A study on optimal control of the aero-propulsion system acceleration process under the supersonic s

• 作 者: Sun Fengyong Du Yao Zhang Haibo
• 机 构: College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Jiangsu P
• 出 处: Chinese Journal of Aeronautics
• 发表日期: 2017年02期
• 关键词: Acceleration control Inlet control design Inlet and engine cooperative working O

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 componentlevel 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 by5%.

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. 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 problem. In an optimal control of the aero-propulsion system acceleration process, the inlet is an emphasized control unit in the optimal acceleration control system. TW 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 be ing modulated passively, acceleration performance could be obviously enhanced. Ax acceleration objectives could be obtained with faster acceleration time by 5%.