| 引用本文: | 王安,曾庆华,周宇宸.基于系统构型替换的固冲发动机故障模式半实物仿真.[J].国防科技大学学报,2019,41(4):79-85.[点击复制] |
| WANG An,ZENG Qinghua,ZHOU Yuchen.Fault simulation of ducted rocket based on system configuration switch method[J].Journal of National University of Defense Technology,2019,41(4):79-85[点击复制] |
|
| |
|
|
| 本文已被：浏览 6401次 下载 5249次 |
| 基于系统构型替换的固冲发动机故障模式半实物仿真 |
| 王安1, 曾庆华2, 周宇宸1 |
|
(1. 国防科技大学 空天科学学院， 湖南 长沙 410073;2. 中山大学 航空航天学院， 广东 广州 510006)
|
| 摘要: |
| 为全面快速验证冲压发动机的故障检测算法，基于构型替换建立了能模拟多种固冲发动机故障的仿真验证平台。基于此平台，搭建了发动机点火故障模型、压强传感器故障模型、设备接口模型，以及与真实控制器中检测算法具有相同外部接口和系统构型的故障检测算法模型等。通过系统构型的切换，将同一个故障模式注入故障检测算法模型和真实发动机系统，并通过对比同一组故障模式下故障检测模型检测结果与发动机控制系统检测结果，来对发动机控制器中的故障检测算法进行快速验证。以无喷管助推器点火的检测为例，讲述了该方法的建模、实验验证及分析过程，此外，该方法还能应用到无喷管助推器关机、进气道前后堵盖打开、燃气发生器点火、燃气流量容错控制等多个故障模式的仿真模拟与验证，具有很强的通用性，能大大地降低控制系统开发与验证的时间成本，具有很强的应用价值。 |
| 关键词: 故障仿真模拟 固冲发动机 系统构型替换 发动机故障建模 |
| DOI：10.11887/j.cn.201904012 |
| 投稿日期：2018-09-25 |
| 基金项目: |
|
| Fault simulation of ducted rocket based on system configuration switch method |
| WANG An1, ZENG Qinghua2, ZHOU Yuchen1 |
|
(1. College of Aeronautics and Astronautics, National University of Defense Technology, Changsha 410073, China;2. School of Aeronautics and Astronautics, Sun YatSen University, Guangzhou 510006, China)
|
| Abstract: |
| In order to comprehensively verify the fault detection algorithm in the ducted rocket rapidly, a simulation platform based on system configuration switch method was built, which can simulate various fault mode for ducted rocket. Based on the simulation platform, the ducted rocket ignite fault model, pressure sensor fault model, device interface model and fault detection algorithm model which have a same interface and system configuration with the aircraft engine controller, etc. were built. Compared with the fault detect result of mathematical model and engine control system under a same fault mode, the fault detection algorithm in the engine control system can be verified rapidly. Taking the fault simulation of nozzleless booster ignition as an example, the modeling, the test, the verification, and the process of analysis were narrated. In addition, it is also applicable to the fault simulation and verification of the shutdown of nozzleless booster, the open of air inlet cover, the ignition of gas generator, and fault tolerant control of gas flow, which has strong universality, and can greatly reduce the time cost on system development and verification, and it has a strong applied value. |
| Keywords: fault simulation ducted rocket system configuration switch aircraft engine fault modeling |
|
|
|
|
|
