Aircraft multi-time delay model approach and controller design method

Abstract

The invention discloses an aircraft multi-time delay model approach and controller design method, which is used for solving the technical problem of difficulty in directly designing an aircraft controller due to lack of a design step of the traditional robust control theory. In the technical scheme, robust stabilizing solvable conditions of a time varying system according to segments are given, a closed loop expected poles fed back by the state of a linear system is directly utilized to select, and according to the characteristic that all real parts of the closed loop expected poles are negative numbers, a limitation conditional inequality is given to directly design a feedback matrix. By the aircraft multi-time delay model approach and controller design method, engineering technical staff in the research field obtains an aircraft model containing the uncertainty of a plurality of time delays from wind tunnel or flight tests to directly design the aircraft controller, and the technical problem that the aircraft controller cannot be directly designed and only the robust stability inequality is given by the current research is solved.

Description

technical field [0001] The invention relates to a controller design method, in particular to an aircraft multiple time-lag model approximation and 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 better static stability. However...

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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 approaching multiple time-lag models of an aircraft and a controller design method; the method provides a robust and stable controller for the actual system Multiple time lags approaching 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, the constraint inequality is given to directly design the feedback matrix, which can be used for wind The flight controller can be directly designed from the aircraft model containing multiple time lag uncertainties obtained from the hole or flight test, 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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