某型辅助动力装置进发相容性试飞技术

针对某型飞机辅助动力装置进气系统的飞行试验，首先建立了该飞机机身和辅助动力装置进气系统的仿真模型，并分别对其在地面和空中进行了数值仿真研究，计算了在不同试验条件下，APU进气系统的性能和畸变指数，然后将数值仿真结果同前期试飞数据进行对比，进一步验证数值仿真方法的可靠性，优化仿真模型，最后利用优化后段仿真模型计算后续即将进行段地面试验和飞行试验，为后续侧风、顺风地面试验以及试飞中试验点的选取提供参考，达到了试飞前预测和优化试飞目的。

Research on the flight test technology of the compatibility of a certain APU

For the flight test of auxiliary power unit(APU) air intake system of a certain aircraft, the simulation models of the fuselage and APU air intake system of the aircraft ware established, and the numerical simulation of the APU air intake system on the ground and in the air was carried out. The performance and distortion index of APU air intake system under different test conditions ware calculated, and then the numerical simulation results ware compared with the previous flight test data. Further verify the reliability of the numerical simulation method, optimize the simulation model, and use the optimized simulation model to calculate the future section ground test and flight test, which provides a reference for the following crosswind, downwind ground test and the selection of test points in the flight test, so as to achieve the purpose of prediction and optimization of flight test before flight test.