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Recent USAF Total In-Flight Simulator (TIFS) Projects

Flight Research Group. Recent USAF Total In-Flight Simulator (TIFS) Projects. SAE Guidance & Control Committee March 2005 Eric Ohmit. Background.

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Recent USAF Total In-Flight Simulator (TIFS) Projects

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  1. Flight Research Group Recent USAF Total In-Flight Simulator (TIFS) Projects SAE Guidance & Control Committee March 2005 Eric Ohmit

  2. Background • The USAF NC-141H TIFS and its twin (CTIFS) were developed during the 70’s to provide an in-flight simulator test beds for civil and military applications • The TIFS has been in operation for over 30 years • The TIFS is operated under a CRADA with the USAF by Calspan in Buffalo NY.

  3. Background • New nose was developed to support NASA HSCT XVS and SVS evaluations during 1998 - 1999 • Develop & demonstrate a Synthetic External Visibility System to allow pilots to navigate & make precision approaches & landings without reference to real-world external windows • Significant reduction in nose weight allowing for additional equipment installation • HDTV, displays, radar, etc

  4. Background • CRADA with USAF • USAF AFRL/VA discontinued operation of TIFS & VISTA Aircraft 1998 • CRADA signed by all parties 11/99 • N793VS assigned to aircraft on 1/01 by FAA

  5. Recent programs • X-40A IAG&C In-Flight Evaluations (Sep-Dec 2003) • USAF AFRL Sponsored • Participants AFRL, Calspan (nee Veridian), Barron Associates, Boeing • IAG&C – Integrated Adaptive Guidance & Control

  6. Program Objectives • Risk Reduction Flight Testing of an autoland control system with algorithms which • Accommodate Single and Multiple Control surface failures (locked surface) • Reconfigure the trajectory as necessary to provide acceptable touchdown locations and sink rates • Reference: “An Approach to Integrated Adaptive Guidance and Control with Flight Test Results” Schierman, Ward, Hull, Gandhi, Oppenheimer & Doman, AIAA JGC&D

  7. Approach profile

  8. Results • Successful demonstration of • Single control surface failures • Multiple control surface failures • Trajectory reconfiguration • Autonomous steep approaches to touchdown under the control of the IAG&C Autoland controller (no pilot or safety pilot interaction after engagement) • Expansion of the TIFS flight path and Side force surface envelopes • Utilized SFS in toed out configuration to produce drag • Original goal had been to evaluate g ~ -27 deg, nominal attained was -8 to -12 deg • Airframe buffet at full SFS deflection prevented higher descent rates • Modified TIFS Model Following algorithm for scaled vertical axis MF

  9. Movie

  10. ITT Viking Program • ITT (nee Kodak) Viking Sensor program • Sponsor ITT • Department of Energy (partial funding for flight testing)

  11. Objectives • Quick-turn Demonstration of Airborne Natural Gas Leak Detection System. • Commercial development, but flight test partially funded by the Department of Energy. • DOE schedule required fast response workaround from original plan • TIFS selected due to ease of installation and available flight status • Used avionics nose configuration of TIFS • Side-force-surfaces removed

  12. Installation

  13. Results • Installed over 1200# of equipment in nose and 1000# in cabin. • Based on a laser system. • Checkout in Buffalo, NY – Aug 2004 • Flight evaluations in Casper, WY – Sep 2004 • Rocky Mountain Oilfield Testing Center, Cheyenne WY • Very successful results • System presently being installed in a Cessna Caravan

  14. Movie

  15. Future Programs & Other Potential uses of TIFS • Scheduled use • Handling Qualities Program (Summer ’05) • Potential uses • Airborne sensor test-bed • UAV Control law or multi-UAV test risk reduction/demonstration • UAV sensor/payload flight testing

  16. Contact Information • Norm Weingarten TIFS Program Manager (716) 631-6925 norman.weingarten@calspan.com

  17. TIFS Typical Systems Equipment (Backup chart) Avionics Nose with APG-66 Radar Aft Crew Station

  18. TIFS Display & Systems Programs (Backup chart) PREVIOUS PROGRAMS: • REMOTELY PILOTED VEHICLE COMPASS COPE - Autoland & Remote Operator • EXTERNAL VISIBILITY & SYNTHETIC VISION SYSTEMS NASA HSCT & Aviation Safety Programs • MARTIN MARIETTA SMART WEAPONS SUITE • AFTPS ASTTA Avionics Systems Test & Training Aircraft • C-141 DISPLAY UPGRADE • WINDSHIELD DISTORTION B-1 • COMMAND FLIGHT PATH DISPLAY • CONTROL SYSTEM RECONFIGURATION

