A Switching Control Method for Satellite Attitude Rapid Maneuvering

Abstract

The invention discloses a satellite attitude rapid maneuver switching control method. A used switching parameter delta is used for judging an amplitude of an angular speed to carry out switching, so that compared with an angular position judging method, the rapid and flexible satellite attitude switching control method can avoid the problem that a satellite attitude cannot enter closed-loop control stage due to factor influence of external interference, inertia perturbation and the like; a used switching parameter gamma can avoid partial time during which a small angular speed is included in when maneuver is started, and avoids the satellite attitude directly entering a closed loop stage during the time when maneuver is started, wherein the partial time meets the condition that the absolute value of omega is less than or equal to delta; and a used switching parameter eta can be used to consider engineering constraint and implement automatic switching of acceleration, constant speed, deceleration and closed loop of the attitude maneuver according to received relative attitude quaternion information. The satellite attitude rapid maneuver switching control method realizes accurate switching; rapid attitude maneuver control can be implemented; maneuver around a quaternion Euler axis is implemented; and path planning and time optimization of attitude maneuver are implemented.

Description

technical field [0001] The invention relates to the technical field of spacecraft attitude control, in particular to a switching control method for rapid maneuvering of satellite attitude. Background technique [0002] Satellites perform attitude maneuver control, and a lot of research has been done at home and abroad, including: [0003] (1) The control methods used include variable structure control, adaptive control, fuzzy control, genetic algorithm, etc. and a combination of related methods. The disadvantage is that the implementation of the method is generally more complicated, and the actual constraints of the on-board computer in the project are not considered; [0004] (2) Although some literatures have properly considered the engineering constraints, the shortcoming is that the output torque of the actuator is not taken as a constraint condition, which has a large gap with the actual engineering; [0005] (3) Many design methods do not use the maximum output torque...

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Problems solved by technology

[0003] (1) The control methods used include variable structure control, adaptive control, fuzzy control, genetic algorithm, etc. and a combination of related methods. The disadvantage is that the implementation of the method is generally more complicated, and the actual constraints of the on-board computer in the project are not considered;

[0004] (2) Although some literatures have properly considered the engineering constraints, the shortcoming is that the output torque of the actuator is not taken as a constraint condition, which has a large gap with the actual engineering;

[0005] (3) Many design methods do not use the maximum output torque of the actuator during the maneuvering process. The disadvantage is that there is a lack of time optimization. When the time index requirements for attitude maneuvering are very strict, the system performance will be affected;

[0006] (4) Some methods use the maximum output torque of the actuator, but the method involves an iterative solution operation. The disadvantage is that the calculation amount is large and the method is complicated;

[0007] (5) Some of the domestically launched satellites have attitude maneuvering capabilities, but the shortcoming is that the rapidity of large-angle maneuvering still has a certain gap with the demand;

[0008] (6) Most of the open-loop maneuvering methods that can be realized in engineering are single-axis attitude maneuvering and maneuvering according to the specified path, which cannot achieve optimal maneuvering

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