某飞行器弹翼变形动态测量风洞试验模型研制  

Development of Wind Tunnel Test Model for Dynamic Measurement of Wing Deformation of Aircraft

作　　者：韩松梅 宋文成[1] 王天旭 HAN Song-mei;SONG Wen-cheng;WANG Tian-xu(AVIC Aerodynamics Research Institute,Shenyang 110034)

机构地区：[1]中国航空工业空气动力研究院,沈阳110034

出　　处：《航空精密制造技术》2018年第6期32-36,共5页Aviation Precision Manufacturing Technology

摘　　要：针对某风洞试验模型,可实现弹翼后掠角和展长单独变形,且可实现后掠角和展长同时变形。该变形机构采用蜗杆传动实现弹翼后掠角变形范围和变形速度;选择电动缸传动和直线导轨限位,实现弹翼展长变形范围和速度;并将变展长机构嵌入变后掠机构中,实现了两种变形同时进行。模型翼根利用弹簧推动密封片,有效地减少了翼根气流串流现象。模型和垫块间利用橡胶圈密封,有效地减少了气流串流现象。According to the test requirement,the wind tunnel test model can be used to realize the change of the wing's sweep angle and wingspan separately,and both of them can be changed at the same time.The half model of wind tunnel is developed,and the range and rate of the sweep angle variation are achieved by worm driving.The electric cylinder and the linear guide rail limit achieve the range and rate of the change of wingspread.The variable length extended mechanism is embedded in the variable swept angle mechanism,and two kinds of deformation are carried out simultaneously.The cross flow at the wing root is effectively reduced by using springs pushing the sealing plates. The cross flow between the fuselage and heel block fixed on the tunnel wall is reduced by installing rubber band on the fuselage.

关 键 词：弹翼变形 风洞试验 半模模型 后掠角变形 展长变形 

分 类 号：V211.74[航空宇航科学与技术—航空宇航推进理论与工程] V224