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Compound attitude control method of grid rudder and lateral jet

An attitude control and composite control technology, which is applied in attitude control, space navigation equipment, space navigation aircraft, etc., to meet the requirements of attitude stability indicators, enhance control efficiency, and achieve the effect of good and stable quality.

Active Publication Date: 2017-02-22
THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD
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Problems solved by technology

[0004] At present, for the attitude stabilization control of solid launch vehicles, there is no precedent in China for the combined attitude control of grid rudders and side jets.

Method used

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  • Compound attitude control method of grid rudder and lateral jet
  • Compound attitude control method of grid rudder and lateral jet
  • Compound attitude control method of grid rudder and lateral jet

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Embodiment Construction

[0027] In order to make the object, technical solution and advantages of the present invention clearer, 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.

[0028] figure 1 It is a flow chart of the grid rudder attitude control method of the present invention. Such as figure 1 Shown, the inventive method comprises the following steps:

[0029] S1. Perform interpolation calculation on the original aerodynamic data to obtain the aerodynamic derivative;

[0030] S2. Obtaining the dynamic coefficient of the projectile according to the calculation of...

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Abstract

The invention discloses a compound attitude control method of a grid rudder and a lateral jet. The compound attitude control method comprises the following steps: S1, carrying out interpolation calculation on original aerodynamic data to obtain an aerodynamic derivative; S2, calculating an elastic body dynamic coefficient according to the aerodynamic derivative and analyzing to obtain an elastic body stability index and a maneuverability index; S3, on the basis of aerodynamic performance analysis, carrying out correction network design based on the lateral jet and the grid rudder respectively; designing a corresponding notching filter so as to reduce influences of elastic vibration; in a designing process, considering the elastic body stability index and the maneuverability index; S4, on the basis of the correction network design and notching filter design, carrying out compound control distribution strategy design on two executing mechanisms including the grid rudder and the lateral jet according to control efficiency. According to the method provided by the invention, the grid rudder and the lateral jet are controlled in a compounding manner and stable control of attitudes of a launch vehicle is realized.

Description

technical field [0001] The invention belongs to the technical field of aerospace vehicle attitude control, and more specifically relates to a composite attitude control method of grid rudders and side jets. Background technique [0002] In recent years, emergency space technology has been greatly developed, which puts forward more demands on low-cost solid launch vehicles. In order to reduce the take-off weight and achieve the purpose of miniaturization of the launch vehicle, the grid rudder can be used as the full-motion rudder surface for attitude stabilization control at the first stage of the launch vehicle. The grid rudder has the advantages of high control efficiency and small control hinge moment. However, in the initial stage of take-off of the launch vehicle, due to the small dynamic pressure, the control efficiency of the grid rudder is very low, and the influence of the disturbance torque cannot be overcome to make the launch vehicle fly stably. The method not o...

Claims

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Application Information

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IPC IPC(8): G05D1/08
CPCB64G1/244
Inventor 郭一江姚少君李焰蒋金龙王志军田群方鲍晓强朱伟杨登峰陈兴褔苏茂
Owner THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD
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