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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

19

20

21

22

23

24

25

26

27

28

29

30

31

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


DRAG COEFFICIENT VERSUS ANGLE OF AI-I'ACKAT


DRAG COEFFICIENT VERSUS ANGLE OF ATTACK AT


LIFT COEFFICIENT VERSUS ANGLE OF ATTACK AT


LIFT COEFFICIENT VERSUS ANGLE OF AI-I'ACKAT






PITCHING MOMENT COEFFICIENT VERSUS ANGLE OF ATTACK

AT MACH: 0.60, WITH SPEEDBRAKES

PITCHING MOMENT COEFFICIENT VERSUS ANGLE OF AI-I'ACK


PITCHING MOMENT COEFFICIENT VERSUS ANGLE OF AI-rACK


PITCHING MOMENT COEFFICIENT VERSUS ANGLE OF ATTACK


THRUST DATA FOR 80 PERCENT ENGINE RPM





35

36

37

38

39

4O

41

42

43

44

45

46

47

48

49

5O

51

52

53

FIGURE

37

38

39

4O

41

42

43

44

45

46

47

48

49

50

51

52

53

LIST OF FIGURES (C(]NTINUED)

DAST ARW-2 OUTBOARD AILERON SERVOVALVE RELOCATION STUDY

SYMMETRIC ELASTIC MODE

MACH: 0.80, ALTITUDE:

SYMMEIIRIC ELASTIC MODE






SYMMETRI C ELASTIC MODE


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,8,000 FEET, UNSCALED EOM

ANTISYMMETRIC ELASTIC MODE DAMPING AND FREQUENCY

WITH PARAIVETER SCHEDULING, MACH: 0.86,

ALTITUDE: 4,250 FEET, UNSCALED EOM


WITH PARAMETER SCHEDULING, MACH: 0.83,



WITH PARAMETER SCHEDULING, MACH: 0.86,


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

105

106

107

108

109

110

111

112

113

114

115

116

117

FIGURE

54

55

56

57

58

59

60

61

62

63

64

65

66

67

68

69

70

71




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 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,


PBASE-GAIN ROOT LOCUS OF ANTISYMMETRIC FSS, NOMINAL SYSTEM,




118

119

120

121

122

123

FIGURE

72

73

74

75

76

77

78

79

8O

81

82

83

84

85

86

87

88

89


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

92

93

94

95

96

97

98

99

100

101

102

103

104

105

106


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

160

161

162

163

164

165

166

167

168

169

170

171

172

173

174

175

177

FIGURE

107

108

109

110

111

112

113

114

115

116

117

118

119

120

121

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


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



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

178

180

182

184

186

188

190

192

194

196

198

200

202

204

207

FIGURE

122

123

124

125

126

127

128

129

130

131

132

133

134

135

136




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


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


CLOSED FOR FORWARD C.G. GLA "rEST CONDITION


RSS, PCS AND GLA STABILIZER LOOPS CLOSED FOR FORWARDC.G. GLA TEST CONDITION


WITH RSS, PCS AND GLA AILERON LOOPS CLOSED FORFORWARD C.G. GLA TEST CONDITION


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


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

143

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


RSS, PCS AND GLA STABILIZER LOOPS CLOSED FOR AFT C.G.GLA TEST CONDITION


WITH RSS, PCS AND GLA AILERON LOOPS CLOSED FOR AFTC.G. GLA TEST CONDITION


CLOSED FOR AFT C.G. GLA TEST CONDITION


AIRPLANE FOR FORWARD C.G. LAUNCH CONDITION

DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCSCLOSED FOR FORWARD C.G. LAUNCH CONDITION


AND GLA CLOSED FOR FORWARD C.G. LAUNCH CONDITION


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


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


AND GLA CLOSED FOR AFT C.G. LAUNCH CONDITION


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


RSS, PCS AND GLA STABILIZER LOOPS CLOSED FOR AFT C.G.LAUNCH CONDITION


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


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


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

276

278

281

284

286

288

290

292

294

296

298

300

302

304

II

FIGURE

167

168

169

170

171

172

173

174

175

176

177

178

179

180

181



CLOSED FOR AFT C.G. HIGH ALTITUDE CONDITION


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


AIRPLAI_Z FOR FORWARD C.G. CRUISE CONDITION


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




FOR FORWARD C.G. CRUISE CONDITION

DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLACLOSED FOR FORWARD C.G. CRUISE CONDITION




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


DAST ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCSAND GLA CLOSED FOR AFT C.G. CRUISE CONDITION


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


RSS, PCS AND GLA STABILIZER LOOPS CLOSED FOR AFT C.G.CRUISE CONDITION

DASTW ITH

C.G.


