大攻角旋转天平支撑系统的设计与研究  

Reasearch and Design of Support System for Rotary Balance of High Attack Angle

作　　者：杨恩霞 

机构地区：[1]哈尔滨工程大学机电学院,哈尔滨150001

出　　处：《机械工程师》2006年第8期56-57,共2页Mechanical Engineer

摘　　要：在对飞机尾旋特性进行分析和预测时,要求获得该飞机的动稳定性导数,这些参数值不能用理论方法计算,必须用风洞试验方法确定。为此,设计了大攻角旋转天平支撑系统,此系统可测定飞机模型在不同姿态角下绕风轴以一系列恒定的角速率旋转时的气动特性。文中简要介绍了研究飞机尾旋的重要性和研究尾旋的方法以及用于低速风洞的大攻角旋转天平支撑系统的总体设计方案、试验能力,该支撑系统角度变化范围大、精度高、风洞的堵塞度小以及支架干扰量小,试验数据的精准度达到了较高的水平,可用于分析、预测飞机的尾旋特性。When analyzing and predicting to spin characteristics of aircraft, it is important to obtain dynamic stability derivatives of the aircraft. These values can not be yielded from theoretical calculations, it must be yielded from wind tunnel tests. The paper has introduced design of the support system for rotary balance of high attack angle, and the importance and methods of studying spin of aircraft. This system is mainly used to measure aerodynamic forces acting on aircraft model rotating around the wind axis. The angle of attack range which the system can measure and control is wide, the accuracy of measuring is high, and the support interference is also low.

关 键 词：风洞试验 旋转天平 尾旋特性 

分 类 号：O133[理学—数学]