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Flight Test Instrumentation Package for the L-29 Delfin Turbojet
For theQuarterly Review of the NASA/FAA Joint University
Program for Air Transportation ResearchFriday June 14th, 2002
Michael S. Braasch, Ph.D., P.E.Curtis CutrightJansen Litter
Avionics Engineering CenterOhio University, Athens
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Purpose
• Hardware/software sensor testbed
• Software INS/GPS integration
• Noise versus dynamic tracking error trade off
• Synthetic aperture radar
• Aircraft system id/flight control design educational tool
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Flight Test Vehicle
• L - 29 Delfin
• High Altitude 11 Km
• High Speed 354 knots
• Fully Aerobatic
Flight Specs Taken From http://aeroweb.brooklyn.cuny.edu/specs/aero/l-29.htm
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Delphin Equipment
•Navigation Grade INS
•Industrial Keyboard
•Shock-hardened Computer
•Industrial Flat Panel Display
•NovAtel GPS Receiver
•Tactical Grade IMU*The IMU will be integrated into the system at a later date
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Project Development
• Initial equipment installation is complete
• GPS and INS data collected simultaneously in real time
• In process of supplying INS unit with 28VDC
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System Block Schematic
ADC INS
PC104
GPS
data
data
data
12 VDC
Aircraft Power
28 VDCINV
115VAC/ 400Hz
Potentiometer
data
Power
Data
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INS Data Collection System Power Specifications
Unit Voltage Current PowerINS 115VAC/400HZ 2A 230W
INS (backup) 28VDC 10A 280W
INS Cooling Fan
28VDC
PC104 8-32VDC 11A Max 85W Max
ADC 28VDC 350mA 10W Max
Monitor 12VDC 3.5A 42W
GPS 6-18VDC 2.8W(3.3W Max)
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PC104 Power Distribution
Component Voltage Current Power
CPU Module 5VDC 2A(1.5A Max) 10W
CM102 Floppy 5VDC 125mA 625mW
CMT107 Hard-drive
5VDC 1A max(fused) 5W
Network Card 5VDC 200mA 1W
Keyboard 5VDC 200mA 1W
GPS +12VDC 235mA 2.8W
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PC104 Power Availability
Voltage Current Power
5VDC 12A 60W
+12VDC 2A 24W
-12VDC 500mA 6W
Maximum Power Output From PC104: 75W
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System Schematic
ADC
Baro ReturnBaro Signal
+5 Baro Excitation
H
LOutput
+28VGND
Case GND
333414
27
9
181936
Potentiometer
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System Schematic Continued
K4
K5
H
LADC Data
151178
115 VAC115 VACChassis GND+28V+28V GND
INS Unit
HL
Input
HL
Output
Mode Select
A8A9
G7G8
F1
ON
(M1)
Middle Insert
Lower Insert
Middle Insert
A5 SDI-MSB
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System Schematic Continued
417
114
ARINC CardPC104
Initialization
Data
Serial Port 2
Serial Port 1
43
21 +5V
+5V GND
+12V GND+12V
Power Plug
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System Schematic Continued
+12V
+12V GND
Power
Serial Port
I/O1 PPS
Novatel GPS Receiver
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Installed Equipment
ADC Inverter
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Installed Equipment Continued
Industrial Keyboard INS On Switch
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Installed Equipment Continued
Novatel GPS Receiver Control Switches
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Installed Equipment Continued
GPS Antenna
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GPS Data
-83 -82.95 -82.939.42
39.43
39.44
39.45
39.46
39.47
39.48
39.49
39.5
Longitude
Latit
ude
Lat/Lon from Delphin Flight Test
Feb 6, 2002 Ross County Airport
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GPS Data Continued
0 5 10 15 20 250
200
400
600
800
Time
Vel
ocity
(ft
/s)
0 5 10 15 20 250
2000
4000
6000
8000
10000
Time
Alti
tude
(ft
)
Feb 6, 2002 Ross County Airport
Rolls
Rolls
Hammer Head Stall
Hammer Head Stall
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GPS Data Continued
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INS
• INS Data has been collected on one flight test
• Latitude and Longitude was post processed from the collected data
• Initially, data seemed to be fine
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GPS and INS Data
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2424
GPS and INS Data Continued
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GPS and INS Data Continued
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GPS and INS Data Continued
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Analysis
• GPS and INS drift apart as expected
• 6 Mile difference by end of flight test
• Error much too large for INS unit
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Analysis Continued
• A problem with the INS installation was discovered and corrected
• INS can send unreliable data if not initialized properly
• Error was masked from view
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INS Static Test
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INS Static Test
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INS Static Test
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Conclusion
• INS and GPS data collection is ongoing
• INS data collection software is still being refined and updated
• More flight testing is needed to determine if the INS problem is really fixed
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Contact Information
Principle Investigator: Dr. Michael Braasch
Research Engineer: Curtis Cutright
Research Associate: Jansen Litter