Satellite-rocket separation transition buffering device

A technology of buffering devices and satellite-rocket separation, which is applied in the field of satellite system-level buffering, can solve the problems of not being able to meet the requirements of connection stiffness and increase transmission distance, and achieve the effect of increasing distance, increasing attenuation, and reducing impact environment

Active Publication Date: 2014-10-01
BEIJING INST OF SPACECRAFT SYST ENG
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  • Abstract
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  • Claims
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AI Technical Summary

Problems solved by technology

However, the way of increasing the transmission distance and adding flexible buffer pads cannot meet the requirements of satellite system-level buffer design and connection stiffness

Method used

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  • Satellite-rocket separation transition buffering device
  • Satellite-rocket separation transition buffering device
  • Satellite-rocket separation transition buffering device

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Embodiment Construction

[0019] The present invention will be described in detail below with reference to the accompanying drawings and examples.

[0020] The present invention provides a star-rocket separation transition buffer device, which is mainly used to buffer the strong impact force during the star-rocket separation process. The specific structure is as follows figure 1 As shown, the device includes an upper connection plate, a lower connection plate and a cross support frame.

[0021] Both the upper and lower connecting discs are discs with a thickness of 20 mm and a diameter of 180 mm. Among them, the upper connection plate is used to connect the satellite, and the lower connection plate is used to connect the launch vehicle; for example figure 1 As shown, 1 is the satellite joint, 2 is the transition buffer device provided by the present invention, and 3 is the launch vehicle joint, wherein the satellite joint can be connected with the device through bolts, and the launch vehicle needs to ...

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Abstract

The invention discloses a satellite-rocket separation transition buffering device, and belongs to the field of a satellite system-level buffering technique. According to the buffering device disclosed by the invention, a connecting interface of a traditional satellite and a carrier rocket is divided into a lower connecting disk, an upper connecting disk and a crossed support frame, wherein the lower connecting disk is connected with the carrier rocket, and an initiating explosive device mounting hole and a top pressure hole for a mandril of a separation spring are formed in the lower connecting disk; the upper connecting disk is connected with satellite contacts, and an initiating explosive device avoiding hole and six bolt connecting holes are formed in the upper connecting disk; a rigidity transition structure, i.e. the crossed support frame is additionally arranged between the lower connecting disk and the upper connecting disk, and one connecting disk is additionally arranged, so that the decrement of an impact load during satellite-rocket separation is increased; and at the same time, the rigidity transition structure is additionally arranged between the upper connecting disk and the lower connecting disk, so that the transferring distance of shock waves is increased, and an impact on the satellite is reduced. The buffering device disclosed by the invention can realize the satellite system-level buffering, and at the same time, can ensure that the rigidity of the whole satellite is basically unchanged, so that the design requirements of a satellite fundamental frequency are met.

Description

technical field [0001] The invention relates to the technical field of satellite system-level buffering, in particular to a satellite-rocket separation transition buffering device. Background technique [0002] The satellite-rocket separation shock is one of the harshest mechanical environments that a satellite needs to experience during launch. At the moment of separation of the satellite and the rocket, a large number of high-frequency impact loads will be generated at the moment of explosion of the pyrotechnics, which will produce high-frequency and high-level transient acceleration responses on the satellite structure. Generally, it can reach tens of thousands of g. The action time is several milliseconds, and the frequency band width reaches 100,000 or even millions of hertz. High-frequency impact loads usually do not cause damage to the results, but they can cause fatal damage to precision electronic equipment on spacecraft such as crystal oscillators and brittle mate...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/64
Inventor 丁继锋肖伟郝文宇王金刚王平柴智渊刘天雄陈忠贵刘晨朱剑涛武向军嵇景全朱位薛宏伟
Owner BEIJING INST OF SPACECRAFT SYST ENG
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