发表机构
Politecnico di Torino; The University of Osaka（都灵理工大学; 大阪大学）
机构由 AI 辅助整理，请以论文原文为准。AI 中文总结
本文针对低轨航天器高精度编队控制，提出端口-哈密顿框架下的自适应边界层滑模控制（AB-SMC），通过动态调整滑模面提升瞬态性能，实现亚毫米级跟踪精度并保证闭环稳定性。
AI 中文摘要
本文针对低地球轨道航天器的高精度编队控制问题展开研究，其动机源于未来空间干涉测量任务（如SILVIA）的需求。所提方法在端口-哈密顿框架内构建相对动力学模型，并引入一种自适应边界层滑模控制（AB-SMC）律，以克服传统常增益滑模控制（SMC）的局限性。其关键创新在于对滑模面进行动态的、依赖于误差的调整，从而在保证高精度轨迹跟踪的同时提升瞬态性能。基于李雅普诺夫的严谨分析确立了跟踪误差的显式最终界，并确保了闭环稳定性；此外，广泛的蒙特卡洛仿真进一步验证了所提AB-SMC相较于标准控制方法的优越性。结果表明，AB-SMC实现了更快的收敛速度、更低的控制能耗以及亚毫米级的跟踪精度，展示了其在真实、不确定的轨道环境中，在满足低推力约束条件下的实际鲁棒性和工程可行性。
英文摘要
This paper addresses high-precision formation control for spacecraft operating in low Earth orbit, motivated by the requirements of future space interferometry missions such as SILVIA. The proposed approach formulates the relative dynamics within a port-Hamiltonian framework and introduces an Adaptive Boundary-layer Sliding Mode Control (AB-SMC) law to overcome the limitations of conventional SMC with constant gains. The key innovation lies in a dynamic, error-dependent adjustment of the sliding manifold, enhancing transient performance while guaranteeing high-precision trajectory tracking. Rigorous Lyapunov-based analysis establishes explicit ultimate bounds on the tracking error and ensures closed-loop stability, while extensive Monte Carlo simulations further validate the proposed AB-SMC compared to standard control approaches. Results show that AB-SMC achieves faster convergence, lower control effort, and sub-millimeter tracking accuracy, demonstrating its practical robustness and implementation feasibility in realistic, uncertain orbital environments while respecting low-thrust constraints.
Journal refControl Engineering Practice, Volume 174, 2026, 107025, ISSN 0967-0661,
DOI：10.1016/j.conengprac.2026.107025
