The co-delivery of a direct-entry probe and an aerocapture orbiter from a single atmospheric entry state is a novel way to include ride-along probes or orbiters on interplanetary missions. This is made possible through combining two technologies: low-cost small satellites and aerocapture. This study investigates the feasibility of this co-delivery method from a flight-mechanics perspective. The availability of direct-entry and aerocapture trajectories from a single entry flight-path angle is assessed for a large range of feasible ballistic coefficients at Earth, Mars, Venus, Titan, and Neptune. Apoapsis altitude, peak heat flux, total heat load, and peak g-load are also quantified across this trade space. A representative scenario implementing closed-loop guidance is presented for a proof of concept, and the trajectory dispersions due to relevant uncertainties are quantified in a Monte Carlo analysis. Passive ballistic impactor or penetrator probes as a secondary mission with a primary lift-modulated aerocapture orbiter is identified as the most promising configuration.

从单一大气进入状态共同交付直接进入探测器和航空捕获轨道飞行器是一种新颖的方式，可以在行星际任务中包括乘坐探测器或轨道飞行器。这是通过结合两种技术实现的：低成本小型卫星和航空捕获。本研究从飞行力学的角度调查了这种共同交付方法的可行性。针对地球、火星、金星、泰坦和海王星的大范围可行弹道系数，评估了从单次进入飞行路径角度直接进入和空中捕获轨迹的可用性。远点高度、峰值热通量、总热负荷和峰值 g 负荷也在这个交易空间中被量化。提出了一个实施闭环指导的代表性场景以进行概念验证，并且在蒙特卡罗分析中量化由于相关不确定性引起的轨迹离散。被动弹道撞击器或穿透器探测器作为带有主升力调制航空捕获轨道器的次要任务被认为是最有前途的配置。