A Novel Hybrid Optimization Method for Optimal Control of Aeroengine Performance

A technology of aero-engine and optimization method, applied in general control system, adaptive control, control/regulation system, etc., to achieve the effect of good global convergence, moderate complexity and fast calculation speed

Inactive Publication Date: 2011-12-21
BEIHANG UNIV
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Problems solved by technology

[0006] In view of the above, the main purpose of the present invention is to overcome the deficiencies of the prior art, to provide a new hybrid optimization method for aero-engine performance optimization, to make up...

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  • A Novel Hybrid Optimization Method for Optimal Control of Aeroengine Performance
  • A Novel Hybrid Optimization Method for Optimal Control of Aeroengine Performance
  • A Novel Hybrid Optimization Method for Optimal Control of Aeroengine Performance

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Embodiment Construction

[0026] like figure 1 As shown, it is a flowchart of the method of the present invention, and the steps are as follows:

[0027] (1) Determine the optimization objectives and constraints of the aero-engine, divide multiple sub-regions within the constraints of the optimization variables, and extract the propulsion system matrix at the center of each sub-region based on the airborne adaptive model.

[0028] Element p of the propulsion system matrix in the step (1) ij The calculation is as follows:

[0029] p ij = Δ Y i Δ x j = Y i ( x j 0 + Δ ...

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Abstract

The invention relates to a novel hybrid optimization method for performance optimization control of aero-engines. The method is a hybrid optimization method based on subregional parallel linear programming and sequential quadratic programming. Its characteristic is that the optimization calculation process is divided into initial optimization and re-optimization There are two stages of optimization: (a) In the initial optimization stage, the global initial feasible solution is solved by using the subregional parallel linear programming method. In the initial optimization stage, no iterative convergence process is required, and the initial feasible solution is allocated to the global optimal solution through the subregional parallel mechanism. In the small area near the optimal solution; (b) In the re-optimization stage, the initial feasible solution is taken as the initial iteration point, and the sequential quadratic programming method is used to iteratively optimize to ensure good global convergence, optimization accuracy and search ability along the constraint boundary. The method of the invention coordinates the relationship between optimization accuracy and convergence speed through combined optimization logic, has the advantages of high optimization accuracy, good real-time performance, and moderate method complexity, and is suitable for solving the problem of aeroengine performance optimization control.

Description

【Technical field】 [0001] The invention belongs to the field of aero-engine performance optimization control, and relates to a novel hybrid optimization method for an aero-engine online performance optimization calculation. 【Background technique】 [0002] With the development of science and technology, the performance optimization control technology has been applied in more and more civil and military aircraft. The performance optimization control technology is based on the airborne model that can reflect the real working conditions of the engine, and online calculates the parameters that characterize the engine performance at the current operating point, such as surge margin, thrust, fuel consumption rate, etc. Performance optimization is carried out at the engine operating point to achieve maximum thrust, minimum fuel consumption, minimum turbine inlet temperature and other optimization modes, so as to give full play to the performance potential of the engine. [0003] It ...

Claims

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Application Information

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IPC IPC(8): G05B13/04
Inventor 张晶杨凌宇申功璋
Owner BEIHANG UNIV
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