No-model adaptive control method for assembled spacecraft attitude and system thereof

An adaptive control and spacecraft technology, applied in the directions of adaptive control, attitude control, general control system, etc., can solve the problems of controller failure, system output data not responding in real time, and inability to effectively control the combined spacecraft, etc. To achieve the effect of improving the accuracy of attitude determination

Inactive Publication Date: 2018-06-05
SHANGHAI AEROSPACE CONTROL TECH INST
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Problems solved by technology

However, when the system has a large time lag, since the system output data obtained by the combined spacecraft is not a real-time response, the adaptive iterative process of the controller will fail, resulting in the controller being unable to effectively control the combined spacecraft

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  • No-model adaptive control method for assembled spacecraft attitude and system thereof
  • No-model adaptive control method for assembled spacecraft attitude and system thereof
  • No-model adaptive control method for assembled spacecraft attitude and system thereof

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Embodiment Construction

[0037] In order to make the purpose, technical solution and advantages of the present invention clearer, the following will further describe the public implementation manners of the present invention in detail with reference to the accompanying drawings.

[0038] refer to figure 1 , shows a flow chart of the steps of a model-free adaptive control method for the attitude of a combined spacecraft in an embodiment of the present invention. refer to figure 2 , shows a schematic workflow diagram of a model-free adaptive control method for the attitude of a combined spacecraft in an embodiment of the present invention. In this embodiment, the model-free adaptive control method of the combined spacecraft attitude includes:

[0039] Step 101, according to the historical control input and historical system output of the combined spacecraft, by minimizing the estimation criterion function, the online parameter estimation of the pseudo-Jacobian matrix in the compact dynamic equivalent...

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Abstract

The invention discloses a no-model adaptive control method for an assembled spacecraft attitude and a system thereof, wherein the method comprises the steps of performing online parameter estimation on a pseudo-Jacobian matrix in a compact-format dynamic equivalent linear model according to historical control input and historical system output of the assembled spacecraft through a minimization estimation criterion function, and obtaining an estimated value of the pseudo-Jacobian matrix; according to the estimated value of the pseudo-Jacobian matrix, through a frontward forecasting error criterion function, obtaining a control input estimated value at a next time point; and using the control input estimated value at the next time point as the control input of the assembled spacecraft at thenext time point, thereby finishing no-model adaptive control of the assembled spacecraft attitude. Through the no-model adaptive control method and the system thereof, adaptive controlling to the long-time-delay assembled spacecraft is realized.

Description

technical field [0001] The invention belongs to the technical field of combined spacecraft control, in particular to a model-free adaptive control method and system for combined spacecraft attitude. Background technique [0002] For the combination formed after the spacecraft captures the non-cooperative target, on the one hand, due to the unknown model parameters of the non-cooperative target, the combination cannot be accurately modeled; on the other hand, due to the incomplete constraints between the captured spacecraft and the target, the combined There may be a time lag in the body system. [0003] At present, for the control of the combined spacecraft, the following method is usually adopted: using the input and output data to design a model-free adaptive controller. However, when the system has a large time lag, since the system output data obtained by the combined spacecraft is not a real-time response, the adaptive iterative process of the controller will fail, res...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B13/04G05D1/08
CPCB64G1/244G05B13/042
Inventor 贺亮袁建平宋婷张宪亮孙俊
Owner SHANGHAI AEROSPACE CONTROL TECH INST
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