ
E3
i'D
( > i,,'_ 1
-- 7-- '
-50. O0 -25. O0
(RAD/SEC)
6
8
o. oo 2s. bo
r_
3
FIGURE 139 (CONTINUED)
DAST ARW-2 GLA STABILIZER LOOP GAIN/PHASE ROOT LOOI WITH RSS, PCS AND GLAAILERON LOOPS CLOSED FOR AFT CoGo GLA TESTCONDtTION
248
APPENDIX E
• GLA TEST• GLA STABILIZER WITH RSS, PCS AND
GLA AILERON CLOSED• MACH- 0.70• ALTITUDE: 15,000 FT,• GROSS WEIGHT" 2200 LBS.
• C.G,: 33_ MAC
t
÷
Z
±
+i
I
tI
@,e
- .60
GRIN,5950l.OOO1.880
I I I I I
I
I t I I
-1.2o -0.80 -0.40 o.oo o.4o
(_(RAD/SEC)
c_
T_
I]
Iv°
0l.u
3,-..,}
(5
c_
c_O. llb
FIGURE 139 (CONCLUDED)
DAST ARW-2 GLA STABILIZER LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLA' AILERON LOOPS CLOSED FOR AFT C.G. GLA TESTCONDITION
249
APPENDIX E
• GLA TEST• BCS WITH RSS CLOSED• MACH: 0.70 •• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2200LBS.• C.G,: 33% MAC
I I I• I
-20. O0
C3C_
C)
LI.I
oo -..• r7
n,"
3"
,6
t_
// I /// J
' I/"/UI I I I '4
- 16. O0 - 12. O0 -8. O0 -q. O0 O. O0 q. O0
(RAD/SEC)
250
FIGURE 140
DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR.... AFT CoG. GLATEST CONDITION .....
APPENDIX E
• GLA TEST• BCS WITH RSS CLOSED• MACH: 0.70• ALTITUDE: 1..5,000 FT.• GROSSWEIGHT: 2200 LBS.• C.G.: 33_ MAC
ORIGINAL PAGE IS'
DE POOR QUALITY
I I
I
C)
"4
C3C'd
FIGURE 140 (CONCLUDED)
DASTARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR' AFT C.G, GLATEST CONDITION .....
251
APPENDIX E
• LAUNCH• RSS• MACH= 0.40• ALTITUDE= 15,000 FT.• GROSS WEIGHT= 2500 LBS.• C.G.: 20_ MAC
r i i I i / i (5NO, GRIN / o')1 .s�so / '
oII
L:
8 ""
t °.:_ ._E3
8
I I ,,"_'_ I
-20.00 -16.00 -12.00 -8.00 -4.00 oloo _:ob
(_(RAD/SEC)
FIGURE 141
DAS'r ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC AIRPLANE FOR....... FORWARDC.G. LAUNCH CONDITION
252
APPENDIX E
• LAUNCH• RSS• MACH: 0.40
• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2500 LBS.• C.G.: 20% MAC
'cJ
I I
CO
•Do -1.2o -o.Bo -o.4o o.oo o.4o
o (RAD/SEC)
C.)
LLJ
CO CO
::2
n,"
3o-,.,.j
COC_
'...:
CO_D
c:;
CO0,,I
c_
COOd
FIGURE 141 (CONCLUDED)
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC AIRPLANE FOR........ FORWARDC.G. LAUNCH CONDITION
253
APPENDIX E
• LAUNCH• RSS WITH PCS CLOSED• MACH: 0.40• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2500 LBS.• C.G.: 20_ MAC
iI I I I I
J
/ C_
C_
A
u.I
3
00
ED
-2o.oo -iB.oo -12.oo -B.O0 -4.00 0.00 4_ob(RAD/SEC)
FIGURE 142
DAS_ ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS CLOSED FOR.... FORWARDC.G. LAUNCH CONDITION
254
APPENDIX E
• LAUNCH• RSS WI151PCS CLOSED• MACH: 0.40• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2500 LBS.• C.G.: 20_ MAC
! .59
0
C_0
• °
tm
c_
c_
0 0 0.6o -_.2o -o.8o -o._o o.oo 0._o o,sb
(RAD/SEC)
A
LU
_3
3.---j
FIGURE 142 (CONCLUDED)
DASTARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS CLOSED FORFORWARDC.G. LAUNCHCONDITION
255
APPENDIXE
• LAUNCH• RSS Wl'n-I PCS AND GLA CLOSED• MACH: 0.40 •• ALTITUDE: 15,000 Fl',• GROSS WEIGHT= 2500 LBS.• C.G.: 20_ MAC
/"Jl'". // I
! L, L_
/'/i/['I
I
\(!I°
-16.00 -12.00 0.00 4.oh-20. O0 -8. O0 -_. O0
c_(RAD/SEC}
(,.)ILl0'3
o C;_
rtr
S
FIGURE 14)
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS AND GLA CLOSED FOR...... FORWARDC,G. LAUNCH CONDITION'
256
APPENDIX E
• LAUNCH• RSS WITH PCS AND GLA CLOSED• MACH: 0.40• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2500 LBS.• C.G.: 20_ MAC
I
NO. GAIN I \ I
I I
•6o -t. 20 -o. eo -o. qo o. oo o. qo
(RAD/SEC)
C_(,D
'oJ
Od
'oJ
GO
C)C_
(D(.O
6
Co
"c;
C_Od
c;o.Bb
CDuJv)
C_<D:
3"I
FIGURE 143 (CONCLUDED)
DASTARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS AND GLA CLOSED FOR........ FORWARDC.Go LAUNCH CONDITION
257
APPENDIxE
• LAUNCH• RSS WITH BCS CLOSED• MACH= 0.40• ALTITUDE= 15,000 FT.• GROSS WEIGHT= 2500 LBS.• C.G.: 20_ MAC
I I I I
-_o.oo -_s.oo -_2.oo -8.oo -qoo o.oo
o" (RAD/SEC)
¢D0
_6
C:;,
"n;
(:Z)
4.oh
FIGURE 144
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS CLOSED FORFORWARDC.G. LAUNCHCONDITION
258
APPENDIX E
• LAUNCH• RSS WITH BCS CLOSED• MACH: 0.40• ALTITUDE= 15,000 FT.• GROSS WEIGHT= 2500 LBS.• C.G.: 20% MAC
-!
NO. GRIN II I
I I8o -_.2o -o.Bo -0.40 o.oo o.qo
(RAD/SEC)
4
(.0
0
OO
C.)LIJL,9
_23
3
c_c_
C_
C_od
oI;
FIGURE 144 (CONCLUDED)
DASTARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS CLOSED FOR..... FORWARDC.G. LAUNCHCONDITION
259
APPENDIX E
.
-20. O0
• LAUNCH• PCS WITH RSS CLOSED• MACH: 0.40• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2500 LBS.• C.G.: 20_ MAC
t I I I I
I
- - -,_]k. ,_,,k.-_
C_
4
0
C_
A
COLLI
i °v
3
I I I I "_-16.00 -12.00 -8.00 -It. O0 0.00 Ll_ob
0_ (RAD/SEC)
FIGURE 145
DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSED FORFORWARDC.G, LAUNCH CONDITION ....
260
APPENDI X E
• LAUNCH• PCS WITH RSS CLOSED• MACH: 0.40• ALTITUDE: 15,000 FT.• GROSS WEIGHT, 2500 LBS.• C.G.: 20_ MAC
I I I
_A
I I I I I
'o-;
CICO
",.,,i
(_,
'...:
0uJ
o ,,,0
',2 _
3°'-'2
0
-1.60 -I. 20 -0. BO -0.40 O. O0 O.40 O.
o (RAD/SEC)
FIGURE 145 (CONCLUDED)
DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR' ' ' FORWARDC.G. LAUNCH CONDITION ....
261
APPENDIX E
• LAUNCH• PCS WITH RSS AND GLA CLOSED• MACH: 0.40• ALTIT1JDE: 15,000 FT.• GROSS WEIGHT: 2500 LBS.• C.G.: 20_ MAC
I I I I I
oc_
(_
I I I
-20. O0 -16. O0 -12. O0 -B. OO -4. O0 O. 00
(_(RAD/SEC)
4.ob
262
FIGURE 146
DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA CLOSED FOR' FORWARDC.G.LAUNCHCONDITION "
APPENDIX E
• LAUNCH• PCS WITH RSS AND GLA CLOSED• MACH: 0.40• ALTITUDE: 15,000 FT.• GROSS WEIGHT= 2500 LBS.• C.G.: 20_ MAC
I I I
I I I I I
-_.60 -1.20 -o.so -0.40 0.00 0.40
o (RAD/SEC)
"eJ
0L_
3
oJ
FIGURE 146 (CONCLUDED)
DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA CLOSED FORFORWARDC.G. LAUNCHCONDITION
263
APPENDIX E
• LAUNCH• BCS WITH RSS CLOSED• MACH: 0.40• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2500 LBS.• C.G.: 20_ MAC
I I I I
\\
FIGURE 147
DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR' FORWARDC.G. LAUNCHCONDITION ....
264
APPENDIX E
• LAUNCH
• BCS WITH RSS CLOSED
• MACH: 0.40
• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2500 LBS.
• C.G.: 20% MAC
AIN
I I
I I
I
-I.60 -I.20 -0.80 -0.40 O.O0 O.LIO
c_(RAD/SEC)
o=
C3
,-G
c_0o
. °
('-3o
c;
o
"c;
,c_
#-,,,
ILl
_o ,_-- OC
3
FIGURE 147 (CONCLUDED)
DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR• ' FORWARD C.G. LAUNCH CONDITION "
265
APPEND I X E
• LAUNCH• RSS• MACH: 0.40• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2200 LBS.• C.G,: •33% MAC
GRNNO.I .59_;0
2 I. 0003 l. 680
I I I
20. O0 - i 6. O0 -12. O0 8. O0
(_ (RAD/SEC)
266
FIGURE 148
DAST ARW-2 RSS SYSTEM GAI N/PHASE ROOT LOCI WI TH BASIC A I RPLANE FOR........ AFT C.G, l_.AI,_ru 'CONDITION._,._,,
APPEND IX E
• LAUNCH• RSS
• MACH: 0.40
• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2200 LBS.• C.G,: 33% MAC
t
l l.OO03 |.680
I I
It •
WI
-1.60 -1,2.0 O.qO
I
-0.80 O. u,O O. O0
(RAD/SEC)
r,-;
0
o,;
CDgO
LULO
-- n,,"
3
(:3
tO
0
0.Bb
FIGURE 148 (CONCLUDED)
DAb_ ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC AIRPLANE FOR....... AFT C.Go LAUNCH CONDITION
267
APPENDIX E
• LAUNCH• RSS WITH PCS CLOSED• MACH: 0.40• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2200 LBS.• C.G,: 33% MAC
o (RAD/SEC)
FIGURE 149
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS CLOSED FOR........ AFT C.G. LAUNCH CONDITION ' "
268
APPENDI X E
• LAUNCHRSS WITH PCS CLOSED
• •• MACH. 0.40• ALTITUDE: 15w000 FT.• GROSS WEIGHT: 2200 LBS.• C.G.: 33_ MAC
=. o.,_j \ ' _ 'i .S9SO X /2 i,ooo X " t
t
t
<D2>I I I I
-_.eo -_.2o -o.8o .o.4o o.oo o.qo
o"(RAD/SEC)
o-;
E3¢0
O4
,...,
(.3LULr)
. °
n.-
3
¢D
(:3C,J
¢3("U
o.Bb
FIGURE 149 (CONCLUDED)
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS CLOSED FOR....... AFT CoG. LAUNCH CONDITION
269
APPENDIX E
• LAUNCH• RSS WITH PCS AND GLA CLOSED• MACH: 0.40• ALTITUDE: 15,000 FT.• GROSS_WEIGHT: 2200 LBS.• C.G.= 33% MAC
I I I I
FIGURE 150
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS AND GLA CLOSED FOR....... AFT C.G. LAUNCH CONDITION
270
APPENDIX E
• LAUNCH• RSS WITH PCS AND GLA CLOSED• MACH: 0.40• ALTITUDE= 15,000 FT.• GROSS WEIGHT: 2200 LBS.• C.G.: 33% MAC
I
I
3 | .680_
I I I 1
I
I
, I I I• 60 -I. 20 -0.80 -O.u,o O. O0
(RAD/SEC)
¢:3to
C)CU
C)QD
"3
Oc_
C)to
c;
C)
°
C)_J
Io.qo O._:b
(..)uJCO
¢=:n-
3
FIGURE 150 (CONCLUDED)
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS AND GLA CLOSED FOR..... AFT C.G. LAUNCH CONDITION
271
APPEND IX E
• LAUNCH• RSS WITH BCS CLOSED• MACH: 0.40• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2200 LBS.• C.G;: 33_ MAC
I I I I / IP__d:IN
L.oooI. 680
I
+
I
_ /
, /, / /i i /
t .
