Star sensor sub-low temperature independent thermal control device of orbit transfer vehicle

Abstract

The invention provides a star sensor sub-low temperature independent thermal control device of an orbit transfer vehicle. The device comprises an imported star sensor A, a domestic star sensor B, thermistors (2), heaters (3), light shields (4), F46 films (5), an S781 white paint thermal control coating (6), mounting supports (7), a self support (8), heat insulation pads (8), a plurality of layers of heat insulation components (10) and thermal protection layers (11). Thermal resistance between stars and the star sensors is increased through the heat insulation pads, heat leakage compensation is greatly reduced, and a foundation is laid for independent temperature control over the star sensors. According to the sub-low temperature design requirement, the S781 white paint thermal control coating is adopted to increase the temperature adaptability of a star sensor motive track. The heat insulation components and the protection layers are adopted, and the radiation influence of a 25N engine on the imported star sensor A is effectively prevented. The device is convenient to implement, high in reliability and adaptability and small in total occupied resource, and the heat radiation of the engine can be effectively prevented.

Description

technical field [0001] The invention belongs to the field of thermal control design of spacecraft, and in particular relates to a low-temperature independent thermal design technology for a star sensor of an orbit transfer vehicle. Background technique [0002] The test target orbit of a certain type of aircraft needs to be able to adapt to the change of the descending node local time 6:30±30min and the orbit altitude of 500-800km. The aircraft needs to maneuver and change orbits many times in orbit. The large changes in orbital conditions lead to large changes in the heat flow conditions outside the aircraft, and the external stand-alone aircraft is exposed to complex conditions. Therefore, the thermal control design of the aircraft, especially the thermal environment of the external single aircraft, is required to have high adaptability. The aircraft uses two star sensors: imported star sensor A and domestic star sensor B. Installed in the fourth quadrant of the load-bear...

AI Technical Summary

Problems solved by technology

[0003] Usually, the satellites where the star sensors are installed are in sun-synchronous orbit, without attitude and yaw mode, and the external heat flow is stable. Covered with multi-layer heat insulation components, the head of the star sensor is pasted with a low-temperature compensation heater (10W per channel, taking up more resources)

At the same time, there is usually no engine installed near the satellite star sensor, so there is no need to consider the impact of engine radiation

However, due to the attitude yaw mode of the star sensor of the transfer orbiter, the external heat flow is unstable. If the measure of half-covering the general satellite is adopted, the change of the external heat flow and the internal power consumption of the star sensor will inevitably be affected by the yaw attitude. In addition, the independent heat dissipation surface of the star sensor is insufficient, which will cause the temperature of the star sensor to rise, approaching or even exceeding the upper limit of the temperature, resulting in safety hazards

Images