An adaptive turbo-shaft engine modeling method based on PS and MRR-LSSVR algorithms

Author:

Wang Jiankang,Zhang Haibo,Yan Changkai,Duan Shujing,Huang Xianghua

Funder

Aeronautical Science Foundation of China

Jiangsu Innovation Program for Graduate Education

Publisher

Elsevier BV

Subject

Mechanical Engineering,Aerospace Engineering

Reference16 articles.

1. Smith BJ, Zagranski RD. Closed loop bench testing of the next generation control system for helicopter engines. In: AHS International 58th Annual Forum, Montreal, Canada; 2002.

2. Desai MC, Crainic C. Adaptive thermodynamic engine model for the next generation control system for helicopter engines. In: AHS International 58th Annual Forum, Montreal, Canada; 2002.

3. Luppold RH, Roman JR, Gallops GW, Kerr LJ. Estimating in-flight engine performance variations using Kalman Filter concepts; 1989. Report No.: AIAA-89-2584.

4. Adaptive model of rotor/turbo-shaft engine;Zou;J Beijing Univ Aeronaut Astronaut,2009

5. Kobayashi T, Simon DL, Litt JS. Application of a constant gain extended Kalman Filter for in-flight estimation of aircraft engine performance parameters; 2005. Report No.: NASA/TM 2005-213865.

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