Very simple configuration spacecraft and space rendezvous control method thereof

Abstract

The invention relates to the technical field of spacecraft space rendezvous control, and provides a very simple configuration spacecraft and a space rendezvous control method thereof. The spacecraft comprises a laser range finder, a camera, inter-satellite communication equipment and first to sixth thrusters. Through a thruster layout scheme with extremely simple configuration, perfect decoupling of translation and rotation of the star can be ensured. And smooth convergence of each channel of the translation channel can be ensured by adopting a guidance control scheme based on a phase plane. In addition, scheduling control of each thruster is carried out based on a thruster hybrid scheduling algorithm, the translational motion control effect in the rendezvous approaching process of the spacecraft is ensured, and a good tail end docking condition is created. According to the method, free control over three axes and six directions of translation of the spacecraft can be achieved under the condition of extremely simple configuration of the thruster, high control precision can be achieved, on-satellite space and manufacturing and operating cost can be saved, meanwhile, single faults of the thruster can be handled, and the method has a higher practical value.

Description

technical field [0001] The present invention generally relates to the technical field of spacecraft space rendezvous control. Specifically, the present invention relates to a spacecraft with extremely simplified configuration and a space rendezvous control method thereof. Background technique [0002] For spacecraft space rendezvous missions, the close-range rendezvous approach guidance of the spacecraft is a crucial part. Traditionally, spacecraft performing space rendezvous missions must ensure that the spacecraft is independent and precisely controllable in its translational three-axis and six-direction directions. This requires the spacecraft's star to deploy at least one thruster. [0003] However, there are some obvious deficiencies in the above-mentioned technical solution: thrusters cannot be deployed on all sides of the spacecraft, for example, the surface where the solar cell array is installed and the surface where cameras and optical sensors are deployed are no...

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Problems solved by technology

[0003] However, there are some obvious deficiencies in the above-mentioned technical solutions: not all sides of the spacecraft can deploy thrusters, for example, the surface where the solar cell array is installed and the surface where cameras and optical sensors are deployed are not suitable for installing thrusters

Moreover, this technical solution cannot cope with single faults of thrusters. If multiple redundant arrangements of thrusters are carried out in the process of thruster layout in order to cope with single faults of thrusters, it will greatly increase the size, weight, and weight of the spacecraft. Power consumption and other costs

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