摘要
根据高速自旋飞行器运动的特点,发展了气动参数辨识的一种数学模型,辨识参数包括静态气动导数、气动阻尼导数和马格努斯力矩导数等。仿真算例证实了该数学模型的有效性。应用该数学模型分析处理了某高速自旋飞行器的飞行试验数据,辨识获得了其主要气动参数,并分析了若干常见误差源对气动参数辨识结果的影响。
One of the important characteristics of rapid self-rotating flight vehicle is that the Magnus effectives must be included. A mathematical model of aerodynamic parameter identification is developed for rapid self-rotating flight vehicle with employment of its kinematical characteristics. The parameters to be identified are composed of static aerodynamic derivatives, aerodynamic damp derivatives, and Magnus moment derivatives. The effectiveness of the mathematical model is validated by a simulation example. With application of the developed mathematical model, the flight test data of some a rapid self-rotating flight vehicle is analyzed and processed. The effects of some primary errors on the identification results are discussed.
出处
《空气动力学学报》
EI
CSCD
北大核心
2004年第1期1-6,共6页
Acta Aerodynamica Sinica
关键词
自旋飞行器
气动参数
马格努斯效应
参数辨识
气动导数
self-rotating flight vehicle
parameter identification
aerodynamic derivatives
Magnus effective
