Method for designing controller of time-varying aircraft model with uncertainty

A design method and technology of aircraft, applied in the direction of adaptive control, general control system, control/regulation system, etc., can solve the problems of inability to directly design the flight controller, lack of design steps, uncertainty, etc.
CN102929142AInactive Publication Date: 2013-02-13NORTHWESTERN POLYTECHNICAL UNIV
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Patent Information

Authority / Receiving Office
CN · China
Current Assignee / Owner
NORTHWESTERN POLYTECHNICAL UNIV
Publication Date
2013-02-13
Estimated Expiration
Not applicable · inactive patent

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Abstract

The invention discloses a method for designing a controller of a time-varying aircraft model with uncertainty, which is used for solving the technical problem that the existing robust control theory lacks design steps, so the flight controller is hard to design directly. The technical scheme is as follows: the time-varying system segmentation robust stability and solvability conditions are given, selection of desired closed-loop poles of linear time-varying system state feedback is directly utilized and a constraint condition inequality direct design feedback matrix is given according to the characteristic that all the real parts of all the desired closed-loop poles are negative, so that the engineering technicians in the research field directly design the flight controller for the time-varying aircraft model with uncertainty obtained through wind tunnel or flight tests, thus solving the technical problem that the current researches only give the robust stability inequality but can not directly design the flight controller.
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Description

technical field

[0001] The invention relates to a controller design method, in particular to a controller design method for an aircraft uncertain time-varying model. Background technique

[0002] Aircraft robust control is one of the key topics in the current international aviation research. When designing high-performance aircraft controllers, robust stability and robust control issues must be considered; the actual aircraft model is a very complex nonlinear model with unknown model structure. Differential equations, in order to describe this complex nonlinearity, people usually use wind tunnel and flight tests to obtain test models described by discrete data; in order to reduce risks and reduce test costs, flight maneuver tests are usually carried out according to different altitudes and Mach numbers, so that , there are not many discrete data describing the aircraft test model, and this model is very practical for the aircraft with better static stability. However, moder...

Claims

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