Elastic Vibration Suppression Method Based on Side Jet Flow Control
A technology of elastic vibration and jet flow control, applied in attitude control, motor vehicles, space navigation equipment, etc., can solve problems such as difficult to achieve precise control of attitude angle, high frequency elastic vibration, consumption of propellant, etc., and achieve good control effect , suppression of interference, and enhanced control efficiency
Active Publication Date: 2021-03-02
THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD
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However, the amount of interference in each flight segment of the launch vehicle is different. Since multiple flight segments share a set of side-jet attitude control engines, the control capability is fixed. When the side-jet attitude control engines provide the same control torque , it will appear that the control torque is much greater than the disturbance torque in some cases. In this case, if no measures are taken, the nozzle will open and close repeatedly, which not only consumes a lot of propellant, but also easily produces high-frequency elastic vibration Phenomenon, it is difficult to achieve precise control of attitude angle and attitude angle rate
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[0018] The present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments.
[0019] In order to make the object, technical solution and advantages of the present invention more clear, the present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the present invention, not to limit the present invention. In addition, the technical features involved in the various embodiments of the present invention described below can be combined with each other as long as they do not constitute a conflict with each other.
[0020] The working principle of the elastic vibration suppression based on the side jet flow control of the present invention is as follows: figure 2 As shown, the control amount is the attitude angle deviation. The attitude angle deviation passes ...
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The present invention relates to a method for suppressing elastic vibration based on side jet flow control. The method includes the following steps: S1. Inputting environmental professional data; Mathematical model of angular velocity of the elastic rocket body; S3. Design the corresponding filter according to the elastic motion characteristics of the rocket body; S4. Design the control threshold that matches the control performance, and reasonably control the opening frequency of the side jet nozzle; S5. Design intelligent energy-saving control The strategy enables adaptive adjustment of the opening frequency threshold. The elastic vibration suppression method based on the side jet flow control of the present invention can realize the intelligent adaptive control strategy of the side jet flow attitude control engine switching action, and can suppress the interference of the high frequency elastic vibration to the attitude control to the greatest extent, so that the control efficiency is greatly enhanced , to meet the requirements of solid launch vehicle attitude control accuracy.
Description
technical field [0001] The invention relates to attitude control of aerospace vehicles, in particular to a method for suppressing elastic vibration based on side jet flow control. Background technique [0002] In recent years, the rapid development of solid launch vehicle technology has put forward more demands. In order to simplify the control system of the launch vehicle, reduce the take-off weight, and achieve the goal of low cost and miniaturization, a scheme of attitude control using a set of side-jet attitude control engines for multiple flight segments is adopted. Side jet flow control obtains control torque through high-speed injection mass, which has the advantages of direct generation of control force, fast response speed, and use without environmental restrictions. At present, it has been successfully applied on many domestic launch vehicles. [0003] When the launch vehicle is flying in each flight segment, the mass, center of mass, moment of inertia and aerody...
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IPC IPC(8): G05D1/08
CPCB64G1/244
Inventor 郭一江李焰张力蒋金龙田群方王志军朱伟鲍晓强陈红艳叶昌
Owner THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD