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A control method for spacecraft rendezvous between orbits of unstable translation points of the sun-earth system

A control method and track rendezvous technology, applied in the direction of non-electric variable control, adaptive control, general control system, etc., can solve the problems of model error influence, open-loop control susceptible to external interference, etc., to overcome navigation error and meet real-time Sexual needs, effects of overcoming limitations in normal rendezvous

Inactive Publication Date: 2017-08-25
DALIAN UNIV OF TECH
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Problems solved by technology

[0003] The invention mainly solves the problem that the open-loop control of the rendezvous of the spacecraft between the orbit families of the unstable translation points of the sun-earth system is easily affected by external interference and model errors, and proposes a method for the spacecraft to rendezvous between the orbits of the unstable translation points of the sun-earth system. The rendezvous control method adopts online solution for open-loop nonlinear optimal control, and continuously updates the control input to form closed-loop control. Feedback information can be used to offset the influence of external disturbances and model errors, ensuring the objectivity and performance of high-precision spacecraft rendezvous

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  • A control method for spacecraft rendezvous between orbits of unstable translation points of the sun-earth system
  • A control method for spacecraft rendezvous between orbits of unstable translation points of the sun-earth system
  • A control method for spacecraft rendezvous between orbits of unstable translation points of the sun-earth system

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[0041]In order to make the technical problems solved by the present invention, the technical solutions adopted and the technical effects achieved clearer, the present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the present invention, but not to limit the present invention. In addition, it should be noted that, for the convenience of description, only parts related to the present invention are shown in the drawings but not all content.

[0042] image 3 The implementation flow chart of the control method for spacecraft rendezvous between orbits of unstable translation points of the sun-earth system provided by the embodiment of the present invention. Such as image 3 As shown, the spacecraft rendezvous control method provided by the embodiment of the present invention between the orbits of the unstable translation...

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Abstract

The invention provides a method for controlling the rendezvous between orbits of a spacecraft at an unstable translation point of the sun-terrestrial system. The method includes: determining the initial orbit, target orbit and time of the rendezvous process of the spacecraft at the orbit rendezvous of the translation point of the sun-terrestrial system, and establishing a controlled aerospace based on the established controlled spacecraft rendezvous dynamics model, a nonlinear optimal control problem is established; the nonlinear optimal control problem is solved by the symplectic numerical method in a finite time, and the co-state variables are obtained; The obtained co-state variables update the control input of the current sub-time interval, complete the dynamics simulation of a sub-time interval, and use the navigation method to obtain the current spacecraft state variables; carry out the progress of the sub-time interval, taking the current spacecraft terminal state as the lower For the initial state of a sub-time interval, steps 302 to 400 are repeated in sequence until the task of rendezvous between the orbits of the unstable translation point of the spacecraft is completed. The invention can ensure the objectivity and performance of high-precision spacecraft rendezvous.

Description

technical field [0001] The invention relates to the technical field of spacecraft deep space exploration, in particular to a control method for spacecraft rendezvous between orbits of unstable translation points of the sun-earth system. Background technique [0002] Deep space exploration, especially space exploration near the translation point, is an important research task in the field of spaceflight in recent years. figure 1 It is a schematic diagram of the circular restrictive three-body model of the Sun-Earth system. refer to figure 1 , due to the balance of gravity and centrifugal force at the three collinear unstable translation points of the circular restricted three-body problem, these spatial positions are ideal places for placing space equipment such as space stations and space telescopes. figure 2 It is the rendezvous diagram of the spacecraft between the north and south Halo near the L2 translation point of the sun-earth system. refer to figure 2 , a typic...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05D1/00G05B13/04
Inventor 彭海军
Owner DALIAN UNIV OF TECH
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