Aircraft anti-interference control method under information fusion

A control method and aircraft technology, applied in the direction of adaptive control, general control system, control/regulation system, etc., can solve the problem of unmeasurable state of aircraft

Active Publication Date: 2020-10-02
NORTHWESTERN POLYTECHNICAL UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The purpose of the present invention is to provide an aircraft anti-jamming control method under information fusion to solve t...

Method used

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  • Aircraft anti-interference control method under information fusion
  • Aircraft anti-interference control method under information fusion
  • Aircraft anti-interference control method under information fusion

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Embodiment Construction

[0080] Now in conjunction with embodiment, accompanying drawing, the present invention will be further described:

[0081] A flow chart of an aircraft anti-jamming control method under information fusion of the present invention is as follows figure 1 As shown, the content of the invention is used to improve the tracking control problem when the aircraft has unknown time-varying disturbances and some system states are unmeasurable. The specific implementation steps are as follows:

[0082] (a) The longitudinal dynamics model of the aircraft considering the unknown time-varying disturbance is

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[0088] Among them, V, h, γ, α and q represent speed, altitude, track angle, angle of attack and pitch angle rate respectively; D, L and M A Respectively represent the drag force, lift force and pitching moment; m, I y and g respectively represent the mass of the aircraft, the moment of inertia of the y-axis and the acceleratio...

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Abstract

The invention relates to an aircraft anti-interference control method under information fusion, belongs to the field of information fusion control methods, and is used for solving the problems of unmeasurable partial state of an aircraft, model uncertainty and tracking control under external interference. The method comprises the steps of: considering the conditions that the partial state of the system is unmeasurable and unknown noise exists, fusing flight control information and inertial navigation information by utilizing adaptive Kalman filtering to realize state estimation; converting theheight subsystem into a strict feedback form, and designing a controller by adopting a backstepping method strategy based on a state estimation value; and designing a disturbance observer to estimatethe uncertain part aiming at the set disturbance formed by the uncertainty of the aircraft model and the external disturbance. According to the method, inertial navigation/flight control system information fusion and flight controller design are organically combined, and an effective way is provided for solving the problem of tracking control when part of states of the aircraft are unmeasurable and model uncertainty and external interference exist.

Description

technical field [0001] The invention relates to a flight control method, in particular to an aircraft anti-jamming control method under information fusion, and belongs to the field of information fusion control methods. Background technique [0002] The design of the flight control system is an important basis for ensuring the safe flight of the aircraft. The backstepping method is widely used in the design of flight control systems, but it requires accurate system models, no interference in the external environment, and there is a "complexity explosion" problem. In order to solve this problem, dynamic surface design and command filter design are applied to reduce the design the complexity. At present, many intelligent controls used in the design of flight control systems are completely measurable based on the state, but in the actual system, some system states are not easy to measure directly, or due to the limitations of the measurement equipment in terms of economy and p...

Claims

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Application Information

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IPC IPC(8): G05B13/04
CPCG05B13/042
Inventor 许斌梁帅呼卫军
Owner NORTHWESTERN POLYTECHNICAL UNIV
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