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Satellite Formation Reconfiguration Method

A technology for satellite formation and formation reconstruction, which is applied in three-dimensional position/channel control and other directions, and can solve the problem that satellite setting control cannot be reliably coordinated.

Active Publication Date: 2017-07-21
蔡远文
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Problems solved by technology

[0004] The purpose of the present invention is to provide a satellite formation reconfiguration method to solve the technical problem that the satellite orbit setting control from the start point to the end point cannot be reliably coordinated during the satellite formation reconfiguration process

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Embodiment Construction

[0024] In this embodiment, based on satellite formation reconstruction, not only must each satellite complete the corresponding orbit transfer process, but also the coordinated movement between formation satellites needs to be considered, and there are certain and uncertain situations in the final state of satellites for different reconstructed trajectories , for the transfer orbit of each satellite in the formation and the fuel consumption strategy of the corresponding micro-thruster, the control signal optimization is carried out from the satellite path layer and the satellite coordination scheme layer respectively, so as to realize the reconstruction scheme with the least energy consumption. Firstly, the improved discrete particle swarm optimization algorithm is responsible for generating the trajectory scheme of each satellite in the reconstruction process, then, the pseudospectral method is used to calculate the energy consumption of each satellite in each trajectory scheme...

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Abstract

A satellite formation reconfiguration method, the main steps of adjusting the satellite transfer trajectory in the formation include: determining the start position and end position of each satellite in the formation reconfiguration process; using pseudospectral algorithm to form The corresponding transfer orbit; form the fuel consumption control signal of the satellite micro-thruster corresponding to the orbit; filter the transfer orbit that will collide through the discrete particle swarm algorithm; according to the constraint conditions, establish the orbit change transfer strategy of each satellite in the reconstruction process; form Control signal strategy for fuel consumption during satellite orbit changes during reconfiguration. The invention forms the double-layer planning of the transfer orbit of the satellites in the formation, calculates the fuel optimal target value of each satellite micro-thruster in the formation reconstruction, and then forms the final reconstruction trajectory scheme.

Description

technical field [0001] The invention relates to a satellite vector thrust control method, in particular to a vector thrust control method for multiple satellites. Background technique [0002] The microsatellite formation flight is different from the fixed constellation flight composed of several satellites, each satellite is an organic composition with complete functions. Due to changes in mission steps, technical performance parameters, etc., it is necessary to reconstruct the formation form. Since the satellites flying in formation are an organic whole in terms of function and control, from the original formation configuration to another new formation configuration, the control of each formation satellite must be coordinated with each other in order to realize the overall function of the formation. [0003] The underlying control methods of configuration reconfiguration can be divided into two categories: impulse-based control and continuous micro-thrust (continuous micr...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05D1/10
Inventor 蔡远文史建伟姚静波程龙辛朝军张宇李岩解维奇
Owner 蔡远文
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