Method for designing controller of aircraft model with uncertainty

Abstract

The invention discloses a method for designing a controller of an 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 method has the following beneficial effects: the 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 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.

Description

technical field [0001] The invention relates to a controller design method, in particular to a controller design method of an aircraft uncertain 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, modern and future f...

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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 uncertain model of the aircraft; the method provides the design conditions of the actual system robust and stable controller , 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 used for wind tunnel or flight tests. The deterministic aircraft model directly designs the flight controller, which solves the technical problem that the current research only gives the robust stability inequality and cannot directly design the flight controller

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