A method for determining that stability of spin motion of three-body tether system in space

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: 2019-02-19
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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  • A method for determining that stability of spin motion of three-body tether system in space
  • A method for determining that stability of spin motion of three-body tether system in space
  • A method for determining that stability of spin motion of three-body tether system in space

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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

A method for determining that stability of spin motion of three-body tether system in space relates to the technical field of spacecraft flight and can determine the spin stability of the system strictly in theory. The invention discloses a method for judging the spin stability of a space loop three-body tether system. The invention comprises the following steps: establishing a non-inertial reference frame with the mass center of the system as the origin, and obtaining a system dynamics equation; The disturbance equation of the system is obtained by introducing vector formal variables. The stability of perturbed equation is analyzed by variational equation. By setting the initial variables of the periodic solution of the spin motion of the system and comparing the relationship between theperiodic solution of the spin motion and the characteristic multiplier, the stability of the spin motion of the system is determined. The invention provides an accurate judging method for the stability of the spin motion of the loop three-body tether system from the mathematical point of view, and can quickly judge the stability change of the system for the same system with different spin velocities and different parameters in theory.

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 Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/20
Inventor 余本嵩金栋平文浩耿凌璐
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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