Rendezvous control method for spacecrafts between orbits at instable libration points of solar-terrestrial systems

A control method and technology for rail rendezvous, which are applied in non-electric variable control, adaptive control, general control systems, etc., and can solve the problems that open-loop control is susceptible to external disturbances and model errors.

Inactive Publication Date: 2015-07-22
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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  • Rendezvous control method for spacecrafts between orbits at instable libration points of solar-terrestrial systems
  • Rendezvous control method for spacecrafts between orbits at instable libration points of solar-terrestrial systems
  • Rendezvous control method for spacecrafts between orbits at instable libration points of solar-terrestrial systems

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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 rendezvous control method for spacecrafts between orbits at instable libration points of solar-terrestrial systems. The rendezvous control method includes determining rendezvous initial orbits, target orbits and rendezvous process time of the spacecrafts between the orbits at the libration points of the solar-terrestrial systems and building rendezvous kinetic models of the controlled spacecrafts; creating nonlinear optimal control problems on the basis of the built rendezvous kinetic models of the controlled spacecrafts; solving the nonlinear optimal control problems by the aid of symplectic preservation numerical processes within a long finite time to obtain co-state variables; updating control input in current time subintervals by the aid of the obtained co-state variables, kinetically simulating each time subinterval and acquiring state variables of the current spacecrafts by the aid of navigation processes; carrying out progression on the time subintervals, utilizing terminal states of the current spacecrafts as initial states of a next time subinterval, and sequentially repeatedly carrying out procedures from a step 302 to a step 400 until rendezvous tasks of the spacecrafts between the orbits at the instable libration points are completed. The rendezvous control method has the advantage that the high-precision spacecraft rendezvous objectivity and performance can be guaranteed by the rendezvous control method.

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 locations 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 Applications(China)
IPC IPC(8): G05D1/00G05B13/04
Inventor 彭海军
Owner DALIAN UNIV OF TECH
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