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Attitude angular velocity control method and device, computer equipment and storage medium

A speed control and attitude angle technology, which is applied in the fields of devices, computer equipment and storage media, and attitude angular velocity control methods to achieve the effects of restraining attitude drift, reducing attitude angle deviation, and achieving stable control.

Pending Publication Date: 2022-04-12
重庆零壹空间航天科技有限公司 +4
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Problems solved by technology

[0004] In view of the deficiencies in the prior art, the attitude angular velocity control method, device, computer equipment and storage medium provided by the present invention solve the problem that there is a strong coupling between the traditional attitude angular velocity and affect the attitude control. The model is connected in series with the rocket kinematics model to obtain an integral decoupling linear system model, so that there is a pseudo-linear transfer relationship between the input and output of the system model after series and there is no coupling correlation, so that the decoupling control between channels can be realized, and It can effectively suppress the attitude drift, reduce the attitude angle deviation, and realize the stable control of the rocket

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  • Attitude angular velocity control method and device, computer equipment and storage medium

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[0029] In order to make the purposes, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments It is a part of the embodiments of this application, but not all of them. Based on the embodiments in the present application, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present application.

[0030] figure 1 Shown is a schematic flow chart of an attitude angular velocity control method provided by an embodiment of the present invention; figure 1 As shown, the attitude angular velocity control method specifically includes the following steps:

[0031] Step S101, generating a dynamic inverse system model according to the roc...

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Abstract

The invention provides an attitude angular velocity control method and device, computer equipment and a storage medium, and the method comprises the steps: generating a dynamic inverse system model according to a rocket kinematics model; obtaining a target attitude angular acceleration according to the current attitude angular velocity control instruction and the current attitude angular velocity; inputting the target attitude angular acceleration into the dynamic inverse system model to obtain a target rudder deflection angle; inputting the target rudder deflection angle into the rocket kinematic model to obtain a target attitude angular velocity in the current attitude angular velocity control instruction, and controlling the rocket to operate according to the target attitude angular velocity; according to the invention, the dynamic inverse system model and the rocket kinematics model are connected in series to obtain the integral decoupling type linear system model, so that decoupling control between channels can be realized, attitude drift can be effectively inhibited, attitude angle deviation can be reduced, and stable control of the rocket can be realized.

Description

technical field [0001] The present invention relates to the technical field of attitude angle control, in particular to an attitude angle velocity control method, device, computer equipment and storage medium. Background technique [0002] At present, after the rocket is separated between stages, the conventional method is to independently control the attitude angle through the three channels of the rocket. However, due to the reverse thrust interference and aerodynamic interference, the attitude angular velocity is relatively large, and the large attitude angular velocity will cause the three channels to appear relatively large. Strong coupling will lead to unstable attitude control, causing the rocket attitude to deviate from the standard trajectory, and affecting the stable and reliable flight of the aircraft. [0003] It can be seen that the control method of the rocket attitude angular velocity in the prior art cannot solve the problem of strong coupling between the att...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D1/08
Inventor 凡玉龙舒畅马超
Owner 重庆零壹空间航天科技有限公司
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