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Nonlinear dynamic inverse control method and device for turboshaft engine

A turboshaft engine, nonlinear dynamic technology, applied in geometric CAD, design optimization/simulation, special data processing applications, etc., can solve the problems of difficult smooth transition of the controller, affecting system stability, etc. The effect of sagging

Inactive Publication Date: 2020-06-05
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Application Information

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Problems solved by technology

However, switching controllers often affects the stability of the system, and it is difficult to transition smoothly between different controllers

Method used

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  • Nonlinear dynamic inverse control method and device for turboshaft engine
  • Nonlinear dynamic inverse control method and device for turboshaft engine
  • Nonlinear dynamic inverse control method and device for turboshaft engine

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Embodiment Construction

[0057] In order to realize the rapid response control of the turboshaft engine, the idea of ​​the present invention is to introduce the nonlinear inverse control method into the turboshaft engine control, and propose a corresponding nonlinear inverse control law according to the actual situation of the turboshaft engine, so as to effectively reduce the helicopter maneuver. Overshoot and droop of turboshaft engine power turbine speed during flight. On this basis, the present invention further uses the Jacobian matrix and the sequence quadratic optimization algorithm to obtain online the state variable model that can accurately express the stability and dynamic characteristics of the turboshaft engine under different flight conditions, and is used for the nonlinear dynamic inversion of the turboshaft engine. control, which improves the robustness of the nonlinear dynamic inverse controller.

[0058] Specifically, the nonlinear dynamic inverse control method of the turboshaft eng...

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Abstract

The invention discloses a nonlinear dynamic inverse control method of a turboshaft engine. The non-linear inverse control method is introduced into the turboshaft engine control for the first time, thereby effectively reducing overshoot and sag of turboshaft engine power turbine speed during helicopter maneuvering flight. The invention further utilizes the Jacobian matrix and the sequential quadratic optimization algorithm to obtain on-line state variable models which can accurately express the stable and dynamic characteristics of the turboshaft engine under different flight conditions, and is used for the nonlinear dynamic inverse control of the turboshaft engine, thereby improving the robustness of the nonlinear dynamic inverse controller. The invention also discloses a non-linear dynamic inverse control device of the turboshaft engine. The invention not only can be applied to the closed-loop control of the power turbine speed of the turboshaft engine under different flight conditions, but also can effectively reduce the overshoot and sag of the power turbine speed during the maneuver flight of the helicopter, thereby realizing the rapid response control of the turboshaft engine.

Description

technical field [0001] The invention relates to a turboshaft engine control method, which belongs to the technical field of system control and simulation in aerospace propulsion theory and engineering. Background technique [0002] With its unique performance advantages, helicopters are increasingly playing an important role in military and civilian fields. Since the 1950s, turboshaft engines have become the main power plant of helicopters due to their outstanding advantages such as light weight, large power-to-weight ratio, low vibration, and easy operation (see [Parametric Instability of Face-gearDrives with a SpurPinion[C] ]). The turboshaft engine drives the rotor and the tail rotor through the power turbine, the transmission system consisting of the reducer and the transmission shaft (see the literature [Modeling and Characteristics of Torsional Vibration of Helicopter Tail Drive System [J]]). In order to meet the high-performance requirements of helicopters, the new ...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/15G06F30/20
CPCG06F30/15G06F30/20
Inventor 张海波汪勇杜紫岩陈浩颖郑前钢
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS