Spacecraft thermal control system directly utilizing sunlight

Abstract

The invention discloses a spacecraft thermal control system directly utilizing sunlight, which comprises a sunlight buncher, a sunlight branching device, a light-guide fiber, a heating unit and a space radiant cooling device. The spacecraft thermal control system directly converges sunlight on the sunward side of spacecraft to be served as thermal control energy of the spacecraft, utilizes light energy produced by converged sunlight to heat a spacecraft light heating device or a single machine, simultaneously reduces the increased temperature caused by sun radiation on the sunward side, solves the problem of low power consumption space thermal control, reduces the thermal control electric power of the spacecraft, also reduces corresponding solar battery array area and accumulator capacity, improves the energy utilization of sunlight, and reduces the design difficulty of spacecraft thermal control and energy equal division systems. The spacecraft thermal control system solves the technical difficulty of thermal control required by navigation of the spacecraft in the solar system, and has certain effects on improving the thermal control efficiency of the spacecraft and the space exploration range, and reducing the resource cost for navigation.

Description

technical field [0001] The invention relates to the technical field of thermal control of space flight spacecraft, in particular to a thermal control system of a spacecraft that directly utilizes sunlight. Background technique [0002] At present, with the increasing diversification of spaceborne equipment inside the spacecraft and the increasing complexity of the working mode, factors such as the uncertainty of the space mission environment have brought new challenges to the design of the spacecraft thermal control system. [0003] Due to the constraints on the mass, volume and power consumption of the spacecraft structure, it brings two main problems to its thermal control design: one is local high heat flux density, and the other is low thermal inertia. [0004] First of all, with the integration of electronic chips and the continuous improvement of packaging level, the size of some MEMS devices has entered the sub-micron level from the micron level, and since 1959, the i...

AI Technical Summary

Problems solved by technology

Therefore, when the satellite enters the shadow of the earth's orbit, the temperature fluctuation of the satellite's skin will increase, coupled with the change of the thermal power consumption of the instrument and equipment itself, the temperature of the instrument and equipment in the satellite will increase, and even exceed its normal operating temperature range

Images