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Spacecraft multi-star sensor layout optimization method

A star sensor and optimization method technology, applied in the direction of instruments, astronomical navigation, satellite radio beacon positioning system, etc., can solve the problem of sunlight entering the field of view of a certain star sensor, improve design efficiency and avoid manual iteration , Optimize the model for reasonable and perfect results

Pending Publication Date: 2022-06-03
INNOVATION ACAD FOR MICROSATELLITES OF CAS +1
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Problems solved by technology

Patent CN 108681617 A first establishes the constraints on the layout of star sensors by sunlight, earth-atmospheric light, and other components on the satellite, and then takes the angle between the optical axes of the star sensors as the optimization target, and describes the multi-star sensor layout design as It is a standard optimization problem, and the corresponding optimization algorithm is used to solve it. However, when the solar angle of the satellite orbit varies widely, it is bound to appear that sunlight enters the field of view of a certain star sensor. Therefore, all star sensors should avoid the sun. As a constraint condition, the optimization model does not have a feasible solution, so it is necessary to improve the optimization model

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  • Spacecraft multi-star sensor layout optimization method
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  • Spacecraft multi-star sensor layout optimization method

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Embodiment Construction

[0026] Taking three star sensors as examples below, the present invention will be further described in conjunction with the accompanying drawings. The whole process is as follows: image 3 shown.

[0027] Step 1. Determine that the life of the satellite is 5 years, the initial orbit parameters are shown in Table 1, and the task attitude is the orientation attitude toward the ground.

[0028] Table 1

[0029]

[0030]

[0031] Step 2. Determine the half cone angle θ of the hood of the star sensor z =20°.

[0032] Step 3. Establish the constraint expressions of sunlight and air light when the star sensor is available.

[0033] When the star sensor is available, the star sensor optical axis vector Vector with sun light position Constraints should be met where θ z is the half cone angle of the hood.

[0034] When the star sensor is available, the star sensor optical axis vector with geocentric vector Constraints should be met where θ e is the half-cone angl...

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Abstract

The invention discloses a spacecraft multi-star sensor layout optimization method, which comprises the following steps of: constructing a multi-target optimization model with the maximum availability rate of double star sensors and an approximately orthogonal included angle between the star sensors, solving by utilizing a multi-target genetic algorithm, obtaining the optimal direction of each star sensor, and determining the optimal layout of the multi-star sensors. According to the method, the dependence on the experience of a designer is reduced, the defect that manual iteration is needed in a traditional method is overcome, and the design efficiency of the star sensor layout is improved.

Description

technical field [0001] The invention belongs to the field of overall design of spacecraft, and relates to a method for optimizing the layout of a spacecraft multi-star sensor. Background technique [0002] Among the commonly used attitude sensors, the measurement accuracy of the star sensor can reach the arcsecond level, so it has become an important attitude measurement device for satellites. The star sensor determines the attitude of the satellite by sensitive star light. Since the star light is weak light, it is easily affected by external stray light. , the measurement accuracy of the star sensor decreases or even fails. In addition, when the measurement information of multiple star sensors is used for joint attitude determination, the closer the angle of the optical axis of each star sensor is to the orthogonal, the higher the attitude determination accuracy. Therefore, in order to ensure the on-orbit availability of the star sensor and improve the accuracy of satelli...

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Application Information

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IPC IPC(8): G01C21/02G01S19/42G01S19/25
CPCG01C21/02G01S19/42G01S19/258Y02T10/40
Inventor 本立言谢祥华严玲玲邱琳刘剑祁海铭赵璟
Owner INNOVATION ACAD FOR MICROSATELLITES OF CAS
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