-20. O0 - ! 6. O0 - 12. O0 -8. O0 -LI. O0
ar (RAD/SEC)
//
/
/
/
//
,/
/°/'
//
o
C_o
CDC_
A
LIJ
._ r_-- ==E
n-_=_
3
0CD
c;
/
COQ
oc)
0.00 4.ob
FIGURE 151
DAS'r' ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS CLOSED FOR..... A'FTC.G. LAUNCH CONDITION
272
APPENDIXE
GRINNO. ,5950
1o000I. 680
• LAUNCH• RSS WITH BCS CLOSED• MACH: 0.40• ALTITUDE= 15,000 FT.• GROSS WEIGHT: 2200 LBS,• C.G,: 33% MAC
N-
! I
-! . 60 -I. 20 -0.80
I I
I
I
j: L I
-o.qo o.0o o._o(RAD/SEC)
o-;
¢,,o
c_("d
",..,;
ILlO3
If",=EO:;v
3
o
c_Eo
c:;
c_(%1
c;o.eb
FIGURE 151 (CONCLUDED)
DAS'T ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS CLOSED FOR........ AFTC.G. LAUNCH CONDITION
273
APPENDIXE
• LAUNCH• PCS WITH RSS CLOSED• MACH: 0.40• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2200 LBS.• C.G.: 33% MAC
NO.123
t-20. O0
GRIN.59501.0_
I I I I
oJ
r_f_j
¢.)LU(,/3
3.-..)
,_.ob-16oo -_zoo -Boo qoo ooo
(RAD/SEC)
FIGURE 152
DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSED FORAFT C.G. LAUNCH CONDITION ....
274
APPEND IX E
• LAUNCH• PCS WITH RSS CLOSED• MACH: 0.40• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2200 LBS.• C.G.: 33% MAC
I I I
tL
lJ
÷
I I
-I .BO -I .20 -0.80
l
i I-0. rio O. O0
(RAD/SEC)
¢,.;
0
r,;
0
,
(,o
"c:;
• °
C'g
I
C_u.J
:=. {_
:3
(:3
FIGURE 152 (CONCLUDED)
DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSED FORAFT C.G. LAUNCH CONDITION
275
APPENDIX E
• LAUNCH• PCS WITH RSS AND GLA CLOSED• MACH: 0.40• ALTITUDE: 15,000 FT.• GROSSWEIGHT: 2200 LBS.• C.G,: 33% MAC
I_. GRIN
S 1.680
I I I' I
I I
cJ
£M
(RAD/SEC)
FIGURE 153
DAS'r ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA CLOSED FOR.... AFT C.G. LAUNCH CONDITION ' '
276
APPENDI X E
• LAUNCH• PCS WITH RSS AND GLA CLOSED• MACH: 0.40• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2200 LBS.• C.G,: 33% MAC
IN_.
3i.ooo
I I I
1.68o
I
i
I I
-1.60 -1.20 -O,BO
I
i I t-0.40 0. O0
0 (RAD/SEC)
0.40
o-;
C)
C:)
A
C/3
r_
3°---.)
C_
• °
t3
'=5
+=5o.sb
FIGURE 153 (CONCLUDED)
DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA CLOSED FOR
.... AFT C.G. LAUNCH CONDITION
277
APPENDIX E
• LAUNCH• GLA AILERON WITH RSS, PCS AND
GLA STABILIZER CLOSED• MACH: 0.40• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2200 LBS.• C.G,: 33% MAC
I I I I
,"- o o n I-20 OO -16. O0 -12.00 -8.00 -it. O0 0.00
o (RAD/SEC)
C3
(:3C_
C3
A
(.3I,,
C3
_= <
3"-"3
C3
C3
I
278
FIGURE 154
DAST ARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLA' STABILIZER LOOPS CLOSED FOR AFT C,G. LAUNCH CONDITION
-125.00 -I00.00 -75.00
APPENDIX E
• LAUNCH
• GLA AILERON WITH RSS, PCS ANDGLA STABILIZER CLOSED
• MACH: 0.40• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2200 LBS.• C.G,: 33% MAC
I I I
I
-50. O0 -25. O0
(RAD/SEC)
¢/1
E_
C_,ul
C3
l:3C3
.(:3
c._LJJ
E3(:3
,u;oa
c:)
o.oo 2s.bo
v
FIGURE 154 (CONTINUED)
DAST ARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLASTABILIZER LOOPS CLOSED FOR AFT C,G. LAUNCH CONDITION
279
t
APPEND IX E
• LAUNCH• GLA AILERON WITH RSS, PCS AND
GLA STABILIZER CLOSED• MACH: 0.40• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2200 LBS.• C.G.: 33% MAC
I I I
/
I I I Io6D -1.20 -0.80 O. 40
I
-0.40 O. O0
o C D/S ;C)
('M
. °
3°,,,_
. °
. °
Jo.sb
280
FIGURE 154 (CONCLUDED)
DASTARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCIWlll-I RSS, PCS AND GLASTABILIZER LOOPS CLOSED FOR• AFT C;G. LAUNCH CONDITION
APPENDIX E• LAUNCH• GLA STABILIZER WITH RSS, PCS
AND GLA AILERON CLOSED• MACH; 0.40• ALTITUDE; 15,000 FT.• GROSSWEIGHT: 2200 LBSo• C.G.: 33% MAC
I I I ._...-- 11
, I-20. O0 - 16. O0 - 12. O0 -8. O0 -¼. O0 0. O0
(_D/SEC)
C_
,rd
A
O _
3
0
"rd
_.ob
FIGURE 155
DAST ARW-2 GLA STAB IL IZER LOOP GA IN/PHASE ROOT LOC I W ITH RSS, PCS AND GLAAILERON LOOPS CLOSED FOR AFT C.G. LAUNCH CONDITION
281
APPENDIXE
-125.00 -100.00 --/5.00
• LAUNCH
• GLA STABILIZER WITH RSS, PCSAND GLA AILERON CLOSED
• MACH: 0.40• ALTITUDE= 15,000 FT.• GROSS WEIGHT= 2200 LBS.• C.G,: 33% MAC
I I I I r-,-
c_LI3
o
o
-¢3
8
-so. oo -zs. oo o. oo zS.bo
(RAD/SEC)
A
(_LLI
c_ o')
rv"
3*'--'3
_3(_
1.13
FIGURE 155 (CONTINUED). . . , . . .
DA_T ARW-2 GLA STABILIZER LOOP GAIN/PHASE ROOT LOCI WIT1-! RSS, PCS AND GLAAILERON LOOPS CLOSED FOR AF'r C.G; LAUNCH CONDITION
282
-I
APPENDI X E
• LAUNCH• GLA STABILIZER WITH RSS, PCS AND
GLA AILERON CLOSED• MACH: 0.40• ALTITUDE: 15,000 FT.• GROSSWEIGHT: 2200 LBS.• C.G.: 33% MAC
I I I
I
I
rJo
Od
aD
:3:°,,_j
C)rE)
¢%t. °
O0
I I I I I_
60 -_.ao -O.BO -O._O o.oo 0._0 o.eb
(7 (RAD/SEC)
FIGURE 155 (CONCLUDED)
DAST ARW-2 GLA STABILIZER LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLA
AILERON LOOPS CLOSED FOR AFT C.G. LAUNCH CONDITION
283
DO 6000 2145 REV 9182
APPENDIX E
• LAUNCH• BCS WITH RSS CLOSED• MACH: 0.40• ALTITUDE= 15,000 FT.• GROSS WEIGHT: 2200 LBS.• C.G.: 33_ MAC
I I I I
FIGURE 156
DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR
..... AFT C.G. LAUNCH CONDITION ....
284
APPENDI X E
• LAUNCH• BCS WITH RSS CLOSED• MACH: 0.40• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2200 LBS.• C.G.= 33% MAC
| NO.
iIf
4-
i
+
•$95o[..oQo
\\
\
i//
//
/
/
//
/
/
,//
/
//
/
// •
/'/
/'
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//
/
{.(}
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C_
, °
0L_
3
_---a.e,p
0 i , I t o."-1.6o -l._o -o.eo -o._o o.oo o._o o.eb
o (RAD/SEC)
FIGURE 156 (CONCLUDED)
DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR.... AFT C.G. LAUNCH CONDITION
285
APPEND IX E
• HIGH ALTITUDE
• RSS
• MACH: 0.70
• ALTITUDE: 50,000 FT.
• GROSS WEIGHT: 2500 LBS.
• C.G.: 20_ MAC
I I INO. GRIN
,59501.0003 t,680
-20. O0 - 16. O0 - 12. O0 -8. O0 -4. O0
o (RAD/SEC)
I
0.00
0
C_
_.ob
FIGURE 157
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC AIRPLANE FORFORWARD C,G. HIGH ALTITUDE CONDITION
286
APPENDI X E
• HIGH ALTITUDE• RSS• MACH: 0.70• ALTITUDE= 50,000 FT.• GROSS WEIGHT= 2500 LBS.• C.G.: 20_ MAC
,o. ._,_I, ooo1,68o
/
I-o. 8o -o. _o o. oo o. 4o
a (RAD/SEC)
c_143
C:)Cu
,-,l
QO
l:I r-_
I ....
