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Interference simulation system

A technology that interferes with simulation and subsystems, applied in the field of aircraft, and can solve the problems of low accuracy of simulation results of hypersonic aircraft

Inactive Publication Date: 2020-11-24
BEIHANG UNIV
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Problems solved by technology

[0003] The purpose of the embodiments of the present application is to provide an interference simulation system to solve the technical problem of low accuracy of simulation results of hypersonic aircraft

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Embodiment Construction

[0020] Hypersonic aircraft refers to aircraft with a flight speed of Mach five or more (for example, aircraft with a flight speed exceeding five times the speed of sound, missiles, artillery shells and other winged or wingless aircraft), which have the characteristics of a high penetration success rate and have huge potential. Military value and potential economic value. Therefore, the development and development of hypersonic vehicles will not only greatly change the style of modern warfare, but also greatly promote and promote the integration and development of countries in aerospace exploration, civil aerospace and other related fields. Shanghai will further play a major strategic significance.

[0021] Adjacent space refers to the airspace between 20 kilometers and 100 kilometers above sea level, which is outside the aviation field where aircraft fly and the space space where ordinary spacecraft operate. It has a safe and stable working environment and is difficult to be d...

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Abstract

The invention provides an interference simulation system. The interference simulation system comprises a vacuum subsystem, a test model subsystem, a propellant supply subsystem and a measurement and control subsystem. The test model subsystem comprises an incoming flow simulation engine, a jet flow simulation engine and an aircraft test model, the incoming flow simulation engine is used for simulating hypersonic test airflow in the flight process of an aircraft, and the jet flow simulation engine is arranged on the aircraft test model and used for simulating jet flow generated in the flight process of the aircraft. According to the scheme, firstly, an interference simulation test is carried out in a vacuum cabin, a thinner low-pressure atmospheric environment can be provided, and under thelow-pressure atmospheric environment, hypersonic test airflow is provided by adopting fuel gas jet flow generated by the incoming flow simulation engine, so that the requirements of high speed and high enthalpy can be met at the same time; therefore, the manufactured test environment is close to the flight environment. Therefore, on the basis of reducing the requirement on equipment, the servicetime of the device can be prolonged, and the accuracy of a simulation result can be improved.

Description

technical field [0001] The present application relates to the field of aircraft, in particular, to an interference simulation system. Background technique [0002] A general hypersonic wind tunnel converts the driven gas into the hypersonic test airflow required for the experiment through conventional heating or shock wave heating. However, if you want to use the above method to achieve high enthalpy test conditions, you have high requirements for heating equipment, vacuum equipment, etc., and the working time of this kind of wind tunnel is very short. In addition, there are still relatively large differences between the test environment manufactured by the above method and the flight environment, and it is difficult to simulate the requirements of flight conditions such as Mach number, enthalpy, low density, and low pressure, which makes the accuracy of the simulation results low. Contents of the invention [0003] The purpose of the embodiments of the present applicatio...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M9/06
CPCG01M9/065
Inventor 袁军娅任翔凌桂龙贺碧蛟翁惠焱
Owner BEIHANG UNIV
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