A method of angular velocity control section taking into account angular deviation control

Abstract

The invention discloses a method for angular velocity control section taking into account angular deviation control. The angular velocity is calculated according to the angular deviation of the first cycle of the angular velocity control section, and the angular velocity is used as the target program angular velocity of the angular velocity control after taking inversion and limiting. In this way, the attitude angle can be moved in the direction of reducing the angular deviation, so that the divergence of the angular deviation can be taken into account during the control of the angular velocity, and the continuous increase of the angular deviation can be avoided, which is simple and effective. The method provided by the invention provides an angular velocity control section taking into account angular deviation control to meet the requirements of angular velocity control accuracy before and after throwing the fairing, and to avoid the negative effect of continuous increase in angular deviation caused by long-term uncontrolled attitude angle, and to provide a better solution for launch vehicle throwing fairings. Front and rear flight safety plays a vital role. The invention reduces the complexity of attitude control network design, is simple and reliable, is easy to realize in engineering, and is suitable for wide popularization.

Description

technical field [0001] The invention relates to the technical field of navigation, guidance and control, and in particular to a method for angular velocity control section taking into account angular deviation control. Background technique [0002] When the launch vehicle is flying in the atmosphere, the fairing is used to protect the payload from aerodynamic heating, aerodynamic force, vibration, etc. When the rocket enters the vacuum, the external interference factors disappear, and the fairing needs to be separated. In order to ensure the safety of the fairing ejection process and avoid the risk of collision, the attitude angular velocity of the rocket body must be strictly controlled at a low level for a period of time before and after the ejection. [0003] Therefore, it is required to use angular velocity control first after starting control, and then attitude control, which will cause the attitude angle to be out of control for a long time, and the angular deviation ...

AI Technical Summary

Problems solved by technology

[0003] Therefore, it is required to use angular velocity control first after starting control, and then attitude control, which will cause the attitude angle to be out of control for a long time, and the angular deviation will continue to increase, causing the actual engine thrust line direction to deviate for a long time, and the rocket body speed and position to deviate from the established trajectory. , which adversely affects the iterative guidance accuracy

If angular deviation and angular velocity control are used, it is easy to cause the required value of angular velocity control to be unable to be reached within the specified time, and at the same time increase the complexity of the control network design

[0004] In view of this problem, a solution to the problem existing in the prior art is proposed. In order to ensure the separation safety of the fairing, the launch vehicle needs to control the angular velocity for a long period of time before and after throwing the fairing. This will cause the attitude angle to be out of control and the angular deviation to continue Increase the method of the problem that affects the accuracy of iterative guidance, so as to more properly and effectively solve the contradiction between angular velocity control requirements and attitude angle control accuracy

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