I .'-'l
t , o
I
c:i
¢D
"¢g
C3
I I¢:;o.sb
FIGURE 157 (CONCLUDED)
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC AIRPLANE FOR..... FORWARDC,G. HIGH ALTITUDE CONDITION
287
APPENDIX E
• HIGH ALTITUDE• RSS WITH PCS CLOSED• MACH: 0.70• ALTITUDE= 50,000 FI".• GROSS WEIGHT= 2500 LBS.• C.G.: 20_ MAC
No. ._i I.. 000t.680
I I I
+
///
/
.
/°
I
r,-,c3
-20. O0 - 16. O0 - 12. O0 -8. O0 -4. O0 O. O0
(RAD/SEC)
(:3C3
OC3
_.ob
288
FIGURE 158
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS CLOSED FOR..... FORWARDC.G, HIGH ALTITUDE CONDITION
APPENDI X E
• HIGH ALTITUDE• RSS WITH PCS CLOSED• MACH= 0.70• ALTITUDE= 50,000 FT.• GROSS WEIGHT= 2500 LBS.• C.G.= 20_ MAC
' NO. GRIN I I _ Il ,$9S02 I. 000
i/ /
+
- I. 60 - 1.20 -0.80 -0. llO O, O0
cr (RAD/SEC)
O. qO
0-;
¢.o
Oa
',-,;
L)ILl
°
3
c_
, °
_o
c;
('%1
c;
0,.I
o.sb
FIGURE 158 (CONCLUDED)
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS CLOSED FOR..... FORWARDC.G; HIGH ALTITUDE CONDITION
289
APPENDIX E
• HIGH ALTITUDE• RSS WITH PCS AND GLA CLOSED• MACH: 0.70• ALTITUDE: 50,000 FT.• GROSS WEIGHT: 2500 LBS.• C.G.: 20% MAC
I I I
t .000I. 680
1-ii
/' J_
I •
• I o
/
//' !,LI
/ / JlJJfot /j+
__ • _--__-20. O0 -I6. O0 -12. O0 -B. O0 -q. O0 O. O0
,,.t,"
3.--._
C3
q;ob
o (RAD/SEC)
FIGURE 159
DA_T ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCl WITH PCS AND GLA CLOSED FOR
...... FORWARDC.G. _HIGH ALTITUDE CONDITION
290
APPENDIX E
• HIGH ALTITUDE• RSS WITH PCS AND GLA CLOSED• MACH: 0.70• ALTITUDE= 50,000 FT.• GROSS WEIGHT= 2500 LBS.• C.G.: 20_ MAC
I NO" I
_ I.O00
t.680
\
\,
t I
÷
I I
+i
I
4-
-I . 60 -t • 20 -0. BO -0. qo O. O0 o.qo
(RAD/SEC)
04
c:)¢.o
t_
LtJ
. C3
n_
3..--}
-+_o.sb
FIGURE 159 (CONCLUDED)
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS AND GLA CLOSED FOR...... FORWARDC.G. HIGH ALTITUDE CONDITION
291
APPENDIX E
• HIGH ALTITUDE• RSS WITH BCS CLOSED• MACH: 0.70• ALTITUDE: 50,000 FT.• GROSS WEIGHT: 2500 LBS.• C.G.: 20_ MAC
I I I IGRIN
.5950t.O00t.680
-20.00
//
//
//
/
/// /: /!
/
/ //$
-16.00 -12.00 -8.00 -q.o0
o (RAD/SEC)
(so')
II
I
I
0
I
I
/,/ (_
/ o
///
/
,./
I
o
",2
0
oJ
0
l oJo.oo _.ob
A
0
co
ra
3
292
FIGURE 160
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS CLOSED FORFORWARDC.G, HIGH ALTITUDE CONDITION
APPENDIX E
• HIGH ALTITUDE• RSS WITH BCS CLOSED
• MACH: 0.70
• ALTITUDE= 50,000 FT.• GROSS WEIGHT= 2500 LBS.
• C.G.: 20_ MAC
GRN
2 l.O003 t.680
I I I
.
-z.Go -_.2o -o.BO O.40 O.Bb
II
II
I
I
-0.40 0.00
(RAD/SEC)
{ o-;
c:,
(._
f..o
oc_
',:5
Od
t ,::;
A0U.IC,3
C3
3
FIGURE 160 (CONCLUDED)
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS CLOSED FOR
.... FORWARD C. G, H I GH ALT ITUDE COND I T I ON
293
APPENDIX E
• HIGH ALTITUDE• PCS WITH RSS CLOSED• MACH: 0.70• ALTITUDE: 50,000 FT.• GROSS WEIGHT: 2500 LBS.• C.G.: 20_ MAC
Ii
1i
e-l
i-20. O0
I I I tGRIN
• 59501.000
l. B80
o(_
_6C_d
C::,C)
cJLIJ/
/ , CD (,'3
/ i"3
/ , i_
0
.oh-16.oo -_z.oo -B,oo -4.oo moo 4
o (RAD/SEC)
294
FIGURE 161
DAST ARW-2 PCS GAIN/PHASE ROOT LOCl WITH RSS CLOSED FOR
FORWARD C.G. HIGH ALTITUDECONDITION
APPENDI X E
• HIGH ALTITUDE• PCS WITH RSS CLOSED• MACH: 0.70• ALTITUDE: 50,000 FT.• GROSS WEIGHT: 2500 LBS.• C.G.: 20_ MAC
NO. GAIN
.SgSO1.000_.680
I I I I I
it = I I
-1.6o -1.2o -0.80 -0.40 o.oo 0.40
o (RAD/SEC)
(:3£D
COC_
f4 C3
FIGURE 161 (CONCLUDED)
DASTARW-2 PCS GAIN/PHASE ROOT LOOI WITH RSS CLOSED FORFORWARDC.G. HIGH ALTITUDECONDIT10N
295
APPENDIX E
• HIGH ALTITUDE
• PCS WITH RSS AND GLA CLOSED
• MACH: 0.70
• ALTITUDE: 50p000 FT.• GROSS WEIGHT: 2500 LBS.
• C.G.: 20_ MAC
I I I INO. GRIN
1 .$9S02 I.ooo3 |.BSO
-20. O0
t�/
/ I
I
I
I
I
I
, _ , , I-16.00 -12.00 -B.O0 -q.O0 0.00
o (RAD/SEC)
C_(:3
C_
06
C..)LJJ
c_ c_
(Z
3
C_
C_
C3(:3
C}
o;4_ob
296
FIGURE 162
DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA CLOSED FOR' FORWARD C;G. HIGH ALTITUDE CONDITION
APPENDI X E
• HIGH ALTITUDE• PCS WITH RSS AND GLA CLOSED• MACH: 0.70• ALTITUDE = 50,000 FT.• GROSS WEIGHT: 2500 LBS.• C.G.: 20_ MAC
r
It
I ! I
(D_D
CDCU
QoD
C_tJJ
Oq
c_
3
CDC_
C_(D
CDCu
0OJ
4- 1.5O - 1.20 -0.80 -0. _o O.DO o. qo o, Bb
0 (RAD/SEC)
FIGURE 162 (CONCLUDED)
DAS'T ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA CLOSED FORFORWARD C.G. HIGH ALTITUDE CONDITION
297
APPENDIXE
• HIGH ALTITUDE• BCS WITH RSS CLOSED• MACH: 0.70• ALTITUDE: 50,000 FT.• GROSS WEIGHT: 2500 LBS.• C.G.: 20_ MAC
NO. I IGAIN1 . $950
g ,:ooo
\\,
\
\
I I
-2o.oo -_6.o0 -z2.oo -e.oo -,_.oo o.oo
o (RAD/SEC)
C3CD
("d
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C_
A
LIJ
3
°....)
C2_
c:;
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o_q.ob
298
FIGURE 163
DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOOI WITH RSS CLOSED FORFORWARDC.G, HIGH ALTITUDE CONDITION
APPENDI X E
• HIGH ALTITUDE• BCS WITH RSS CLOSED• MACH: 0.70• ALTITUDE: 50,000 FT.• GROSS WEIGHT: 2500 LBS.• C.G.- 20_ MAC
NO. GRIN; l .5950, 2 t. 000
; 3 t.68o
+
I
L-1.60 -1.20
-- I
I t [ I
-0.80 -0. _0 O.O0 O. 40
LO
O£M
/
rJL4J
3
. "--}
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c_£'4
c;
(RAD/SEC)
(:3C_J
o.Bb
FIGURE 163 (CONCLUDED)
DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS CLOSED FORFORWARDC.G.: HIGH ALTITUDE CONDITION
299
APPENDIX E
• HIGH ALTITUDE
• RSS
• MACH: 0.70• ALTITUDE: 50,000 FT.
• GROSS WEIGHT: 2200 LBS.
• C.G,: 33% MAC
I I I
I
-20. O0 - t 6. O0 - ! 2. O0 -8. O0 -q. O0 O. O0
(RAD/SEC)
FIGURE 164
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOOI WITH BASIC AIRPLANE FOR
...... AFr C.G, HIGH ALTITUDE CONDITION
300
APPENDIX E
• HIGH ALTITUDE• RSS• MACH: 0.70• ALTITUDE: 50,000 FT.• GROSS WEIGHT: 2200 LBS.• C.G,: 33% MAC
-1.61
I I
I I
-z.2o -o.8o -o.qo o.oo o.qo
a (RAD/SEC)
,,,.;
c_
C_GO
• °
A
LIJoq
c:) "_.
r'Y
3°--_
CDC_
¢J0
0
C)
o:sb
FIGURE 164 (CONCLUDED)
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC AIRPLANE FOR....... AFT C.G. HIGH ALTITUDE CONDITION
301
APPENDIX E
• HIGH ALTITUDE• RSS WITH PCS CLOSED• MACH: 0.70• ALTlll.IDE: 50,000 FT.• GROSS WEIGHT: 2200 LBS.• C.G.: 33% MAC
(RAD/SEC)
FIGURE 165
DAST'ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS CLOSED FOR
...... AFT C.G. HIGH ALTITUDE CONDITION
302
APPENDIX E
• HIGH ALTITUDE• RSS WITH PCS CLOSED• MACH: 0.70
• ALTITUDE: 50,000 FT.• GROSS WEIGHT: 2200 LBSo• C.G,: 33% MAC
i
i i I- 1.60 - 1.20 -0.80 -0. qO O. O0
(RAD/SEC)
0.40
C_
_J
C_GO
• °
_=_
0LU
IiTM
n-
3.-==_
0
'c;
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C_(-_
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o_Bb
FIGURE 165 (CONCLUDED)
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS CLOSED FOR..... AFT C.G. HIGH ALTITUDE CONDITION
303
APPENDIX E
• HIGH ALTITUDE• RSS WITH PCS AND GLA CLOSED
• MACH- 0.70
• ALTITUDE: 50,000 FT.• GROSS WEIGHT" 2200 LBS.
