一种涡轴发动机系统应急状态快速响应控制方法  

A new rapid response emergency control method for turbo-shaft engines

作　　者：陈国强[1] 张海波[1] 严长凯[1] 王健康[1] 

机构地区：[1]南京航空航天大学,能源与动力学院,南京210016

出　　处：《航空动力学报》2012年第11期2609-2615,共7页Journal of Aerospace Power

基　　金：航空科学基金(2010ZB52011);高校基本科研业务费专项基金(NS2010055)

摘　　要：针对直升机应急状态下特殊快速响应需求,基于涡轮放气原理,提出了一种新的应急状态快速响应控制方法.在应急状态下,除了燃油控制外,同时将涡轮放气量作为发动机控制变量,采用多变量鲁棒方法设计了应急状态直升机/涡轴发动机三变量快速响应控制器,该综合控制方法不仅实现了直升机垂飞通道的控制,而且在保持输出功率通道稳定,即自由涡轮转速恒定的前提下,借助于涡轮放气实现了燃气涡轮转速的闭环控制,有效实现了发动机功率快速跟随能力.最后,以直升机UH-60/涡轴发动机T700综合模型为对象,仿真验证了在直升机应急状态急升-急降过程中,直升机垂飞速度、发动机自由涡轮转速以及燃气涡轮转速跟踪指令的情况,结果表明:相比传统的PID(proportional integration differential)控制,基于快速响应控制方法建立的闭环系统响应迅速,动静态品质良好,能够达到直升机应急状态的特殊设计要求.According to the special need in helicopter＇s emergency state, a new fast re- sponse control method of integrated Helicopter/turbo-shaft engine system was proposed to solve this control problem for helicopter＇s emergency control. Turbine bleeding was another control input except for fuel flow in this new scheme, and the control law including three control loops was based on multi-variables robust control design theory. Specially in this hy- brid control law, not only the helicopter climbing velocity was controlled, the gas turbine speed of turbo-shaft engines was also effectively controlled by turbine bleeding to realize engines＇ power rapid tracking while keeping the power turbine speed constant. In the final stage, the control law was implemented in an integrated UH-60 helicopter and T700 engine system and the transient performance of the closed-loop system in helicopter＇s climbing and desending emergency flights. The simulation results show clearly that the response time of the closed-loop system designed by the new fast response control law is much reduced com- pared with that designed by traditional PID （proportional integration differential） method, and it meets the special need of helicopter＇s emergency control.

关 键 词：涡轴发动机 直升机 应急状态 快速响应 涡轮放气 鲁棒控制 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]