舵面天平技术及其在高超声速风洞的应用研究  

Hinge moment balance technique and application in hypersonic wind tunnel

作　　者：熊琳[1] 刘展[1] 陈河梧[1] 

机构地区：[1]航天空气动力技术研究院,北京100074

出　　处：《实验流体力学》2007年第3期54-57,共4页Journal of Experiments in Fluid Mechanics

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.

关 键 词：铰链力矩 应变天平 控制舵 高超声速 风洞试验 

分 类 号：TH715.112[机械工程—测试计量技术及仪器] V211.74[机械工程—仪器科学与技术]