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<p>This study proposes an orbit design strategy for reusable space vehicles performing short-duration surveillance and reconnaissance missions, aiming to simultaneously achieve fast initial target access and enhanced revisit performance. Generally, conventional orbit designs have ensured target revisit primarily through repeat ground track. This study proposes additional target revisits by exploiting ground track intersection in inclined orbits. The orbit design problem is formulated as an optimization problem that minimizes the residuals of three nonlinear equality conditions derived from spherical geometry and <i>J</i><sub>2</sub>-perturbed orbit dynamics, where each residual is interpreted as a surface distance error for quantitative performance assessment. Simulation results indicate that the proposed method improves the 47.3-h revisit interval reported in the prior study to a maximum of 20.2&#xa0;h and a minimum of 3.3&#xa0;h (average 11.7&#xa0;h) without altering mission constraints. Additionally, a procedure for deriving initial conditions for high-fidelity numerical propagation from optimal orbital elements is presented.</p>

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Fast Access Revisit Orbit Design Via Ground Track Intersection Point

  • 期刊论文

  • 发表日期：

    2026年6月27日

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  • Seonwoo Son,
  • Jinah Lee,
  • Kwanyeong Kim,
  • Chandeok Park

摘要

This study proposes an orbit design strategy for reusable space vehicles performing short-duration surveillance and reconnaissance missions, aiming to simultaneously achieve fast initial target access and enhanced revisit performance. Generally, conventional orbit designs have ensured target revisit primarily through repeat ground track. This study proposes additional target revisits by exploiting ground track intersection in inclined orbits. The orbit design problem is formulated as an optimization problem that minimizes the residuals of three nonlinear equality conditions derived from spherical geometry and J2-perturbed orbit dynamics, where each residual is interpreted as a surface distance error for quantitative performance assessment. Simulation results indicate that the proposed method improves the 47.3-h revisit interval reported in the prior study to a maximum of 20.2 h and a minimum of 3.3 h (average 11.7 h) without altering mission constraints. Additionally, a procedure for deriving initial conditions for high-fidelity numerical propagation from optimal orbital elements is presented.