Construction method of release dynamics model for ribbon-tethered satellite

A dynamic model and tethered satellite technology, applied in the field of spacecraft control, can solve the problem that the configuration change during the release process of the space ribbon tether cannot be accurately described, the system dynamics phenomenon cannot be truly revealed, and the system dynamics modeling is immature And other issues

Active Publication Date: 2021-02-05
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

[0003] Through the discussion of the previous research results, it can be found that researchers in western developed countries have paid attention to the importance of the ribbon-tethered satellite system, but the dynamic modeling of the system is not mature enough to truly reveal the dynamic phenomena of the system
In particular, it is impossible to accurately describe the configuration changes during the release process of the space ribbon tether

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  • Construction method of release dynamics model for ribbon-tethered satellite
  • Construction method of release dynamics model for ribbon-tethered satellite
  • Construction method of release dynamics model for ribbon-tethered satellite

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Embodiment Construction

[0112] In order to enable those skilled in the art to better understand the technical solutions of the present invention, the present invention will be described in further detail below in conjunction with specific embodiments.

[0113] The embodiment of the present invention provides a method for constructing a belt-tethered satellite release dynamics model. The belt-tethered satellite system is as follows: figure 1 As shown, the system is composed of a space belt tether and the on-orbit spacecraft (namely the main star M) and the terminal load (namely the secondary star S) connected by the tether.

[0114] In order to accurately describe the dynamic characteristics of the release process of the belt-tethered satellite system, three sets of coordinate reference systems are introduced to establish an inertial coordinate system O-XYZ fixed at the center of gravity O of the earth, its X-axis points to the ascending node, and its Z-axis is perpendicular to the orbit plane, the Y...

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Abstract

The invention discloses a method for constructing a release kinetic model of a belt-shaped tethered satellite, relates to the field of spacecraft control, can accurately describe the complex configuration changes of the space belt-shaped tether during the release process, and effectively reveal belts with different bending stiffnesses. The influence of the ribbon tether on the system dynamics accurately reflects the configuration change of the ribbon tether during the release process. The invention includes: uniformly discretizing the space band-shaped tether into several rigid body units, establishing the dynamic equation of a single rigid body unit and the constraint equation between the rigid body units, wherein, according to the constant change of the released length of the tether in the release stage, the rigid body The constraint equations between elements are divided into three categories, namely: the constraints between the unreleased elements in the main star, the constraints between the rigid body element being released and the previous element, the constraints between the released elements, and then according to the release process. The constraint equation between the rigid body elements in the middle and the final derivation is the dynamic equation of the release process of the ribbon tethered satellite system.

Description

technical field [0001] The invention relates to the field of spacecraft control, in particular to a method for constructing a release dynamics model of a ribbon tethered satellite. Background technique [0002] The space belt tethered satellite is different from the traditional tethered satellite system. It is composed of a belt-shaped metal rope whose width is much greater than the thickness and has a certain bending moment and torque, which plays a connecting role, the in-orbit spacecraft and the terminal load. The ribbon-tethered satellite greatly improves the space survival rate of the system, and at the same time, it has a wide range of applications in the fields of space exploration, satellite maneuvering, and space debris cleaning. It is worth noting that due to the complexity of the system model, Masakazu et al. studied the dynamic characteristics of the belt-like tether considering bending and torsion, and studied the nonlinear behavior of the belt-like tether using...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/20G06F119/14
CPCG06F30/20G06F2119/06
Inventor 余本嵩金栋平文浩代朋宾
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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