基于专家控制系统的发动机入口压力闭环控制方案  

Study on closed loop control of rocket engine inlet pressure based on expert control system

作　　者：朱丹波[1] 南渭林[1] 薛会建[1] 

机构地区：[1]西安航天动力试验技术研究所,陕西西安710100

出　　处：《火箭推进》2009年第3期42-46,共5页Journal of Rocket Propulsion

摘　　要：液体火箭发动机在地面试验过程中,试车台推进剂供应系统必须保证发动机的入口压力在任务要求的范围内,而目前采用压力继电器控制进气电磁阀来调节入口压力,这种方式调节精度低,响应滞后。根据试车台增压系统的特点和增压系统开环控制数年所积累的经验,提出基于专家控制思想和以孔板矩阵作为执行机构的压力闭环控制方案。该控制方法无需精确的数学模型,又能按照设定的精度智能调节增压孔板矩阵,使发动机入口压力自动跟随设定值而变化。Inlet pressure of the liquid rocket engine should be controlled in a range by the propellant supplying system in the ground test. At present, the pressure is controlled by an electromagnetic valve which is driven by a pressure relay. But the regulation precision is low and the response hysteresis is significant. A new project is put forward in this paper which is based on the expert control system and the experience of the open-loop control system during these years, the executive is a series of valves. The virtue of the new project is that it does not need precision mathmatic model and the pressure will follow the set value well after controlling of the valve matrix in the design precision.

关 键 词：液体火箭发动机 入口压力 专家控制 孔板矩阵 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]