基于快速原型化的小型涡喷发动机起动过程控制  

Starting Process Control of Small Turbojet Engine Based on Rapid Control Prototype Technology

作　　者：王灿森 李睿超[1] 赵万里 徐建强 郭迎清[1] WANG Cansen;LI Ruichao;ZHAO Wanli;XU Jianqiang;GUO Yingqing(School of Power and Energy,Nonthwestem Polytechmical University,Xi'an 710129,Chima)

机构地区：[1]西北工业大学动力与能源学院,陕西西安710129

出　　处：《测控技术》2024年第1期50-54,62,共6页Measurement & Control Technology

基　　金：国家科技重大专项(J2019-V-0003-0094)。

摘　　要：为快速验证小型涡喷发动机起动过程控制规律,基于快速原型化技术搭建了半物理试验平台。设计了快速原型试验系统整体架构,对控制系统的软硬件设计和智能节点的工作原理进行了说明,使用Speedgoat Mobile实时目标机作为电子控制器,以STM32为核心设计智能节点,选用Modbus协议对信号进行编码,实现电子控制器和智能节点之间的数据通信。针对小型涡喷发动机的起动过程设计了一种控制规律,利用自动代码生成技术生成电子控制器可执行程序,部署到实时目标机中,完成了起动过程控制规律的试验验证。仿真结果表明,电子控制器和智能节点通信正常,工作可靠稳定,起动过程平稳迅速、不熄火、不超温、不超转,提出的快速原型化控制技术能够有效地缩短开发周期,具有良好的工程实用价值。In order to quickly verify the control law of small turbojet engine starting process,a semi-physical test platform is built based on rapid prototype technology.The overall architecture of the rapid prototype test system is designed.The software and hardware design of the control system and the working principle of the smart node are described.The Speedgoat Mobile real-time target machine is used as the electronic controller,and the STM32 is used as the core to design the smart node.Modbus protocol is selected to encode the signal to realize the data communication between the electronic controller and the smart node.A control law is designed for the starting process of a small turbojet engine.The executable program of the electronic controller is generated by using the automatic code generation technology and deployed to the real-time target machine to run.The experimental verification of the control law of the starting process is completed.The simulation results show that the electronic controller and smart node work reliably and stably,and the starting process is stable and rapid,without stalling,overtemperature,and overrunning.The rapid control prototype technology can effectively shorten the development cycle,and has good engineering practical value.

关 键 词：小型涡喷发动机 快速原型化技术 智能节点 MODBUS协议 

分 类 号：V216[航空宇航科学与技术—航空宇航推进理论与工程] V23