Method for realizing narrow-view-field load pointing calibration by satellite attitude maneuver assistance

A satellite attitude and calibration method technology, applied in the aerospace field, can solve problems such as interference, inability to install a two-dimensional turntable, affecting the stability of the laser load boresight pointing, etc., and achieve the effect of reducing complexity

Active Publication Date: 2021-05-25
SHANGHAI JIAO TONG UNIV
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Problems solved by technology

For micro-satellites with narrow field of view payloads, the payload two-dimensional turntable will interfere with the satellite body during operation, which will affect the

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  • Method for realizing narrow-view-field load pointing calibration by satellite attitude maneuver assistance
  • Method for realizing narrow-view-field load pointing calibration by satellite attitude maneuver assistance
  • Method for realizing narrow-view-field load pointing calibration by satellite attitude maneuver assistance

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[0021] In order to facilitate the understanding of the present application, the present application will be described more fully below with reference to the relevant drawings. A preferred embodiment of the application is shown in the drawings. However, the present application can be embodied in many different forms and is not limited to the embodiments described herein. On the contrary, the purpose of providing these embodiments is to make the disclosure of this application more thorough and comprehensive.

[0022] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the technical field to which this application belongs. The terms used herein in the specification of the application are only for the purpose of describing specific embodiments, and are not intended to limit the application. As used herein, the term "and / or" includes any and all combinations of one or more of the associa...

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Abstract

The invention discloses a method for realizing narrow view field load pointing calibration by satellite attitude maneuver assistance. The method comprises the following steps that a target staring attitude is established according to orbit parameters of a local satellite and a target satellite and a theoretical value of a load installation matrix; in a vertical load visual axis plane in a satellite staring coordinate system, an Archimedes spiral is calculated from a central point, and the scanning direction of a load visual axis is planned in real time; a scanning attitude of a satellite relative to a staring coordinate system in real time is calculated according to a load visual axis direction planned by a spiral line by taking an orbital plane normal as a reference vector, a target attitude of the satellite relative to an orbital coordinate system is calculated in combination with the staring attitude, and an expected angular velocity of the satellite is obtained; the deviation of the attitude and the angular velocity is calculated according to the current attitude and the angular velocity of the satellite so as to realize spiral line scanning in the load signal direction; after the two parties capture the signals, the current attitude is recorded, the actual measurement value of the installation matrix corresponding to the load is calculated in combination with the theoretical attitude, and normal communication of the narrow-view-field load can be realized without spiral scanning again.

Description

technical field [0001] The invention relates to the field of aerospace, in particular to a method for calibrating load pointing in a narrow field of view with satellite attitude maneuver assistance. Background technique [0002] The Ku-band and Ka-band high-speed data transmission antennas and laser communication loads installed on satellites are all typical narrow field of view loads. The half-cone angle of the field of view of the Ku-band antenna is on the order of 0.15°, and the half-cone angle of the field of view of the laser communication load is on the order of 0.1°. During the establishment of the communication link, usually the two-dimensional turntable carried by the payload itself controls the direction of the signal, so that the boresight of the payload points to the theoretical direction of the target star, and then starts a coverage scan from the center of the uncertain area. After the other satellite receives the signal, Calibrate the pointing deviation, and ...

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Application Information

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IPC IPC(8): G01S19/23
CPCG01S19/23
Inventor 杜宁吴树范王世耀陈文晖徐家国慕忠成
Owner SHANGHAI JIAO TONG UNIV
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