The presence of parts separating from the launch vehicle (LV) during of the active part of the flight, such as the tail and interstage compartments, and payload fairing calls for the solution of the problem associated with the allocation of significant impact areas. This is a common problem in all spaceships, including the cases when recoverable and reusable first stages are used, for example, Falcon 9 launch vehicles. This paper considers one of the possible solutions to this problem, based on the combustion of separating parts during the descent trajectory flight. The study subject is a combustible demonstrator (CD), a small element of the three-layer shell of the payload fairing. The layers of the shell are the sheathings and the filler charge placed between them. The filler charge is a pyrotechnic composition (PC) initiated by the command, and the sheathing is a combustible polymer composite material (PCM). The material for the structures of the separating parts is produced as follows. First, a CD is created due to the chosen PCs and sheathings. Then, the required strength of the CD is ensured. Finally, the demonstrator structure is guaranteed to burn up or be fragmented finely for the given time.

在飞行的有效部分期间，与发射运载工具（LV）分开的部件（如尾部和级间舱室）以及有效载荷整流罩的存在，要求解决与重要撞击区域的分配有关的问题。这是所有宇宙飞船的普遍问题，包括使用可回收和可重复使用的第一级时的情况，例如Falcon 9运载火箭。本文基于下降轨迹飞行过程中分离零件的燃烧情况，考虑了该问题的一种可能解决方案。研究对象是可燃演示器（CD），是有效载荷整流罩三层外壳的一小部分。壳层是护套，填充剂位于它们之间。填充料是由该命令启动的烟火成分（PC），护套是可燃聚合物复合材料（PCM）。用于分离部件的结构的材料如下生产。首先，由于选择了PC和护套，因此创建了CD。然后，确保所需的CD强度。最后，保证演示器结构在给定时间内燃烧或被细碎。