A study on optimal control of the aero-propulsion system acceleration process under the supersonic state
发布时间：2020-01-13 点击次数：
张海波（教授）
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- 博士生导师 硕士生导师
- 电子邮箱：
- 所在单位：能源与动力学院
- 职务：能源与动力学院控制工程系主任
- 学历：南京航空航天大学
- 办公地点：A10-538
- 联系方式：zh_zhhb@126.com
- 学位：工学博士学位
- 所属院系：能源与动力学院
- 学科：动力工程及工程热物理
航空宇航科学与技术
能源动力
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- 所属单位：能源与动力学院
- 发表刊物：CHINESE JOURNAL OF AERONAUTICS
- 关键字：Acceleration control Inlet control design Inlet and engine cooperative working Optimal control
- 摘要：In order to solve the aero-propulsion system acceleration optimal problem, the necessity of inlet control is discussed, and a fully new aero-propulsion system acceleration process control design including the inlet, engine, and nozzle is proposed in this paper. In the proposed propulsion system control scheme, the inlet, engine, and nozzle are simultaneously adjusted through the FSQP method. In order to implement the control scheme design, an aero-propulsion system component-level model is built to simulate the inlet working performance and the matching problems between the inlet and engine. Meanwhile, a stabilizing inlet control scheme is designed to solve the inlet control problems. In optimal control of the aero-propulsion system acceleration process, the inlet is an emphasized control unit in the optimal acceleration control system. Two inlet control patterns are discussed in the simulation. The simulation results prove that by taking the inlet ramp angle as an active control variable instead of being modulated passively, acceleration performance could be obviously enhanced. Acceleration objectives could be obtained with a faster acceleration time by 5%. (C) 2017 Production and hosting by Elsevier Ltd.
- ISSN号：1000-9361
- 是否译文：否
- 发表时间：2017-04-01
- 合写作者：Sun Fengyong,Du Yao
- 第一作者：张海波
- 通讯作者：张海波