某型弹用涡喷发动机启动加速控制规律设计  

Starting and acceleration control law design for a missile turbojet engine

作　　者：谢光华[1] 牛天华[1] 王亿军[1] 苏祥荣 

机构地区：[1]航天科工集团公司31所,北京100074 [2]空军驻京丰地区军代表室,北京100074

出　　处：《推进技术》2003年第3期232-235,共4页Journal of Propulsion Technology

摘　　要：为满足某弹用涡喷发动机大空域风车启动加速要求,分析了发动机控制系统原控制方案的局限性,通过引入新的控制输入参数提出了新的控制方案,进行了涡喷发动机新方案控制规律研究和设计。通过地面台架与高空模拟台验证试验结果表明,新方案控制规律满足发动机大空域风车启动加速要求,新控制方案是切实可行的,某涡喷发动机数字电子控制系统控制规律设计一次成功。In order to meet the request for a certain missile turbojet engine that it should start in a large airspace under wind-milling condition, the localization of the control system's old control plan of the engine was analyzed and a new control plan was brought forward in this paper by dint of introducing an additional control input parameter. According to the new control plan, a control law of the turbojet engine was investigated and designed. Through the result of validate test on ground bed and simulated altitude and Mach number test, it showed that the demand of starting and acceleration in a large airspace under windmilling condition for the engine was satisfied. So it can be said that the new control plan is feasible for the engine, and it was succeeded in designing a control law for the digit electronic control system of a certain turbojet engine at the first time.

关 键 词：涡轮喷气发动机 控制系统 控制规律设计 

分 类 号：V233.75[航空宇航科学与技术—航空宇航推进理论与工程]