RSS, PCS AND GLA AILERON LOOPS CLOSED FOR AFTCRUISE CONDITION


CLOSED FOR AFT C.G. CRUISE CONDITION


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


CLOSED FOR FORWARD C.G. MAXIMUM DYNAMIC PRESSURECONDITION


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)


CLOSED FOR FORWARD C.G. MAXIMUM DYNAMIC PRESSURE

CONDITION


AIRPLAI_E FOR AFT C.G. MAXIMUM DYNAMIC PRESSURE

CONDITION


CLOSED FOR AFT C.G. MAXIMUM DYNAMIC PRESSURE CONDITION


AND GLA CLOSED FOR AFT C.G. MAXIMUM DYNAMIC PRESSURE

CONDITION




FOR AFT C.G. MAXIMUM DYNAMIC PRESSURE CONDITION




RSS, PCS AND GLA STABILIZER LOOPS CLOSED FOR AFT C.G.MAXIMUM DYNAMIC PRESSURE CONDITION

DAST

W ITH

C.G.


RSS, PCS AND GLA AILERON LOOPS CLOSED FOR AFTMAXIMUM 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_

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APPENDIX A

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• I • • • • • • i" • • • • • • •I I I I I I I

¢,r)

I---,,=:Z:

,.,y,l,J..l

>-.l---

e_

Z

i,..-4I'-"(,,.3

e,,,,'

I

I--

..-]

C',J

e',,,"

(,.0

L.I....

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 ; :

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i: _ . ._ " ...... , ".....:t._...._ .. . :!......./....:..:....._......_--...._..... _....;.............:..-

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' : --/-; • : ' i :_i..: .......'.... _ _:-_": "-:-'_........_ !-i: "_-::' ,

-8. -6._.-4/.,'-Z-. : ...... :2. i..g ...... 6 .... 8 .:i.10. 12

.....i.....', =/'_ _ANC___O£_ATI,_.X,_.I_EGI_EES1____._

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....... _" "_,_.... 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


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 , : _ - ; :

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...._ _:._._ ,: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


- 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


' ' , ........... _ ...... 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


• STABILIZER: 0.0

i i.L - " .........

" i

FIGURE 15'

LIFT COEFFICIENT VERSUS ANGLE OF ATTACK, CRUISE CONDITION

32

APPENDIX A

• MACH: 0°80


..... 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


,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


FIGURE 21


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


FIGURE 22


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

• . i ":---"':::-f=_.:-::._:_-'i:.-.:::'--_:}Z:::'_--''-=:'---":".--':-:--:_-:{. --. - - _ -.r.:

• . . :-: ._:'=.-_/_:-_-3_-_'_Ci{_:_i-.-.@_:_:2:'r_=:.}-T':-'"'::_:-:.=:__-!:!--:: . _-.-

-_ ,ii+ _: _ _i: _;-? i" .... - .....

o I 2 3 4 5 6 7 8

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

' :i 0 ..---;:-::-::: .-:- ---:-.:_:- ..---:_-L::-:-::.-'-.:.:-.-!: : •

i.o _ o _:--.:___-- -

i:-_ 2°°--- .... ':-:---_%!-_2-_)_::::-:-:_ :..__.

0.8_ --__:_ :._-..-------

• : . : :.- : - i:- :_'_::_'_-:-----L-,t.;-_='_:-_::':::-:-_::'_::-_: -:" :-:-;-:.T:...] . " .. :- .: . : . : . . •

o.7.... _ :::!-_:_-_; :::_-:_:_--. : : ...........

0.5

LIFTCOEFFICIENT

0.4 :

0.3

.. :--_-._r2___:_ .-__\.: 2 _:.- .-_

-: ...... ;..__:_::_ ---:. ====================== - _ :_. -. :. : . • . . _

-:-: -.'- _ :-::::5:! :-.'::-_-. .:_! :"- " " _:_.: - - . .

.......... :------.-_.:-i._:_:-,::: :-_i--_?_-:._:----_:-:':"_ ....... _.............

0. I :-. _:: _:,:_ ._. --.-:i.:.-! T:=_i::i._:--.-_:-_;::-::-:;C:_ -:_-:.- "....

" " ' -:-":::-;-:_:-"----_'--=:- NOT CORRECTED FOR FLEXIBILITY__

::_:-=================================00 I 2 6 7 83 4 5


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


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


FIGURE 26


43

APPEND I X A

" " - : ........ T": ...............

