Fact Sheet Display

AERODYNAMIC AND PROPULSION TEST UNIT

The Aerodynamic and Propulsion Test Unit (APTU) is a blow down wind tunnel designed for aerodynamic testing of supersonic and hypersonic systems and hardware at true flight conditions. Given its versatile design, APTU can support a myriad of test setups: propulsion, material, structures, store separation, and directed energy lethality/survivability.

FACILITY DESCRIPTION

A combustion air heater (CAH) provides the required temperature to simulate the enthalpy to which a flight vehicle is exposed during high-speed flight. The CAH is designed to operate over a range of total pressure from 50 psia to 2,800 psia and a range of total temperature from <1,000°R to 4,700°R. Liquid oxygen is added upstream of the CAH to provide the correct oxygen content (mole fraction) in the flow. The facility is computer-controlled during a run, and rapid transitions in pressure and temperature (altitude and/or speed changes) can be accomplished. Axisymmetric nozzles generate the required environments in the test section. Five fixed freejet nozzles are currently available to produce test conditions from Mach 3.1 to Mach 7.2. The remote location of the facility in addition to the straight line ejector exhaust configuration allow for unique test capabilities like ammunition, explosive or live-fire testing. The facility can be sited for 10,000 pounds of Class 1.3 explosives.

A 22,000-cubic-foot air reservoir, which can be pressurized to 4,000 psia, allows run durations from 30 seconds to 6 minutes, depending on the Mach number and altitude required for the run. This air storage system also supplies an annular air ejector, located in the exhaust duct. The ejector lowers the test cell pressure to minimize the facility startup loads on the test article, and to obtain/sustain altitude conditions in the cell during testing.

Cooling water is supplied to APTU from the AEDC pumping station through a 36-inch-diameter main pipe at 90 psig. This water can be used directly for low-pressure test article cooling requirements. If high-pressure cooling water is needed five pumps are available that can be used individually or in combination as necessary. Water pressure can be provided up to 2,000 psig.

An endothermic fuel heater is installed to support hydrocarbon-fueled testing of scramjet engines. The fuel heater is able to generate and control endothermically reacted hydrocarbon fuels up to 7.2 lbm/sec at 1,300°F. Greater fuel flow rate is available at reduced temperature output. Maximum heater operating pressure is 1,000 psia.

HISTORY AND FUTURE PLANS

From 1981 to 2005, APTU used its vitiated air heater (VAH) to conduct over 275 runs for a wide range of system development programs. The maximum pressure and temperature of the VAH were limited to 300 psia and 2,000ºR, respectively. Significant improvements in test productivity were made during that time frame with as many as four runs per day.

In 2002, under the High-Speed/Hypersonic Air-Breathing Propulsion Test and Evaluation Capability (HAPTEC) program, APTU began a series of major upgrades to provide a ground-test capability for supersonic and hypersonic systems up to Mach 8. Upgrades are planned through 2014 that will be implemented with minimal interference to customer test schedules.

Phase I of the upgrade, completed in 2004, modified the APTU utility supply systems (high-pressure air, isobutane, liquid oxygen and water) and replaced the air ejector system to increase the facility's altitude simulation capability.

Phase II centered on replacing the VAH with a much more capable high-pressure, high-temperature CAH. APTU in its CAH configuration reached initial operational capability of Mach 7.2 in September 2007.

Possible future upgrades that are being considered include variable Mach number test capability, and clean air heater technology.

The HAPTEC upgrades provide customers with a much needed ground-test capability for the research, development and acquisition of high-speed and hypersonic aerospace systems.

LANDING GEAR TEST FACILITY

Overview

The Landing Gear Test Facility (LGTF) has been a cornerstone of aerospace testing at Wright-Patterson Air Force Base since 1942, dedicated to ensuring the reliability and performance of aircraft landing gear systems.

Throughout its history, the LGTF has supported the warfighter by providing critical data to enhance the safety and effectiveness of landing gear, wheels, tires, and brakes, directly contributing to the mission of the United States Department of Defense. In addition to its military focus, the LGTF offers comprehensive testing services to commercial entities, employing world-unique test machines capable of simulating real-life conditions with unparalleled accuracy.

Guided by the core values of Integrity, Service, and Excellence, the LGTF consistently delivers precise and dependable data to both military and commercial partners.

Test Machine Capabilities

 

 Overall System Specifications:

Max Speed: 250 mph
Max Acceleration: 21 ft/s2
Inertial Equivalent: 2,445 - 20,063 lbs.
Max Kinetic Energy: 41,750,000 ft-lbs.
 

South Carriage Specifications:

Max Load: 40,000 lbs.
Max Torque: 375,000 in-lbs.
Max Tire Size: 64 in
 

North Carriage Specifications:

Max Load: 25,000 lbs.
Max Torque: 72,000 in-lbs.
Max Tire Size: 48 in

Overall System Specifications:

Max Speed: 350 mph
Max Acceleration: 24 ft/s2

South Carriage Specifications:

Max Load: 150,000 lbs.
Max Yaw: ± 20°
Max Camber: ± 20°

North Carriage Specifications:

Max Load: 100,000 lbs.

 

Overall System Specifications:

Max Speed: 200 mph
Max Acceleration: 2 ft/s2
Inertial Equivalent: 10,147 - 162,987 lbs.
Max Kinetic Energy: 205,000,000 ft-lbs.

South Carriage Specifications:

Max Load: 301,500 lbs.
Max Brake Torque: 5,800,000 in-lbs.

Overall System Specifications:

Max Speed: 250 mph
Max Acceleration: 16 ft/s2
Max Vertical Load: 150,000 lbs.
Max Yaw: ± 20°
Max Camber: ± 10°

Overall System Specifications:

Max Compressive Load: 3,000,000 lbs.
Max Tension Load: 1,000,000 lbs.
Max Stroke: 60 in
Max Height: 28 ft
Max Width: 10 ft
Platen Size: 60.5 x 96 in

Overall System Specifications:

Max Vertical Load: 75,000 lbs.
Max Side Load: 30,000 lbs.
Max Yaw: ± 90°
Max Camber: ± 10°
Max Tire Size: 56 in.
Table Length: 20 ft.
Max Travel Speed: 3 in/s
Roll Distance: 217 in

 

Overall System Specifications:

Below-grade safety enclosure
Dimensions: 72 x 120 x 126 in.
Water Pressure Limit: 5,000 psi
Rate of Inflation: 10 psi/min

Drop Tower #1

Load Range: 750 - 3,600 lbs.
Wing Lift: 200 - 3,600 lbs.
 

Drop Tower #2

Load Range: 2,000 - 10,300 lbs.
Wing Lift: 200 - 10,300 lbs.
 

Drop Tower #3

Load Range: 6,500 - 50,000 lbs.
Wing Lift: 200 - 35,000 lbs.
 

Drop Tower #4

Load Range: 35,000 - 150,000 lbs.
Wing Lift: 200 - 150,000 lbs.

Load frame that accommodates multiple hydraulic cylinders to provide controlled forcing and operational stresses to test objects in all 6 axes.

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CONTACT US

704 TG/OL-ACL
Landing Gear Test Facility
1981 5th Street
Area B, Bldg. 31
Wright-Patterson AFB, OH 45433
(937) 255-9216
704.tg.olac@us.af.mil

 

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