Variant aircraft T-S fuzzy control method based on Kalman filtering

A variant aircraft and fuzzy control technology, applied in the direction of non-electric variable control, attitude control, control/adjustment system, etc., to achieve the effect of tracking control and continuous control system

Inactive Publication Date: 2020-08-25
NORTHWESTERN POLYTECHNICAL UNIV
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Problems solved by technology

[0005] The object of the present invention is to provide a kind of variant aircraft T-S fuzzy control method based on Kalman filter, to solve the tracking control problem of variant aircraft when the partial state of the system is unmeasurable

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  • Variant aircraft T-S fuzzy control method based on Kalman filtering
  • Variant aircraft T-S fuzzy control method based on Kalman filtering
  • Variant aircraft T-S fuzzy control method based on Kalman filtering

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Embodiment Construction

[0043] Now in conjunction with embodiment, accompanying drawing, the present invention will be further described:

[0044] A kind of variant aircraft T-S fuzzy control method flow chart based on Kalman filtering 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 some states of the variant aircraft are unmeasurable. The specific implementation steps are as follows:

[0045] (a) Considering the nonlinear dynamic model of the variant aircraft

[0046]

[0047] Among them, V represents the flight speed; h represents the flight height; γ represents the track angle; α represents the angle of attack; q represents the pitch rate; 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 acceleration of gravity; F Ix , F Iz , F Ikz and M Iy respectively represen...

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Abstract

The invention relates to a variant aircraft T-S fuzzy control method based on Kalman filtering. According to the method, an aircraft model is divided into a plurality of subsystems according to different deformation structures of a morphing aircraft, a small disturbance linearization method is adopted to obtain local linearization models at balance points of the different subsystems, and then a global T-S fuzzy model is constructed through a fuzzy set and a fuzzy rule based on the local linearization models; considering that part of the state of the morphing aircraft is unmeasurable and measurement noise exists, and fusing flight control information and inertial navigation information by utilizing a Kalman filter to realize state reconstruction; and finally, designing a global T-S fuzzy controller based on the system state estimation value.

Description

technical field [0001] The invention relates to flight control of a variant aircraft, in particular to a T-S fuzzy control method for a variant aircraft based on Kalman filtering, and belongs to the field of information fusion control methods. Background technique [0002] The morphing aircraft is a multifunctional and multi-form new aircraft. Its main feature is that it can obtain the best aerodynamic characteristics suitable for the current flight environment by adjusting its external structure. This feature makes the morphing aircraft applicable to more complex Flight environment and special mission requirements. [0003] The aerodynamic force, aerodynamic moment, center of gravity, and moment of inertia of the morphing aircraft will change greatly during the deformation process. The aircraft has strong time-varying and nonlinear characteristics, which makes the controller design of the morphing aircraft more complicated. At present, controllers for morphing aircraft hav...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D1/08G05D1/10
CPCG05D1/0825G05D1/101
Inventor 许斌梁帅张睿寿莹鑫
Owner NORTHWESTERN POLYTECHNICAL UNIV
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