A fluid circuit system suitable for multi-cabin spacecraft

Abstract

The invention discloses a fluid loop system suitable for a multi-cabin spacecraft, and belongs to the technical field of multi-cabin spacecrafts. The fluid loop system comprises cold plates, fluid pipelines, a radiator, four liquid path detachable connectors and a separation device. The two cold plates are installed between an in-cabin device and the upper surface of an instrument plate as well as between an in-cabin device and the lower surface of the instrument plate correspondingly, and annular holes of the two cold plates communicate through the pipelines. The radiator is fixed to the outer surface of a sealed cabin. The liquid path detachable connector I and the liquid path detachable connector II are installed at the butt-joint position of a braking cabin and a service cabin through the separation device. The liquid path detachable connector III and the liquid path detachable connector IV are installed at the butt-joint position of a recovery cabin and the braking cabin. One ends of the two fluid pipelines are connected with the annular holes of the cold plates correspondingly, and the other ends of the fluid pipelines pass through the liquid path detachable connector III or the liquid path detachable connector IV, and the liquid path detachable connector I or the liquid path detachable connector II in sequence, then penetrate through the shell body of the service cabin and are connected with the tubular structure of the radiator. According to the fluid loop system suitable for the multi-cabin spacecraft, the gesture of a returning cabin is not influenced through layout of the fluid pipelines and connection design between the cabins.

Description

technical field [0001] The invention belongs to the technical field of multi-cabin spacecraft, and in particular relates to a fluid circuit system suitable for multi-cabin spacecraft. Background technique [0002] The returnable satellite has become a satellite platform dedicated to the space experiment research of "microgravity science and space life science". With the increase in the demand for space science experiments, the number of experimental load equipment in the returnable satellite recovery cabin is also increasing, and the average power consumption is also higher than before. Temperature requirements are also more stringent. The traditional means of cooling the recovery cabin can no longer meet the load requirements. [0003] In order to meet the demand of high power consumption of the recovery cabin load, the active thermal control technology of the fluid circuit is applied, that is, a cold plate is installed inside the recovery cabin to collect the heat consum...

AI Technical Summary

Problems solved by technology

[0005] 1. If the fluid circuit pipeline is to be connected across the cabin, the pipeline connection must have a disconnector that can be assembled or separated with the cabin. Therefore, the installation of the disconnector should be considered when the cabin is docked and separated. For problems such as connection and separation, corresponding installation interfaces and operation ports must be provided structurally to increase the responsibility of structural design;

[0006] 2. It is necessary to consider how to realize the separation of the breaker between the pipeline cabins when the on-orbit cabin section is separated, and after the separation, the working medium in the pipeline cannot leak to the space and other cabins, which is the classification of the breaker Higher requirements are put forward, and the traditional tape separation method cannot be realized;

[0007] 3. If the compartment breaker adopts the passive separation method, the external force required for the breaker’s own separation must be considered, that is, the separation force acting on the breaker should be greater than the insertion and withdrawal force of the breaker itself, which means Higher requirements are put forward for the separation of cabins. It is necessary to increase the force when the cabin is separated to drive the breaker to separate, and the force is relatively large, which often requires a large price or technical difficulties.

[0008] When the satellite is running at high speed and the compartment separation force is large, the attitude of the satellite may change. The solution is to make the breaker separation force act on the center of mass of the satellite, which is often difficult to achieve in terms of layout. The traditional method It is a symmetrical distribution of disconnectors. Due to the difference in plugging force when the disconnectors are separated, the separation is not synchronized, etc., this method cannot eliminate the influence on the satellite attitude. It can only be reduced as much as possible, and other means are used to reverting to changed attitudes, resulting in the need for additional analysis and other safeguards in the design

In addition, when the installation of the breaker on the star cannot achieve a symmetrical arrangement, the impact on the attitude will be more serious

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