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A Coordinated Orbit Control Method for Formation Satellites

An orbit control and satellite technology, which is applied to space navigation equipment, space navigation equipment, space navigation aircraft, etc. It can solve problems such as insufficient control accuracy, and achieve the effects of high calculation accuracy, good applicability, and clear process.

Active Publication Date: 2021-08-10
SHANGHAI AEROSPACE CONTROL TECH INST
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Problems solved by technology

[0003] The technical problem solved by the present invention is: Aiming at the problem that in the current prior art, the constraints on multi-satellite coordinated orbit control of formation satellites and the control method are too simple, resulting in insufficient control precision, a method for controlling the coordinated orbit of formation satellites is proposed

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  • A Coordinated Orbit Control Method for Formation Satellites
  • A Coordinated Orbit Control Method for Formation Satellites
  • A Coordinated Orbit Control Method for Formation Satellites

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Embodiment Construction

[0028] A formation satellite coordinated orbit control method, by continuously increasing the latitude argument corresponding to the control point, using the latitude argument to calculate the formation configuration eccentricity vector phase angle after orbit control and the current actual formation satellite formation configuration state parameters Comparison, and finally select the latitude argument that can best meet the conditions as the latitude argument corresponding to the control point, and use the selected latitude argument to calculate the jet start time of the main star and other auxiliary stars in the formation satellite, as shown in figure 1 As shown, the specific process is as follows:

[0029] (1) According to the current orbital semi-major axis a of the formation main star in the formation satellite, the orbit decay rate The range L of the ground trajectory, the orbital angular velocity n of the main star, that is, the six numbers of the orbit, calculate the ...

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Abstract

A formation satellite coordinated orbit control method, by traversing the latitude argument corresponding to the main satellite orbit control point, using the latitude argument to calculate the formation configuration eccentricity vector phase angle after orbit control and the current actual formation satellite formation configuration state parameter Compare, finally choose the latitude argument that can satisfy the condition best as the latitude argument corresponding to the control point, and use the selected latitude argument to calculate the starting and controlling jet time of the main star and other auxiliary stars in the formation satellite, the present invention reduces as much as possible Orbit control destroys the formation configuration, adopts the method of simultaneous start and the same control amount, which can be realized independently on the star, with a clear process and high calculation accuracy.

Description

technical field [0001] The invention relates to a method for controlling a coordinated orbit of formation satellites, belonging to the field of high-precision formation and orbit control of satellites. Background technique [0002] Affected by atmospheric resistance during satellite operation, the altitude of the satellite continues to drop, the operating cycle continues to shorten, and the actual state continues to deviate from the nominal state. Therefore, for conventional single satellites, the orbit is often controlled regularly based on constraints such as ground trajectory drift or local time drift. Track keeping control is achieved by raising the semi-major axis of the track. Similarly, for formation satellites, there are also orbit keeping requirements. When a single satellite changes into a multi-satellite formation, the orbit maintenance of the formation satellites requires multi-satellite cooperative control based on formation configuration and inter-satellite s...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/24B64G1/26
CPCB64G1/242B64G1/26
Inventor 杜耀珂完备王文妍王嘉轶陈桦龚腾上刘美师崔佳何煜斌岳杨贾艳胜王禹
Owner SHANGHAI AEROSPACE CONTROL TECH INST
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