FIGURE 27


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

-0.1

-0.2

-0.3

--!T SPEEDBPJ%KES" Lz

_ o°................................

" : -- l nl I : : : ======================= -- : I u ............

_.. ..... -= :: ii::=-:;-_i:z:._:__:e=e:_=_NOT CORRECTED FOR FLEXIBILITY

FIGURE 29


WITH SPEEDBRAKES

0.70,

46

APPENDIX A

• . _. ,_ ,.J

!'_OOg :::j ITYI

PITCHINGMOMENT

COEFFICIENT

0.3 :-:-::. SPEEDBI_KES ::-':._:-::--:-:_-:..-__--;:_:--_::.-:-_:_.---:..:-_---_--._:.:.z.::::-:._ ........

:.... -2-0° "----i:--:'_:--_-_--:-:-_-Z::_-<--:=-_Y----:_-:-_---:_i-i--_:-:-_:-:-i..._.£200 ....... :::::................ ===:- ........ ":---'--:-: .

..........................................:-.....-::: .......... :-::-:;_:_.-_--:-:T--_T:_:_'_.-F_-_--:-::-:::._::i_:-_:-i:-::::: : -

0.2 -_ S0o ..... _:._---:-_:-::-__:__-_.-:-i:L--_"_-:.:-_-._:--.:::_i----!:L :-.-::.L_ 60° ...... !.-.:-::_/_-::!!_:--'-_:_!--_::_:-:__-:_:--::::-L:-. i.: ::..

' " -_ : :...::........ =---_:-:--:i_-_-:-:::----_:: -.:--.. :: .................................

• .-: _ :L- ... :_::.:---:::-:_-:Y':---"-_:":::_:-_T.:-L--_:_::-.-.::. :i.- : -- :_

0, ], . . " . _-.-:_ 1:_::.'-:-:.:--::::T-:-:-_.Y__.-T_:.-:':--_._:_:T-_-.---_--:::-_-:::-:--.- - : - " - : ....... . ...........

-- .!:- -.-:::_:-£-_--T:-:__:TL:::_-___:...__-:.:_.-__.___-._-:_::_= ---:__:_:_.1:-.: . - . .

0 " " _:-:::--::i:-.-'_:.-_-:.-_--_:_--_::-:-_:_-_:-:i-_ :::-:--:-"-_-...... - " -

:_-i::_ .....::::-.:__:::__-_"_:-'_.._-_ ........... - -,.... ................

_--_" ..... ',,r,............................ =--:'-_"'-'-"--:_;';---::- .. _

-o .... : -'_...... _. _._:_::-----_:--v __..__--=-:_..=_.-:-_ _,,;----i- ---- :

--. ......... : _ -_ -- _ _..,,_.= _ _ ...._.j,__----.. __._'------==.,_______............. ,,,.,..',,,,,,.i.-,--__,..=_.--_ . ..:_ -. - . - .. _ . ,

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53

(This page intentionally left blank)

54

APPENDIX B


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


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)


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,



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.



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.



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



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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.

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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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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.

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177

APPENDIX E

• MLA TEST• RSS

• MACH: 0.42

• ALTITUDE: 10,000 FT.• GROSS WEIGHT= 2500 LBS.• C.G.: 20_ MAC

I I I

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(RAD/SEC)

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178

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

i I

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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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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

I I

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(RAD/SEC)

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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

t

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183

APPENDIX E

• MLA TEST• RSS WITH BCS CLOSED• MACH: 0.42• ALTITUDE: 10,000 FT.• GROSS WEIGHT: 2500 LBS.• C.G.: 20_ MAC

I I I

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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

I

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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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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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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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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

I I INO, GRIN

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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

! .59502 t. 000

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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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Igl

APPENDIX E

• MLA TEST• RSS• MACH: 0.42• ALTITUDE= 10,000 FT.• GROSS WEIGHT= 2200 LBS.• C.G.: 33_ MAC

t I I I / INO. GRINII.59S0 /

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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

I _ I I

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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

2 t.O00

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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

,- \N10" i. ooo _ _ /

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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

I I I INO. GAIN / lII .sgso /2 l. DO0 /,

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196

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

J 2 i:000, /

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]97

APPENDIXE

• MLA TEST• RSS WITH BCS CLOSED• MACH: 0.42• ALTITUDE: 10,000 FT.• GROSS WEIGHT: 2200 LBS.• C.G.: 33_ MAC

t

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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

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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

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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

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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

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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

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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

