Satellite formation analytical fuel optimization control method and system

Abstract

An analytical fuel optimization control method for satellite formation. Based on state space mapping, the motion state is converted into geometric configuration parameters, and a fuel optimal formation planning model described by geometric parameters is established, and the formation is carried out under the constraints of the final state equation. For the fuel lower bound required for maneuver planning, by comparing multiple lower interfaces and the accessibility of the lower interfaces, the optimal sufficient and necessary conditions for fuel are finally obtained, and an analytical fuel optimization control strategy with the shortest time and the least number of pulses is obtained. The invention can provide a fast analytical fuel optimal planning method for satellite formation flight, has the advantages of clear meaning, simple form, small calculation amount, etc., and can meet the short-distance orbit maneuvering requirements of low-earth orbit satellites.

Description

Technical field [0001] The invention relates to a low-Earth orbit satellite formation maneuver planning method in the field of aerospace technology, in particular to a satellite formation analytical fuel optimization control method and system. Background technique [0002] Facing the distributed satellite earth observation system, aiming at the problem of optimal planning of low-Earth orbit formation maneuvering fuel, a fast planning method with analytical form is proposed, which provides key technology and method support for the construction of distributed satellite system, and has important application value. At present, various numerical calculation methods are widely used in China to solve the problem. On the one hand, the amount of calculation is large and it is difficult to be practical; on the other hand, it is not known where the limit of fuel consumption is, and it is difficult to obtain the optimal solution in the true sense. Approximate or approximate. Therefore, it i...

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Problems solved by technology

However, the technical problems that this technology cannot solve include: 1. It uses the genetic algorithm to optimize the solution, which requires a large amount of calculation, and it is easy to fall into the local optimal solution, and it is impossible to judge whether the optimized result is the global optimal solution; 2. This method only It can solve the case for given specific numerical values, but does not give the minimum limit of fuel consumption, and whether the limit can be realized, and does not propose a universally applicable method for optimal fuel formation maneuver control

However, the technical problems that this technology cannot solve include: 1. This technology first constrains the number of pulses, which is essentially a solution to the pulse value under a fixed number of pulses. It does not treat formation maneuver control as an optimization problem, nor does it use Any optimization analysis method, so the result obtained is not the optimal solution; 2. In the derivation process of this technology, it is not explicitly mentioned but it is assumed that the normal pulse is zero. This assumption is in the analytical results of this technology as It is an inevitable conclusion, so to a certain extent, the method proposed by this technology has better fuel performance, and is optimal in some cases, but not most of the time; The small thrust continuous optimal control method does not consider

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