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Design method for layout optimization of spacecraft multi-star sensor

A technology of star sensor and design method, which is applied in the direction of instrumentation, calculation, and electrical digital data processing, etc., can solve the problems of designers' experience dependence and long design links, etc., to solve the problem of excessive dependence on experience, improve design efficiency, and improve multiple The effect of star sensitivity measurement accuracy

Active Publication Date: 2018-10-19
BEIJING INST OF SPACECRAFT SYST ENG
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Problems solved by technology

[0004] Problem solved by the technology of the present invention: the present invention proposes a layout optimization design method for multi-satellite sensors of spacecraft, which describes the layout problem of multi-satellite sensors of spacecraft as a standard optimization problem, thereby obtaining the optimal design method of multi-satellite sensors through quantitative calculation. Optimal layout scheme to solve the problem of traditional star sensor layout relying too much on designer experience and long design links

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  • Design method for layout optimization of spacecraft multi-star sensor
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Embodiment Construction

[0047] The present invention will be further described below in conjunction with the accompanying drawings. The whole process is as follows Image 6 As shown,

[0048] 1. Sunlight constraint

[0049] The satellite body coordinate system and the geocentric first equatorial coordinate system are as figure 1 As shown,

[0050] Where Ω represents the right ascension of the ascending node of the satellite orbit, i represents the inclination of the satellite orbit, and u represents the position of the satellite on the orbit.

[0051] The conversion relationship from the first equatorial coordinate system of the earth to the satellite body coordinate system is as follows:

[0052]

[0053] The coordinates of the solar unit vector in the geocentric first coordinate system are

[0054] x 1s =cosδ s cosα s

[0055] y 1s =cosδ s sinα s

[0056] z 1s =sinδ s

[0057] Where δ s Represents the solar declination, α s Represents the sun's right ascension.

[0058] The coordinates of the solar unit vector i...

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Abstract

The invention discloses a design method for the layout optimization of a spacecraft multi-star sensor. The method comprises the steps of: (1) determining the change range of declination and right ascension of a direct shone point of sunlight, which is caused by the revolution and the rotation of earth, defining a star-sensitive optical axis vector and establishing a sunlight constraint expression;(2) analyzing the relative position relationship between an elliptical orbit of a satellite and the earth, determining the included angle between the optical axis direction of a star sensor and a satellite-ground connection line when the satellite moves to a perigee and establishing an earth atmosphere light constraint expression; (3) describing rays starting from the star sensor, which are inside a star sensor sunshade, by using a cone set, describing cube parts and cylinder parts in the satellite in the form of sets and describing that the rays within the cone range of the star sensor sunshade are not shielded through an analytic expression; and (4) constructing an index function for optimizing the layout of a multi-star sensor, obtaining the optimal orientation of the multi-star sensorand determining the optimal layout of the multi-star sensor.

Description

Technical field [0001] The invention relates to a spacecraft multi-satellite sensor layout optimization design method, which belongs to the field of satellite overall design. Background technique [0002] As the most important satellite attitude determination device, the star sensor is an important part of the overall design of the satellite structure. With the rapid development of satellite technology, the orbits, platforms, and tasks of satellites are becoming more and more diversified. There are more and more newly developed satellites in different orbits and different platforms. Large components such as solar wings, antennas, and cameras are also installed on the satellites. More and more, the layout constraints of satellite sensors are becoming more and more complicated. [0003] The traditional layout process is for the configuration designer to rely on experience to give the layout angle and simple field of view analysis. The orbit and attitude control designer simulates it...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/00
Inventor 余快吴蓓蓓刘凤晶刘云鹤李果王成伦张胜祖家国赵华
Owner BEIJING INST OF SPACECRAFT SYST ENG
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