Stage separation trajectory simulation test technique in high speed wind tunnel
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摘要: 针对多级航天器级间分离研究的地面试验需求，在高速风洞中发展了能够同时模拟前、后级运动的级间分离试验技术。利用风洞的上、下迎角机构，配置电机、传动系统和控制系统，建立了可变迎角和x向位移的上驱动机构，以及可变迎角、x向位移和y向位移的下驱动机构。分别将多级航天器的前、后级模型及测力天平与风洞上、下驱动机构连接，在级间分离计算机控制下，可开展前级迎角、后级迎角、前后级x向和y向相对位置协同模拟的轨迹模拟试验。调试和应用结果表明：上驱动机构可实现迎角–15°～15°、x向0～200 mm范围内的受控运动；下驱动机构可实现迎角–11°～49°、x向0～680 mm、y向0～507 mm范围内的受控运动；系统可用于常规测力试验、投放试验、网格测力试验和轨迹捕获试验。Abstract: Stage separation trajectory capturing test technique in the FL-23 wind tunnel was developed for investigating the stage separation dynamics of future multi-stage launch vehicle systems. By making use of the tunnel's upper and lower attack angle support mechanism and modification of servo-motors, transmission mechanism and control modules, a upper rig with two degrees of freedom of alpha, x, a lower rig with three degrees of freedom of alpha, x and y, and a coupling motion control system were set up. For a two stage vehicle, the two stage models and their force balances could be mounted on the upper and lower rigs respectively, and the stage separation trajectory could be simulated in the wind tunnel under control of the stage separation test computer, with coordinated motion of the angle of attack of the fore stage model, the angle of attack of the aft stage model, and the relative position in x and y directions of the two stage models. Conclusions could be obtained from verification experiments and client experiments, namely, the upper driving mechanism of the stage separation test system could pitch from –15° to 15°, and move from 0 to 200 mm in the x direction. The lower driving mechanism could pitch from –11° to 49°, and move from 0 to 680 mm in the x direction and from 0 to 507 mm in y direction. And the system could be used to conduct the tests for force measurement, model injection experiment, grid force measurement and capture trajectory simulation.
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表 1 飞行器质量特性
Table 1. Mass properties of aircrafts
质量m/kg 转动惯量Iz /（kg·m2） 前级 500 618 后级 500 103 
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表 2 分离初始条件
Table 2. Initial conditions of stage separation
初始马赫数 初始高度/
km弹道倾角/
（°）分离迎角/
（°）分离速度/
（m·s–1）3.0 10 –70 0 10
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