• C.G,: 33% MAC
c_(RAD/SEC)
FIGURE 166
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS AND GLA CLOSED FOR....... AFT C.G, HIGH ALTITUDE CONDITION
304
APPENDIX E
.e HIGH ALTITUDE• RSS WITH PCS AND GLA CLOSED• MACH: 0.70• ALTITUDE= 50,000 FT.• GROSS WEIGHT= 2200 LBS.• C.G;: 335 MAC
I I
I• 60 -1.20 -0.80 -0.40 O. O0
(RAD/SEC)
! I
O.qO
(,D
C_GO
u..I
3.,,.,.j
C_C_
C_(0
C:)('_
FIGURE 166 (CONCLUDED)
DAS't"ARW-2 RSS SYSTEN GAIN/PHASE ROOT LOCI WITH PCS AND GLA CLOSED FOR....... AFT C,Go HIGH ALTITUDE CONDITION
3O5
APPENDIXE
• HIGHALTITlJDE• RSS WITH BCS CLOSED• MACH: 0.70• ALTITUDE: 50,000 FT.• GROSS WEIGHT: 2200 LBS.• C.G;: 33_ MAC
I I I
-20. O0 -16.00 -12.00 -8.00 -=4.00
( RAD/SEC}
O. O0
FIGURE 167
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS CLOSED FOR...... AFT C.Go HIGH ALTITUDE CONDITION
306
APPENDIX E
• HIGH ALTITUDE• RSS WITH BCS CLOSED• MACH: 0.70• ALTITUDE: 50,000 FT.• GROSSWEIGHT: 2200 LBS.• C.G,: 33% MAC
I !
-1.60 ol.20 -0.80
o-;
f.D
b_
C_('%1
,00
-...:
A
LU
C1¢v
3
0o
- ._ . .,_ " o.eb
(RAD/SEC)
FIGURE 167 (CONCLUDED)
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS CLOSED FOR...... AFT C,G. HIGH ALTITUDE CONDITION ' '
307
APPENDIX E
• HIGH ALTITUDE• PCS WITH RSS CLOSED• MACH: 0.70• ALTITUDE: 50,000 FT.• GROSSWEIGHT: 2200 LBS.• C.G.: 33% MAC
I I I I
I I
/
I
iI
II
I
II
I
i l i
c_(I-)
0C3
.e,i
(:30
0_
A
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n.-
3
C:I
c_
C)CO
COCO
-20•O0 -16.00 -12.00 -8.00 -it. O0 0.00
q (RAD/SEC)
FIGURE 168
DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR' ' AFT C.G. HIGH ALTITUDE CONDITION
308
APPENDIX E
• HIGH ALTITUDE• PCS WITH RSS CLOSED• I_CH: 0.70• ALTITUDE: 50,000 FT.• GROSSWEIGHT: 2200 LBS.• C.G,: 33% MAC
I I I
-1.60 -1.20 -0. BO -0. llO O. O0 0.40
(_ (RAD/SEC)
0_
C)_D
Od
C__o
T-
A
LIJ
tY"v
.-.._
¢:3LO
c;
0
c;
C_t'u
c_o.Bb
FIGURE 168 (CONCLUDED)
DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR• • . AFTC.G. HIGH ALTITUDE CONDITION " "
309
APPENDIX E
• HIGH ALTITUDE• PCS WITH RSS AND GLA CLOSED• MACH: 0.70• ALTITUDE: 50,000 FT.• GROSS WEIGHT: 2200 LBS.• C.G,= 335 MAC
I I I I
c_
,fJ:3c_J
0
. ¢'_.I
£z)
, _ ""
r-,,
/ 3
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-20. O0 -16. O0 -12. O0 -B. O0 -4. O0 O. O0
(_(RAD/SEC)
C:}
",-d
_.0b
FIGURE 169
DA_ ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA CLOSED FOR.... AFT C.G. HIGHALTITUDE CONDITION
3]0
APPENDIX E
• HIGH ALTITUDE• PCS WITH RSS AND GLA CLOSED• MACI..I: 0,70• ALTITUDE: 50,000 FT.• GROSSWEIGHT: 2200 LBS.• C.G;= 33_ MAC
I ! I
, ,, , + \1 I• 60 -1.20 -0.80 -0. qO O. O0
o (RAD/SEC)
i o-;
CO0o
c)go
=oc;
C':,t'_
• °
¢M
I coo.4o olob
3LU
v
3
C:)C_
FIGURE 169 (CONCLUDED)
DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA CLOSED FOR.... AFT C.G_. HIGH ALTITUDECONDtTION
311
312
APPENDIX E
• HIGH ALTITUDE• GLA AILERON WITH RSS, PCS AND
GLA STABILIZERCLOSED• MACH: 0.70• ALTITUDE: 50,000 FT.• GROSS WEIGHT: 2200 LBS.• C.G,: 33% MAC
I I I I
T
C)0
C_c_
c'd.
c_c_
LI.I
11"r_r_,.
3,,-.,j
0
=-20.00 -16.00 -12.00 -e.O0 -_.OO 0.OO _.ob
O (RAD/SEC)
FIGURE 170
DAST ARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLASTAB I L IZER LOOPS CLOSED FOR AFT C.G. H I GH ALT ITUDE CONDI T I ON
APPENDIXE
• HIGHALTITUDE• GLA AILERON WITH RSS, PCS AND
GLA STABILIZERCLOSED• MACH: 0.70• ALTITUDE: 50,000 FT.• GROSS WEIGHT: 2200 LBS.• C.G,: 33% MAC
I I
.U_
0
-0
0
0
I
-so.oo -as.oo o.oo as.bo
o (RAD/SEC)
A
,,.i.I
r,,.-
3
FIGURE 170 (CONTINUED)
DAS'T ARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLASTAB I L IZER LOOPS CLOSED FOR AI=T C.G. H I GH ALT I TUDE CONDI T I ON
313
APPENDIX E
• HIGH ALTITUDE• GLA AILERON WITH RSS, PCS AND
GLA STABILIZER CLOSED• I_CH: 0.70• ALTITUDE= 50,000 FT.• GROSS WEIGHT= 2200 LBS.• C.G,: 33_ MAC
I I I
+
[.60 -1.20
1 o.;
to
0
LLI0'3
•-; ==C
o
r.-:
,5
0
•_, ,--,_
-o. 8o -o. 40 o. oo o. 4o o. 81o
o" (RAD/SEC)
:9
FIGURE 170 (CONCLUDED)
DAST ARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLASTABILIZER LOOPS CLOSED FOR AFT CoGoHIGH ALTITUDECONDITION
314
APPENDIX E
• HIGH ALTITUDE• GLA STABILIZER WITH RSS, PCS
AND GLA AILERON CLOSED• HACH: 0.70• ALTITUDE: 50p000 FT.• GROSS WEIGHT: 2200 LBS.• C.G.: 335 MAC
I I I ...,.._ I I
00
FIGURE 171
DAS'I"ARW-2 GLA STABILIZER LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLA' AILERONLOOPS CLOSED FOR AFT C.G. HIGH ALTITUDE CONDITION
3]5
APPENDIX E
• HIGH ALTITUDE• GLA STABILIZER WITH RSS, PCS
AND GLA AILERONCLOSED• MACH: 0.70• ALTITUDE= 50,000 FT.• GROSS WEIGHT= 2200 LBS.• C.G,: 33_ MAC
I I I I
\\
-lr,5.00 -lO0.O0 -75. O0I
-50. O0 -25. O0
(RAD/SEC)
u_
C3(:3
°0
.U3
0
=;-0
==
=;.I-O_
o. oo 2s. bo
A
LUoo
FIGURE 171 (CONTINUED)
DA_ ARW-2 GLA STABILIZER LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLAAILERON LOOPS CLOSED FOR AFT C.G. HIGH ALTIT1JDE CONDITION
316
APPENDIXE
• HIGHALTITUDE• GLA STABILIZER WITH RSS, PCS AND
GLA AILERON CLOSED• I_CH: 0.70• ALTITUDE= 50,000 FT.• GROSS WEIGHT= 2200 LBS.• C.G;: 33% MAC
t •
I t I
-1.6o -1.2o -o.eo -0.40 o.oo o.qo
c (RAD/SEC)
C:)f,o
c_
'oJ
C3gO
L,IJC/3
=' (:::3
-_..=_r_,
3,,,--,)
0
''5
f-,
1,5o.8b
FIGURE 171 (CONCLUDED)
DAb_ ARW-2 GLA STABILIZER LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLAAILERONLOOPS CLOSED FOR AFT C.G. HIGH ALTITUDE CONDITION
317
APPENDIX E
• HIGH ALTITUDE• BCS WITH RSS CLOSED• MACH: 0.70• ALTITUDE= 50,000 FT.• GROSSWEIGHT: 2200 LBS.• C.G,: 33% MAC
I I I I
\\
I I-20. OO -16. O0 -l 2. O0 -8. O0 -It.O0
0, (RAD/SEC)
0
0
L-J
O_
C3
I-
o.oo _ob
FIGURE 172
DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR' AFT C.G. HIGH ALTITUDE CONDITION ' "
318
APPENDI X E
• HIGH ALTITUDE• BCS WITH RSS CLOSED• MACH: 0.70• ALTITUDE: .50,000 FT.• GROSSWEIGHT: 2200 LBS.• C.G,: 335 MAC
I
I
I
I
I
: i I _,- I-0. qO O. O0
o (RAD/SEC)
-1.60 -1.20 -0.80 O.qO
(%1
m_o.ob
FIGURE 172 (CONCLUDED)
DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR.... AFT CoG. HIGH ALTITUDE CONDITION •
319
APPENDIX E
• CRUISE• RSS• 1.0g FLIGHT• MACH: 0,80• ALTITUDE= 46,800 FT.• GROSS WEIGHT= 2500 LBS.• C.G.: 20_ MAC
t,,o., .s_ t ' '1.000
3 t. 680
I
, ,, , ._
/ , /_
// ' /_
/i/ I ru
3
/ "_
-20.00 -1_.oo -t2.oo -8.oo -q.oo o.oo
c_ (RAD/SEC)
C:)
",-G
C)
,-,;Li. Ob
FIGURE 173
DASTARW-2 RSS SYSTEM GAIN/PHASE ROOT LOOI WITH BASIC AIRPLANE FOR..... FORWARDC.G. CRUISE CONDITION
320
NO.
!
3
i
APPENDIX E
• CRUISE• RSS• 1.0g FLIGHT• MACH: 0,80• ALTITUDE: 46,800 FT.• GROSS WEIGHT: 2500 LBS.• C.G.: 20_ MAC
GR N'_,. I . I
fi
JI
i I I I-l.so -1.2o -o.8o -o.qo o.oo
(RAD/SEC)
_D
C_
"oJ
J
c_
A
c.)LUCO
oc
3°'b
(:3C_
O('_
I0.40 O._:b
FIGURE 173 (CONCLUDED)
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC AIRPLANE FOR....... FORWARDC.G. CRUISE CONDITION
321
APPENDIX E
• CRUISE• RSS WITH PCS CLOSED• 1.0g FLIGHT• MACH: 0.80• ALTITUDE: 46,800 FT.• GROSS WEIGHT: 2500 LBS.• C.G.: 20_ MAC
!
