固冲发动机补燃室压强控制技术研究  

Research on Afterburning Chamber Control Technologies of A Solid Propellant Ducted Rocket

作　　者：齐鑫 胡大庆 张格 何颐 QI Xin;HU Daqing;ZHANG Ge;HE Yi(The 41st Institute of the Fourth Academy of CASC,Nationalkey Laboratory of Combustion,Flow and Thermo-structure,Xi’an 710025,China;The Fourth Academy of CASC,Xi’an 710025,China)

机构地区：[1]中国航天科技集团公司第四研究院第四十一研究所燃烧、流动和热结构国家级重点实验室,西安710025 [2]中国航天科技集团公司四院,西安710025

出　　处：《计算机测量与控制》2021年第7期100-105,共6页Computer Measurement &Control

摘　　要：以固体冲压发动机为动力的导弹,其纵向通道控制系统设计中需要考虑固冲发动机的可控性、控制的经济性以及发动机的安全性,需要对固冲发动机开展充分的试验验证,通过补燃室压强控制试验验证发动机性能,为导弹总体控制创造条件;文章提出了一种基于补燃室压强闭环的控制策略,可以在固冲发动机地面直连试验中有效验证固冲发动机控制性能;建立了固冲发动机燃气发生器、补燃室数学模型,设计控制律并进行数学仿真;仿真结果表明,文章设计的补燃室压强闭环控制系统可实现补燃室压强控制,充分反应了固冲发动机控制性能,可根据研究结果开展导弹纵向通道控制系统设计,实现导弹总体对固冲发动机能量管理及进气道保护等方面的需求。In the design of solid propellant ducted rocket missile longitudinal channel control system,the controllability,economical efficiency and safety of ducted rocket should be considered.The ducted rocket itself should be fully verified by experiments,and the problems should be found and solved through experiments,to create conditions for the control of the missile.In this paper,one method is proposed with afterburning chamber control strategy.Based on mathematical linearization control model of solid propellant ducted rocket,the control rate is designed and following the model is simulated.As a result,the simulation results show that the afterburning chamber control system from this paper can realize energy control,and the inlet can be protected to meet ducted rocket’s requirements.

关 键 词：固冲发动机 补燃室 控制技术 

分 类 号：V448[航空宇航科学与技术—飞行器设计]