Robust flight controller design method

Abstract

The invention discloses a robust flight controller design method 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 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 robust flight 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, modern and future fighter jets have ...

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Problems solved by technology

[0004] In order to overcome the technical insufficiency that the existing robust control theory design calculation error is too large and it is difficult to directly design the flight controller, the present invention provides a robust flight controller design method; the method provides the practical system robust and stable controller design Sufficient and necessary conditions, directly using the closed-loop expected pole selection configuration weighting matrix of the linear system state feedback, and using the orthogonalization method to solve H ∞ For the control problem, there is no need to repeatedly solve the Riccati equation with complex calculations and large errors, and the flight controller can be directly designed for the uncertain aircraft model obtained from the wind tunnel or flight test, which solves the problem that the current research only gives robust stability The technical problem of not being able to directly design the flight controller due to gender inequality

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