!J
-20.00
l, oooI._
I
I
i i- !6. O0 - 12. O0 -8. O0 -q. O0 O. O0
j//
/ /;//
/
/ ,,
o (RAD/SEC)
//
/
/'
(:3
{3LU
oo
O_
3
c_
E_(:_
(:3(3
(3
q. 0b
322
FIGURE 174
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS CLOSED FOR.... FORWARDC.G. CRUISECONDITION
APPENDIXE
• CRUISE• RSSWITH PCS CLOSED• l oOg FLIGHT• MACH: 0.80
• ALTITUDE: 46,800 FT.• GROSS WEIGHT: 2500 LBS.
• C.G.: 20_ MAC
I I I
2 l.O003 1.680
I
r
I I I- 1.60 -1.20 -0.80 -0. qo O. O0
c_ (RAD/SEC)
UP
_4
c_)LU03
o..:_ C3
r,,"
3
i •"'J
1o
of.o
c_
c:;
I
(DOd
Io. qo 0.'_
FIGURE 174 (CONCLUDED)
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS CLOSED FOR..... FORWARDC. G. CRUI SE CONDI T I ON • •
323
APPENDIXE
• CRUISE• RSS WITH PCS AND GLA CLOSED
• 1.0g FLIGHT• MACH: 0.80
• ALTITUDE: 46,800 FT.• GROSS WEIGHT: 2500 LBS.• C.G.: 20_ MAC
I I I
I
FIGURE 175
DA_T ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS AND GLA CLOSED FOR........ FORWARDC.G. CRUISE CONDITION
324
t
2 t .0003 !. 680
APPENDI X E
• CRUISE• RSS WITH PCS AND GLA CLOSED
• 1,0g FLIGHT• MACH- 0,80
• ALTITUDE= 46,800 FT.• GROSS WEIGHT." 2500 LBS.• C.G.= 20_ MAC
I I I
i , I I I-z.so -_.2o -o.eo -o.qo o.oo 0.40
(RAD/SEC)
o;
C3¢0
C_OJ
C_QO
A
r_LUo'3
TM
C3'¢Cn,"
3.-,,_
0(-_
C3C_J
o.sb
FIGURE 175 (CONCLUDED)
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS AND GLA CLOSED FOR.... FORWARDC.G. CRUISE CONDITION
325
APPENDIX E
• CRUI SE• RSS WITH BCS CLOSED
• 1.0g FLIGHT• MACH: 0,80• ALTITUDE, 46,800 FT.• GROSS WEIGHT: 2500 LBS.• C.G." 20_ MAC
NO. GAIN.$9502 t.O003 L.880
I I I
3.-,,_
-20.00 -16.00 -t2.OO -8.00 -q.O0 0.00 4.ob
(_ (I_D/SEC)
FIGURE 176
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS CLOSED FOR.... FORWARDC.G. CRUISE CONDITION
326
APPENDIX E
• CRUISE• RSS WITH BCS CLOSED
• 1,0g FLIGHT• MACH: 0.80
• ALTITUDE= 46,800 FT.• GROSS WEIGHT= 2500 LBS.• C.G.: 20_ MAC
_,I I _ INO OR," \
2 I.OOO \
: I-1.6o -1.2o -o.eo -o,4o o.oo 0.40
(RAD/SEC)
C_(.D
c_c,J
0
U'3
3
0c_
¢D
Od
FIGURE 176 (CONCLUDED)
DAST ARW-2 RSS SYS'TEM GAIN/PHASE ROOT LOCI WITH BCS CLOSED FOR..... FORWARDCoG. CRUISECONDITION
327
tEP
I
-20.O0
APPENDIX E
• CRUISE• PCS WITH RSS CLOSED• 1.0g FLIGHT• MACH: 0.80
• ALTITUDE: 46,800 FT.• GROSS WEIGHT: 2500 LBS.
• C.G.: 20_ MAC
I I I I
I I I
00
Od
00
A
r_"v
3°..--_
j J° -(3
0C_
00
0
-16.00 -12.00 -8.00 -ll.O0 0.00 4.
o (RAD/SEC)
FIGURE 177
DAST ARW-2 PCS GAIN/PHASE ROOT LOOI WITH RSS CLOSED FORFORWARDC.G. CRUISE CONDITION
328
APPENDI X E
• CRUI SE• PCS WITH RSS CLOSED• 1oOg FLIGHT• MACH= 0,80• ALTITUDE- 46,800 FT.• GROSS WEIGHT: 2500 LBS.• C.G,: 20_ MAC
I I I
4-
J
I
II I I-1.60 -1.20 -0.80 -0._0 O. O0 O. qo
C:,
OGO
. °
LI.I
::a, C3
3°.-...)
C,C_
qD
C_J
"c;
00,.I
o.sb
o (RAD/SEC)
FIGURE 177 (CONCLUDED)
DAST ARW-2 PCS GAIN/PHASE ROOT LOOI WITH RSS CLOSED FOR' " FORWARDC.Go CRUISE CONDITION
329
APPENDIXE
• CRUISE• PCS WITH RSS AND GLA CLOSED• 1.0g FLIGHT• MACH: 0.80• ALTITUDE: 46,800 FT.• GROSS WEIGHT: 2500 LBS.• C.G.: 20_ MAC
I I I I
i
iI
eE_.- e,le- I
I I I I
C_C_
£3C_
00
.ob-20.00 -16.00 -12.00 -8.00 -ll.O0 0.00
0 (RAD/SEC)
FIGURE 178
DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA CLOSED FORFORWARDC.G.CRUISECONDITION
330
lo
APPENDI X E
• CRUISE• I:_S WITH RSS AND GLA CLOSED• 1,0g FLIGHT• MACH= 0.80
• ALTITUDE= 46,800 FT.• GROSS WEIGHT= •2500 LBS.• C.G.= 20_ MAC
I I I
I
I I I I
O
(_
00
(i)
.,,--)
0
0
c_
C)
C)
o.8b- I. 60 - 1.20 -0.80 -0. q,o 0. O0 O. qO
(RAD/SEC)
FIGURE 178 (CONCLUDED)
DAST ARW-2 PCS GAIN/PHASE ROOT LOOI WITH RSS AND GLA CLOSED FORFORWARDC.G.CRUISECONDITION
331
APPENDI X E
• CRUISE• BCS WITH RSS CLOSED• 1.0g FLIGHT• MACH: 0,80• ALTITUDE= 46,800 FT.• GROSS WEIGHT= 2500 LBS.• C.G.: 20_ MAC
I I' I I
t I-2o.oo -_6.oo -12.oo -e.oo -q.oo o.oo
o (RAD/SEC)
C_C3
Cd
FIGURE 179
DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR' FORWARDC.G. CRUISECONDITION '
332
APPENDIX E
• CRUI SE• BCS WITH RSS CLOSED
• 1.0g FLIGHT• MACH: 0,80
• ALTITUDE= 46,800 FT.• GROSS WEIGHT= 2.500 LBS.
• C.G.: 20% MAC
I I I
(:3c_
I (:3('%1
I ,,c_-o._o o.oo o.40 o.8b
(_ (RAD/SEC)
FIGURE 179 (CONCLUDED)
DAS'T ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS CLOSED FORFORWARDC.G. CRUISECONDITION "
333
APPENDIX E
• CRUISE• RSS• 1.2g FLIGHT• MACH: 0.80• ALTITUDE: 46,800 FT.• GROSS WEIGHT: 2200 LBS.• C.G,: 33_ MAC
I I IGlen
2 t.O003 t. 680
t
-20.00 -16.00 -12.00
//!
//
//
/
//
1
I//
/'I
/ J
I //
-8. O0 -q. O0
(RAD/SEC)
,/
/
//
A
LLI
3
c_c_
-=;
C_c_
C_0
o.oo q.eb
FIGURE 180
DAS'T ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC AIRPLANE FOR........ AFT C.Go CRUISECONDITION
334
NO. / GRIN Ii I / .5950
I:%
Jir
- . 60
APF_ENDI X E
• CRUI SE• RSS
• 1.2g FLIGHT• MACH: 0,80• ALTITUDE; 46,800 FT.• GROSSWEIGHT: 2200 LBS.• C.G,: 33% MAC
I
-t .20
I
I
JiI I
-0.80 0 40 0 O0 0 40
tO
r3
CO
CO
CO
0,_
a (RAD/SEC)
C3
3
FIGURE 180 (CONCLUDED)
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC AIRPLANE FOR....... AFT C.G. CRUISECONDITION
335
APPENDIX E
• CRUISE• RSS WITH PCS CLOSED• 1,2g FLIGHT• MACH: 0,80• ALTITUDE= 46,800 FT.• GROSS WEIGHT= 2200 LBS.• C.G.: 33_ MAC
No.
+
!
I
GRIN.59501.0001.600
I I
//
/
i I-20. O0 - 16. O0 - 12. O0 -8. O0 -q. O0 O. O0
(RAD/SEC)
C3'0
C_
I
C3,
¢.>LIJO0
r", •<En."
_o=;
q.ob
FIGURE 181
DAS'I"ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS CLOSED FOR.... AFTC.G. CRUISE CONDITION
336
APPENDI X E
• CRUI SE• RSS WITH PCS CLOSED
• 1.2g _FLIGHT• NIACH: 0,80• ALTITUDE: 46,800 FT.• GROSSWEIGHT= 2200 LBSo• C.G,-. 33_ I_C
NO GR N I '-, I (", I," .$9 0 \ \2 t. ooo x
I I
=$(
.60 -1.20 -0.80 -0.40 0.00
o (RAD/SEC)
GO
Ck]
C)CO
• °
A
OLU
c_ L/')
r..; r-_
n.-
t_
GO.
c)
(%1
"¢5
Cd
i ¢5o.4o o.sb
FIGURE 181 (CONCLUDED)
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS CLOSED FOR........ AFT C.G. CRUISE CONDITION ' •
337
APPENDIXE
• CRUISE• RSS WITH PCS AND GLA CLOSED• 1,2g FLIGHT• MACH: 0,80
• ALTITUDE* 46,800 FT.• GROSS WEIGHT: 2200 LBS.
• C.G,: 33% MAC
t
-20. O0
GRINNO. .5950
2 bOO03 1.680
ii j/j!i/ / , -o
, 3
__m I
-16.00 " -12,00 -8.00 -U,.O0 0,00
C)c)
c)O
4.ob
(RAD/SEC)
FIGURE 182
DAS'T ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS AND GLA CLOSED FOR........ AFT C.G. CRUISE CONDITION
338
• MACH:• ALTITt
• GROSS• C.G..
•SgSOX2 l .ooo "x
APPENDIX EORUI SE
RSS WITH PCS AND GLA CLOSED1,2g FLIGHT
0,80ALTITUDE: 46,800 FT.GROSSWEIGHT= 2200 LBS.
