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Judgment method for spin motion stability of space ring three-body tether system

A three-body rope, spin motion technology, applied in the field of spacecraft flight, can solve the problem of lack of strict proof from mathematical angles

Active Publication Date: 2021-05-11
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

[0004] To sum up, the existing determination of the spin motion stability of the space multi-body tether system is often limited to the numerical simulation method, lacking a strict proof from the mathematical point of view, and each numerical calculation can only study the stability of a set of system parameters , as a parameter or spin velocity changes, the stability determination needs to be restarted

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  • Judgment method for spin motion stability of space ring three-body tether system
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  • Judgment method for spin motion stability of space ring three-body tether system

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[0054] In order to enable those skilled in the art to better understand the technical solutions of the present invention, the present invention will be further described in detail below in conjunction with specific embodiments.

[0055] The embodiment of the present invention provides a method for judging the spin motion stability of a space ring three-body tether system, which is suitable for a spin ring three-body tether system running in an orbital plane. The spin-ring three-body tether system running in the orbital plane to be determined, such as figure 1 As shown, the three masses are m 1 、m 2 and m 3 satellite and three tethers S 1 , S 2 , S 3 The satellite is connected in sequence by three tethers. The three tethers can withstand tension but not pressure. The length and stiffness of the tethers are L 0 and EA; the center of mass o of the system to be determined is always moving on a fixed circular orbit around the earth with an angular velocity Ω, and the system t...

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Abstract

The invention discloses a method for judging the spin motion stability of a space ring three-body tether system, relates to the technical field of spacecraft flight, and can strictly judge the spin stability of the system theoretically. The invention includes: establishing a non-inertial reference system with the center of mass of the system as the origin to obtain the system dynamics equation; introducing vector form variables to obtain the system disturbance equation; using the variational equation to analyze the stability of the disturbance equation; The initial variable is compared with the relationship between the periodic solution of the spin motion and the characteristic multiplier, so as to determine the stability of the spin motion of the system. The present invention provides an accurate judgment method for the spin motion stability of the ring-shaped three-body tether system from a mathematical point of view, and can quickly and theoretically judge the stability change of the system for the same type of system with different spin speeds and different parameters Happening.

Description

technical field [0001] The invention relates to the technical field of spacecraft flight, in particular to a method for judging the spin motion stability of a space ring three-body tether system. Background technique [0002] The space multi-body tether system is usually composed of three or more satellites formed by tether formation, and the satellites often need to maintain a relatively stable configuration in space to complete various space missions. It is worth noting that using spin to maintain system stability is a method that has attracted the attention of many scientific researchers. For example, Kim et al. studied the Tetra Star-shaped multi-body tether system in space, and a large number of simulation results show that the system is unstable under uncontrolled conditions. [0003] Pizarro-Chong et al. discussed the stability of the radial-axle multibody tether system in a circular orbit. Numerical results show that when the number of satellites is greater than or ...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/20
CPCG06F30/20
Inventor 余本嵩金栋平文浩耿凌璐
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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