Orbital period characteristic-based star sensor precision correction method
A technology of star sensor and orbital period, used in instruments, navigation through velocity/acceleration measurement, measurement devices, etc., can solve the complex method of eliminating aberration errors, difficult to eliminate installation matrix errors, affecting the accuracy of star sensors, etc. problem, to achieve high-precision attitude determination, eliminate attitude determination errors, and improve the effect of ability
Pending Publication Date: 2021-08-13
INNOVATION ACAD FOR MICROSATELLITES OF CAS +1
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[0007]
In order to at least partially solve the problems in the prior art that the installation matrix error between the star sensor and the payload system is difficult to eliminate and the aberration error elimination method is complicated, which affects the accuracy of the star sensor, the present invention proposes a star sensor based on orbital period characteristics Accuracy correction methods, including:
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[0063] It should be noted that components in the various figures may be shown exaggerated for the purpose of illustration and are not necessarily true to scale. In the various figures, identical or functionally identical components are assigned the same reference symbols.
[0064] In the present invention, unless otherwise specified, "arranged on", "arranged on" and "arranged on" do not exclude the presence of intermediates between the two. In addition, "arranged on or above" only means the relative positional relationship between two parts, and under certain circumstances, such as after the product direction is reversed, it can also be converted to "arranged under or below", and vice versa Of course.
[0065] In the present invention, each embodiment is only intended to illustrate the solutions of the present invention, and should not be construed as limiting.
[0066] In the present invention, unless otherwise specified, the quantifiers "a" and "an" do not exclude the scen...
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The invention relates to the technical field of spacecraft attitude control, and provides an orbital period characteristic-based star sensor precision correction method. The method comprises the steps that a spacecraft corrects aberration in star sensor measurement according to the orbital period characteristic, and the spacecraft corrects a thermal elastic deformation error of a star sensor installation matrix according to the orbital period characteristic. The spacecraft speed is autonomously calculated through the spacecraft, so that a star sensor interface protocol is simplified; aberration correction is directly carried out on the quaternion output by the star sensor, and the technology is simple and easy to implement; and the installation matrix influenced by the temperature is calculated in real time by utilizing spacecraft orbit motion and on-orbit data fitting, so that attitude determination errors caused by thermal elastic deformation can be eliminated in real time, and the capability of a spacecraft attitude determination system is improved.
Description
technical field [0001] The present invention generally relates to the technical field of spacecraft attitude control, in particular to a method for correcting the accuracy of a star sensor based on orbital period characteristics. Background technique [0002] The accuracy of spacecraft attitude determination is an important basis for spacecraft attitude control, and it is also the key to the success of spacecraft performing various tasks. All kinds of space missions put forward high requirements on the attitude determination accuracy of the spacecraft, and the star sensor is usually the most accurate among the various attitude measurement components of the spacecraft. [0003] The star sensor measures the attitude information of the star-sensitive optical measurement coordinate system relative to the inertial space in real time on orbit, and through the installation matrix conversion between the star sensor and the payload system, the attitude orientation information of the ...
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Login to View More IPC IPC(8): G01C25/00G01C21/02G01C21/16
CPCG01C25/005G01C21/025G01C21/16Y02T90/00
Inventor 齐凯华万松李东南朱让剑孙国文顾文娟
Owner INNOVATION ACAD FOR MICROSATELLITES OF CAS