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首页> 外文会议>International Astronautical Congress >AN ENGINEERING MODEL TO DESCRIBE FRAGMENTS CLOUDS PROPAGATING INSIDE SPACECRAFT IN CONSEQUENCE OF SPACE DEBRIS IMPACT ON SANDWICH PANEL STRUCTURES
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AN ENGINEERING MODEL TO DESCRIBE FRAGMENTS CLOUDS PROPAGATING INSIDE SPACECRAFT IN CONSEQUENCE OF SPACE DEBRIS IMPACT ON SANDWICH PANEL STRUCTURES

机译：一种工程模型，用于描述航天器中传播的碎片云，结果是对夹层面板结构的空间碎片影响

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All spacecraft in Earth orbit are exposed to the risk of impact with micrometeoroids and orbital debris. When such particles have enough energy to penetrate the hull of the vehicle, clouds of fragments are ejected into spacecraft and they can eventually compromise the functionality of various components encountered in their flight path. Knowledge of the clouds' properties (e.g. fragments mass and velocity) is therefore a key factor to obtain accurate predictions of the response of interior equipment to space debris threat. However, generation and evolution of debris clouds from hypervelocity impact is a complex phenomenon governed by a large number of parameters, and existing models mostly refer to fragments originated by impact on simple aluminium plates only, while the few models available for sandwich panels do not provide information on the fragments mass. In such context, this paper presents an engineering mode] describing debris clouds created by space debris impacts on honeycomb sandwich panels representative of satellites structural bodies. The model consists of a set of empirical equations providing three pieces of information, i.e. the geometric description of the cloud, the velocity distribution and the mass distribution of the fragments. The proposed equations are derived from analogous formulas for debris clouds originated by impacts on simple aluminium plates, by applying proper corrections to account for different materials effects and different behaviour of sandwich panels compared to plates of same material. The model is finally evaluated by comparing its predictions with few experimental data on triple wall structures (sandwich panel plus internal equipment cover plate), where debris clouds exiting the panels' rear skin are used to assess the failure of the third wall. In this latter case, the proposed model is also compared with the SRL equations.
机译：地球轨道的所有航天器都暴露于对微晶体和轨道碎片影响的风险。当这种颗粒具有足够的能量来穿透车辆的船体时，片段的云被喷射到航天器中，并且它们最终可以损害在其飞行路径中遇到的各种组件的功能。因此，了解云属性（例如碎片质量和速度）是获得内部设备对空间碎片威胁的准确预测的关键因素。然而，来自超高速影响的碎片云的生成和演变是由大量参数控制的复杂现象，并且现有的模型主要是指仅由简单铝板的影响的碎片，而夹层面板的少数型号也不提供碎片质量的信息。在这种情况下，本文介绍了一种工程模式，描述由空间碎片影响的空间碎片对卫星结构体代表蜂窝夹层面板产生的碎片云。该模型包括一组经验方程，提供三条信息，即云的几何描述，速度分布和碎片的质量分布。所提出的方程从类似的公式导出的碎片云起源由简单铝板的影响，通过施加适当的修正，以考虑不同的材料效果和夹层板的不同的行为相比，相同的材料构成的板。最终通过将其预测与少量关于三墙结构（夹层板加上内部设备盖板）进行比较来评估模型，其中用于退出面板后皮的碎屑云来评估第三壁的故障。在后一种情况下，所提出的模型也与SRL方程进行比较。

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