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A peak correction method for near-field test of spacecraft pyroshock source function

A pyrotechnic shock and spacecraft technology, which is applied in the fields of instruments, electrical digital data processing, special data processing applications, etc., can solve problems such as the indeterminacy of shock loads

Active Publication Date: 2018-05-04
BEIJING INST OF SPACECRAFT SYST ENG +1
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Problems solved by technology

[0004] In view of this, the purpose of the present invention is to provide a method for correcting the peak value of the near-field test of the pyrotechnic impact source function of a spacecraft, and correct the source force function obtained by direct modeling and solving with Hydrocodes, so as to further solve the problem of pyrotechnics of the spacecraft. Unable to determine the impact load in the environment prediction of impact mechanics

Method used

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  • A peak correction method for near-field test of spacecraft pyroshock source function
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  • A peak correction method for near-field test of spacecraft pyroshock source function

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Embodiment 1

[0076] Taking a typical point-type satellite-rocket separation structure as an example, the implementation of the single-frequency point correction method for the near-field test of the spacecraft pyroshock source function is described.

[0077] (1) Proximity field test of star-rocket pair

[0078] This test uses a set of satellite-rocket joints (including a satellite joint 4 and a carrier support joint 5), and a scaled model of a counterweight 3 with 1 / 4 satellite mass is added to carry out the test. The installation of the star-arrow joint adopts the same installation state as the actual star-arrow joint. One side of the satellite joint 4 is connected with the counterweight 3 of 1 / 4 satellite quality, and is suspended on the crane 1 by suspension rings and ropes (such as image 3 ). At the same time, the measuring points are arranged on the side of the satellite joint 4, such as image 3 shown. The A2 measurement point data in the test results are compared with the calcu...

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Abstract

The invention discloses a method for correcting the near field test peak value of an explosive impulse source function of a spacecraft. By means of the method, details of explosion of an explosive in an initiating explosive device, fracture of the initiating explosive device and transmission of explosion stress waves can be simulated, the coupling effect structurally caused by explosion of the initiating explosive device can be well treated, thereby characteristics of a vibration source are analyzed, effective extraction is conducted on the force function of the vibration source, and theoretically, the method is a reasonable way for obtaining the function of the explosive impulse vibration source; in addition, the force function of the vibration source at the explosive impulse separation surface is corrected through Hydrocodes solution, the corrected vibration source force function can be decoupled and loaded to a whole-spacecraft finite element model containing a near field model or an analysis model obtained through other methods, and the foundation is laid for solving the problems of response and prediction of explosive impulse of the spacecraft from the engineering angle.

Description

technical field [0001] The invention belongs to the technical field of spacecraft dynamic shock response prediction, and in particular relates to a method for correcting the peak value of a near-field test of a spacecraft pyrotechnic shock source function. Background technique [0002] The spacecraft pyrotechnic shock environment refers to the response of the shock load generated by the pyrotechnic detonation on the spacecraft to the main load-bearing structure, which constitutes the shock mechanics environment of the spaceborne equipment. The impact mechanical environment of spacecraft pyrotechnics is one of the harshest mechanical environments experienced during spacecraft launch and on-orbit work. The material stress wave and structural resonance response caused by the explosion of pyrotechnics can affect the impact of instruments and equipment containing sensitive components. Cause fatal damage, resulting in the failure of the space mission. [0003] Quantitative descri...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F17/50
CPCG06F30/23G06F30/367
Inventor 赵欣韩增尧邹元杰丁继锋郑世贵
Owner BEIJING INST OF SPACECRAFT SYST ENG
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