为获得羽烟对激光透过率的影响，用烟箱法对2种配方的缩比发动机羽烟在1.06μm、10.6μm激光波段的透过率进行测试。采用1.064μm激光调制发射、接收、数据采集系统对1.06μm激光波段烟雾透过率测试；用黑体、光谱辐射计、数据采集系统可测出2μm ～13μm 的光学透过率，从中提出10.6μm激光波段烟雾透过率，得到不同推进剂配方、不同烟雾浓度情况下10.6μm光波和1.06μm光波的烟雾透过率测试数据。烟箱1.8m烟道上的测试数据表明：配方2推进剂优于配方1推进剂，10.6μm光波的烟雾透过率96%～97%大于1.06μm光波的烟雾透过率92%～93%。

The main performance of hyper-velocity kinetic missile and its solid propellants is described. The mechanism of laser attenuation caused by the plume of solid rocket motor is analyzed. The plume transmittance of two solid-propellant formulations was tested by the aid of a smoke-box when the laser wavebands were 1.06μm and 10.6μm. The plume transmittance in 1.06μm laser was tested with 1.064μm laser modulation emitting, receiving and data acqui-sition system. The plume transmittance of 10.6μm laser was derived after the optical transmittance of 2μm ～13μm laser was tested with the blackbody radiation source, spectroradiometer and data acquisition system. The tested data indicates that formulation 2 is better than formulation 1, and the plume transmittance 96%～97% of 10.6μm laser is higher than that 92%～93% of 1.06μm laser.