33_ MAC
-1I I I I
60 -1.2o -o.Bo -0.40 o.oo o.qo
(_ (RAD/SEC)
_D
C)('d
CDCO
. °
"c;
Od
o,Bb
A
r.)LLI03
ocv
3
c:)
FIGURE 182 (CONCLUDED)
DAST ARW-2 RSS SYSTl_M GAIN/PHASE ROOT LO01 WITH PCS AND GLA CLOSED FOR..... AFT C.G. (_RUISE CONDITION
339
APPENDIX E
• CRUISE• RSS WITH BCS CLOSED
• 1.2g FLIGHT• MACH: 0,80
• ALTITUDE: 46,800 FT.• GROSSWEIGHT: 2200 LBS.
• C.G,: 33% MAC
I I I
FIGURE 183
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS CLOSED FOR........ AFT C.G, CRUISE CONDITION " ' "
34O
N'_30._ GRIN
.59S01.000t.680
i
Jb!
tJI
ii
I
,4-i
r-1.60 -1.20 -0.80
APPENDIX E
• CRUISE• RSS WITH BCS CLOSED• 1.2g FLIGHT• MACH: 0;80• ALTITUDE: 46,800 FT.• GROSSWEIGHT: 2200LBS.• C.G,: 33_ MAC
_D
C3
(RAD/SEC)
o
z=.f--
C_)Lu
• C3
3...--:,
FIGURE 183 (CONCLUDED)
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS CLOSED FOR....... AFTC.G. CRUISE CONDITION
341
,
t-
APPENDIX E
• CRUISE• PCS WITH RSS CLOSED
• 1.2g FLIGHT• MACH: 0,80• ALTITUDE:- 46,800 FT.• GROSS WEIGHT: 2200LBS.• C.G.: 33_ MAC
i. z& I,
I I I I
cJo')
C;,
-4
A
/ t,,
-....
3
C3(:_
Q
-GJO. O0 - 16. O0 - 12. O0 -B. O0 -q. O0 O. O0 it. O0
(RAD/SEC)
FIGURE 184
DAST ARW-2 PCS GAIN/PHASE ROOT LOOI WITH RSS CLOSED FOR' ' AFTC.Go CRUISE CONDITION "
342
APPENDI X E
• CRUISE• PCS WITH RSS CLOSED• 1.2g FLIGHT• MACH: 0;80
• ALTITUDE: 46,800 FT.• GROSS WEIGHT: 2200 LBSo• C.G;= 33_ MAC
I i o_...,.
1
!
I
I
-0.80 -0. LlO O. O0
(RAD/SEC)
0;
C:,
0
QD
A
I.iJu3
n.,
3
CD
CD
0t_
c;
¢'d
J f_0.40 o.sb
FIGURE 184 (CONCLUDED)
DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR" ' ' AFTC.G.CRUISE CONDITION ""
343
f
fi
lr
APPENDI X E
• CRUI SE• PCS WITH RSS AND GLA CLOSED• 1.2g FLIGHT •• MACH= 0.80• ALTITUDE= 46,800 FT.• GROSSWE IGHT: •2200 •LBS0• C.G.= 33_ MAC
(lr.)
C_0
/ .// _0
/j,/
/' I
1
/ I /
I t-20.00 -16.00 -12.00 -8.00 -Lto O0 0.00
(RAD/SEC)
LU
n,"
3
c;
0o
00
_.ob
FIGURE 185
DAS'I" ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA CLOSED FOR.... AFT C°Go CRUISE CONDITION _ '
344
APPENDIX E
• CRUI SE• PCS WITH RSS AND GLA CLOSED
• 1.2gFLIGHT• HACH: 0,80• ALTITUDE; 46,800 FT.• GROSSWE IGHT: •2200 LBS.• C.G,: 33% MAC
JI
I4
+
tf
t
-1.60 -1.20 -0.80
" _i_, i
-0. qO O. O0
(RAD/SEC)
0
TM
v
3o_
O
jo._o o.Bb
FIGURE 185 (CONCLUDED)
DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA CLOSED FOR.... AFT C.G. CRUISE CONDITION ' '
345
APPENDIXE• CRUISE
• GLA AILERON WITH RSS, PCS ANDGLA STABILIZERCLOSED
• 1.2gFLIGHT• MACH= 0.80
• ALTITUDE: 48,800 FT.• GROSS WEIGHT: 2200LBS.• C.G.: 33_ MAC
I I I I
J
-20.00 -_e.O0 -_2.00 -e.oo -_.00 0.00
(RAD/SEC)
C3(:3
O_
0
C)0
.=_
0L._
3.--,_
C_
0
FIGURE 186
DA_T ARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLASTABILIZER LOOPS CLOSED FOR AFT C,G. CRUISE CONDITION
346
APPENDIX E
• CRUISE
• GLA AILERON WITH RSS, PCS ANDGLA STABILIZERCLOSED
• t.2gFLIGHT• MACH: 0,80• ALTITUDE= 46,800 FT.• GROSS WEIGHT= 2200LBS.• C.G.: 33_ MAC
I Itni_-
c_
c_,_1")
OJ
0
-C:)
A
(.)u.I
n,,
3
C_C3
-c;u')
C_
C_
"¢j
I
I o
-so.oo -zs.oo o.oo zs.bo
_(RAD/SEC)
FIGURE 186 (CONTINUED)
DAST ARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLASTABILIZER LOOPS CLOSED FOR AFT C;Go CRUISE CONDITION
347
APPENDIX E
• CRUISE• GLA AILERON WITH RSS, PCS AND
GLA STABILIZER CLOSED• MACH: 0.80• ALTITUDE: 46,800 FT.• GROSS WEIGHT: 2200 LBS.• C.G.: 33% MAC
I I I
/
O
r_
. 0
. °
i
:_._o o:oo o:4o o.8_
(RAD/SEC)
348
FIGURE 186 (CONCLUDED)
DA_T ARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLASTABILIZER LOOPS CLOSED FOR AFT C,G. CRUISE CONDITION
APPENDIXECRUISE
GLA STABILIZER WITH RSS, PCSAND GLA AILERONCLOSED
-e 1,2gFLIGHT• MACH: 0,80• ALTIT1JDE: 46,800 FT.• GROSS WEIGHT: 2200 LBS.• C.G,: 33_ MAC
C_
Od
C_C)
P,J
C_C_
o_
I I I ._..--='
C_
O
"c4
4.ob
t
I
I
I
I
, I-20.00 -le.oo -12.oo -e.oo -q.oo o.oo
(RAD/SEC)
LU
'=En"v
3o--,_
FIGURE 187
DAST ARW-2 GLA STABILIZER LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLAAILERON LOOPS CLOSED FOR AFT C.G; CRUISE CONDITION '
349
APPENDIX E
• CRUISE• GLA STABILIZER WITH RSS, PCS
AND GLA AILERON CLOSED
• 1,2gFLIGHT• MACH: 0;80• ALTITUDE: 46,800 FT.• GROSS WEIGHT: 2200LBS.• C.G.: 33% MAC
I I I
I-',_5. O0 -tO0.O0 -75. O0 -50. O0 -25. O0 O. O0
(RAD/SEC)
u;
,,.=
.u";
t_
,%-('kl
0
0ILl03
• r",
n,"
3
0
-4
.p=
0
• °
t_
i'M
zs.bo
FIGURE 187 (CONTINUED)
DAsT ARW-2 GLA STABILIZER LOOP GAIN/PHASE ROOT LOOI WITH RSS, PCS AND GLA' AILERON LOOPS CLOSED FOR AFT C.G. CRUISE CONDITION
35O
APPEND IX E
• CRUI SE• OLA STABILIZER WITH RSS, PCS AND
OLA AILERON CLOSED• MACH: 0.80• ALTITUDE: 46,800 FT.• OROSSWEIOHT: 2200 LBS.• C.G.: 33% MAC
I I I I I
----.._..__....,..,fI
I I l I
• 60 - I. 20 -0. BO -0. LiD 0.00 0. _0
(_ (RAD/SEC)
C_
od
_D
A
0
C_
..: _cr,.,
0
. °
_uO
c;
3
o.sb
FIGURE 187 (CONCLUDED)
DA_T ARW-20LA STABILIZER LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLAAILERON LOOPS CLOSED FOR AFT C.O. CRUISE CONDITION •
351
APPENDIX E
• CRUISE• BCS WITH RSS CLOSED
• • 1.2g FLIGHT• MACH: 0,80
• ALTITUDE: 46,800 FT.• GROSS WEIGHT: 2200 LBS.
• C.G.: 33_ MAC
\
; /oz_ ,
0
cd(%1
0
A
3
00
00
"rd
-20. O0 - 16. O0 - _2. oo -8. oo -_. oo o. oo _.
o" (RAD/SEC)
FIGURE 188
DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR.... AFTC.G. CRUISE CONDITION ....
352
APPENDIX E
• CRUISE• BCS WITH RSS CLOSED
• 1.2g FLIGHT• I_CH: 0,80
• ALTITUDE: 46p800 FT.
• GROSS WEIGHT: 2200 LBS.• C.G.: 33_ MAC
- .60
r'-
I I I
-- --QI_I
- l. 20 -0.80 -0. u,o O. O0 O. 40
O" (RAD/SEC)
Q
c;oLBb
FIGURE 188 (CONCLUDED)
DAST ARW-2 BCS SYSTEM GAI N/PHASE ROOT LOCI WI TH RSS CLOSED FORAFT CoG. CRUISE CONDITION
353
APPENDIX E
• MAXIMUM 0 (Vd)• RSS• MACH= 0.86• ALTITUDE= 15,000 FT.• GROSS WEIGHT= 2500 LBS.• C.G.: 20_ NAC
I I I
A
LU
C3¢=:,'I"
3..,-_
-20.00 -t6.00 -t2.00 -8.00 -_,00
C_ (RAO/SEC)
FIGURE 189
DAS'I"ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC AIRPLANE FORFORWARDC.G. MAXIMUMDYNAMIC PRESSURE CONDITION
354
APPEND IX E
• MAXIMUM Q (Vd)• RSS• MACH: 0.86• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2500 LBS.• C.G.: 20_ MAC
I !
-0, qO O. O0
(RAD/SEC)
FIGURE 189 (CONCLUDED)
DAST ARW-2 RSS SYSTEM GAI N/PHASE ROOT LOOI WI TH BASI C A I RPLANE FORFORWARDC.G. MAXIMUMDYNAMIC PRESSURE CONDITION
355
APPENDI X E
• MAXIMUM _) (Vd)• RSS WITH PCS CLOSED• MACH: 0.86• ALTITUDE: 15,000 FT.• GROSS WEIGHT= 2500 LBS.• C.G.: 20_ MAC
I I I
I-20, O0 -16,00 -12.00 -8.00 -q.O0 0.00
C_ (RAD/SEC)
0
00
¢G_.ob
A
L_or}
(::3
3
356
FIGURE 190
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LO01 WITH PCS CLOSED FOR.... FORWARDC.G. MAXIMUM DYNAMICPRESSURECONDITION ''
BOEJ/IM'O
• MAXIMUM Q (Vd)• RSS WITH PCS CLOSED• MACH: 0.80• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2500 LBS.• C.G.: 20_ MAC
I I I
I I
I
i I i
0l£I
o
0
uJ
n,-
3
C:)c_
0
0
l::)
0
0
- .60 -t. 20 -0, 80 -0. tlO O.O0 O.qo O.
