Inter-satellite relative attitude control method based on bidirectional LOS vector
A technology of relative attitude and control method, applied in the directions of artificial satellites, space navigation equipment, space navigation aircraft, etc., can solve the problem of not satisfying the rapid response of the relative controller, save control reaction time, simple design, and control structure. simple effect
Active Publication Date: 2021-05-14
RES & DEV INST OF NORTHWESTERN POLYTECHNICAL UNIV IN SHENZHEN +1
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Problems solved by technology
[0004] In order to solve the problem in the prior art that the relative controller can not meet the fast response requirement, the present invention provides a relative attitude control method between satellites based on two-way LOS vector , this method is a relative attitude control method for micro-nano satellites with simple design, low computational complexity, good real-time performance and wide application range
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[0062]The present invention performs the relative attitude control between the two-way LOS vectors, including the following five steps:
[0063]S1, using an array antenna to measure the two-way LOS vector between the main spacecraft and the spacecraft;
[0064]S2, using an array antenna measurement service spacecraft and bidirectional LOS vector between spacecraft;
[0065]S3, calculate the main spacecraft and the LOS vector error equation between the spacecraft and the LOS vector error equation between the service spacecraft and the spacecraft;
[0066]S4, the error equation is represented by two sets of LOS vector and desired relative posture to design control input.
[0067]The specific steps are as follows:
[0068]S1 uses an array antenna to measure the main spacecraft and the two-way LOS vector between the spacecraft
[0069]Seefigure 1 Down, CV in the figure1Indicates the main spacecraft, DVkRepresents an array antenna from the spacecraft, both an array antenna, using an array signal processing a...
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The invention discloses a relative attitude control method based on a bidirectional LOS vector. The method comprises the following steps: measuring the bidirectional LOS vector between a master spacecraft and a slave spacecraft by using an array antenna; measuring a bidirectional LOS vector between a service spacecraft and the slave spacecraft by using the array antenna; calculating an LOS vector error equation between the master spacecraft and the slave spacecraft and an LOS vector error equation between the service spacecraft and the slave spacecraft; and representing the error equations by using two groups of LOS vectors and an expected relative attitude, and further designing control input. According to the method, the dynamic topological structure of rapid change of the satellite formation is considered, the control input only comprises the information of the LOS vector, and the relative attitude between satellites can be controlled without taking the absolute attitude of the satellites, so that the control response time is saved, and the control structure is simple.
Description
Technical field[0001]The present invention belongs to the field of relative attitude control, and more particularly to a relative posture control method based on bidirectional LOS vectors.Background technique[0002]With the small size trend of satellites, satellites can formulate a formation of various complex tasks, such as detecting atmosphere, detecting the environment, constitutes synthetic aperture radar, and the like. Precise relative posture information in the formation is the basis for these tasks to complete.[0003]Since the satellite formation changes, the real-time performance of relative attitude control is very high, the controller needs to quickly respond to the relative attitude of the relative attitude, and the traditional relative attitude controller often needs to calculate the absolute posture of the satellite, thus consumed most The time does not meet the needs of the relative controller to quickly respond.Inventive content[0004]In the prior art, the present invent...
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IPC IPC(8): B64G1/24B64G1/10G06F17/11G06F17/16
CPCB64G1/244B64G1/10G06F17/11G06F17/16
Inventor 郑子轩王姣安效民
Owner RES & DEV INST OF NORTHWESTERN POLYTECHNICAL UNIV IN SHENZHEN