海军航空工程学院学报Issue(2)：146-150,5.
直升机在风切变气流场中的响应特性
Response of Helicopter in Wind Shear Field
宋岩 1章晓冬 2商兴华 3费洋4
作者信息
- 1. 海军航空工程学院 基础实验部，山东烟台264001
- 2. 海军航空工程学院 研究生管理大队，山东烟台264001
- 3. 91224部队，上海200235
- 4. 91115部队，浙江舟山316000
- 折叠
摘要
Abstract
For the purpose of studing the response of helicopter in wind shear field, the wind shear model was established based on reference. The complete helicopter flight dynamic model was established when considering the non-uniform inflow of main rotor, and Runge-Kutta technique was used to solve the equations. It was found that from the results, the wind shear made the attitude angle shake, which deteriorated the stability of helicop⁃ter. Especially peak values of the roll angle difference reached to 73.14 degrees. The windshear had greater ef⁃fect on the helicopter’s track, The results showed that falling distance could be up to 53.19 m and yaw dis⁃tance could be up to 93.79 m in 10 seconds.关键词
直升机/风切变/动态响应/飞行动力学Key words
helicopter/wind shear/dynamic response/flight dynamics分类
航空航天引用本文复制引用
宋岩,章晓冬,商兴华,费洋..直升机在风切变气流场中的响应特性[J].海军航空工程学院学报,2013,(2):146-150,5.
