Actuating mechanism of spacecraft for integrating heat control and liquid momentum wheel

Abstract

The invention relates to an actuating mechanism of a spacecraft for integrating the heat control and a liquid momentum wheel, comprising a liquid storage device, a circulating pump assembly, a heat-dissipating public loop, a heating assembly, a heating public loop and an irradiator/momentum generator integration device, wherein the circulating pump assembly is used for driving liquid working substance to flow; the heat-dissipating public loop includes a first flow rate distribution valve, a first heat exchanging device and a first bypassing branch, wherein the first heat exchanging device is connected in parallel with the first bypassing branch; the heating assembly heats fluid working substance for heating the heat-dissipating public loop; the heating public loop includes a second flow rate distribution valve, a second heat exchanging device and a second bypassing branch, wherein the second heat exchanging device is connected in parallel with the second bypassing branch; the irradiator/momentum generator integration device comprises at least two different pipelines which are connected in parallel and a device which controls the distribution of the liquid momentum in the different pipelines, and are used for dispersing heat out of the spacecraft and providing large enough and changeable angular momentum; the heat-dissipating public loop, the heating public loop and the irradiator/momentum generator integration device are sequentially connected and then in series connected with the liquid storage device and the circulating pump assembly to form a working substance circulating loop, and the liquid working substance flows in the working medium circulating loop.

Description

technical field [0001] The present invention relates to spacecraft control, in particular to thermal control and attitude control of spacecraft. More specifically, the present invention provides a modular spacecraft thermal control system integrated with a liquid momentum wheel that can provide attitude control torque installation. Background technique [0002] The function of the spacecraft thermal control subsystem is to maintain the on-board equipment within a suitable temperature range in the space environment to ensure the normal operation of the on-board equipment. After decades of development, there have been a variety of mature and effective spacecraft thermal control technologies, which can be mainly divided into passive and active types: passive thermal control mainly relies on a reasonable overall layout of the spacecraft, and the selection of thermal materials, correctly organize the heat exchange process inside and outside the spacecraft, so that the equipment ...

AI Technical Summary

Problems solved by technology

[0012] The inventors of the present application thought of: (1) Utilizing a fluid circulation system driven by a mechanical pump to form a common circuit for spacecraft thermal control, and integrating a tube-sheet heat exchanger that can be tailored in size and heat dissipation capacity on the surface of equipment that requires temperature control , and connect the tube-sheet heat exchanger to the public circuit through the thermal switch/valve, modularize and generalize the thermal control system of the spacecraft, get rid of the dependence on the heat dissipation surface in the layout of the heating equipment, and realize the three-dimensional layout in the star, Then improve the integration of the spacecraft; (2) heat the heat collected by the fluid circuit to the equipment with little heat through the thermal control common circuit, and comprehensively utilize the heat of the spacecraft, which can not only reduce the temperature required for maintaining the temperature of low-temperature equipment The electric heating power can reduce the thermal load of the radiator, thereby reducing the weight of the radiator; (3) transfer the heat dissipated by the sub

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