Title:
DESIGN METHOD FOR OPTIMIZING AERO-ENGINE TRANSITION STATE CONTROL LAW
Document Type and Number:
WIPO Patent Application WO/2020/093264
Kind Code:
A1
Abstract:
A design method for optimizing an aero-engine transition state control law. The SQP algorithm is adopted for optimizing the transition state of an engine, and the transition state control law design under the constraint boundary condition is realized. Moreover, the fuel flow rate value is adjusted, other constraint conditions are unchanged, and transition state control laws under different constraints are designed. By constructing a transition state time evaluation function, transition state time under each transition state control law is calculated. A lookuptable interpolation table is established by means of the calculated transition state time and the corresponding fuel flow to realize fuel flow scheduling under different transition state times. The fuel flow obtained by scheduling at the desired time is taken as the acceleration and deceleration plan of closed-loop control of the engine, output is used as a reference instruction of the acceleration process, combination of engine transition state optimization and closed-loop control is achieved, and a theoretical basis is provided for closed-loop control of the engine.
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Inventors:
DU XIAN (CN)
MA YANHUA (CN)
SUN XIMING (CN)
MA YANHUA (CN)
SUN XIMING (CN)
Application Number:
PCT/CN2018/114327
Publication Date:
May 14, 2020
Filing Date:
November 07, 2018
Export Citation:
Assignee:
UNIV DALIAN TECH (CN)
International Classes:
F02C9/26; F02C9/44; G01M15/00
Foreign References:
| CN106323640A | 2017-01-11 | |||
| CN108375474A | 2018-08-07 | |||
| CN102289203A | 2011-12-21 | |||
| CN105715384A | 2016-06-29 | |||
| CN108762089A | 2018-11-06 | |||
| US20080177456A1 | 2008-07-24 |
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