  19. TIFS Sensors (Backup chart) • AIR DATA: a, b, V, Turbulence, h, h-dot, g (Raw data & Complementary filtered) • ANGULAR MOTION: q, j, y, p, q, r • LINEAR MOTION: Airspeed, Rate of Climb Nx, Ny, Nz (cg & Pilot) • ALTITUDE: Pressure, Radar • NAVIGATION: LTN-72R(INS), D-GPS, LORAN, TACAN, VOR • DIGITAL DATA BUSES: MIL 1553B and ARINC 429 & 561 • IRIG TIME CODE: Available in computer, data recording and video recording

  20. TIFS Power, Weight, Cooling (Backup chart) • Power available: 28V DC: 115 Amps 400 Hz AC, 3 Phase: 40 KVA 60 Hz AC: 7 KVA • Weight available for customer equipment: ~ 1,000 pounds in aft cabin ~ 1,500 pounds in avionics nose 6’ deep with two Radomes (12 gHz & 36 gHz) ~ 500 pounds in simulation cockpit • Rugidization: Accommodate “office” environment & prototype equipment: sensors, computers, displays • Cooling: Auxiliary air conditioner ~ 36,000 BTUs. Exhaust fans: 270 cfm in simulation cockpit 800 cfm in aft cabin Cooling air & exhaust can be directly plumbed to/from equipment for positive cooling

  21. TIFS Performance Capabilities (Backup chart) • V-max: 270 Kt • V-touchdown: 115 Kt - 150 Kt • V-stall (@15 deg Faps): 95 Kt • Max Sink Rate @ Touchdown: 10 Ft/Sec • Steep Approach: -15 deg Flight Path(g), 270 Kt • Max Rate of Climb: 2000 Ft/Min • Nz range: 0 to 2.0 g • Ny range: +/- 0.25 g • h-max for simulation: 10,000 Ft • h-min: 0 Ft (for runway touchdown) • h-min: 500 Ft (over terrain) • Max Flight Duration: 2.0 Hr • Crew Size: 2 Safety Pilots 2 Test Engineers 4 Customer Engineers/Pilots/Observers

  22. TIFS Piloted Simulation Nose (Backup chart)

  23. TIFS Avionics Nose (Backup chart)

  24. TIFS Piloted Simulation Nose Configuration (Backup chart) 6 DOF MODEL FOLLOWING SIMULATION • ELEVATOR • AILERON • RUDDER • DIRECT LIFT FLAPS • SIDE FORCE SURFACES • DIRECT THRUST CONTROL VARIABLE FEEL CONTROLLERS • WHEEL • CENTERSTICK • SIDESTICK COMPUTERS: • RUDDER PEDALS • SILICON GRAPHICS ONYX SERVO THROTTLE • RAPID SYSTEMS (5 DSPs) RECORDERS: • 260 CHANNELS • BERNOULLI DRIVE • ZIP DISK • VIDEO & VOICE • FULL SENSOR SUITE • SEPARATE RECONFIGURABLE • GPS SYSTEM SIMULATION COCKPIT INSTRUMENT PANEL & FLOOR • LITTON 72R INS • PROGRAMMABLE 19" CRT & F-18 TYPE HEAD-UP AND HEAD-DOWN DISPLAYS

  25. TIFS Avionics Nose Configuration (Backup chart) • RADAR DIGIBUS INTERFACE • SILICON GRAPHICS ONYX • RAPID SYSTEM DSP COMPUTER • ACCOMODATE CUSTOMER EQUIP. • DIGITAL DATA & VIDEO RECORDERS AVIONICS AFT CREW STATION • STANDARD INSTRUMENTS • PROGRAMMABLE DISPLAYs • FBW CONTROL OF AIRCRAFT • CONTROL OF ALL EQUIPMENT SIDEFORCE SURFACES • F-16 APG-66 CAN BE REMOVED RADAR • FULL SENSOR SUITE • LTN-72R INS • AN/AAS-36 IRDS • GPS SYSTEM • E/O TV CAMERA • MAVERICK SEEKER HEAD • ACCOMODATE CUSTOMER EQUIP.

  26. TIFS Typical Simulation Cockpit Configurations (Backup chart) • Room for Large Displays & Radar • Wide Unobstructed Field-of-View • Large Center Console • with Throttle Feel System • Side Consoles • for Controllers & Instruments • Two Floor Configurations: • Level & Sloped 7 Deg Nose-up

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