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Aircraft stability control method

A stable control method and aircraft technology, applied in attitude control, non-electric variable control, control/adjustment system, etc., can solve the problems of seeker azimuth frame angle overrun, overall large interference, seeker loss of capture, etc. Achieve the effect of preventing system divergence, improving accuracy and increasing stability

Inactive Publication Date: 2019-03-01
湖北航天飞行器研究所
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AI Technical Summary

Problems solved by technology

[0004] Aiming at at least one defect or improvement requirement of the prior art, the present invention provides an aircraft stability control method, the purpose of which is to solve the problems of system divergence, seeker azimuth frame angle overrun, Seeker loss problem

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Embodiment Construction

[0043] 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.

[0044] The control principle of the aircraft is that the seeker captures the target information before shooting, the gyro and the meter add components to obtain the angular velocity and overload information of the projectile, the guidance system generates a guidance deviation signal, and the stability control system generates a servo control signal according to the deviation signal, and drives T...

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Abstract

The invention discloses an aircraft stability control method. The method comprises steps: S1, dynamic coefficients affected by a jet vane and an air rudder in pitching, yawing and rolling channels aresuperimposed respectively, and according to the dynamic coefficients after superposition, missile body transfer functions in the pitching, yawing and rolling channels are calculated; S2, a three-loopcontrol structure for the pitching, yawing and rolling channels is established, wherein the three-loop control structure comprises an angular rate feedback loop, a pseudo-attitude angle feedback loopand a trajectory inclination rate feedback loop; S3, according to the missile body transfer functions in the pitching, yawing and rolling channels and the three-loop control structure, pitching, yawing and rolling channel control equations are generated respectively; and S4, the control parameters in the pitching, yawing and rolling channel control equations are matched, and three-channel dynamical decoupling is realized. The air rudder and the jet vane are adopted for linkage control on the aircraft, steady-state errors are eliminated, system divergence caused by integral overshoot is prevented, and attitude stability is realized.

Description

technical field [0001] The invention belongs to the technical field of aircraft stability control, and more specifically relates to an aircraft stability control method. Background technique [0002] The new generation of aircraft widely adopts advanced guidance technologies such as laser, infrared imaging, millimeter wave, optical fiber and dual / multi-mode, and the aircraft guidance technology tends to be diversified. also increased further. Infrared imaging guidance will develop from the first generation of optical-mechanical scanning infrared imaging to the second generation of staring focal plane array infrared imaging, and its intelligence will be further improved. [0003] However, the traditional aircraft guidance technology has the following problems: First, the initial air rudder control force is insufficient due to factors such as low dynamic pressure of the aircraft, large interference of the angular velocity of the exit cylinder, large overall interference, and ...

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Application Information

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IPC IPC(8): G05D1/08
CPCG05D1/0825
Inventor 王莹黄广程新占唐志明李执山马振琨伊蕾赵伟
Owner 湖北航天飞行器研究所
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