1. 1 Flight Test Instrumentation Package for the L-29 Delfin Turbojet For the Quarterly Review of the NASA/FAA Joint University Program for Air Transportation Research Friday June 14 th, 2002 Michael S. Braasch, Ph.D., P.E. Curtis Cutright Jansen Litter Avionics Engineering Center Ohio University, Athens

2. 2 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

3. 3 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

4. 4 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

5. 5 Project Development Initial equipment installation is complete GPS and INS data collected simultaneously in real time In process of supplying INS unit with 28VDC

6. 6 System Block Schematic ADCINS PC104 GPS data 12 VDC Aircraft Power 28 VDC INV 115VAC/ 400Hz Potentiometer data Power Data

7. 7 INS Data Collection System Power Specifications UnitVoltageCurrentPower INS115VAC/400 HZ 2A230W INS (backup)28VDC10A280W INS Cooling Fan 28VDC PC1048-32VDC11A Max85W Max ADC28VDC350mA10W Max Monitor12VDC3.5A42W GPS6-18VDC2.8W(3.3W Max)

8. 8 PC104 Power Distribution ComponentVoltageCurrentPower CPU Module5VDC2A(1.5A Max)10W CM102 Floppy5VDC125mA625mW CMT107 Hard- drive 5VDC1A max(fused)5W Network Card5VDC200mA1W Keyboard5VDC200mA1W GPS+12VDC235mA2.8W

9. 9 PC104 Power Availability VoltageCurrentPower 5VDC12A60W +12VDC2A24W -12VDC500mA6W Maximum Power Output From PC104: 75W

10. 10 10 System Schematic ADC Baro Return Baro Signal +5 Baro Excitation HLHL Output +28V GND Case GND 33 34 14 27 9 18 19 36 Potentiometer

11. 11 11 System Schematic Continued K4 K5 H L ADC Data 1 5 11 7 8 115 VAC Chassis GND +28V +28V GND INS Unit H L Input H L Output Mode Select A8 A9 G7 G8 F1 ON (M1) Middle Insert Lower Insert Middle Insert A5SDI-MSB

12. 12 12 System Schematic Continued 4 17 1 14 ARINC Card PC104 Initialization Data Serial Port 2 Serial Port 1 4 3 2 1 +5V +5V GND +12V GND +12V Power Plug

13. 13 13 System Schematic Continued +12V +12V GND Power Serial Port I/O 1 PPS Novatel GPS Receiver

14. 14 14 Installed Equipment ADCInverter

15. 15 15

16. 16 16 Installed Equipment Continued Industrial Keyboard INS On Switch

17. 17 17 Installed Equipment Continued Novatel GPS ReceiverControl Switches

18. 18 18 Installed Equipment Continued GPS Antenna

19. 19 19 GPS Data

20. 20 20 GPS Data Continued Rolls Hammer Head Stall

21. 21 21 GPS Data Continued

22. 22 22 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

23. 23 23 GPS and INS Data

24. 24 24 GPS and INS Data Continued

25. 25 25 GPS and INS Data Continued

26. 26 26 GPS and INS Data Continued

27. 27 27 Analysis GPS and INS drift apart as expected 6 Mile difference by end of flight test Error much too large for INS unit

28. 28 28 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

29. 29 29 INS Static Test

30. 30 30 INS Static Test

31. 31 31 INS Static Test

32. 32 32 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

33. 33 33 Contact Information Principle Investigator:Dr. Michael Braasch Braaschm@ohiou.edu Research Engineer:Curtis Cutright Cutright@ieee.org Research Associate:Jansen Litter JansenLitter@hotmail.com