Low-orbit satellite deorbit control method and system based on particle swarm algorithm

A particle swarm algorithm and low-orbit satellite technology, which is applied in the system, neural learning method, and calculation of the spacecraft returning to the earth's atmosphere, which can solve the problem of lack of algorithm implementation.

Active Publication Date: 2020-11-03
PLA PEOPLES LIBERATION ARMY OF CHINA STRATEGIC SUPPORT FORCE AEROSPACE ENG UNIV
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Problems solved by technology

[0004] The purpose of this application is to provide a method and system for deorbiting control of low-orbit satellites based on particle swarm algorithm, and then at least to a certain extent overcome the lack of research on the implementation of algorithms in the direction of deorbiting control

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  • Low-orbit satellite deorbit control method and system based on particle swarm algorithm
  • Low-orbit satellite deorbit control method and system based on particle swarm algorithm
  • Low-orbit satellite deorbit control method and system based on particle swarm algorithm

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Embodiment 1

[0124] Below in conjunction with this embodiment, the low-orbit satellite de-orbit control method based on the particle swarm algorithm of the present application is described. In the present embodiment, it is realized through the following steps: Step 1, given the spacecraft's own parameters and small thruster parameters; Step 2 , given the working orbit of the spacecraft and the semi-major axis, eccentricity and orbital inclination of the two disposal orbits; Step 3, given the parameters of the augmented Lagrangian particle swarm optimization algorithm; Step 4, calculating the deorbit time without thrust ; Step five, calculate the optimal control rate, deorbit time and fuel consumption of the two disposal orbits.

[0125] Among them, the parameters of the spacecraft itself and the small thruster are shown in Table 1, the semi-major axis, eccentricity and orbital inclination of the spacecraft’s working orbit and two disposal orbits are shown in Table 2, and the parameters of t...

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Abstract

The invention discloses a low-orbit satellite deorbit control method and system based on a particle swarm algorithm, belongs to the field of constellation management, and can solve the problem of lackof research on algorithm implementation in the deorbit control direction. The method comprises the following steps: constructing an objective function according to position parameters and perturbation acceleration of particles in a particle swarm, and a preset Lagrange multiplier and a penalty factor; calculating an objective function value of each particle in the particle swarm based on the objective function, determining the objective fitness of each particle and the population fitness of the particle swarm according to the calculation result, updating the position parameter and speed of each particle, and obtaining the population optimal fitness at the maximum iteration frequency; and updating a Lagrange multiplier and a penalty factor according to the population optimal fitness, comparing the objective deviation value with a preset convergence condition, and determining objective population fitness and objective position parameters according to a comparison result to obtain an objective deorbit mode. The method is used for deorbit control of the low-orbit satellite.

Description

technical field [0001] The present application relates to the technical field of constellation operation management, in particular to a particle swarm algorithm-based de-orbit control method and system for low-orbit satellites. Background technique [0002] With the continuous increase of human spaceflight missions, the orbital space of low orbit and middle and high orbit is gradually crowded, which makes the collision probability of satellites in orbit gradually increase. According to the "IADC Space Debris Mitigation Guidelines" compiled by the Institutional Space Debris Coordination Committee (IADC), when the natural orbit exceeds 25 years, the low-orbit satellite needs to enter the disposal orbit within 25 years and burn up in the atmosphere. At the same time, the development of small satellite technology and the reduction of launch costs have led to a sharp increase in the number of satellites in the low-orbit satellite constellation. OneWeb plans to launch a constellat...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/24G06N3/00
CPCB64G1/242G06N3/006B64G1/26B64G1/62G06N3/08B64G1/247
Inventor 胡敏李玖阳李强王许煜云朝明张学阳孙天宇宋庆雷
Owner PLA PEOPLES LIBERATION ARMY OF CHINA STRATEGIC SUPPORT FORCE AEROSPACE ENG UNIV
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