航天器设计的最佳化，以确保其报废和生存能力;
Spacecraft design optimisation for demise and survivability
摘要：
在为处理空间碎片问题而采取的减缓措施中，有一项是使退役卫星脱离轨道。再入物体准则要求地面伤亡风险不高于0.0001。为了符合这一要求，可以通过为消亡而设计的理念来设计卫星。尽管如此，一个设计为死亡的航天器必须在碎片密集的太空环境中生存多年。卫星的可拆卸性和生存性都可以受到一组常见设计选择的影响，例如材料选择，几何定义和组件的位置。在这方面，开发了两种模型来分析卫星的报废和生存能力。考虑到可放弃性和生存性的竞争性质，开发了一个多目标优化框架，目的是为卫星的初步设计确定折衷解决方案。由于该问题是非线性的，涉及到连续和离散变量的组合，经典的导数为基础的方法是不适合的，而遗传算法被选中。遗传算法使用开发的可灭绝性和生存性标准作为多目标算法的适应度函数。本文提出了一个测试案例，它考虑了初步优化的坦克的材料，几何形状，位置和数量的坦克的一个代表性的地球观测任务。航天器外部结构的配置是固定的。选择坦克是因为它们对两种设计要求都很敏感：它们是销毁过程中的关键部件，撞击损坏可能因泄漏和破裂而导致任务损失。结果提出了可能的权衡解决方案，构成从多目标优化得到的帕累托前沿。
英文摘要：
Among the mitigation measures introduced to cope with the space debris issue there is the de-orbiting of decommissioned satellites. Guidelines for re-entering objects call for a ground casualty risk no higher than 0.0001. To comply with this requirement, satellites can be designed through a design-for-demise philosophy. Still, a spacecraft designed to demise has to survive the debris-populated space environment for many years. The demisability and the survivability of a satellite can both be influenced by a set of common design choices such as the material selection, the geometry definition, and the position of the components. Within this context, two models have been developed to analyse the demise and the survivability of satellites. Given the competing nature of the demisability and the survivability, a multi-objective optimisation framework was developed, with the aim to identify trade-off solutions for the preliminary design of satellites. As the problem is nonlinear and involves the combination of continuous and discrete variables, classical derivative based approaches are unsuited and a genetic algorithm was selected instead. The genetic algorithm uses the developed demisability and survivability criteria as the fitness functions of the multi-objective algorithm. The paper presents a test case, which considers the preliminary optimisation of tanks in terms of material, geometry, location, and number of tanks for a representative Earth observation mission. The configuration of the external structure of the spacecraft is fixed. Tanks were selected because they are sensitive to both design requirements: they represent critical components in the demise process and impact damage can cause the loss of the mission because of leaking and ruptures. The results present the possible trade off solutions, constituting the Pareto front obtained from the multi-objective optimisation.
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