A trajectory optimization method for spacecraft relative orbit transfer based on time-fuel optimal control

Abstract

The invention provides an optimization method of a relative orbit transfer path of a spacecraft based on time-fuel optimum control and relates to the optimization method of the relative orbit transfer path of the spacecraft. The optimization method of the relative orbit transfer path of the spacecraft is used for solving the problem that the finite thrust amplitude is not considered in the existing method and the problem that only time optimum or only the fuel consumption is considered in the existing method when a tracking spacecraft is in a relative orbit coordinate system. The optimization method comprises the following steps: firstly, establishing a kinematics and dynamics model as shown in the specification of the relative orbit, and designing control quantities ux, uy and uz applied along three axes respectively; secondly, decoupling the kinematics and dynamics model of the relative orbit into three subsystems; after decoupling into three subsystems, transforming the total performance index as shown in the specification considering transfer time and fuel consumption of the tracking spacecraft into monoaxial performance index as shown in the specification of each axis, and finally obtaining the time-fuel optimal control law as shown in the specification for controlling the tracking spacecraft. The optimization method is suitable for optimizing the relative orbit transfer path of the spacecraft.

Description

technical field

[0001] The invention relates to a method for optimizing a relative orbital transfer trajectory of a spacecraft. Background technique

[0002] The relative orbital motion of spacecraft is to study the law of continuous motion of one spacecraft (tracking spacecraft) around another spacecraft (target spacecraft). The research focus of orbit transfer is mainly in two aspects. On the one hand, it is to consider whether the program can correctly guide the spacecraft to reach the designated position; For the problem of optimal time, starting from engineering reality, the fuel carried by the spacecraft is limited, so sometimes it is necessary to consider the problem of optimal fuel consumption, or even consider the problem of comprehensive optimization of time and fuel consumption. The basic method commonly used to solve the optimal control problem is the classical variational method. When there are constraints on the control quantity, such as the thrust amplitude t...

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