FL-23风洞级间分离与网格测力试验系统  

The stage separation and proximity matrix test in FL-23 wind tunnel

作　　者：何彬华[1] 凌忠伟[1] 胡向鹏[1] 高鹏[1] 

机构地区：[1]中国空气动力研究与发展中心,四川绵阳621000

出　　处：《实验流体力学》2013年第4期109-112,共4页Journal of Experiments in Fluid Mechanics

摘　　要：近年来,随着飞行器研制不断高速化发展,一些型号要求在超声速条件下实现级间分离与网格测力试验。为了实现超声速飞行器级间分离与网格测力风洞试验,利用FL-23跨超声速风洞独有的投放机构,通过对上、下支撑及其控制系统进行改造升级,实现了X、Y两个方向的复合运动,建立了马赫数0.3～4.0的级间分离系统。经过多期型号试验验证,该系统对模型定位控制精度达到要求,满足飞行器高马赫数下开展级间分离与网格测力风洞试验需求。Recent advancement in aircraft design has promoted the stage separation and proximity matrix test in supersonic flow for certain aircraft models.The challenges and difficulties involved to realize these tests in a wind tunnel are about ensuring the model’s fixed position and gesture during wind tunnel tests.In order to realize such tests in the FL-23wind tunnel,we propose a stage separation system for aircrafts with Mach number from 0.4to 4.0.This is achieved by refining the support framework of model and the control system for a combinatorial motion in both Xand Ydirections.The system precision is tested under various aircraft models which indicated the effectiveness of the proposed model for aircrafts with high Mach number.

关 键 词：风洞 超声速流动 控制系统 级间分离 网格测力 

分 类 号：V211.73[航空宇航科学与技术—航空宇航推进理论与工程]