Free-flight test in horizontal wind tunnel with powered aircraft

被引：0
|
作者：
Wang J. [1 ]
Lu S. [1 ]
Feng S. [1 ]
机构：
[1] Aerodynamics for Low Speed and High Reynolds Number, Aerodynamics Research Institute, Aviation Industry Corporation of China Limited, Harbin
来源：
Hangkong Dongli Xuebao/Journal of Aerospace Power | 2023年 / 38卷 / 11期
关键词：
flight control system; free-flight; powered model; similarity criterion; wind tunnel test;
D O I：
10.13224/j.cnki.jasp.20220018
中图分类号：
学科分类号：
摘要：
In order to carry out aerodynamic/flight/control integration research at the early stage of design， shorten the development cycle and reduce the development cost， a model free-flight test system was established in FL-10 open wind tunnel. The system was used to design the scale verification machine model according to the similarity criteria of size， mass and moment of inertia， invent the flight control system， on this basis， the system was modeled and simulated， and the closed-loop stability increasing control law was designed to realize the stable flight at the trim angle of attack. The test results showed that the structure and parameters of the flight control law were designed according to the similarity criterion，the simulated trim angle of attack was 5°，the trim elevator deviation was −4.5°，and the wind tunnel test angle of attack was controlled within (5±0.2)°. Because the power supply and signal cables gave the test model a positive pitch moment， the elevator deviation was controlled at about −3.2°， which was slightly less than the simulated trim elevator deviation. © 2023 BUAA Press. All rights reserved.
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页码：2601 / 2609
页数：8
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