基于多模式加速及反步滑模的航空发动机压气机压力模拟方法

doi:10.12382/bgxb.2023.0354

摘要/Abstract

摘要：

在航空发动机硬件在环仿真试验中,压气机出口压力模拟是一个重要的环节。为模拟压气机失稳过程中的气流突变现象,需要设计一种高精度的压力模拟系统,通过该模拟系统生成真实压力信号为全权限数字发动机控制器提供准确的压力激励。根据开关阀特性提出多模式加速切换策略,设计加速驱动波形及生成方法,结合现场可编程门阵列模块精确输出加速波形,提高开关阀启闭速度;在传统三模式与五模式切换的基础上设计七模式切换方法,结合反步滑模控制方法提高控制精度并证明了控制系统的稳定性。研究结果表明:在稳态压力测试中最大平均超调量为1.25%,最大平均稳态误差为0.016MPa;在随机阶跃响应试验与正弦跟踪试验中仅有低于0.02MPa的平均误差;压力模拟方法可满足航空发动机硬件在环仿真试验的高精度压力模拟需求,低成本的实现精准模拟压力。

关键词: 压气机, 压力模拟, 硬件在环仿真, 开关阀, 反步滑模控制

Abstract:

In the aero-engine hardware-in-the-loop simulation test, the compressor outlet pressure simulation is an important part. In order to simulate the sudden change of airflow in the process of compressor destabilization, a high-precision pressure simulation system is designed, through which a real pressure signal is generated to provide an accurate pressure excitation for the full authority digital engine control. A multi-mode acceleration switching strategy is proposed according to the characteristics of the switching valve, and the acceleration drive waveform and generation method are designed to combine with the field-programmable gate array module to accurately output the acceleration waveform and improve the opening and closing speeds of switching valve. A seven-mode switching method is designed based on the traditional three-mode and five-mode switching methods. The backstepping sliding mode controller is combined with the seven-mode switching method to improve the control accuracy, and the stability of control system is proven. The test results show that the maximum average overshoot in the steady-state pressure test is 1.25%, and the maximum average steady-state error is 0.016MPa. The average errors in the random step response and sinusoidal tracking tests are less than 0.02MPa. The proposed pressure simulation method can meet the requirements for high-accuracy pressure simulation of aero-engine hardware-in-the-loop simulation tests and achieve the accurate pressure simulation at a low cost.

Key words: compressor, pressure simulation, hardware-in-the-loop simulation, switching valve, backstepping sliding mode control

中图分类号:

V233.7

林忠麟, 王海涛, 刘文超, 甘锦裕, 张天宏, 黄峰. 基于多模式加速及反步滑模的航空发动机压气机压力模拟方法[J]. 兵工学报, 2024, 45(6): 1776-1786.

LIN Zhonglin, WANG Haitao, LIU Wenchao, GAN Jinyu, ZHANG Tianhong, HUANG Feng. Aero-engine Compressor Pressure Simulation Method Based on Multi-mode Acceleration and Backstepping Sliding Mode[J]. Acta Armamentarii, 2024, 45(6): 1776-1786.

图/表 15

图1 压力模拟系统示意图

Fig.1 Schematic diagram of pneumatic pressure simulation system

图2 24V常规PWM驱动波形作用下的阀响应特性

Fig.2 Response characteristics of valve under the action of 24V conventional PWM drive waveform

图3 双电压式加速波形作用下的阀响应特性

Fig.3 Response characteristics of valve under the action of dual-voltage acceleration waveform

图4 加速波形生成

Fig.4 Accelerated waveform generation

图5 加速电路板

Fig.5 Accelerated circuit board

图6 开环充气对比测试

Fig.6 Open-loop charging comparison test

表1 七模式具体形式

Table 1 Specific forms of seven-mode

模式	效果	充气阀状态	放气阀状态
1	快速充气	不加速开启	关闭
2	慢速充气	加速开启	关闭
3	细微充气	加速开启	加速开启
4	停止	关闭	关闭
5	细微放气	加速开启	加速开启
6	慢速放气	关闭	加速开启
7	快速放气	关闭	不加速开启

图7 七模式切换策略

Fig.7 Seven-mode switching strategy

图8 气动控制系统框图

Fig.8 Block diagram of pneumatic control system

图9 压力模拟试验平台实物图

Fig.9 Pressure simulation platform

图10 软件架构设计

Fig.10 Design of software architecture

表2 稳态过程压力跟踪试验

Table 2 Steady-state pressure tracking tests

组别/MPa	平均超调量/ %	平均调整时间/ s	平均稳态误差/ MPa
0.1~0.2	1.25	0.523	0.016
0.1~0.3	1.02	1.034	0.013
0.1~0.4	0.55	1.502	0.009
0.1~0.5	0.45	2.049	0.008
0.1~0.6	0.52	2.326	0.010

图11 稳态过程压力跟踪试验结果

Fig.11 Results of steady-state pressure tracking test

图12 随机阶跃信号跟踪试验结果

Fig.12 Results of random step signal tracking test

图13 正弦信号跟踪对比试验结果

Fig.13 Results of sine signal tracking comparison tests

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