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

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Presentation on theme: "Recent USAF Total In-Flight Simulator (TIFS) Projects SAE Guidance & Control Committee March 2005 Eric Ohmit Flight Research Group."— Presentation transcript:

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

3 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.

4 Background New nose was developed to support NASA HSCT XVS and SVS evaluations during –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

5 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

6 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

7 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

8 Approach profile

9 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  ~ -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

10 Movie

11 ITT Viking Program ITT (nee Kodak) Viking Sensor program –Sponsor ITT –Department of Energy (partial funding for flight testing)

12 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

13 Installation

14 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

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16 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

17 Contact Information Norm Weingarten TIFS Program Manager (716)

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

19 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

20 TIFS Sensors (Backup chart) AIR DATA: , , V, Turbulence, h, h-dot,  (Raw data & Complementary filtered) ANGULAR MOTION: , , , 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

21 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

22 TIFS Performance Capabilities (Backup chart) V-max: 270 Kt V-touchdown: 115 Kt Kt V-stall deg Faps): 95 Kt Max Sink Touchdown: 10 Ft/Sec Steep Approach: -15 deg Flight Path(  ), 270 Kt Max Rate of Climb: 2000 Ft/Min Nz range: 0 to 2.0 g Ny range: +/ 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

23 TIFS Piloted Simulation Nose (Backup chart)

24 TIFS Avionics Nose (Backup chart)

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

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

27 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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