Abstract

In this paper, we study the scheme of a descent vehicle’s return from the Moon using several intermediate passages of the Earth’s atmosphere before landing. The features of the behavior of these trajectories near the Earth are shown for a ballistic capsule and gliding descent vehicles with low aerodynamic quality (0.3–0.5). Using the atmosphere as a natural braking method reduces inertial and thermal loads in comparison with direct entry at near-parabolic velocity. However, a decrease in the magnitude of loads is accompanied by an increase in the duration of their impact. Even in the case of one intermediate passage of the atmosphere, this leads to the burnout of a noticeably larger (compared to direct entry) mass of the heat-protective coating, which is a key factor in ensuring the safety of the descent. This paper shows that the use of trajectories with one intermediate passage of the atmosphere makes it possible to change the nature of the carryover of a heat-protective coating consisting of a filler and binder. For direct entry with a near-parabolic velocity, the destruction of the filler occurs accompanied by a change in the shape of the vehicle. When using the scheme with preliminary atmospheric braking, the bulk of the carried away matter falls on the binder, which brings the descent mode closer to the repeatedly worked out in practice descent from low near-Earth orbit.

中文翻译：

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使用多个进入大气层的弹道胶囊和滑翔下降飞行器从月球返回的轨迹的热分析

摘要

在本文中，我们研究了下降飞行器从月球返回的方案，在着陆前使用地球大气的几个中间通道。这些轨迹在地球附近的行为特征显示为具有低空气动力学质量 (0.3-0.5) 的弹道胶囊和滑翔下降飞行器。与以近抛物线速度直接进入相比，使用大气作为自然制动方法可减少惯性和热负荷。但是，载荷大小的减小伴随着冲击持续时间的增加。即使在大气的一个中间通道的情况下，这也会导致明显更大（与直接进入相比）质量的隔热涂层被烧毁，这是确保下降安全的关键因素。该论文表明，使用具有一个大气中间通道的轨迹可以改变由填料和粘合剂组成的隔热涂层的携带性质。为了以接近抛物线的速度直接进入，填充物的破坏伴随着车辆形状的改变而发生。当使用带有初步大气制动的方案时，大部分被带走的物质落在结合物上，这使得下降模式更接近于从近地低轨道在实践中反复制定的下降模式。填充物的破坏伴随着车辆形状的变化而发生。当使用带有初步大气制动的方案时，大部分被带走的物质落在结合物上，这使得下降模式更接近于从近地低轨道在实践中反复制定的下降模式。填充物的破坏伴随着车辆形状的变化而发生。当使用带有初步大气制动的方案时，大部分被带走的物质落在结合物上，这使得下降模式更接近于从近地低轨道在实践中反复制定的下降模式。