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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

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(RAD/SEC)

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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

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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

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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

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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

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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

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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

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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

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(RAD/SEC)

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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

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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

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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

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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

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0

0

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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

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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

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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

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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


• C.G.: 20_ MAC

P

NO. GRINl .59502 l. O003 I. 680

fi

J

I

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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

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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)

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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 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

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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 STABI L IZER CLOSED• MACH: 0.70


• 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


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

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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

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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

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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

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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* / '

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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

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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

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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

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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

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....... 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

/

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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

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....... 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

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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

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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

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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

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DAST ARW-2 PCS GAIN/PHASE ROOT LOCI WITH RSS AND GLA CLOSED FORAF'r CoG. GLA TEST CONDITION

243

APPEND IX E


GLA STAB I L I ZER CLOSED• MACH: 0.70• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2200 LBS,

• C.G,: 33% MAC

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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 STAB I L I ZER CLOSED• MACH: 0.70• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2200 LBS.• C.G,: 33_ MAC

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245

APPENDIX E


GLA STABILIZER CLOSED• MACH= 0.70• ALTITUDE= 15,000 FT.• GROSS WEIGHT= 2200 LBS.• C.G.= )3% MAC

GRINNO. .5950

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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


• O.G,: 33% MAC

I I I I

0

,.i- ed

t

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(RAD/SEC)

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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

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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

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(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

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C3C'd


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 / '

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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

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CO

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o (RAD/SEC)

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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

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00

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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

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(RAD/SEC)

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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

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c_(RAD/SEC}

(,.)ILl0'3

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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

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(RAD/SEC)

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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

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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

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NO. GRIN II I

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259

APPENDIX E

.

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• LAUNCH• PCS WITH RSS CLOSED• MACH: 0.40• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2500 LBS.• C.G.: 20_ MAC

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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

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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

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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

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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

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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


• C.G.: 20% MAC

AIN

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265

APPEND I X E

• LAUNCH• RSS• MACH: 0.40• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2200 LBS.• C.G,: •33% MAC

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APPEND IX E

• LAUNCH• RSS

• MACH: 0.40

• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2200 LBS.• C.G,: 33% MAC

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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

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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

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271

APPEND IX E

• LAUNCH• RSS WITH BCS CLOSED• MACH: 0.40• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2200 LBS.• C.G;: 33_ MAC

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272

APPENDIXE

GRINNO. ,5950

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273

APPENDIXE

• LAUNCH• PCS WITH RSS CLOSED• MACH: 0.40• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2200 LBS.• C.G.: 33% MAC

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274

APPEND IX E

• LAUNCH• PCS WITH RSS CLOSED• MACH: 0.40• ALTITUDE: 15,000 FT.• GROSS WEIGHT: 2200 LBS.• C.G.: 33% MAC

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275

APPENDIX E

• LAUNCH• PCS WITH RSS AND GLA CLOSED• MACH: 0.40• ALTITUDE: 15,000 FT.• GROSSWEIGHT: 2200 LBS.• C.G,: 33% MAC

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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

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.... 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

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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

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(RAD/SEC)

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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

/

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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)

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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


• MACH: 0.40• ALTITUDE= 15,000 FT.• GROSS WEIGHT= 2200 LBS.• C.G,: 33% MAC

I I I I r-,-

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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

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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.

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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.


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I I INO. GRIN

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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

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287

APPENDIX E

• HIGH ALTITUDE• RSS WITH PCS CLOSED• MACH: 0.70• ALTITUDE= 50,000 FI".• GROSS WEIGHT= 2500 LBS.• C.G.: 20_ MAC

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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

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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

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...... 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

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291

APPENDIX E

• HIGH ALTITUDE• RSS WITH BCS CLOSED• MACH: 0.70• ALTITUDE: 50,000 FT.• GROSS WEIGHT: 2500 LBS.• C.G.: 20_ MAC

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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

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293

APPENDIX E

• HIGH ALTITUDE• PCS WITH RSS CLOSED• MACH: 0.70• ALTITUDE: 50,000 FT.• GROSS WEIGHT: 2500 LBS.• C.G.: 20_ MAC

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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

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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

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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

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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

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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

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299

APPENDIX E

• HIGH ALTITUDE

• RSS

• MACH: 0.70• ALTITUDE: 50,000 FT.


