A Synchronous Detonation Device for Hypersonic Vehicle Parts Separation Wind Tunnel Experiment

An aircraft component and hypersonic technology, applied in the direction of machine/structural component testing, measuring devices, instruments, etc., can solve the problems of detonation process monitoring, time synchronization, false detonation, etc., to avoid false detonation, reduce development costs and cycles Effect

Active Publication Date: 2019-01-04
广东空天科技研究院(南沙)
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Problems solved by technology

[0003] The purpose of the present invention is to provide a synchronous detonation device for the separation of hypersonic vehicle components in wind tunnel experiments, to solve the problems of synchronization between the detonation process and the effective experiment time of the wind tunnel, and the monitoring of the detonation process, and to avoid the strong electromagnetic interference of the wind tunnel auxiliary high-power equipment Induced false detonation problem, further improving the level of hypersonic wind tunnel component separation experiments

Method used

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  • A Synchronous Detonation Device for Hypersonic Vehicle Parts Separation Wind Tunnel Experiment
  • A Synchronous Detonation Device for Hypersonic Vehicle Parts Separation Wind Tunnel Experiment

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Embodiment 1

[0017] Example 1: see figure 1 , figure 2 , A synchronous detonation device for separating wind tunnel experiment of hypersonic vehicle components, including: synchronous trigger unit 1, detonation control unit 2, constant current unit 3;

[0018] The synchronization trigger unit 1 receives the chamber gas formation signal transmitted by the pressure sensor installed in the wind tunnel chamber, and determines the time delay amount of the synchronization trigger unit 1 according to the start time of the wind tunnel nozzle in the hypersonic vehicle component separation experiment, Then send a detonation start signal to the detonation control unit 2 to realize the detonation of the explosive bolt at the same time that the flow field of the hypersonic vehicle component separation experiment wind tunnel is established;

[0019] After the detonation control unit 2 receives the detonation signal sent by the synchronization trigger unit 1, it turns on the constant current unit 3, loads th...

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Abstract

The invention discloses a synchronous detonation device for a hypersonic aircraft component separation wind tunnel experiment. The synchronous detonation device comprises a synchronous trigger unit (1), a detonation control unit (2) and a constant current unit (3). The synchronous detonation device solves the problems of time synchronization of a detonation process and a wind tunnel effective experiment, monitoring of the detonation process and the like, avoids the problem of erroneous detonation induced by strong electromagnetic interference of wind tunnel aided high-power equipment, provides an experimental foundation for verifying the feasibility of an aircraft component separation scheme with a wind tunnel, allows the component separation verification scheme not to be limited to actual flight experiments, and reduces the aircraft research and manufacturing cost and cycle.

Description

Technical field [0001] The invention belongs to the technical field of wind tunnel experiments for high-speed aircraft, and particularly relates to a synchronous detonation device for separating wind tunnel experiments of hypersonic aircraft components. Background technique [0002] The separation of hypersonic aircraft components includes: the separation of the air inlet protective cover, the separation of the booster stage and the cruise stage, and the separation of the cabin wing, etc. The feasibility of its component separation scheme and the movement trajectory of the separated components are essential to the safety of the aircraft. The separation of hypersonic components is different from the separation of rocket fairings. Because the separation of rocket fairings has already rushed out of the atmosphere during separation, the numerical simulation and ground tests of the hood ejection process are relatively simple. In the hypersonic vehicle component separation experiment, ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01M9/04
CPCG01M9/04
Inventor 苑朝凯王春姜宗林
Owner 广东空天科技研究院(南沙)
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