Configuration and Design Method of Space Debris Removal System
Active Publication Date: 2019-08-27
NORTHWESTERN POLYTECHNICAL UNIV
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Problems solved by technology
The configurations of various space debris removal systems in the prior art are relatively complex, and the stability is relatively low. Coupled with the limitations of the technology itself, it is difficult to carry out the removal of space debris in civil applications
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[0039] The present invention will be further described in detail below in conjunction with specific embodiments, which are explanations of the present invention rather than limitations.
[0040] The configuration of a space debris removal system in the present invention can effectively complete the task after feasibility analysis. The configuration of the space debris removal system has 17 degrees of freedom except the base, and the base can move freely, including translation along three axes and rotation around three axes. Therefore, the system has a total of 23 degrees of freedom.
[0041] Such as Figure 1-Figure 4 As shown, the configuration of the space debris removal system includes: a six-degree-of-freedom base 1, a first telescopic rod 3 that moves along the base 1 perpendicular to the direction of the solar panel 2, and a telescopic rod nested inside the first telescopic rod 3 The second telescopic rod 4, the first joint 5 that can rotate around the direction axis o...
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The invention provides a space debris removal system structure and a design method thereof. The system is simple in structure, reasonable in design, small in size, easy to operate, large in working range and convenient to control. The removal system structure comprises a six-freedom-degree base, solar panel substrates are symmetrically arranged on the base, a first stretchable rod moving in the direction, perpendicular to the solar panel substrates, of the base, a second stretchable rod nested into the first stretchable rod, a first joint capable of rotating around the axis direction of the stretchable rods, a second joint rotating around the direction perpendicular to the axis direction of the first joint, a third joint rotating around the axis direction of the second joint, and a tail end capture device. The design method comprises the steps of building a space debris removal system, building a three-dimensional model, performing dynamics modeling, and performing path planning on a capture mask of the space debris removal system; according to the obtained path planning, completing virtual reality simulation of the whole system, verifying the correctness of the space debris removal system and completing structure design.
Description
technical field [0001] The invention relates to the structural design of a space debris removal system, in particular to a space debris removal system configuration and a design method thereof. Background technique [0002] Using active debris removal technology can quickly and effectively reduce the amount of space debris. As for the space debris removal system, the United States, Europe and Japan started research earlier, and have proposed their own debris removal programs, and some key technologies have been demonstrated in orbit. [0003] In August 2010, the US Defense Advanced Research Projects Agency (DARPA) announced the space debris removal technology demonstration and verification project under development - Electric Debris Remover (EDDE). The Japan Aerospace Exploration Agency (JAXA) is working on a tiny satellite system to demonstrate active space debris removal technology, the Space Debris Microremoval Device (SDMR). The robot arm is used to capture the target,...
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IPC IPC(8): B64G4/00G06F17/50
CPCB64G4/00G06F30/20
Inventor 罗建军许若男王明明袁建平朱战霞
Owner NORTHWESTERN POLYTECHNICAL UNIV