Star sensor setting angle determining method based on mission planning

A star sensor, mission planning technology, applied in the direction of aerospace vehicle guidance devices, etc.

Active Publication Date: 2010-06-30
AEROSPACE DONGFANGHONG SATELLITE
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  • Claims
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Problems solved by technology

According to the working requirements of the star sensor navigation system, when the satellite is in the working state of earth observation, it is necessary to ensure that at least two star sensors can be used at the same time in the target attitude, so as to directly observe the three-axis attitude of the satellite and obtain sufficient measurements Accuracy, which is often difficult to meet with traditional design methods

Method used

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  • Star sensor setting angle determining method based on mission planning
  • Star sensor setting angle determining method based on mission planning
  • Star sensor setting angle determining method based on mission planning

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Embodiment

[0108] Considering the different earth observation attitudes of satellites in the earth imaging area, the installation angles of each star sensor are reasonably designed, and the star sensor system is required to ensure at least 2 A star sensor is used to observe the three-axis attitude. Since the satellite orbit information, sun azimuth information, and earth azimuth information are all known, the iterative solution method is adopted for the design of the installation angle of the star sensor. Firstly, the initial installation angle value is designed according to the basic shape of the satellite star configuration, and then combined with various earth observation attitude conditions set by the mission planning, by calculating the angle between each star sensor and the sun light vector and the earth center vector, the star sensitive The sun-to-ground visibility of the device is analyzed, and on this basis, the installation angle value is continuously adjusted until the design ...

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Abstract

The invention relates to a star sensor setting angle determining method based on mission planning, aiming to satisfy the visibility demand to the sun and the earth of a star sensor when a satellite orbits. In the method, the angles between the axis of the star sensor and the sun or the earth are calculated and analyzed, the influence of various imaging working conditions to earth, which are determined by the mission planning, on the star sensor is considered emphatically, the setting angle and the working conditions of the star sensor are continuously adjusted to determine the proper setting angle of the star sensor. The method of the invention fully considers the influence of stray light on the star sensor under various working conditions and attitudes, is particularly applicable to the overall design work of the high-resolution quick satellite which need adopt large angle maneuver to perform earth observation, and can establish good feedback mechanism between the user unit which expresses satellite design requirements and performs the mission planning of the satellite and the engineering unit which designs the satellite.

Description

technical field [0001] The invention belongs to the field of spacecraft attitude control and relates to a method for determining the installation angle of a star sensor. Background technique [0002] In order to meet the mission requirements of high-resolution and agile earth observation, not only the satellite platform is required to have large-angle agile maneuvering control capabilities, but also the payload is required to work normally within the range of 45 degrees from the satellite attitude to the sub-satellite point. The high stability of the three-axis attitude of the star can be maintained during the payload's work on the ground. For this reason, a necessary condition is that the three-axis attitude of the satellite must be measurable in order to accurately maintain the target working attitude of the satellite. In order to determine the three-axis attitude change after the satellite establishes the target attitude and correct it, a common method is to use the gyro...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/24B64G1/36
Inventor 阎诚黄琳杨芳
Owner AEROSPACE DONGFANGHONG SATELLITE
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