Synchronous detonation device for hypersonic aircraft component separation wind tunnel experiment

An aircraft component, hypersonic technology, which is applied in the testing, measuring devices, instruments, etc. of machine/structural components, can solve the problems of detonation process monitoring, time synchronization, false initiation, etc., so as to avoid false initiation and reduce development cost and cycle. Effect

Active Publication Date: 2017-05-24
INST OF MECHANICS - CHINESE ACAD OF SCI
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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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  • Synchronous detonation device for hypersonic aircraft component separation wind tunnel experiment
  • Synchronous detonation device for hypersonic aircraft component separation wind tunnel experiment

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Embodiment 1

[0017] Embodiment 1: see figure 1 , figure 2 , a hypersonic vehicle component separation wind tunnel experiment synchronous detonation device, comprising: synchronous trigger unit 1, detonation control unit 2, constant current unit 3;

[0018] The synchronous triggering unit 1 receives the resident gas formation signal sent by the pressure sensor installed in the wind tunnel resident room, and determines the time delay of the synchronous triggering unit 1 according to the start time of the wind tunnel nozzle of the hypersonic vehicle component separation experiment, Then send a detonation start signal to the detonation control unit 2, so that the detonation bolts are detonated while 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 synchronous trigger unit 1, it connects the constant current unit 3, and loads the detonation current to bot...

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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 high-speed aircraft wind tunnel experiments, and in particular relates to a synchronous detonation device for hypersonic aircraft component separation wind tunnel experiments. Background technique [0002] The separation of hypersonic aircraft components includes: the separation of the inlet protective cover, the separation of the booster stage and the cruise stage, and the separation of the cabin wing. The separation of hypersonic components is different from the separation of rocket fairings. Since the separation of rocket fairings has already rushed out of the atmosphere during separation, the numerical simulation and ground test of the ejection process are relatively simple. In the separation experiment of hypersonic aircraft components, due to the aerodynamic force, it is difficult to predict the trajectory of the separated components numerically, and the cost of the actual flight test is too high. C...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M9/04
CPCG01M9/04
Inventor 苑朝凯王春姜宗林
Owner INST OF MECHANICS - CHINESE ACAD OF SCI
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