摘要
介绍纵轴分离式和轮毂式铰链力矩天平的设计技术,及其近年来在Φ0.5m高超声速风洞铰链力矩试验中的应用情况。根据尾翼/弹身组合体全动操纵舵布局特点,通过采用天平不同的连接形式（纵轴分离式天平、轮毂式天平竖置和轮毂式天平斜置）,分别测量了3种舵面外形的气动特性,给出M=5-8之间舵面的法向力系数、铰链力矩系数和弦向压力中心随迎角的变化特性,定量描述了大迎角大舵偏角条件下,舵面气动特性的非线性效应,以及由此引起控制力增量的变化趋势。
The design technique of hinge moment balances of five-components balance gauge with a hinge cap and wheelboss is discussed, and their application in Φ0 .5m hypersonic wind tunnel in recent years is introduced here. The aerodynamic characteristics of three kinds of control flaps were respectively investigated at Mach number of 5 - 8. The results of the normal force coefficient, hinge moment coefficient and pressure center position of control flaps were obtained with angle of attack. The nonlinear effect of aerodynamic characteristics, as well as the control force augmentation induced by nonlinear effect, is quantitatively described for the control flaps at large angles of attack and large angles of flaps.
出处
《实验流体力学》
EI
CAS
CSCD
北大核心
2007年第3期54-57,共4页
Journal of Experiments in Fluid Mechanics
关键词
铰链力矩
应变天平
控制舵
高超声速
风洞试验
hinge moment
strain gauge balance
control flaps
hypersonic
wind tunnel test
