Journal of Jilin University(Engineering and Technology Edition) ›› 2019, Vol. 49 ›› Issue (3): 972-978.doi: 10.13229/j.cnki.jdxbgxb20180072

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Layout design method of star sensor based on particle swarm optimization algorithm

Kai XU1(),Zhi⁃gang CHEN1(),Jing⁃hua ZHAO2,3,Lu DAI1,Feng LI1   

  1. 1. Attitude and Orbital Control Laboratory, Chang Guang Satellite Technology Co. , Ltd. , Changchun 130000, China
    2. College of Computer, Jilin Normal University, Siping 136000, China
    3. State Key Laboratory of Automotive Simulation and Control,Jilin University, Changchun 130022, China
  • Received:2018-01-18 Online:2019-05-01 Published:2019-07-12
  • Contact: Zhi?gang CHEN E-mail:xukai118@126.com;asir0422@163.com

Abstract:

In order to effectively solve the star sensor layout problem with higher efficient, the particle swarm optimization algorithm is applied. Firstly, the spherical projection method is utilized to select the points which can effectively avoid the ground light as the particle population. Secondly, the error from angle between the star sensor optical vector and the sun vector to the sun exclusion angle of the star sensor is selected as population evaluation function, and the best layout of the star sensor is found through the particle swarm searching of the global optimal solution. The effectiveness of star sensor layout scheme selected by the proposed method in this paper is proved by the experiments.

Key words: aerospace system engineering, satellite, star sensor layout, space spherical projection, particle swarm optimization

CLC Number: 

  • V44

Fig.1

Flow diagram of PSO"

Fig.2

Schematic diagram of angle relation between geo?optic edge vector and earth vector"

Fig.3

Projection of the ground light vector"

Fig.4

Effective area for star sensor excludeing ground gas light"

Fig.5

Layout of the star sensors on XX01 satellite"

Table 1

Case 1 star sensor validation for left maneuver"

机动

角度

左摆20°
前摆20° 前摆10° 后摆10° 后摆20°
与地球矢量夹角 110.1° 109.1° 104.0° 100.0°
与太阳矢量夹角 75°~122° 73°~124° 69°~123° 67°~128°
有效性

全年全纬

度有效

全年全纬度有效 全年全纬度有效

全年全纬

度有效

Table 2

Case 1 star sensor validation for right maneuver"

机动

角度

右摆20°
前摆20° 前摆10° 后摆10° 后摆20°
与地球矢量夹角 150.0° 148.1° 139.8° 134.2°
与太阳矢量夹角 35°~159° 35°~160° 36°~160° 38°~156°
有效性 全年全纬度有效

全年全纬

度有效

全年全纬

度有效

全年全纬

度有效

Fig.6

Layout of the star sensors on XX02 satellite"

Table 3

Case 2 star sensor validation for left maneuver"

机动角度 左摆25°
前摆24° 前摆10° 后摆10° 后摆24°
与地球矢量夹角 116.4° 114.3° 107.1° 99.8°
与太阳矢量夹角 87°~151° 86°~153° 79°~158° 74°~164°
有效性 全年全纬度有效

全年全纬

度有效

全年全纬

度有效

全年全纬

度有效

Table 4

Case 2 star sensor validation for right maneuver"

机动角度 右摆25°
前摆24° 前摆10° 后摆10° 后摆24°
与地球矢量夹角 166.1° 159.4° 145.0° 134.1°
与太阳矢量夹角 37°~169° 38°~171° 41°~173° 45°~178°
有效性 全年全纬度有效 全年全纬度有效 全年全纬度有效 全年全纬度有效
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