(RAD/SEC)
FIGURE 190 (CONCLUDED)
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS CLOSED FORFORWARDC.G. MAXIMUM DYNAMIC PRESSURE CONDITION
357
APPENDIX E
• MAXIMUM Q (V d)• RSS WITH PCS AND GLA CLOSED• MACH: 0°86• ALTITUDE: 15,000 FTo• GROSS WEIGHT: 2500 LBS°• C.G.: 20_ MAC
I I I
I
t I-20,00 -16,00 -12,00 -8.00 -u_0 O0 0,00
cr (RAD/SEC)
0
_.ob
358
FIGURE 191
DAST'ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH POS AND GLA CLOSED FORFORWARD C.G° MAXIMUM DYNAMIC PRESSURE CONDITION
APPENDI X E
• MAXIMUM Q (Vd)• RSS WITH PCS AND GLA CLOSED• MACH: 0.80• ALTITUDE: 15,,000 FT.• GROSS WEIGHT: 2500 LBS.
• C.G.: 20% MAC
I I I
Io a I o
- 1.60 - ! . 20 -0.80 -0. _0 O.O0
(RAD/SEC)
0
0
0
0
0
0
0..0 0.eb
A
0LU
C= C/3
3
FIGURE 191 (CONCLUDED]
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS AND GLA CLOSED FORFORWARDC.G. MAXIMUM DYNAMIC PRESSURE CONDITION
359
APPENDIX E
• MAXIMUM Q (V d)• RSS WITH BCS CLOSED• MACH: 0.8b• ALTITUDE= 15,000 FT.• GROSS WEIGHT: 2500 LBS.• C.G.: 20_ MAC
/=//i
-20. O0 -16.00 -t2.00 -8.00 --q,.O0 0.00
OJ
(RAD/SEC)
0
0
aO
A
c.)LU
• r_
3
00
0
t-J• •
00
00
,_;ob
FIGURE 192
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS CLOSED FORFORWARDC.G. MAXIMUM DYNAMIC PRESSURE CONDITION
360
APPENDIX E
• MAXIMUM Q (V d)• R_S WITH BCS CLOSED• MACH= 0.86• ALT I TUDE, 15 _,OOO FT.• GROSS WEIGHT= 2500 LBS.• C.G.= 20_ MAC
NO.2
i 3
GRIN•59S0t.O001.680
I
I
-1.60 -1.20
C_(,D
c_t",J
c)OD
T=
o
T.-:
I o
oI .I-o
-o. 8o -o. 4o o. oo o. 4o o. 8b
c_ (RAD/SEC)
LI.I
(:3¢=Cn,"
3,-.,._
FIGURE 192 (CONCLUDED)
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS CLOSED FORFORWARDC.G. MAXIMUM DYNAMIC PRESSURECONDITION
361
DO 6000 2145 REV 9182
APPENDIX E
• MAXIMUM Q (Vd)• PcS W lll-IRSS CLOSED• MACH: 0.86
• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2500 LBS.
• C.G.: 20_ MAC
N_"
I I I I
(_
I
o I-20.00 -16.oo -12.0o -8.00 -4.00 o.oo _.ob
F I GURE 193
DAST AI_W-2 PCS GAIN/PHASE ROOT LOOI WITH RSS CLOSED FOR• 'FORWARD C.G; MAXIMUM DYNAMIC PRESSURE CONDITION '
362
APPENDI X E
• MAXIMUM Q (v d)• PCS WITH RSS CLOSED• MACH: 0.86• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2500 LBS.• C.G.: 20_ MAC
-I. 6O
I I I
I
o4
LO
C_('%1
(DOlD
A
Lul(./3
TM
m,.
£:D
(D(m
I"kl
c;
-1.20 -0. BO -O. qO 0.00 0. qo O_Bb
o (RAD/SEC)
FIGURE 193 (CONCLUDED)
DAST ARW-..2 PCS GAIN/PHASE ROOT LOOI WITH RSS CLOSED FOR' 'FORWARD C.G. MAXIMUM DYNAMIC PRESSURE CONDITION
363
APPEND IX E
• MAXIMUM Q (V d)• F_;S WITH RSS AND GLA CLOSED• MACH: 0.86• ALTll'UDE: 15,000 FT.• GROSS WEIGHT: 2500 LBS.• C.G.: 20_ MAC
I t I t
F
LU
I / o
Il i I _;-2o.oo -_6.oo -I_.oo -B.O0 -4.00 0.00 4.oh
o (RAD/SEC)
364
FIGURE 194
DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA CLOSED FORFORWARDC.G. MAXIMUM DYNAMIC PRESSURE CONDITION
APPENDIX E
• MAXIMUM Q (V d)• PCS WITH RSS AND GLA CLOSED• MACH= 0.86
• ALTITUDE; 15p000 FT.• GROSSWEIGHT: 2500 LBS.• C.G.= 20_ MAC
lP
I I I
o-;I
<-,;
C_co
• •
C.)LI.I_J3
g:3
3.,.-,_
"c:;
c__d
-t. 6o -1.2o -o. BO -0.40 O.O0 O.qO O.Bb
(RAD/SEC)
FIGURE 194 (CONCLUDED)
DAS_ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA CLOSED FOR.... FORWARDC.G. MAXIMUM DYNAMICPRESSURE CONDITION •
365
APPENDIX E
• MAXIMUM 0 (Vd)• BCS WITH RSS CLOSED• MACH: 0.86• ALTITUDE: 15,000 F"T.• GROSS WEIGHT= 2500 LBS.• C.G.: 20_ MAC
.o.\.___ ' ' ' '
8
\
l
I I I I
I:
0o
c_CZ)
ij c_
/ xI c_
' IiI
I
-zo.oo -t6.oo -t2.oo -8.oo -q.oo o.oo 4ob
o (RAD/SEC)
A
u.I
S°...,}
FIGURE 195
DAS'I"ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR• FORWARDC.G. MAXIMUM DYNAMIC PRESSURE CONDITION
366
APPENDI X E
• MAXIMUM Q (V d)• BCS WITH RSS CLOSED• MACH: 0.86• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2500 LBS.• C.G.: 20% MAC
I:
ii
-1.20 -0.80
C)oD
C_(O
c_
=;
\ ' o-l. 60 -0. LLO O. O0 O. 40 O. 8b
c_ (RAD/SEC)
FIGURE 195 (CONCLUDED)
DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR.... FORWARDC.G. MAXIMUM DYNAMICPRESSURECOND1TION
367
APPENDIX E
• MAXIMUM Q (V d)• RSS• MACH: 0.86• ALTITUDE= 15,000 FT.• GROSS WEIGHT= 2200 LBS.• C.G.: 33% MAC
I I I t
(RAD/SEC)
FIGURE 196
DA_ ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC AIRPLANE FOR
AFT C.G. MAXIMUM DYNAMICPRESSURECONDITION
368
APPENDIX E
• MAXIMUM Q (Vd)• RSS• MAC'H: 0.86
• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2200 LBS.
• C.G.: 33_ MAC
I I I I
3- 1.68o
I
f
L.'.
I
-1.60 -1.20
¢3
_4
=o
---,-_....
f I
t IO. O0 O. qO
C3
o,;
C3(0
LUC/'J
. °
n,.
• °
to
"(5
(:3
'c;
-o.eo -o._o o.eb
c_ (RAD/SEC)
F I GURE 196 (CONCLUDED)
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BASIC AIRPLANE FOR' AFT C,G. MAXIMUM DYNAMICPRESSURECONDITION
369
APPENDIX E
• MAXIMUM Q (V d)• RSS WITH PCS CLOSED• MACH: 0.86• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2200 LBS.• C.G.: 33_ MAC
I I !NO. GAIN
l -4.5dB
2 0 dB (NOMINAL)
3 +4.5dB'/)/;///, /'i/'2
I
I
J l-20.00 -16.00 -12.00 -8.00 -q. O0 0.00
/I
I
I
A
r,_)LI.I'L/')
C3
n,"v
30--,_
C;,
<5
o
0c_
C:)Q
(7 (RAD/SEC)
FIGURE 197
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS CLOSED FOR'" AFTC.G.MAXIMUM DYNAMIC PRESSURECONDITION "
370
APPENDIX E
• MAXIMUM Q (V d)• RSS WITH PCS CLOSED• MACH: 0.86
• ALTITUDE: 15,000 FT.• GROSSWEIGHT: 2200 LBS.• C.G.: 33% MAC
ft
l
1
Tf
[t
i
t
I
t
GRNs_1.0001.680
I !
- I. 60 - I. 20 -0.80
, I ,-0. u,O O. O0 O. qo
_ (RAD/SEC)
C)
(DLIJU'3
°
3
C'D¢:3
¢Dto
¢:)
"6
C_J
+6o.Bb
FIGURE 197 (CONCLUDED)
DAST ARW-2 RSS SYSTEM GAIN�PHASE ROOT LOCI WITH PCS CLOSED FORAFT C.G.I_%XIMUM DYNAMIC PRESSURE CONDITION
371
APPENDIX E
e MAXIMUM Q (V d)• RSS WITH PCS AND GLA CLOSED• MACH" 0.86• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2200 •LBS.• C.G,: 33% MAC
I t I t
-20.00 -16.00 -12.00 -8.00 4.00 0.00
(_ (RAD/SEC)
Q
,-G
O
oJ41ob
FIGURE 198
DAb_ ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS AND GLA CLOSED FORAFTC.G. MAXIMUMDYNAMIC PRESSURE CONDITION
372
APPENDI X E
• MAXIMUM Q (V d)• RSS wl'n-I PCS AND GLA CLOSED• MACH: 0.86• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2200 LBS.• C.G.: 33% MAC
l-1,60
I I I
(D
¢,i
A
rjILl(,'3
.E3
3
C_
"c;
C)t_
• °
I I I I I-_.2o -o.ao -o.qo o.oo o.qo o.ab
(RAD/SEC)
FIGURE 198 (CONCLUDED)
DA:_T ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS AND GLA CLOSED FOR.... AFT C.G. MAXIMUM DYNAMIC PRESSURE CONDITION
373
APPENDIXE
• MAXIMUM Q (V d)• RSS WITH BCS CLOSED• MACH: 0.86• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2200 LBS.• C.G,: 33_ MAC
l
./
_J
-20.00 -16.00
//
//
/'
I-12.00
I !
///
//
//
/
/J /
/1'
/
(/o/ °
I-8. O0
/
//
/
/
//
//
//
!
oI ,o.
-q,. O0 O. O0 u,. O_D
C)
/
C_0
'=:;
a (RAD/SEC)
A
LJ.JC/'}
C3
3.°,--j
F I GURE 199
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS CLOSED FOR• ' AFT C.G. MAXIMUM DYNAMIC PRESSURECONDITION
374
APPENDIX E
• MAXIMUM Q (V d)• RSS WITH BCS CLOSED• MACH: 0.86• ALTITUDE; 15,000 FT.• GROSSWEIGHT: 2200 LBS.• C.G.,: 33_ MAC
i1
I I I !
