Design method of comprehensive disturbance rejection control system for single-rotor wing helicopter/turboshaft engine

Abstract

The invention discloses a design method of a comprehensive disturbance rejection control system for a single-rotor wing helicopter / turboshaft engine. The invention designs a helicopter multi-model fused robust controller for controlling a helicopter and a turboshaft engine nonlinear model forecasting controller for controlling a turboshaft engine respectively, wherein the multi-model fused robust controller is obtained with a method comprising the following steps of: firstly, selecting a certain characteristic parameter of a controlled object, and partitioning the range of the characteristic parameter into a plurality of control subspaces; secondly, designing a corresponding sub-controller in each control subspace respectively; and lastly, performing online fusion on each sub-controller; and the nonlinear model forecasting controller is established with a method comprising the following steps of: training a turboshaft engine model on line to obtain a forecasting model; performing rolling optimization design on the forecasting model with a sequence secondary planning algorithm library; and performing feedback compensation. According to the method, the disturbance rejection capability of a single-rotor wing helicopter / turboshaft engine comprehensive control system can be improved remarkably.

Description

technical field [0001] The invention belongs to the field of system control and simulation in aerospace propulsion theory and engineering, and specifically relates to a design method for a single-rotor helicopter / turboshaft engine integrated anti-disturbance control system. Background technique [0002] Helicopter, a very complex multi-variable nonlinear object, its dynamics is unstable and non-minimum phase characteristics even in the vicinity of the equilibrium point in a small range. Advanced control algorithms such as PID control, LQR control, H∞ control, etc. have been far from meeting the needs. In recent years, with the rapid development of methods such as modern robust control and adaptive control, to a certain extent, it provides a good technical means for the design of control laws of complex multivariable objects, but these methods are only suitable for objects with uncertain If it is too large, for a highly nonlinear object like a helicopter, only a single robus...

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Problems solved by technology

[0004] Domestic and foreign helicopter power system control has long used simple manipulation input (such as total moment or torque, etc.) feedforward + proportional differential link, Smith B J et al. in 2001 "Next generation control system for helicopter engines" article gave a The structure of vibration filter feedback + neural network transient torque feedforward can increase the bandwidth of the closed-loop system and improve the performance of the helicopter from a dynamic point of view, but its shortcomings are also obvious, that is, it is strongly dependent on the accurate online real-time model, and at the same time it must have Excellent online optimization algorithm, the cost of project implementation is relatively high

Secondly, Garg S et al. introduced an engine nonlinear predictive control technology in "Introduction to advanced engine control concepts" in 2007, but it was only applied in turbofan engines, and only Yao Wenrong in 2008 " Turboshaft Engine Nonlinear Model Predictive Control” has done related research work, and realized the anti-disturbance control of the engine under small disturbances, but it is only based on the turboshaft engine with rotors, and there is no complete helicopter / turboshaft engine system

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