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Radiation capsule for star sensor

A technology of star sensor and small cabin, applied in the field of small radiation cabin, can solve the problems of difficult implementation and complicated thermal control design of star sensor, and achieve the effect of low implementation difficulty, easy guarantee of thermal control effect, and simple design.

Active Publication Date: 2013-09-18
BEIJING INST OF SPACECRAFT SYST ENG
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AI Technical Summary

Problems solved by technology

[0005] In view of this, the present invention provides a radiation cabin for star sensors, which can solve the problems of complex thermal control design and difficult implementation of star sensors

Method used

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  • Radiation capsule for star sensor

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Embodiment Construction

[0024] The present invention will be described in detail below with reference to the accompanying drawings and examples.

[0025] The present invention provides a radiation cabin for star sensors, comprising a cabin body 1, an optical secondary surface mirror, a heater and a multilayer heat insulation assembly 2, such as figure 1 As shown, the peripheral device is a star sensor 3, and the star sensor 3 includes a light shield 4 and a star sensor head 5, wherein:

[0026] Such as figure 2 As shown, the small cabin body 1 made of aluminum alloy with good thermal conductivity has a polyhedral cavity structure, and is covered outside the star sensor 3. On the one hand, it is used to block the external heat flow and reduce the heat generated by the external heat flow on the star sensor 3. Radiation, on the one hand, is used as the heat sink of the star sensor 3, and releases the radiation heat dissipation of the star sensor 3 to the cold space; on the small cabin body 1, there is...

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Abstract

The invention discloses a radiation capsule for a star sensor, and belongs to the technical field of thermal control design of star sensors. The radiation capsule comprises a capsule body, an optical solar reflector, a heater and a multi-layer thermal insulation component, wherein peripheral equipment is the star sensor; the star sensor comprises a light shield and a star sensing head; the radiating problem of the star sensor is solved through adopting the radiation heat exchange manner between the radiation capsule and the star sensor; heat conducting components such as a hot pipe are not required, so that the radiation capsule is simple and reliable in design; as the radiation capsule is adopted, the mismatching connection between the star sensor and a thermal control part is not caused; the requirement on the processing and mounting precision of the capsule is not high, the implementation difficulty is low, and the thermal control effect is easy to ensure; the optical solar reflector is stuck on the outer surface of the capsule body to enhance the radiation heat exchange with the cold space; coating with high infrared hemispherical emissivity is sprayed on the inner surface to enhance the radiation heat exchange with the star sensor; and the multi-layer thermal insulation component is arranged on an opening to prevent external heat flow from irradiating in the capsule body.

Description

technical field [0001] The invention relates to a radiation cabin for a star sensor, and belongs to the technical field of star sensor thermal control design. Background technique [0002] The star sensor is a high-precision spacecraft attitude measurement device, and its working reliability plays a vital role in the attitude control of the spacecraft. The measurement accuracy of the star sensor optical system is more sensitive to temperature. Therefore, in order to ensure the measurement accuracy of the star sensor optical system, it is necessary to design its thermal control according to its temperature control requirements to ensure that its operating temperature is within a certain range. [0003] At present, the thermal control design for star sensors generally adopts the "heat radiator + heat pipe" scheme, that is, the carbon fiber aluminum honeycomb panel with optical secondary surface mirror attached to the surface is used as the heat radiator, and the star sensor an...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/52G01C21/02
Inventor 韩崇巍赵剑锋赵啓伟
Owner BEIJING INST OF SPACECRAFT SYST ENG
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