÷
-1.60 -1.20
(3&O
C3c_d
"oJ
IC3
A
C.)
C_
¢=;
n."
tl_ _._
3
m
I
I
-0.80 -0. u,o O. O0 O. qO
or (_D/SEC)
0
°
t_°
o
C)
o,sb
FIGURE 199 (CONCLUDED)
DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH BCS CLOSED FOR' AFTC,G,MAXIMUM DYNAMIC PRESSURECONDITION
375
APPENDIXE
• MAXIMUM Q (V d)• PCS WITH RSS CLOSED• MACH: 0.86• ALTITUDE: 15,000 FT.• GROSS WEIGHT= 2200 LBS.• C.G,= 33_ MAC
INO. GAIN
1 -4.5dB
2 0 dB (NOMINAL)3 +4.5dB
I I I
I I I
/
-_o.oo -_6.oo -_z.oo -B.oo_ -4.oo o.oo
(RAD/SEC)
C)
4.oh
A
LUC_
r'_
v
3
FIGURE 200
DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR' ' AFT C.G. MAXIMUM DYNAMIC PRESSURE CONDITION ' '
376
APPENDIX E
• MAXIMUM q (V d)• PCS WITH RSS CLOSED• MACH: 0.86• ALTITUDE; 15,000 FT.• GROSS WEIGHT: 2200LBS.• C.G,= 33_ MAC
NO. GAIN.59502 I.OgO3 1.680
1 ! I
II
C
ir-1.50 - t.20 -0.BO -0.40 O. O0
(RAD/SEC)
co
(Jo
c_£M
0.40 o.Bb
Ac.)L_
r'h
°,_
FIGURE 200 (CONCLUDED)
DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS CLOSED FOR• ' ' AFT C.G, MAXIMUM DYNAMIC PRESSURE CONDITION
377
APPENDIX E
• MAXIMUM O (Vd)
• PCS WITH RSS AND GLA CLOSED• MACH: 0.86
• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2200 LBS.
• C.G,: 33% MAC
t .000i. 680
I I I I
C_C)
I I I I
-20. O0 - ! 6. O0 - I Z. O0 -8. O0 -q. O0 O. O0
(RAD/SEC)
¢3
¢3¢3
FIGURE 201
DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA CLOSED FOR' AFT C,G. MAXIMUM DYNAMIC PRESSURE CONDITION • _
378
APPENDIX E
• MAXIMUM Q (V d)• PCS WITH RSS AND GLA CLOSED• MACH: 0.86• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2200 LBS.• C.G.: 33_ MAC
NO. GRIN! .5950
2 i.O003 l. 680
l
F
t t t I I- 1.60 -1.20 -0o 80 -0. qO O. O0 O. qO
o" (RAD/SEC)
C_
cd
LI.I
r't
3
c_:l.
¢.o
t_d
FIGURE 201 (CONCLUDED)
DASTARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA CLOSED FORAFT C.G. MAXIMUM DYNAMIC PRESSURECONDITION
379
NO. GRIN! ,59502 1.0003 1.680
0
APPEND IX E
MAXIMUM Q (Vd)
GLA AILERON WITH RSS, PCS ANDGLA STABILIZER CLOSED
MACH: 0.86
ALTITUDE: 15,000 FT.GROSS WEIGHT: 2200 LBS.
C.G.: 33_ MAC
J/
/
/
//
/
//
,/
/
//!
/
/
/
/
÷i
i
i-20. O0
//
/
/
//
//
/
/J
.z_._l
/
//
//
/
/
/
J
- 12. O0 -8.00 -q. O0 O. O0
o (RAD/SEC)
4-L"J
r
l
",-G
(S)
-Z6.O0 q.o_
r-_
3.--.,j
380
FIGURE 202
DAS'r ARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLASTABILIZER LOOPS CLOSED FOR AFTC,G, MAXIMUM DYNAMIC PRESSURE CONDITION
APPENDIX E
MAXIMUM Q (V d)GLA AILERON WITH RSS, PCS ANDGLA STABILIZER CLOSEDMACH: 0,86
ALTITUDE: 15p000 FT,GROSS WEIGHT: 2200 LBS,C.G.: 335 MAC
i I INO. GRIN• ,5950
I.O001.680
i \
-125.00 -lO0.O0
I I t __
/
i/
/
/i
!i
//
/
'i //, /,/
'/ /"/
i/
I
r
i-7s. oo
(D
/,/ ,
ii
d
(/)
.' [
I'-_ 3
/
c)
0o
cS
_ C21i u;,Od
-so. oo -2s. oo o. oo 2s.bo
cr (RAD/SEC)
FIGURE 202 (CONTINUED)
DAST ARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCI WITH RSSp PCS AND GLASTABILIZER LOOPS CLOSED FOR AFTC.G,MAXIMUM DYNAMIC PRESSURE CONDITION
381
APPENDIXE
• MAXIMUM Q (V d)• GLA AILERON WITH RSS, PCS AND
GLA STABILIZER CLOSED• MACH: 0.86
• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2200 LBS.• C.G.: 33_ MAC
"?" ._4_2 t.O003 1.680
I ! I
J
t
i/-1.60
I I
-I. 20 -0. BO
/ i'"I
-0. qO O, On
(_ (RADISEC)
\
N. LIFI
i c_)
0
3I -,
J i:-1.. -
0
382
FIGURE 202 (CONCLUDED)
DAST ARW-2 GLA AILERON LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLASTABILIZER LOOPS CLOSED FOR AFT C.G. MAXIMUM DYNAMIC PRESSURE CONDITION
APPENDIX E
• MAXIMUM Q (V d)• GLA STABILIZER WITH RSS, PCS
AND GLA AILERON CLOSED• MACH: 0.86• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2200 LBS.• C.G,: 33% MAC
I
3 t;ss0
-- t __
-4-
-2O O0 -t6.00
/
/f
Y
/
\,
\ \
" -"\ ,\
• ._.
2---ii
- 12. O0 -8.00
.I"
/t./
7
/J"
//(
//'
/
f/
/
c_
.f./_
i@
1
i 4-q. O0 O. O0
(RAD/SEC)
A
! c.)ILl
i <:J L/')
I (:_ °'J:b
I
I0CO
(00
oJ.lob
FIGURE 203
DAST ARW-2 GLA STABILIZER LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLA
AILERONLOOPS CLOSED FOR AFT C.G. MAXIMUMDYNAMIC PRESSURE CONDITION
383
APPENDIX E
• MAXI_JM Q (Vd)
• GLA STABILIZER WITH RSS, PCSAND GLA AILERON CLOSED
• MACH: 0.86• ALTITUDE: 15,000 FT.• GROSSWEIGHT: 2200 LBS.• C.G.: 33% MAC
+N_
i+
L
i
+
J\
AN
l.O00l.B80
I I I
\
\\
'\
\,
\
x ',
i-125.00 -I00.00
I . I t , - -- -_
T _
I _.t o
(:3°
t-r
c-j
oc:)
-zs oo -so.oo -zs.oo o.oo 25.bo
(_ (RAD/SEC)
(3LU(I)
r'_(z:rr
3
FIGURE 203 (CONTINUED)
DAS'TARW-2 GLA STABILIZER LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLAAILERON LOOPS CLOSED FOR AFT C.G. MAXIMUMDYNAMIC PRESSURE CONDITION
384
'I NO.pl
3
4-
+
i
r
-1,60
APPENDIX E
• .MAXIMUM Q (V d)
• GLA STABILIZER WITH RSS, PCSAND GLA AILERON CLOSED
• MACH= 0.86
• ALTITUDE- 15,000 FT.• GROSS HEIGHT: 2200 LBS.
• C.G.: 33% MAC
i i iGAIN.$950L.O00
t.680J
I
I0, 00
0c_
o
!1 "o
LLIC_
,. °
3
o
i
c)c_
'c5
-l. 20 -0.80 -0, qo O.qO O.8b
cr (RAD/SEC)
FIGURE 203 (CONCLUDED)
DAS'I'ARW-2 GLA STABILIZER LOOP GAIN/PHASE ROOT LOCI WITH RSS, PCS AND GLA
AILERON LOOPS CLOSED FOR AFT C,G. MAXIMUM DYNAMIC PRESSURE CONDITION
385
APPENDIX E
• MAXIMUM Q (V d)• BCS WII_I RSS CLOSED• MACH: 0.86• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2200 LBS.• C.G.: 33% MAC
+\\
\
I
I I I
'\
\
'\\
\
"\\, '\
I I
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FIGURE 204
DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS CLOSED FORAFT C.G. MAXIMUM DYNAMIC PRESSURE CONDITION
386
APPENDIX E.
• MAXIMUM Q (V d)• BCS WITH RSS CLOSED• MACH: 0.86• ALTITUDE= 15,000 FT.• GROSS WEIGHT= 2200 LBS.• C.G,: ))_ MAC
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FIGURE 204 (CONCLUDED)
DAST ARW-2 BCS SYSTEM GAIN/PHASE ROOT LOCI WITH RSS CLOSED FORAFT C.G. MAX1MUM DYNAMIC PRESSURE CONDI T I ON
387
Standard BibliographicPage
1. Report No. 2. Government Accession No. 3. Recipient's Catalog No.
NASA CR-177959, Part 2
4. Title and Subtitle
DESIGN VERIFICATION AND FABRICATION OF ACTIVE CONTROL
SYSTEMS FOR THE DAST ARW-2 HIGH ASPECT RATIO WING,PART 2 - APPENDICES
7. Author(s)
C. R. McGehee
9. Per_rming Organization Name and Address
Boeing Military Airplane CompanyP.O. Box 7730
Wichita, Kansas 67277-7730
12. Sponsoring Agency Name and Addr_s
National Aeronautics and Space Administration
Washington, DC 20546i
5. Report Date
January 1986
6. Performing Organization Code
8. Performing Organization Report No.
0500-10897- l
I0. Work Unit No.
11. Contract or Grant No.
NAS l-16010
Contractor Report14. Sponsoring Agency Code
15. Supplementary Notes
16. Abstract
A study was conducted under Drones for Aerodynamic and Structural Testing .(DAST) program to accomplish the final design and hardware fabrication forfour active control systems compatible with and ready for installation in
the NASA Aeroelastic Research Wing No. 2 (ARW-2) and Firebee II drone flight
test vehicle. The wing structure was designed so that Active Control Systems
(ACS) are required in the normal flight envelope by integrating control
system design with aerodynamics and structure technologies. The DAST ARW-2
configuration uses flutter suppression, relaxed static stability and gustand maneuver load alleviation ACS systems, and an automatic flight control
system. Performance goals and criteria were applied to individual systems
and the systems collectively to assure that vehicle stability margins,
flutter margins, flying qualities and load reductions were achieved.
17. Key Words (Sugg_t_ by Authors(s))
Flutter Suppression
Relaxed Static StabilityManeuver Load Alleviation
Gust Load Alleviation
18. Distribution Statement
Until January 1988
19. S_urity Cl_sif.(of this report) [ 20. S_urit Classif.(of this page) 21. No. of Pag_ 22. Price
Unclassified I Unclassified 387
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