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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。
In recent years, with the rapid development of aircraft research and development, some models require interstage separation and grid force testing under supersonic conditions. In order to achieve interstage separation between supersonic aircraft and wind tunnel test of grid force measurement, a special delivery mechanism of FL-23 transonic supersonic wind tunnel was adopted to upgrade and support the upper and lower supports and their control systems, The direction of the compound movement, the establishment of Mach number 0.3 ~ 4.0 interstage separation system. After the multi-period model test, the system meets the requirements of model positioning control accuracy and meets the need of interstage separation and grid force wind tunnel test under high Mach number of aircraft.