Method for designing controller of multi-interval aircraft model

Abstract

The invention discloses a method for designing a controller of a multi-interval aircraft model, 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 multi-interval system robust stability and solvability conditions are given, selection of desired closed-loop poles of linear 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 multi-interval aircraft system model 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.

Description

technical field [0001] The invention relates to a controller design method, in particular to a controller design method for an aircraft multi-interval 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 good static stability. However, modern and futu...

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Problems solved by technology

[0004] In order to overcome the technical deficiency that the existing robust control theory lacks design steps and is difficult to directly design the flight controller, the present invention provides a controller design method for the multi-interval model of the aircraft; the method provides a robust and stable controller for the actual multi-interval system Approximating the design conditions, directly using the closed-loop expected pole selection of the linear system state feedback, and according to the characteristics that the real parts of all closed-loop expected poles are all negative numbers, the constraint inequality is given to directly design the feedback matrix, which can be obtained from wind tunnel or flight tests The multi-interval system model of the aircraft directly designs the flight controller, which solves the technical problem that the current research only gives the robust stability inequality but cannot directly design the flight controller

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