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Control Method of Rocket Booster Launch Based on Robust Control Theory

A theoretical and robust technology, applied in the field of aircraft flight control, can solve the problems of the control system's weak anti-interference ability, the failure of the UAV to launch and take off, and the high sensor configuration requirements, so as to achieve a stable control effect and suppress the excessive angle of attack. The effect of large and lower production cost

Active Publication Date: 2020-11-20
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

[0002] At present, the take-off process of most target drones adopts the take-off and launch method based on pitch angle control. This control method adopts the take-off and launch method of fixed pitch angle based on the classic PID control theory. Its advantages are simple control structure and simple design process. , which is easy to implement in engineering, but the disadvantage is that the control system is not strong in anti-interference ability and poor in robustness. In addition, it has high requirements for sensor configuration, and an attitude angle sensor is required.
[0003] For conventional reconnaissance, strike or reconnaissance UAVs, this sensor configuration is more reasonable, but for target drones positioned as pure consumables, the sensor configuration cost of this control method is relatively high, and the attitude angle-based The control method lacks quick and effective suppression measures for the external disturbance torque generated by the thrust point of the rocket but not the center of gravity. The man-machine launch failed to take off, so it is urgent to propose a control strategy with strong robustness, fast response speed and low production cost. The present invention is produced under this background

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  • Control Method of Rocket Booster Launch Based on Robust Control Theory
  • Control Method of Rocket Booster Launch Based on Robust Control Theory
  • Control Method of Rocket Booster Launch Based on Robust Control Theory

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Embodiment Construction

[0051]Embodiments of the invention are described in detail below, examples of which are illustrated in the accompanying drawings. The embodiments described below by referring to the figures are exemplary only for explaining the present invention and should not be construed as limiting the present invention.

[0052] The control method of the rocket-boosted launch based on the angular rate plus fusion climb angle compensation based on the robust control theory, the specific design steps are as follows:

[0053] Step 1, design an inner loop controller based on robust servo control theory;

[0054] like figure 2 As shown, it is a robust servo chain structure. In the figure, a and K are the coefficients of the chain proportional term and the chain integral term respectively. Robust servo control is a typical optimal control method, which combines the advantages of robust analysis method and quadratic optimal control, and integrates the system's requirements for robust stability...

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Abstract

The invention discloses a robust control theory-based rocket-assisted launching control method adopting angular rate control and fusion climbing angle compensation. Compared with an attitude control method based on the elevation angle, the method adopts an angular rate control method in the launching process of a certain target aircraft, and can accelerate the response to unfavorable disturbance suppression in the launching process, improve the capacity of a system for resisting external uncertain interference and guarantee that the target aircraft is launched and takes off safely; besides, based on the angular rate control method, the hardware production cost of the target aircraft is greatly reduced, and meanwhile the success rate and reliability of rocket-assisted launching can be improved.

Description

technical field [0001] The present invention relates to a control strategy for the launching section of a rocket-assisted unmanned aerial vehicle, in particular to a control method for the take-off and launching section of a target drone configured with low-cost sensors, and specifically relates to an anti-friction control strategy based on robust servo control theory plus fusion climb angle compensation. The invention relates to a disruptive launch take-off technology, which belongs to the technical field of aircraft flight control. Background technique [0002] At present, the take-off process of most target drones adopts the take-off and launch method based on pitch angle control. This control method adopts the take-off and launch method of fixed pitch angle based on the classic PID control theory. Its advantages are simple control structure and simple design process. , is easy to implement in engineering, but the disadvantage is that the control system is not strong in a...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05D1/08G05D1/10
CPCG05D1/0825G05D1/101
Inventor 李春涛李雪兵聂禾玮陈桃
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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