Combined satellite simulator control method based on discrete high-order all-drive system method

Abstract

The invention discloses a combined satellite simulator control method based on a discrete high-order all-drive system method, and belongs to the technical field of spacecraft control. The method comprises the steps of 1, establishing a discrete high-order all-drive system model for a combined satellite simulator system of a laboratory; step 2, proposing a control target; step 3, establishing an augmentation system; 4, designing a feedback controller and solving problems; 5, parameterizing the control law; and 6, performing experimental verification. According to the invention, the ground environment is utilized to simulate the combined body motion control after the service satellite captures the target satellite in the real space environment, and compared with the traditional related research about the motion control of the combined spacecraft, the invention provides an experimental link support for the provided control method; the complexity of converting an original system model into a first-order state space model and the difficulty of processing nonlinearity and other problems under a state space method framework are avoided, meanwhile, the controller design method is simple, the parameter solving process numerical value is stable, and certain engineering value is achieved.

Description

technical field [0001] The invention belongs to the technical field of spacecraft control, and in particular relates to a combined satellite simulator control method based on a discrete high-order full-drive system method. Background technique [0002] Generally speaking, the process of the service star capturing the target star in orbit can be divided into four stages: the stage of acquiring the target, the stage of approaching the target, the stage of capturing the target, and the stage of motion control of the assembly after the capture is completed. For the control stage of the assembly, there are two more prominent problems: 1) Since the manipulator has the characteristics of variable structure and strong coupling, its corresponding control system is a nonlinear system, so there are large modeling errors and external disturbances, etc. Many uncertain factors; 2) After the capture is completed, the mechanical parameters such as mass, volume, velocity and moment of inerti...

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Problems solved by technology

For the control stage of the assembly, there are two more prominent problems: 1) Since the manipulator has the characteristics of variable structure and strong coupling, its corresponding control system is a nonlinear system, so there are large modeling errors and external disturbances, etc. Many uncertain factors; 2) After the capture is completed, the mechanical parameters such as mass, volume, velocity and moment of inertia of the assembly will change suddenly, and the target star may still have disturbing forces and moments, which may lead to the original control The parameters cannot meet the performance requirements, and even directly cause the combined system to deviate from the stable state

[0003] On the one hand, most of the existing studies on the motion control of combined spacecraft are based on the framework of the first-order state-space method for system analysis and design. It is necessary to transform the high-order original model of the system into a state-space model, which is a cumbersome process. Moreover, under the framework of the state-space method, dealing with nonlinear problems brings many problems and challenges; on the other hand, from the perspective of practical application, the relevant analysis of most studies only stays at the simulation level, and there is no experimental link. support

Moreover, for the simulation experiments related to the motion control of combined spacecraft, due to the high cost of experimental equipment, the difficulty of system construction, and the high requirements of the microgravity environment required, it is generally difficult to achieve

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