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

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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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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