Energy-optimal large-angle attitude maneuver control method for linear pseudospectral spacecraft
An energy-optimized and attitude-maneuvering technology, applied in attitude control, aircraft, space navigation aircraft, etc., can solve the problems of inability to guarantee the accuracy of the terminal state, complex calculations, and inability to guarantee the optimal energy consumption of control corrections, etc.
Active Publication Date: 2020-09-18
BEIHANG UNIV
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Problems solved by technology
The problems of the LQR method are as follows: (1) The control quantity obtained by LQR solution is the optimal control correction quantity in the infinite time domain, which cannot guarantee that the terminal state accuracy can meet the requirements within a limited time, nor can it guarantee that the control correction quantity is within a limited time (2) The control correction quantity solved by LQR only guarantees the optimal energy consumption of the control correction quantity, but not the optimal energy consumption of the corrected control quantity; (3) The effect of LQR control depends on Q, The selection of the R array needs to be selected for different attitude maneuver tasks
The main problems faced by the MPC method are that the calculation is too complex, consumes a lot of computer resources, and it is difficult to guarantee the real-time performance of the calculation.
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[0119] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.
[0120] The energy-optimized large-angle attitude maneuver task of an outer space vehicle is described as follows: the vehicle can be regarded as a rigid body, equipped with multiple thrusters that can provide continuous thrust, so that it can generate thrust in the three channels of pitch, roll, and yaw. Continuous but limited control torque. The aircraft needs to realize the maneuver from the initial attitude to the terminal attitude within a ce...
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A linear pseudo-spectrum outer-space aircraft energy optimal large angle attitude maneuvering control method disclosed by the present invention comprises the following steps of initializing a maneuvering task, obtaining an attitude maneuvering energy optimal reference control track, setting the correction method parameters, maneuvering according to the reference control, controlling the updating check, and controlling the instruction correction, and realizes the energy optimal attitude maneuvering satisfying the attitude maneuvering terminal constraint by correcting a reference attitude maneuvering control quantity. The key technology of the present invention is to deduce an analytic formula between the attitude maneuvering terminal state deviation and the control correction quantity basedon the thought of linear pseudo-spectrum model prediction control, and the method has the characteristics of being high in calculation efficiency and solution precision. The linear pseudo-spectrum control can reach the terminal precision approximate to the linear quadratic regulator (LQR) control, thereby realizing the large angle attitude maneuvering within the limited time of the aircraft, andconsuming less energy than the LQR control. Meanwhile, the control instructions are smoother, thereby satisfying the real-time performance of the attitude maneuvering control online use.
Description
technical field [0001] The invention relates to the field of aircraft attitude maneuver control, in particular to a linear pseudo-spectrum outer space aircraft energy optimal large-angle attitude maneuver control method. Background technique [0002] A class of outer space vehicles represented by kinetic energy interceptors usually need to have good attitude maneuvering capabilities in order to achieve mission requirements such as striking targets and evading attacks. Compared with spacecraft represented by artificial satellites and space stations, the attitude maneuvers of such outer space vehicles have the following characteristics: (1) The maneuvering angle is large and the time is short, that is, it is necessary to achieve a large-angle attitude maneuver within a limited time; ( 2) The control method is generally active control, and the reaction control system (RCS) is often used for control; (3) the fuel carried is limited, and the energy consumption of maneuvering is r...
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IPC IPC(8): G05D1/08
CPCB64G1/244
Inventor 陈万春冯逸骏杨良
Owner BEIHANG UNIV