A Spacecraft Formation Flight Method in the Weakly Stable Boundary Region

Abstract

A spacecraft formation flying method in a weak-stability boundary area of the invention comprises the following steps: (1) solving out an earth-moon low-energy transfer orbit of a main spacecraft based on weak stability boundary properties under a sun-earth-moon-spacecraft four-body model; (2) deriving a relative dynamic equation of an accompanying spacecraft under the sun-earth-moon-spacecraft four-body model; (3) designing a Hamiltonian structure shape maintenance controller; (4) solving out a bounded relative flying orbit of the accompanying spacecraft; and (5) planning a main spacecraft and accompanying spacecraft formation flying orbit based on the earth-moon low-energy transfer orbit of the main spacecraft obtained in step (1). The precision of a formation flying basic dynamic model is improved. The factors of gravity environment change are taken into consideration in formation control. Moreover, a formation flying control method based on a Hamiltonian structure shape maintenance controller is put forward to generate a bounded relative flying orbit in the earth-moon low-energy transfer process.

Description

technical field [0001] The invention relates to a spacecraft formation flight method based on the Earth-Moon low-energy transfer orbit in the unstable boundary region under the restricted four-body model of the Sun-Earth-Moon-spacecraft, especially a multi-spacecraft based on a Hamiltonian structure-preserving controller Device formation control method. Background technique [0002] Spacecraft formation flight refers to the realization of the functions of a large space vehicle through the mutual communication and cooperative work of multiple small space vehicles, and even the completion of complex space tasks that cannot be achieved by traditional large space vehicles. Compared with ordinary single spacecraft, the multi-spacecraft formation technology has the following four important advantages: optimizing the integrity of the spacecraft system; improving the reliability of the spacecraft system; enhancing the adaptability of the spacecraft system; reducing the design cost....

AI Technical Summary

Problems solved by technology

However, the design and derivation of the Earth-Moon low-energy transfer orbit based on the nature of the weakly stable boundary is based on the four-body problem model of the Sun-Earth-Moon-spacecraft, the nonlinearity is further increased, and the requirements for formation difficulty and control accuracy are also further increased

[0006] (2) The traditional formation method is difficult to adapt to the complex gravitational and space environment changes in the Earth-Moon transfer process

[0007] Traditional formation control methods are not ideal for formation control during Earth-Moon transfer

The traditional formation control method is more based on the classic proportional-integral-derivative controller (PID). Although it is widely used in engineering control practice, it has many side effects due to the introduction of error integral feedback. At the same time, it gives The obtained control quantity is the linear combination of the error in the past, present and future three states, and the combination of this linear combination in the typical nonlinear four-body problem of the Earth-Moon low-energy transfer formation flight based on the nature of the weakly stable boundary The effect needs to be further explored

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