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Space intersection control method of two-stage constant thrust

A technology of space rendezvous and control method, which is applied to the propulsion system device of space navigation vehicle, the guidance device of space navigation vehicle, etc., and can solve the problems of demand and large amount of calculation.

Inactive Publication Date: 2012-07-18
NORTHWESTERN POLYTECHNICAL UNIV
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Problems solved by technology

This method takes into account the maximum thrust constraint of the engine, and the optimized engine thrust takes multiple different constant values ​​within the maximum thrust range, and changes with the change of the rendezvous conditions, which requires a large amount of calculation and requires offline optimization

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  • Space intersection control method of two-stage constant thrust
  • Space intersection control method of two-stage constant thrust
  • Space intersection control method of two-stage constant thrust

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Embodiment Construction

[0032] The process of the two-stage fixed thrust space rendezvous control method with limited engine on / off time of the present invention is as follows:

[0033] 1) The discretization model of spacecraft rendezvous motion in relative coordinate system is as formula (1)

[0034] X(k+1)=F(X(k))+G(U(k))+Δ(k) (5)

[0035] The state vector X and the control vector U are

[0036] X=[X 1 x 2 x 3 x 4 x 5 x 6 ] T , U=[u x u y u z ] T

[0037] Among them, X 1 = x, x 2 = y, x 3 = z, And x, y, and z are the relative positions of the tracking spacecraft relative to the target spacecraft; and is the relative velocity of the tracking spacecraft relative to the target spacecraft; u x , u y and u z are the acceleration control quantities of the tracking spacecraft on the three axes of the coordinate system, and the discrete domain of the control quantity amplitude is A U ={-u high ,-u low ,0,u low , u high}, where u high >0 is the maximum acceleration...

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Abstract

The invention discloses a space intersection control method of two-stage constant thrust, which is used for solving the technical problem that the engine is opened and closed frequently during the intersection process when the prior intersection control method of constant thrust is achieved. The technical solution is that the minimum opening-closing time Tmin constraint of the engine is introduced to the intersection control problem of the two-stage constant thrust engine; and the optimal intersection thrust under quadratic optimization function index is designed by rolling forecast principle. Because of considering the minimum opening-closing time constraint of the engine, the problem that the engine is opened and closed frequently is solved and the design difficulty of the engine is reduced; and the optimal design method has good robustness for design model error, measurement error and intersection thrust error.

Description

technical field [0001] The invention relates to a space rendezvous control method, in particular to a two-stage fixed thrust space rendezvous control method. Background technique [0002] The document "The Most Fuel-Efficient Trajectory for Rendezvous with Limited Thrust (Gu Dake, Duan Guangren, Zhang Maorui. Acta Astronautica Sinica, 2010, 31(1): 75-81)" discloses a control method for rendezvous with limited constant thrust. In this method, the thrust constraint is transformed into virtual control without constraint by using triangular transformation technology, the control quantity is described parametrically and expressed as a piecewise constant function, and then the optimal control problem is transformed into a nonlinear programming problem. This method takes into account the maximum thrust constraint of the engine. The optimized engine thrust takes multiple different constant values ​​within the maximum thrust range, and changes with the rendezvous conditions. Conten...

Claims

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Application Information

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IPC IPC(8): B64G1/24B64G1/40
Inventor 侯明善葛志远沈昱恒张松唐成师
Owner NORTHWESTERN POLYTECHNICAL UNIV
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