基于飞行试验数据的进气道畸变预测与试验验证  

Prediction and test verification of inlet distortion based on flight test data

作　　者：姜健[1,2] 赵海刚[2] 李俊浩[2] JIANG Jian;ZHAO Haigang;LI Junhao(School of Power and Energy,Northwestern Polytechnical University,Xi’an 710129,China;Chinese Flight Test Establishment,Aviation Industry Corporation of China Limited,Xi’an 710089,China)

机构地区：[1]西北工业大学动力与能源学院,西安710129 [2]中国航空工业集团有限公司中国飞行试验研究院,西安710089

出　　处：《航空动力学报》2020年第8期1706-1715,共10页Journal of Aerospace Power

基　　金：装备预研航空工业联合基金(6141B05050202)。

摘　　要：采用响应曲面的试验设计方法,构建了基于试飞数据的进气道压力畸变预测模型,进行不同飞行工况进气道畸变模型预测与飞行试验验证研究。研究结果表明:模型预测与飞行试验结果相比,综合压力畸变指数平均相对误差为4.21%,稳态周向畸变指数平均相对误差为7.99%,结果吻合良好,能够满足对该型进气道畸变预测要求;大迎角、侧滑及其组合飞行时,进气道内部附面层气流分离是造成进气道出口畸变的主要因素;进气道出口低压区的位置与飞行姿态角相对应,并在周向上向压气机的旋转方向有小范围偏转,偏转角度与发动机状态相关;采用"模型预测+飞行试验"的模式能够完整、安全高效地考核评估飞机进气道的畸变特性,具有很好的工程适用性。Experimental design of response surface methodology was adopted to construct the inlet pressure distortion prediction model based on flight test data, while the inlet distortion model prediction and flight test verification were studied under different flight conditions. The results showed that, compared with the flight test results, the model prediction average relative error of the comprehensive pressure distortion index was 4.21%, and the average relative error of the steady-state circumferential distortion index was 7.99%, which were in agreement with each other and can meet the requirement of the inlet distortion prediction. At large angle of attack, sideslip and combined flight conditions, the flow separation of the boundary layer inside the inlet contributed a lot to the distortion of the inlet outlet. The position of the inlet outlet low pressure zone corresponded to the flight attitude angle, and there was a small range of deflection in the direction of the compressor rotation in the circumference direction, and the deflection angle was related to the engine state. The model of "model prediction+flight test" can be used to evaluate the distortion characteristics of aircraft inlet completely, safety and efficiently, and it has good engineering practicability.

关 键 词：飞行试验 稳态周向畸变指数 进气道畸变 模型预测 发动机稳定性 

分 类 号：V217.39[航空宇航科学与技术—航空宇航推进理论与工程]