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Nonlinear prediction control design method for variable cycle engine

A variable cycle engine and non-linear prediction technology, applied in the direction of adaptive control, general control system, control/regulation system, etc., can solve the problems of difficult modeling and low model accuracy, achieve great application prospects, improve control performance, Easy to debug

Inactive Publication Date: 2018-06-22
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Abstract
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Problems solved by technology

[0006] Aiming at the deficiencies of the above-mentioned prior art, the purpose of the present invention is to provide a nonlinear predictive control design method for variable cycle engines, which effectively solves the problems of strong nonlinearity, difficult modeling, and low model accuracy of existing variable cycle engines. Under the effective control problem, the present invention does not need the mathematical model of the engine, and the design is simple and the debugging is convenient

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  • Nonlinear prediction control design method for variable cycle engine
  • Nonlinear prediction control design method for variable cycle engine
  • Nonlinear prediction control design method for variable cycle engine

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Embodiment Construction

[0040] In order to facilitate the understanding of those skilled in the art, the present invention will be further described below in conjunction with the embodiments and accompanying drawings, and the contents mentioned in the embodiments are not intended to limit the present invention.

[0041] refer to figure 1 Shown, the non-linear predictive control design method of a kind of variable cycle engine of the present invention comprises the following steps:

[0042] Step 1: Establish the standard form of the block diagram of the variable cycle engine model: first put figure 1 The nonlinear model shown in is expressed by an operator as:

[0043] u 0 =W 1k (u) (1)

[0044] Among them, W 1k is the component-level model of the variable cycle engine; u is the output of the nonlinear predictive controller to be designed; u 0 is the output of the sensorless model of the variable cycle engine. followed by figure 1 A linear subsystem with time delay in is represented by the fol...

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Abstract

The invention discloses a nonlinear prediction control design method for a variable cycle engine, and the method comprises the steps: building a standard form of a variable cycle engine model block diagram; obtaining a nonlinear generalized minimum variance controller according to the standard form; estimating the impact on the control performance of the variable cycle engine from all design parameters of the nonlinear generalized minimum variance controller; and carrying out the contrastive analysis to determine the design parameters of an optimal controller. Aiming at the problems that a variable cycle engine is strong in nonlinearity, is difficult to model and is not high in model precision, the method employs a novel nonlinear generalized minimum variance control method, and can enablethe control performance of the variable cycle engine to be remarkably improved.

Description

technical field [0001] The invention belongs to the technical field of system control and simulation in aviation propulsion theory and engineering, and specifically relates to a nonlinear predictive control design method for variable cycle engines. Background technique [0002] A variable cycle engine refers to a gas turbine engine that changes its thermodynamic cycle parameters by changing the geometry, size or position of certain parts of the engine. Some cycle parameters of the engine, such as boost ratio, air flow or bypass ratio, are changed through variable cycle regulation, so that the engine has good performance under various working conditions. In the field of turbojet / turbofan engines, variable The focus of cycle engine research is to change the bypass ratio, such as reducing the bypass ratio during acceleration, climb and supersonic flight, so that the engine has performance characteristics similar to turbojet (high unit thrust); during takeoff and subsonic flight...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B13/04
CPCG05B13/042
Inventor 王继强胡忠志
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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