A temperature-stable star sensor thermal design method

A star sensor and thermal design technology, applied in astronomical navigation and other directions, can solve the problems of large temperature coupling, poor thermal insulation, and large influence of optical lens radiation, so as to reduce temperature influence, high temperature stability, and improve thermal stability performance. Effect

Active Publication Date: 2021-04-13
BEIJING INST OF CONTROL ENG
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Problems solved by technology

[0013] The technical problem solved by the present invention is: to overcome the deficiencies of the prior art, to provide a thermal design method for the star sensor with stable temperature, and to solve the problem of large temperature coupling between the front section and the back section inside the star sensor hood, the hood assembly and the star sensor. The heat insulation between the sensor body structure is poor, the rear section of the hood and the circuit board components surrounding the optical lens have a greater impact on the radiation of the optical lens

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  • A temperature-stable star sensor thermal design method
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Embodiment Construction

[0034] The present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0035] A temperature-stabilized thermal design method for a star sensor, the method includes a thermal design method for a star sensor shading assembly and a thermal design method for an optical lens of the star sensor;

[0036] like figure 1 As shown, the star sensor includes a star sensor hood assembly 1, a star sensor body structure 2, and a support assembly 3 (4 sets);

[0037] like figure 2 As shown, the shading cover assembly includes a front section 4, a rear section 5, a thermal insulation pad 6 and a heating sheet 7;

[0038] The thermal design method for the star sensor shading assembly includes adding a heat insulation pad between the front section of the star sensor shading assembly and the rear section of the star sensor shading assembly, The surface mount heating sheet of the segment and the use of support components...

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Abstract

The invention relates to a temperature-stable star sensor thermal design method, in particular to a temperature-stable star sensor thermal design method, belonging to the technical field of spacecraft attitude control. A star sensor thermal design method with high temperature stability proposed by the present invention realizes a high temperature stability of the star sensor body, and the temperature of the star sensor body is between 19°C and 21°C in the sunny area and the shadow area Within the temperature range; the invention realizes the temperature decoupling between the star sensor hood assembly and the star sensor body structure, realizes a temperature difference of about 30°C between the front section and the rear section of the shading cover, and also realizes the connection between the rear section of the shading cover assembly and the star sensor body structure. The minimum temperature difference of about 15°C between the structure of the star sensor body greatly reduces the temperature influence of the star sensor shading assembly on the star sensor body.

Description

technical field [0001] The invention relates to a thermal design method of a star sensor with stable temperature, in particular to a thermal design method of a star sensor with highly stable temperature, belonging to the technical field of spacecraft attitude control, and the temperature stability refers to the temperature of the star sensor 19-21°C. Background technique [0002] The star sensor is an important part of the high-precision attitude and orbit control of the spacecraft, and its attitude measurement accuracy and reliability play a vital role in the attitude control of the spacecraft. The star sensor takes the star as the measurement target, images the star on the image detector through the optical system, and sends the output signal to the data processing unit through A / D conversion, and determines the optical axis vector of the star sensor through star point extraction and star map identification The orientation in the inertial coordinate system is determined b...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01C21/02
CPCG01C21/02
Inventor 余成武刘婧武延鹏谌颖隋杰陈建峰钟红军王龙孙鹏孙建波孙艳洪帅吕文华戴舒颖杜伟
Owner BEIJING INST OF CONTROL ENG
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