FL-23风洞级间分离与网格测力试验系统

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。

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

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.