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Testing device and method for aircraft fuel system in simulated high altitude environment

A technology of fuel system and testing device, which is applied in the direction of aircraft component testing, ground equipment, aircraft parts, etc., and can solve problems such as complex system, high cost, and accuracy error

Active Publication Date: 2016-04-13
象限空间(天津)科技有限公司
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AI Technical Summary

Problems solved by technology

Most of the existing tests are based on empirical calculations or environmental chamber simulations. The working conditions of components can be preliminarily calculated through empirical formulas, but there are still errors in the accuracy; and environmental chamber simulations also have the disadvantages of high cost and complex systems
Especially for the test of the aircraft fuel system, since the fuel system is the core component of the aircraft, if there are errors in the test, there will be hidden dangers in the flight of the aircraft

Method used

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  • Testing device and method for aircraft fuel system in simulated high altitude environment

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Embodiment Construction

[0025] In order to overcome the shortcomings of the prior art, the present invention provides a test device and method for simulating the fuel system of an aircraft in a high-altitude environment. By adjusting the working pressure and temperature of the fuel system, a low-temperature and low-pressure (such as plateau or high altitude) environment is simulated. , To record the working parameters of the fuel system for analysis and testing.

[0026] Such as figure 1 Shown is the schematic diagram of the test device for the aircraft fuel system in the simulated high altitude environment, including a low temperature air supply system connected to the fuel system and a vacuum exhaust system connected to the pressure-resistant fuel tank of the fuel system.

[0027] The low-temperature gas supply system includes a gas storage tank 11, a first regulating valve 12, an expansion turbine unit 13, an electric heater 15 and a plate heat exchanger 17 which are sequentially connected through a ga...

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Abstract

The invention provides a testing device for an aircraft fuel system in a simulated high altitude environment, comprising a low temperature gas supply system, a vacuum pumping system and a fuel system, wherein the low temperature gas supply system is used for creating a low temperature environment of the simulated high altitude; the vacuum pumping system is used for pumping air out of a pressure-proof fuel tank to create a low pressure environment of the simulated high altitude; the fuel system comprises the pressure-proof fuel tank, a fuel pump and an engine which are sequentially arranged; the low temperature gas supply system realizes the purpose of cooling fuel in the pressure-proof fuel tank through a plate type heat exchanger; and the vacuum pumping system is connected with the pressure-proof fuel tank. Accordingly, the invention also provides a testing method for the aircraft fuel system in the simulated altitude environment. Therefore, by adjusting the working pressure and temperature of the fuel system, the low temperature and low pressure environment of the high altitude is simulated, and working parameters of the fuel system are recorded, thereby analyzing and testing the fuel system.

Description

Technical field [0001] The invention relates to the technical field of fuel system testing, in particular to a test device and method for simulating the fuel system of an aircraft in a high-altitude environment. Background technique [0002] With the rapid application and development of aviation technology, more and more military and civilian fields have applied aviation methods to improve efficiency and save costs, such as search and rescue, broadcast, investigation, medical rescue, and so on. As the flight altitude increases, the ambient temperature and pressure gradually decrease. In order to maintain the flight safety and performance of the aircraft, it is necessary to conduct simulation tests on the components of the aircraft in the early stage. Existing tests are mostly based on empirical calculations or environmental chamber simulations. The working conditions of components can be calculated through empirical formulas, but there are still errors in accuracy. Environmental ...

Claims

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Application Information

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IPC IPC(8): B64F5/00B64F5/60
Inventor 黄智
Owner 象限空间(天津)科技有限公司
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