A docking and locking interface device capable of active heat conduction for space vehicles

Abstract

The invention discloses a docking and locking interface device capable of active heat conduction for a space vehicle, comprising: an active end and a passive end; the active end includes: a six-degree-of-freedom floating liquid circuit breaker movable end and a cold plate pipeline assembly; The plate pipeline assembly includes: cold plate, hose, cold plate joint A and cold plate joint B; the passive end also includes: the fixed end of the six-degree-of-freedom floating breaker; the multi-function pin includes: height limit part, tightening part , the locking part; the height limiting part is a straight pin with a set length; the tightening part is an inclined plane located at the front end of the multifunctional pin; the locking part is located at the rear end of the height limiting part on the multifunctional pin, and It is higher than the height limit part; a guide hole is processed on the shell, one side of the guide hole is composed of a slope part and a plane part, and there is a square hole at the bottom of the guide hole; it can realize the guidance and positioning of the exposed load and the exposed platform outside the aircraft cabin. , Active tightening, automatic plugging and unplugging of six-degree-of-freedom floating liquid circuit breaker and active heat conduction.

Description

technical field [0001] The invention relates to the field of space application equipment, in particular to a docking and locking interface device for a space vehicle that can actively conduct heat. Background technique [0002] Space vehicles such as space stations and manned spacecraft have arranged a large number of exposure load test platforms on the outer wall of the cabin to expand the exposure test capabilities of space vehicles. At present, the International Space Station has used various forms of payload docking and locking interface devices to support exposure experiment tasks. [0003] However, for the exposed load outside the cabin and the exposed platform outside the cabin, the docking and locking interface device in the prior art cannot automatically capture the exposed load outside the cabin, the degree of automation is not high, the operation ability of the astronaut or the mechanical arm is high, and the mechanism is complicated. Poor maintainability, low re...

AI Technical Summary

Problems solved by technology

[0003] However, for the exposed load outside the cabin and the exposed platform outside the cabin, the docking and locking interface device in the prior art cannot automatically capture the exposed load outside the cabin, the degree of automation is not high, the operation ability of the astronaut or the mechanical arm is high, and the mechanism is complicated. Poor maintainability, low reliability, poor thermal conductivity

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