摘要
在讨论共轴双旋翼气动干扰模型的基础上 ,建立了一种共轴式直升机飞行动力学仿真数学模型。以某型共轴式直升机为样例机 ,在定直水平飞行条件下进行配平计算 ,并与国外计算结果作了对比分析 ,两者基本一致。给出了共轴式直升机在不同操纵输入下的动态响应数值模拟结果。仿真计算表明 。
A non-linear mathematical model for coaxial helicopter flight dynamics is established based on the development of a simplified and practical coaxial contra-rotating twin rotor loads model. The mathematical model is used to calculate trims in the steady straight level flight and dynamic responses to different control inputs for the sample coaxial helicopter made in BUAA. The results of trim computation are well in agreement with the data provided from Russia. Numerical simulations show that the non-linear mathematical model captures the motion trend of the sample coaxial helicopter correctly. The correctness of the model is preliminarily validated.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2003年第4期293-295,共3页
Acta Aeronautica et Astronautica Sinica
