Perturbation orbit four-pulse intersection rapid optimization method

An optimization method and four-pulse technology, applied in the field of aerospace navigation control, can solve problems such as slow convergence and long calculation time

Active Publication Date: 2020-06-12
NAT UNIV OF DEFENSE TECH
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0003] The invention provides a fast optimization method for four-pulse rendezvous of a perturbed orbit, which is used to overcome the defects of long calculation time and slow convergence in the prior art, realize the accuracy of the iterative model, and improve the calculation efficiency

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  • Perturbation orbit four-pulse intersection rapid optimization method
  • Perturbation orbit four-pulse intersection rapid optimization method
  • Perturbation orbit four-pulse intersection rapid optimization method

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Embodiment 1

[0019] as attached figure 1 As shown, the embodiment of the present invention provides a fast optimization method for four-pulse rendezvous of a perturbed orbit, which is characterized in that it includes the following steps:

[0020] Step 1. According to the known conditions of the spacecraft and the target, the control quantity and the minimum velocity increment are obtained through the control model whose optimization result is to eliminate the orbital element difference at the rendezvous moment;

[0021] According to the pulse that converts a part of the control amount and speed increment into two pulses with fixed intervals, the spacecraft changes the number of orbits during the first lap of the orbit; converts the remaining control amount and speed increment into the other two pulses with fixed intervals The pulse controls the spacecraft to complete the rendezvous during the last circle of the orbit; estimate the magnitude of the four pulses and the components in the rad...

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Abstract

The invention discloses a perturbation orbit four-pulse rendezvous rapid optimization method, which comprises: according to known conditions of a spacecraft and a target, obtaining a control quantityand a minimum speed increment through a control model taking elimination of an orbit element difference at a rendezvous moment as an optimization result; establishing a four-pulse rendezvous optimization model according to the control quantity and the speed increment, taking the values of the moments and the sizes of the first two pulses in the neighborhood according to the estimated values in theabove steps, and recalculating the last two pulses according to the actual orbit recursion result; and replacing the analytic perturbation kinetic model with a full-perturbation accurate kinetic model, taking the optimal solution of the analytic kinetic model as an initial value, and solving again to obtain a four-pulse intersection optimal solution under the accurate kinetic model. The problemsof low calculation speed and the like in the prior art are solved, and calculation efficiency is improved.

Description

technical field [0001] The invention relates to the technical field of aerospace navigation control, in particular to a fast optimization method for four-pulse rendezvous of a perturbed orbit. Background technique [0002] In low-Earth orbit, the earth's non-spherical gravitational perturbation and atmospheric drag are the most important perturbations. In the optimization of pulse rendezvous orbit, the influence of perturbation term must be considered, but the corresponding orbit integral calculation amount is significantly increased compared with the two-body analytical dynamic model. In addition, the existing methods for solving optimal velocity increments for orbital rendezvous lack reasonable initial value settings. When using evolutionary algorithms, the range of solution space to be searched is large, and the calculation time is long, especially when the rendezvous transfer time is long, the convergence is very slow. Existing algorithms mostly use analytical perturbat...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/24
CPCB64G1/242
Inventor 罗亚中黄岸毅李恒年伍升钢张进杨震
Owner NAT UNIV OF DEFENSE TECH
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