在终止设计范例下初步航天器构型的约束优化;
Constrained optimisation of preliminary spacecraft configurations under the design-for-demise paradigm
摘要：
在过去几年中，对实施“为消亡而设计”措施的兴趣稳步增加。目前发射并已在轨道上的大多数中型卫星未能达到0.0001的伤亡风险阈值。因此，卫星制造商和飞行任务运营商需要通过受控重返进行处置，而这种方式成本较高，复杂性也有所增加。通过为报废而设计的范例，可以消除这种额外的费用和复杂性，因为航天器直接符合伤亡风险条例。然而，建造一个航天器，使其大部分部件报废，可能会导致设计更容易受到空间碎片的影响，从而损害飞行任务的可靠性。事实上，与可让渡性和可生存性相关的要求通常是相互竞争的。鉴于这种相互竞争的性质，可以找到折衷的解决办法，既有利于实施报废设计措施，又能保持航天器对空间碎片撞击的承受能力。一个多目标优化框架已开发的作者在以前的作品。该框架的目标是，从飞行任务设计的早期阶段起，考虑到航天器的可弃性和生存性的相互竞争性质，找到初步设计解决办法。通过这种方式，可以实现更集成的设计。目前的工作重点是改进的多目标优化框架，包括约束。本文显示了应用程序的约束优化两个相关的例子：优化的坦克组装和优化的一个典型的卫星配置。
英文摘要：
In the past few years, the interest towards the implementation of design-for-demise measures has increased steadily. Most mid-sized satellites currently launched and already in orbit fail to comply with the casualty risk threshold of 0.0001. Therefore, satellites manufacturers and mission operators need to perform a disposal through a controlled re-entry, which has a higher cost and increased complexity. Through the design-for-demise paradigm, this additional cost and complexity can be removed as the spacecraft is directly compliant with the casualty risk regulations. However, building a spacecraft such that most of its parts will demise may lead to designs that are more vulnerable to space debris impacts, thus compromising the reliability of the mission. In fact, the requirements connected to the demisability and the survivability are in general competing. Given this competing nature, trade-off solutions can be found, which favour the implementation of design-for-demise measures while still maintaining the spacecraft resilient to space debris impacts. A multi-objective optimisation framework has been developed by the authors in previous works. The framework's objective is to find preliminary design solutions considering the competing nature of the demisability and the survivability of a spacecraft since the early stages of the mission design. In this way, a more integrated design can be achieved. The present work focuses on the improvement of the multi-objective optimisation framework by including constraints. The paper shows the application of the constrained optimisation to two relevant examples: the optimisation of a tank assembly and the optimisation of a typical satellite configuration.
机构、总结、中文摘要均由AI分析而来，可能存在错误，请以论文正文为准。
