领航-跟随编队控制使用差分阻力和有效表面调节
Leader-Follower Formation Control Using Differential Drag and Effective Surface Regulation
AI总结：
本文提出基于积分反推技术的控制策略，通过姿态机动实现小卫星间相对定位，利用差分阻力实现闭环稳定性，通过Lyapunov理论和数值模拟验证有效性。
摘要：
随着航天活动的增长，新的航天运营商和创新任务概念不断出现。小卫星如立方卫星降低任务成本，通常以星座或编队飞行部署。由于它们通常无推进，被动轨道控制策略是标准，主要通过姿态控制机动实现的差分阻力。本文开发了一个控制系统，以实现虚拟领航员和真实跟随器编队飞行中两颗小卫星之间的通用相对定位，完全依赖于通过姿态机动实现的差分阻力。我们提出了一种基于积分反推技术的控制律，在闭环与旋转动力学结合时，导致闭环系统平衡点的渐近稳定性。我们利用Lyapunov理论证明闭环系统平衡点的渐近稳定性，并通过数值模拟评估控制策略的有效性和准确性。
英文摘要：
The growing interest in space activities has led to the emergence of new space operators and innovative mission concepts. Small satellites such as CubeSats reduce mission costs and are typically deployed in constellations or formation flights. Since they are often propulsionless, passive orbital control strategies are the standard, primarily through differential drag achieved via attitude control maneuvers. This work develops a control system to achieve a generic relative positioning between two small satellites in a virtual leader and real follower formation flight, relying entirely on differential drag achieved through attitude maneuvers. We propose a control law based on the integrator backstepping technique, which, in a closed loop with the rotational dynamics, results in the asymptotic stability of the closed-loop system equilibrium points. We demonstrate the asymptotic stability of the closed-loop system equilibrium points using the Lyapunov theory, and a numerical simulation assesses the effectiveness and accuracy of the control strategy.
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。
