Method for designing aircraft controller with nonlinearity

Abstract

The invention discloses a method for designing an aircraft controller with the nonlinearity, which is used for solving the technical problem that an existing robust control principle is lack of design steps, so that a flight controller is difficult to directly design. The invention adopts the technical scheme that a robust stable solvability condition of a system with an uncertain nonlinear term is given out; closed-loop expectation poles fed back by a state of a linear system are directly utilized to select; and according to the characteristic that real parts of all the closed-loop expectation poles are all negative numbers, a limiting condition inequality is given out to directly design a feedback matrix. Therefore, engineering technicians in the research field can directly design the flight controller for a flight model with the uncertain nonlinear term, which is obtained by a wind tunnel or flight test; and the technical problem that in the current research, only a robust stability inequality is given out so as not to directly design the flight controller is solved.

Description

technical field [0001] The invention relates to a controller design method, in particular to a nonlinear aircraft controller design method. 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 future fighter jets ha...

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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 method for designing an aircraft controller containing nonlinearities; The design conditions of the rod-stable controller directly use 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 condition inequality is given to directly design the feedback matrix, which can be used for the wind tunnel Or the aircraft model containing uncertain nonlinear items obtained from the flight test 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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