A method of using a low-inclination satellite star sensor
A star sensor and low inclination angle technology, which is applied in the direction of artificial satellites, aircraft, space navigation aircraft, etc., can solve the problems that affect the availability of star sensors in orbit, affect the measurement accuracy of star sensors, and the inability of satellites to determine the attitude with high precision , to achieve the effect of improving mission execution capability, ensuring on-orbit availability, and improving on-orbit availability
Active Publication Date: 2020-06-16
SHANGHAI ENG CENT FOR MICROSATELLITES
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Problems solved by technology
Since the star light source is a weak light, the interference of stray light such as sunlight, earth atmosphere light, and moon atmosphere light will affect the measurement accuracy of the star sensor, and even cause the star sensor to be unusable, which seriously affects the performance of the star sensor. On-orbit availability
[0003] Although a hood is installed in front of the lens of the star sensor, it can only prevent a certain amount of stray light interference, and low-inclination satellites are more likely to be interfered by stray light such as sunlight and atmospheric light due to their orbits. A single star sensor cannot guarantee that it will always be available in orbit, resulting in the inability of the satellite to perform high-precision attitude determination all the time, which has caused certain limitations to the satellite's mission execution
[0004] Aiming at the problem that the star sensor is susceptible to stray light interference, there are mainly two traditional methods, one is to improve the design of the hood, increase the length of the hood or increase the number of stages of the hood, this method can improve to a certain extent The ability of the star sensor to stray light, but the room for improvement is relatively limited, and the stray light near and beyond the hood cannot be suppressed very well; Astigmatism suppression is the largest installation position, but this method also has limitations, that is, it can only suppress the entry of stray light at a specific angle, and cannot guarantee that the star sensor will be free from stray light interference for a long time
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[0041] In the following description, the present invention is described with reference to various examples. One skilled in the art will recognize, however, that the various embodiments may be practiced without one or more of the specific details, or with other alternative and / or additional methods, materials, or components. In other instances, well-known structures, materials, or operations are not shown or described in detail so as not to obscure aspects of the various embodiments of the invention. Similarly, for purposes of explanation, specific quantities, materials and configurations are set forth in order to provide a thorough understanding of embodiments of the invention. However, the invention may be practiced without these specific details. Furthermore, it should be understood that the various embodiments shown in the drawings are illustrative representations and are not necessarily drawn to scale.
[0042] In this specification, reference to "one embodiment" or "the...
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The invention discloses a method for using a low-inclination satellite star sensor, which includes: determining the number and installation layout of the star sensor according to the constraints of the star sensor's sun suppression angle and earth suppression angle; on the premise of ensuring energy supply, Design the attitude of the satellite to ensure the availability of the star sensor. This method can enhance the ability of the star sensor to suppress stray light such as sunlight and atmospheric light, and improve the on-orbit usability of the star sensor, thereby ensuring the accuracy of the satellite's attitude determination and improving the satellite's mission execution capability.
Description
technical field [0001] The invention relates to the technical field of spacecraft attitude control. Specifically, the present invention relates to a method for using a star sensor suitable for low-inclination satellites. Background technique [0002] The star sensor is a high-precision optical sensor with the star as the attitude reference light source, and it is an important attitude measurement component in the spacecraft control system. Since the star light source is a weak light, the interference of stray light such as sunlight, earth atmosphere light, and moon atmosphere light will affect the measurement accuracy of the star sensor, and even cause the star sensor to be unusable, which seriously affects the performance of the star sensor. On-orbit availability. [0003] Although a hood is installed in front of the lens of the star sensor, it can only prevent a certain amount of stray light interference, and low-inclination satellites are more likely to be interfered by...
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IPC IPC(8): B64G1/10B64G1/24B64G1/36
CPCB64G1/10B64G1/24B64G1/36B64G1/245
Inventor 严玲玲张锐谢祥华刘剑董祯祁海铭赵璟本立言黄志伟何夏维胡志强
Owner SHANGHAI ENG CENT FOR MICROSATELLITES
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