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A kind of anti-short-circuit fault isolation device of launch vehicle tail section tb

A launch vehicle, fault isolation technology, used in transportation and packaging, aerospace vehicle docking devices, aerospace vehicles, etc.

Active Publication Date: 2021-06-11
BEIJING AEROSPACE AUTOMATIC CONTROL RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] These two measures have a certain isolation or protection effect on short-term high temperature and heat flow. However, for long-term flight missions, the above two measures cannot completely avoid the risk of short circuit of the control system power supply bus caused by TB heat flow

Method used

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  • A kind of anti-short-circuit fault isolation device of launch vehicle tail section tb
  • A kind of anti-short-circuit fault isolation device of launch vehicle tail section tb
  • A kind of anti-short-circuit fault isolation device of launch vehicle tail section tb

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Embodiment Construction

[0027] The application will be further described below in conjunction with the accompanying drawings. The following examples are only used to illustrate the technical solutions of the present invention more clearly, but not to limit the protection scope of the present application.

[0028] A TB anti-short-circuit fault isolation device at the tail section of a launch vehicle. An electrical sub-interface and an electrical sub-control interface are added to the cable of the rocket-ground separation and drop-off interface (abbreviated as TB). The breakaway interface (TB) cable is divided into two parts, the tail section of the rocket body and the system on the arrow, to achieve fault isolation.

[0029] Such as figure 1 As shown, the fault isolation device includes: a first electrical sub-interface (i.e. electrical sub-interface 1), a second electrical sub-interface (i.e. electrical sub-interface 2), a third electrical sub-interface (i.e. electrical sub-interface 3), a fourth el...

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Abstract

This application discloses a TB anti-short-circuit fault isolation device at the tail section of a carrier rocket. An electrical sub-interface and an electrical sub-control interface are added to the interface cable of the rocket-ground separation and drop-off interface. The interface cable is separated into two parts: the tail section of the rocket body and the system on the arrow. The fault isolation device includes: a first electrical sub-interface, a second electrical sub-interface, a third electrical sub-interface, a fourth electrical sub-interface, a signal transfer interface and an electrical sub-interface; The cable can be disconnected so as to be isolated from the rocket-on system, which completely solves the problem that the arrow-ground separation and fall-off interface cable is short-circuited due to the rocket tail environment when the interface protection cover fails due to the separation of the rocket and the ground.

Description

technical field [0001] The invention belongs to the field of launch vehicle control, in particular to a TB anti-short-circuit fault isolation device at the tail section of a launch vehicle. Background technique [0002] As the link between the rocket and the ground test, launch and control system, the TB is the only path to realize the data communication of the rocket-ground test, the power supply of the product on the rocket and the system test. Normality plays an extremely important role in the control system. Usually the TB cable is installed at the tail of the rocket core stage, and is equipped with a protective cover to prevent the ablation and short circuit of the TB cable from the engine exhaust flame during the rocket flight. Since the protective cover is a mechanical spring structure, its reliability is poor, and it is a single point. When the protective cover fails, the tail flame and the thermal environment of the tail will cause the TB cable to be ablated and sh...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/10B64G1/22B64G1/64
CPCB64G1/10B64G1/22B64G1/64
Inventor 杨岫婷苏磊张嗣锋权赫孙兆牛王雨萌李学锋田建宇
Owner BEIJING AEROSPACE AUTOMATIC CONTROL RES INST