High-adaptability temperature control device of loop heat pipes

Abstract

The invention discloses a high-adaptability temperature control device of loop heat pipes. The high-adaptability temperature control device comprises an evaporator, a plurality of four-way reversing valves and a plurality of radiators which are connected with one another by the loop heat pipes to form a loop. The high-adaptability temperature control device is characterized in that two or more than two radiators are designed, and by utilization of the reversing function of the four-way reversing valve, when the heat loss of the early stage of in-orbit operation of a spacecraft is lower, a small amount of radiators are applied to dissipate heat of the spacecraft. When the heat loss of the early stage of in-orbit operation of a spacecraft is larger, all the radiators are applied to dissipate heat of the spacecraft. The high-adaptability temperature control device disclosed by the invention has the advantages that by utilization of the reversing function of the four-way reversing valve, when external heat flow or heat loss of the spacecraft is changed, the radiant heat-dissipating area of the radiators is adjusted; the applicability of the loop heat pipes is improved, the precious electric energy on the spacecraft is saved, the blocking times of the loop heat pipes are reduced and the life of in-orbit operation of the loop heat pipes is prolonged.

Description

technical field [0001] The invention relates to a heat dissipation device in the technical field of spacecraft thermal control, in particular to a highly adaptable loop heat pipe temperature control device. Background technique [0002] The thermal condition of a spacecraft refers to the conditions of the spacecraft's internal and external heating and heat dissipation during orbital operation. A spacecraft will experience various thermal conditions during orbital operation. The main reasons include: the direction and position of the spacecraft relative to the space thermal environment are constantly changing; the attitude of the spacecraft is changing; the heating of the internal heat source of the spacecraft is constantly changing; the uncertainty of the launch date and orbiting time of the spacecraft ; Increased external heat flow caused by degradation of thermal control coatings, etc. [0003] From the perspective of safety and reliability, thermal design usually select...

AI Technical Summary

Problems solved by technology

A lot of valuable electrical energy on the spacecraft is wasted by heating the heater

Images