Microsatellite group formation consumption optimization method

An optimization method and technology of microsatellites, applied in the directions of instruments, adaptive control, control/regulation systems, etc., can solve the problem that the energy consumption of orbit changing maneuvers cannot be further reduced, so as to overcome the poor local search ability, enhance flexibility, and improve robustness. great effect

Active Publication Date: 2015-02-04
蔡远文
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Problems solved by technology

[0006] The purpose of the present invention is to provide a method for optimizing the consumption of micro-satellite group formation to solve the technical problem that the energy consumption of orbit changing maneuvers in the double-pulse maneuver mode cannot be further reduced during the satellite group formation process

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  • Microsatellite group formation consumption optimization method
  • Microsatellite group formation consumption optimization method

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Embodiment Construction

[0031] When a single star enters the formation, with two impulses v 1 , v 2 The required energy consumption is taken as the performance index J, and the scheme with the smallest energy consumption is selected as the scheme for entering the formation around the star, J=min{||v 1 ||+||v 2 ||}

[0032] In the asynchronous establishment strategy of the formation, the time for each orbiting star to leave the initial point is different, the time to arrive at the rendezvous point of the relative orbit is different, and the transfer time is not necessarily the same. Therefore, according to the order in which the orbiting stars enter the formation, the initial position and initial velocity of each orbiting star and the phase when entering the formation must be calculated separately, and then the energy consumption is calculated according to the method of a single orbiting star entering the formation. The sum of energy consumption is the total energy consumption of formation establis...

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Abstract

A microsatellite group formation consumption optimization method mainly includes the step: determining satellite orbital transfer time and factors related to fuel consumption as transfer time and a final position; determining an inter-satellite encoding structure in a satellite group; forming a satellite orbital transfer energy consumption calculation method; performing niche genetic algorithm analysis for formed satellite orbital transfer energy consumption to form optimal orbital transfer energy consumption data, and converting the data into corresponding double-pulse engine energy consumption control parameters. By the aid of niche technology and genetic algorithm, energy consumption is taken as an optimization objective, the method is applicable to a single surrounding satellite, multi-satellite synchronous formation and multi-satellite asynchronous formation, the algorithm does not require satellite group release sites, and flexibility of microsatellite group release can be enhanced. The method retains the advantages of high robustness, global search, parallelism and the like of a genetic algorithm, and the shortcomings of poor local search capacity of the genetic algorithm are overcome.

Description

technical field [0001] The invention relates to a space attitude control method, in particular to an energy control method for satellite release and positioning. Background technique [0002] In the establishment process of the micro-satellite formation, the usual method is to release the orbiting star from the reference point to form a flying formation. The space platform releases the orbiting star from the designated location to form a formation, which will increase the flexibility of the mission. However, satellite formation is a process of establishing the space attitude of a satellite group rather than a single satellite. When the release location has been designated and the formation formation strategy has been determined, it is also necessary to optimize the consumption required in the process of establishing the formation of the micro-satellite group, such as energy consumption, time consumption, and so on. Due to the limited platform, the energy carried by microsat...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B13/04
Inventor 蔡远文史建伟程龙姚静波辛朝军李岩张宇解维奇
Owner 蔡远文
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