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Method for planning attitude maneuver in imaging process of agile satellite

An attitude maneuver and satellite technology, applied in the field of attitude maneuver planning algorithms, can solve the problems of increasing the workload of the ground system, the large amount of data, and the complex content of the attitude maneuver imaging instructions.

Active Publication Date: 2015-08-19
BEIJING INST OF SPACECRAFT SYST ENG
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Problems solved by technology

The ensuing problem is that in the face of various complex imaging situations, if the method of injecting instructions and related information on the ground before the imaging task is still used, the workload of the ground system will be increased, and the amount of injection required for attitude maneuver imaging The command content is complex and the data volume is large

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Embodiment Construction

[0101] Such as figure 1 As shown, it is a flow chart of the attitude maneuver planning algorithm of the present invention, and the specific steps are as follows:

[0102] (1) According to the geographic location of the start and end points of the specified ground imaging strip, the start time and end time of imaging, and the calculation step size on the star, calculate the position of the imaging point corresponding to each time point.

[0103] Let the starting point of the imaging observation strip be A, and its geographic latitude and longitude be Lon A,d and Lat A,d , the corresponding time is t A ; Let the end point of the imaging observation strip be B, and its geographic latitude and longitude be Lon B,d and Lat B,d , the corresponding time is t B . The step size of calculation time on the star is Δt.

[0104] The ground imaging observation band is shown as figure 2 shown. In this method, the observation strips formed between the starting point and the ending p...

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Abstract

The invention discloses a method for planning attitude maneuver in the imaging process of an agile satellite. The method comprises the following steps: firstly, calculating an imaging point position corresponding to each time point according to starting and ending geographic positions of a designated ground imaging strip and imaging time corresponding to two endpoints; secondly, calculating a relative position vector of the satellite and imaging points in a geocentric equatorial inertial coordinate system according to orbital parameters of the satellite and the imaging point positions of corresponding moments; thirdly, calculating a component of the relative position vector in a satellite body coordinate system according to a series of conversion matrixes from the geocentric equatorial inertial coordinate system to a satellite orbital coordinate system; fourthly, calculating a roll angle, a pitch angle, a roll angle speed and a pitch angle speed during satellite imaging according to the component of the relative position vector in the satellite orbital coordinate system; finally, calculating a yaw angle and a yaw angle speed of the satellite according to the roll angle, the roll angle speed, the pitch angle and the pitch angle speed which are obtained, the orbital parameters and the corresponding imaging point positions to obtain the planned attitude information of the satellite in the imaging process.

Description

technical field [0001] The invention relates to an attitude maneuver planning algorithm suitable for low-orbit remote sensing satellites with agile attitude maneuver capability in the ground imaging process, in particular to an attitude maneuver planning method in the agile satellite imaging process. Background technique [0002] With the continuous development of remote sensing satellites, remote sensing satellites continue to enrich their own functions and improve their performance. Among them, the agile and mobile imaging capability is currently a technology that is more concerned. The agile maneuvering imaging capability mainly refers to the ability of the satellite platform to have a wide range of rapid attitude maneuvering, and to implement flexible earth observation within the limits of the maximum attitude angle and attitude maneuvering speed, so as to achieve rapid response to the observation target and multiple modes of observation. imaging capabilities. In additi...

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Application Information

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IPC IPC(8): G01C21/20G01C1/00
CPCG01C1/00G01C21/20
Inventor 赵峭黄美丽冯昊田百义周静高珊雪丹
Owner BEIJING INST OF SPACECRAFT SYST ENG
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