Increased focus on space debris push regulations by the UN and thereby the demand for debris removal systems to be implemented in future spacecraft. This research focuses on debris removal of post-mission satellites in LEO using drag augmented deorbit into the earth's atmosphere. By using gossamer sails (drag sails), aerodynamic breaking can effectively be achieved in LEO up to 700 km. The presented work supplements the research performed in the H2020 project Technologies for Self-Removal of Spacecraft (TeSeR), in which the Self-Deployable Deorbiting Space Structure (SDSS) has been further developed. It is devised how to obtain a self-deployable drag sail folded nine times for use in debris removal for a 6U CubeSat, i.e. an SDSS/9. Achieving nine folds of Highly Flexible Frame (HFF) is essential to maximize the drag sail area when it is unfolded and hereby increasing drag force. The nine times folded HFF has been modeled in computer simulations and demonstrated in a lab. From lab-based research, several issues have been identified when folding the HFF nine times.

Of these, two main issues are addressed in this paper, i.e. relaxation and uncoiling. When folded nine times, the von Mises stresses computed by FEM reach 1857 MPa. Combined with residual stresses, this is causing yield and relaxation in the HFF and reducing the deployability. A minimum drag sail diameter is identified for this setup, and the high-strength stainless steel should be heat treated to relieve residual stresses before folding. A side-mounted design is chosen for the configuration of the SDSS. This reduces friction during the release and deployment of the drag sail. From thorough testing, it is observed that the uncoiling of the HFF during storage in the pocket significantly reduces the deployability of the SDSS. To mitigate both radial and axial uncoiling of the HFF in the pocket, the pocket diameter and height should be designed with an exact fit to the folded diameter and height of the ideally folded HFF with the drag sail included. Based on this research, a new design of the SDSS/9 for CubeSats is devised, and preliminary testing indicates good consistencies more test is necessary to determine the reliability of the side mounted SDSS. Hence, from the research, it is concluded that SDSS/9 is a feasible solution for a low-cost add-on debris removal system. Furthermore, the side-mounted design allows integration with additional collision protection of the spacecraft.

联合国对空间碎片的更多关注推动了法规，从而需要在未来的航天器中实施碎片清除系统。这项研究的重点是使用阻力增强脱轨进入地球大气层，清除 LEO 任务后卫星的碎片。通过使用游丝帆（拖帆），可以在 LEO 长达 700 公里的范围内有效实现空气动力破坏。所介绍的工作补充了 H2020 航天器自行移除技术 (TeSeR) 项目中进行的研究，其中进一步开发了可自行部署的脱轨空间结构 (SDSS)。设计了如何获得折叠九次的自展开式拖帆用于6U CubeSat的碎片清除，即SDSS/9。实现高柔性框架 (HFF) 的 9 折对于在展开时最大化阻力帆面积并因此增加阻力至关重要。九次折叠的 HFF 已在计算机模拟中建模并在实验室中进行了演示。根据实验室研究，在折叠 HFF 九次时已经确定了几个问题。

其中，本文讨论了两个主要问题，即松弛和展开。当折叠 9 次时，FEM 计算的 von Mises 应力达到 1857 MPa。结合残余应力，这会导致 HFF 屈服和松弛并降低可部署性。确定了此设置的最小阻力帆直径，并且高强度不锈钢应在折叠前进行热处理以释放残余应力。SDSS 的配置选择了侧装设计。这减少了在拖帆的释放和部署期间的摩擦。从彻底的测试中可以看出，在口袋中存储期间 HFF 的展开显着降低了 SDSS 的可部署性。为了减轻袋中 HFF 的径向和轴向开卷，口袋直径和高度的设计应与包含拖帆的理想折叠 HFF 的折叠直径和高度精确匹配。在此研究的基础上，为立方体卫星设计了一种新的 SDSS/9 设计，初步测试表明一致性良好，需要更多的测试来确定侧装 SDSS 的可靠性。因此，从研究中得出的结论是，SDSS/9 是低成本附加碎片清除系统的可行解决方案。此外，侧面安装的设计允许与航天器的额外碰撞保护集成。初步测试表明良好的一致性需要更多的测试来确定侧面安装的 SDSS 的可靠性。因此，从研究中得出的结论是，SDSS/9 是低成本附加碎片清除系统的可行解决方案。此外，侧面安装的设计允许与航天器的额外碰撞保护集成。初步测试表明一致性良好，需要更多的测试来确定侧装 SDSS 的可靠性。因此，从研究中得出的结论是，SDSS/9 是低成本附加碎片清除系统的可行解决方案。此外，侧面安装的设计允许与航天器的额外碰撞保护集成。