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用一个１：１６的缩比固体推进剂发射装置，逼真。模拟了全尺寸垂直发射系统（ＶＬＳ）的瞬时压力和材料烧蚀特性的试验。在火箭发动机中测得的瞬时压力曲线，用四阶勒恩－库塔法的分块参数进行了验证。发射装置其它部件上的瞬时压力曲线与火箭发动机内的压力相似。为模拟全尺寸ＶＬＳ的喷管群，用２孔和４孔喷管分别作了试验，以研究喷管构型对压力和烧蚀材料的影响。喷管喉部面积较小，发射持续过程就较短并产生较高的质量流率。这些质量流从火箭发动机流入增压室。对烧蚀材料腐蚀深度的轮廓线的重复试验表明，已被烧蚀的表面比材料还未烧蚀的平整表面有更好的防烧蚀作用。烧蚀材料的烧蚀主要取决于从喷管喷出的质量流率和烧蚀材料的结构。
Use a 1:16 ratio solid propellant launcher, realistic. Simulations of instantaneous pressure and material ablation characteristics of a full-size vertical launch system (VLS) were performed. The instantaneous pressure curve measured in a rocket motor was verified by the block parameters of the fourth-order Lön-Kutta method. The instantaneous pressure profile on the other components of the launcher is similar to the pressure inside the rocket engine. To simulate a full-size VLS nozzle cluster, experiments were conducted with 2-hole and 4-hole nozzles to study the effects of nozzle configuration on pressure and ablative material. The laryngeal nozzle area is smaller and the launcher duration is shorter and produces a higher mass flow rate. These mass flows from the rocket engine into the plenum. Repeated tests of the profile of the ablation depth of the ablative material showed that the ablated surface had a better anti-ablation effect than the ablated ablated surface of the ablation material. Ablation of ablative material depends primarily on the mass flow rate ejected from the nozzle and the structure of the ablated material.