Quick release method and device for space vehicle power system external control equipment

Abstract

The invention discloses a quick detaching method and device for outboard control equipment used for a power system of a spacecraft. The device comprises a fixed bracket, a connecting structure, a mounting plate, locking pins and an equipment shell. The equipment shell is a shell of the outboard control equipment and is positioned on the mounting plate. The connecting structure comprises a concave connecting structure and a convex connecting structure, which are respectively arranged outside the two side walls of the equipment shell. The fixed bracket comprises a convex fixed bracket and a concave fixed bracket, which are arranged on the mounting plate and respectively fixed together with the two side walls of the equipment shell. The locking pins are respectively arranged on the concave connecting structure and the concave fixed bracket. The invention further provides a method for quickly detaching the outboard control equipment used for the power system of the spacecraft. The quick detaching method and device for the outboard control equipment used for the power system of the spacecraft, disclosed by the invention, is anti-floatation, accessible, visible and the like and has the advantages of simple operation, safe and fast replacement, high reliability, high universality, simple structure and the like.

Description

technical field [0001] The present invention relates to a method and device for power supply control equipment of a space power supply system, in particular to a quick release method and device for an external control equipment of a space vehicle power supply system. Background technique [0002] With the continuous development of my country's space manned aircraft application technology, the functional requirements of future manned spacecraft will become more and more powerful, the mission requirements will become more and more complex, and the life requirements will be longer and longer. The life cycle of the internal power system control equipment And high reliability and other aspects put forward higher requirements. Since the manned spacecraft is limited by many factors such as launch weight, overall layout, and final assembly, it cannot rely on the use of a large number of redundant designs to improve the reliability of the equipment. Therefore, in order to ensure the ...

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Problems solved by technology

[0004] The purpose of the present invention is to provide a method and device for the maintainability design of spacecraft power control equipment, which can solve the problem of astronauts wearing space suits in the harsh space environment outside the aircraft, and relying on limited maintenance within the specified maintenance time. Under the condition of limited maintenance resources, the problem of quick disassembly and replacement of the external control equipment of the spacecraft power system

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