JASC News

On August 22, 2003, JASC, Inc. completed performance verification testing of three five-channel hot fuel control valve arrays slated for use on the Ground Demonstration Engine V2.0 (GDE-2.0) later this year, with Pratt & Whitney taking delivery of the valves the following week. These Hot Gas Valves (HGVs) form an integral part of the scramjet engine’s fuel control system, which will be used to precisely control the flow of high-temperature, gaseous hydrocarbon fuel to various regions of the engine’s combustor.

This engine will be tested in the NASA LaRC 8-ft High-Temperature Tunnel (HTT), which will provide data to further define critical engine operating parameters, fine-tune the engine’s thermal management system, and validate CFD analysis for the full-height and width, single module, flight-weight engine. This engine is the penultimate version of the one envisioned to power the X-43C Hypersonic Research Vehicle, scheduled to make its maiden flight in CY06.

An artist’s rendering of the air-breathing, hypersonic X-43C, part of NASA’s Hyper-X series of flight demonstrators. CREDIT: Media Fusion, Inc./NASA

All valves performed flawlessly during ambient temperature testing at JASC, and exceeded all performance requirements for dynamic response, metering accuracy, repeatability, and sealing. Proof pressure testing was performed at levels simulating actual worst-case loading conditions at the design temperature & pressure. Valve testing with high-temperature fuel is scheduled for this fall, after which the valves will be installed on the engine. Engine testing in the 8’HTT is scheduled to occur during Q1-04.

The program is being funded through the Air Force’s Hydrocarbon Scramjet Engine Technology (HySET) Program, under the broader Hypersonic Technology (HyTECH)
Program. The engine will ultimately operate in the Mach 4.5-6.5 range and has both military and commercial applications.

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In July 2003, JASC was awarded a contract from Hamilton Sundstrand, of San Diego, CA, to develop the Fuel Control System and Inlet Guide Vane Actuator for the PW-980. The PW-980 is the Auxiliary Power Unit (APU) that will be used on the Airbus A-380 (seen below). The A-380 is a next-generation Jumbo Jet, designed to carry 555 passengers over 8,000 nautical miles.

The largest commercial APU currently available is the PW-901, found on the Boeing 747-400 series aircraft. The PW-980 is a larger derivative of the original PW-901 design and will assume the role as the largest commercial APU when it enters service on the A-380 (scheduled for 2006).

The PW-980 APU, to be used on the Airbus A-380, will be equipped with a Fuel Control System and Inlet Guide Vane Actuator developed by JASC

Control systems are not new to JASC. The company has been developing a wide variety of controls and has over 40 years of experience in the field. From small UAVs (see the article “Mini-Motors to Drive Small UAVs, Missiles” in the July 29, 2002 issue of Aviation Week & Space Technology), to large industrial power applications, JASC is a proven name in fuel controls.

JASC is also establishing itself as the leader in fuel controls for hypersonic research aircraft. It has developed the fuel controls for the X-43A (Hyper-X) vehicle, as well as follow on engine/vehicles (see the articles “Component Tests Aid Scramjet Development and Flight-Weight Scramjet Readied for Tests” in the June 24, 2002 issue of Aviation Week & Space Technology).

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JASC is pleased to announce the completion and shipment of our Pulse Width Modulated (PWM) Fuel Control Valve. This valve is used to meter fuel to small compression ignition engines. Target applications for this valve include the engines used to power the developing field micro UAV/drone aircraft for the U.S. armed forces. These drones weigh about five pounds, measure about nine inches in diameter and are designed to fit inside a soldiers backpack. These drones are intended to be part of an autonomous aircraft and ground vehicle network that will perform a wide range of military missions. The Micro UAV’s can carry small cameras and may be used to fly “over the next hill” to perform reconnaissance
for other robotic or manned units (1).

The PWM Fuel Control Valve meters fuel flow and provides positive fuel shutoff for either diesel or JP-8 by using a modest fuel tank head pressure as the motive force. The PWM Fuel Control Valve is operated by a PWM signal from an electronic fuel management computer. The fuel-metering schedule is a function of duty cycle at a fixed frequency, as commanded by the electronic fuel management computer. This design provides for a low cost, small and lightweight fuel metering valve for small engines and is based upon existing JASC technology for “clapper type” fast-response solenoid valves.

The Pulse Width Modulated Fuel Control Valve is another example that demonstrates JASC’s capabilities in designing innovative flow control devices to fit a wide range of applications. For a detailed list of the products that JASC currently manufactures, please visit the Products page.

PWM Fuel Control Valve operating characteristics:

• Input Signal: 5.0 ± .5 VDC @ 30 HZ
• Duty Cycle: 12% to 75% range
• Max. Current: .50 amps.
• Flow: 0.2 to 2.0 PPH @ 10 inches of head pressure
• Seat Leakage: Zero
• Temp. Range: -65 to +350 °F
• Dry Weight: 2.0 oz. Max.
• Dimensions: 0.500” F X 1.500” length max.

(1) Popular Science Magazine, June 2003.

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JASC has shipped the first two Inlet Guide Vane Actuators for the Airbus A-380 APU, the PWC-980A. The PWC-980A will be the largest commercial APU when it enters service in 2006, and JASC’s Inlet Guide Vane Actuator (IGVA) will be used for controlling the Inlet Guide Vanes (Please see archived article A380 Contract for additional details).

This actuator is a scaled up version of another JASC designed Inlet Guide Vane Actuator that is currently used on the Hamilton-Sundstrand APS-3200 APU, which provides auxiliary power on the Airbus A-320 family of aircraft.

This actuator incorporates JASC’s innovative direct acting, clevis type servo to drive the piston that is used to control the angle of the engine’s inlet guide vanes. The clevis type servo has a number of operating characteristics that make it ideal for this type of application:
• Low cost
• High-pressure gains
• Operation that is unaffected by changes in supply pressure
• Low null leakage rates
• Dry coil
These, and other features, are what help to make JASC’s IGVA for the A-380 APU an excellent choice for a demanding job.

For additional information on the clevis type servo, and JASC’s other innovative products, please click see our Products.

Some of the key features of the IGVA are listed below:
• Full stroke slew rate of 0.200 seconds
• 350 ± 25 psid operating pressure
• Filtered inlet and return ports (10 µ in. nominal, 25 µ in. absolute)

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In December of 2002, JASC signed a Long Term Agreement (LTA) with Hamilton-Sundstrand San Diego to continue supplying JASC production components for the Hamilton-Sundstrand APS-3200 Auxiliary Power Unit (APU). The APS-3200 APU is used on the Airbus A-320 commercial airliner and provides electrical power and air conditioning while the aircraft is on the ground.

Hamilton-Sundstrand’s APS-3200 Auxiliary Power Unit. JASC supplies a variety of fluid and electro-hydraulic control components for the APS-3200. The APS-3200 is mounted on the Airbus A-320 commercial airliner

This latest LTA is effective through December of 2007 and is the second consecutive LTA that JASC has signed with Hamilton-Sundstrand for APS-3200 components. These LTA’s are a sign of JASC’s commitment to continue supplying quality aerospace control components to its valued customers.

The components that JASC supplies for this APU include: servo valves, inlet guide vane actuators (IGVA), pressure regulators, flow dividers and small filter assemblies.

The Airbus A-320 commercial airliner. The Hamilton-Sundstrand APS-3200 APU is used to supply electrical power and air conditioning while the aircraft is on the ground

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