• C.G,: 33% MAC

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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

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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

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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

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3O5

APPENDIXE

• HIGHALTITlJDE• RSS WITH BCS CLOSED• MACH: 0.70• ALTITUDE: 50,000 FT.• GROSS WEIGHT: 2200 LBS.• C.G;: 33_ MAC

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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

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307

APPENDIX E

• HIGH ALTITUDE• PCS WITH RSS CLOSED• MACH: 0.70• ALTITUDE: 50,000 FT.• GROSSWEIGHT: 2200 LBS.• C.G.: 33% MAC

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308

APPENDIX E

• HIGH ALTITUDE• PCS WITH RSS CLOSED• I_CH: 0.70• ALTITUDE: 50,000 FT.• GROSSWEIGHT: 2200 LBS.• C.G,: 33% MAC

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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

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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

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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

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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

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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

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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

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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

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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

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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

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318

APPENDI X E

• HIGH ALTITUDE• BCS WITH RSS CLOSED• MACH: 0.70• ALTITUDE: .50,000 FT.• GROSSWEIGHT: 2200 LBS.• C.G,: 335 MAC

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319

APPENDIX E

• CRUISE• RSS• 1.0g FLIGHT• MACH: 0,80• ALTITUDE= 46,800 FT.• GROSS WEIGHT= 2500 LBS.• C.G.: 20_ MAC

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320

NO.

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i

APPENDIX E

• CRUISE• RSS• 1.0g FLIGHT• MACH: 0,80• ALTITUDE: 46,800 FT.• GROSS WEIGHT: 2500 LBS.• C.G.: 20_ MAC

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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

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APPENDIXE

• CRUISE• RSSWITH PCS CLOSED• l oOg FLIGHT• MACH: 0.80


• C.G.: 20_ MAC

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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

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DA_T ARW-2 RSS SYSTEM GAIN/PHASE ROOT LOCI WITH PCS AND GLA CLOSED FOR........ FORWARDC.G. CRUISE CONDITION

324

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APPENDI X E

• CRUISE• RSS WITH PCS AND GLA CLOSED

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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

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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

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327

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APPENDIX E

• CRUISE• PCS WITH RSS CLOSED• 1.0g FLIGHT• MACH: 0.80


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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

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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

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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

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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

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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

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333

APPENDIX E

• CRUISE• RSS• 1.2g FLIGHT• MACH: 0.80• ALTITUDE: 46,800 FT.• GROSS WEIGHT: 2200 LBS.• C.G,: 33_ MAC

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334

NO. / GRIN Ii I / .5950

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APF_ENDI X E

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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.

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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

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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

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-16.00 " -12,00 -8.00 -U,.O0 0,00

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(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

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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

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.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

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(RAD/SEC)

o

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• C3

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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,

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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

!

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(RAD/SEC)

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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

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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

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t

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(RAD/SEC)

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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)

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.=_

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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

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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

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(RAD/SEC)

348


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

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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

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(RAD/SEC)

u;

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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

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I I l I

• 60 - I. 20 -0. BO -0. LiD 0.00 0. _0

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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


• C.G.: 33_ MAC

\

; /oz_ ,

0

cd(%1

0

A

3

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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


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)


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

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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

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3

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0

0

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0

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(RAD/SEC)


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

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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

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o

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c_ (RAD/SEC)

LI.I

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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


• 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

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o (RAD/SEC)


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

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3.,.-,_

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-t. 6o -1.2o -o. BO -0.40 O.O0 O.qO O.Bb

(RAD/SEC)


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_

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A

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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)


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


• C.G.: 33_ MAC

I I I I

3- 1.68o

I

f

L.'.

I

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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

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J l-20.00 -16.00 -12.00 -8.00 -q. O0 0.00

/I

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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

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, I ,-0. u,O O. O0 O. qo

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C)

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"6

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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

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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

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3

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(RAD/SEC)


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

//

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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 !

÷

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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

/

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(RAD/SEC)

C)

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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

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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


• C.G,: 33% MAC

t .000i. 680

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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

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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

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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

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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

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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

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AILERONLOOPS CLOSED FOR AFT C.G. MAXIMUMDYNAMIC PRESSURE CONDITION

383

APPENDIX E

• MAXI_JM Q (Vd)


• MACH: 0.86• ALTITUDE: 15,000 FT.• GROSSWEIGHT: 2200 LBS.• C.G.: 33% MAC

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384

'I NO.pl

3

4-

+

i

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-1,60

APPENDIX E

• .MAXIMUM Q (V d)


• MACH= 0.86

• ALTITUDE- 15,000 FT.• GROSS HEIGHT: 2200 LBS.

• C.G.: 33% MAC

i i iGAIN.$950L.O00

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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

+\\

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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

0.40

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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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