The potentially hazardous asteroid is not only the target of planetary defense missions but also an ideal one for scientific exploration of near-Earth objects due to minimal launching budget during its close encounter with Earth. The flyby segment of asteroid shows to be hyperbolic in an Earth-centred inertial frame. To guide the spacecraft captured by the asteroid under the common Earth's gravity, the Hamiltonian-structure-preserving (HSP) controller, based only on the feedback of relative positions, is constructed to transform the topological structure of the equilibrium point from hyperbolic to elliptic. On account of the small mass of flyby asteroid, a hyperbolic two-body model is used to derive the form of controller. The controller is also proved to work effectively in the hyperbolic three-body model. Critical control gains for both transient and long-term stabilities are investigated, as well as the controlled frequencies caused by different gains. To avoid collision with an asteroid, the artificial potential function (APF) is employed to improve the HSP controller.

潜在危险的小行星不仅是行星防御任务的目标，而且是近地物体科学探索的理想选择，因为在与地球的近距离接触中发射预算极低。在以地球为中心的惯性系中，小行星的飞越部分显示为双曲线。为了引导小行星在共同的地球重力作用下捕获的航天器，仅基于相对位置的反馈，构造了哈密尔顿结构保持（HSP）控制器，将平衡点的拓扑结构从双曲线转换为椭圆形。由于飞越小行星的质量较小，因此使用了双曲线两体模型来导出控制器的形式。该控制器还被证明在双曲三体模型中有效工作。研究了瞬态和长期稳定性的关键控制增益，以及由不同增益引起的受控频率。为了避免与小行星碰撞，采用了人工势函数（APF）来改进HSP控制器。