Method for separating satellite and rocket separation electric connector by redundancy backup

A technology for separating electrical connectors and star arrows, which is applied in the direction of offensive equipment, weapon types, projectiles, etc., can solve the problems that the star arrows cannot be disconnected normally, and achieve short action time, simple separation methods, and easy installation Effect

Active Publication Date: 2011-03-30
AEROSPACE DONGFANGHONG SATELLITE
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

If there is an abnormal situation, the normal fall-off of the star arrow cannot be guaranteed.

Method used

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  • Method for separating satellite and rocket separation electric connector by redundancy backup
  • Method for separating satellite and rocket separation electric connector by redundancy backup
  • Method for separating satellite and rocket separation electric connector by redundancy backup

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Embodiment Construction

[0018] like figure 1 Shown is the flowchart of the method of the present invention. First, connect the micro-satellite body to the docking bracket through the strap and the explosive bolt assembly. After the connection is completed, use the aramid rope to connect the detachment with the support at the bottom through the operation port on the side of the bracket. After the connection is completed, plug it The operation port, the satellite and the bracket are integrated and docked with the launch vehicle. After the carrier is launched, 1.2s before the separation of the star and arrow, the detachment is automatically separated from the micro-satellite body by issuing an electric detachment command. The two redundant backup methods realize the reliable separation of de-plugging and micro-satellites.

[0019] like figure 2 As shown, is a schematic diagram of a microsatellite and its docking bracket. In the figure, 1 is the body of the microsatellite, 2 is the docking bracket be...

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PUM

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Abstract

The invention discloses a method for separating a satellite and rocket separation electric connector by redundancy backup, which realizes the reliable separation of the separation electric connector from a satellite in a redundancy backup mode and uses an electric separation command as a main separation mode and aramid rope forced separation as a backup separation mode. After the launching of a carrier rocket, the separation electric connector separates from a micro satellite according to an electric signal when receiving an electric connector separation command from the ground; 1.2 seconds later, a carried blasting bolt is unlocked, a separation spring of a connecting bracket base ejects the micro satellite out of the carrier rocket and the connecting bracket stays on the carrier rocket;and if the separation electric connector does not separate successfully, the separation spring of the connecting bracket base ejects the micro satellite out in the flight direction and, at the same time, the loose aramid rope is tightened to pull the separation electric connector out in a direction opposite to the flight direction to separate the separation electric connector. The method of the invention has the characteristics of high reliability, short action time and simplicity and convenience for operation.

Description

technical field [0001] The invention relates to a method for separating an electrical connector when a star and arrow are separated. Background technique [0002] Microsatellites generally refer to satellites weighing less than 100 kilograms. Considering factors such as launch costs, microsatellites generally adopt the method of piggyback launch. When the satellite is docked and installed with the launch vehicle, the micro-satellite is generally installed inside the bracket of the main star, so the micro-satellite needs to be installed first, and then the docking between the main star and the launch vehicle is completed. [0003] The satellite-rocket separation electrical connector (also known as detachment) is an interface for ground testing of micro-satellites at the launch site. When the satellite enters orbit, this electrical connector must be separated from the satellite. Since the microsatellite is in the middle of the launch vehicle and has a large span from the end...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F42B15/36
Inventor 包锦忠冷允激常新亚张晓敏罗鹰
Owner AEROSPACE DONGFANGHONG SATELLITE
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