Abstract Mission analysis using aerogravity-assist (AGA) maneuver at Titan is presented in this paper. Considering Saturn arrival, Titan encounter, and different post-AGA orbits, the analysis uses vector diagrams to illustrate the relations among all conditions as well as design constraints. The analysis focuses on Enceladus mission concept and also present a summary result for Cassini-type Saturn system missions. Turn angles using AGA maneuver at Titan are quantified via numerical simulation, showing that 25-deg AGA turn angles are achievable with a Titan inbound excess velocity ( V ∞ , IN ) of 10–20 km/s. Results show that for an Enceladus mission, V ∞ , IN of 10 km/s is the minimum velocity required for AGA maneuver to achieve an outbound transfer orbit directly to Enceladus; the corresponding peak g-load is less than 6 g, peak heat rate less than 200 W/cm2, and total heat load of around 25 kJ/cm2. For a Cassini-type Saturn mission, a minimum V ∞ , IN of 5 km/s can be used for Titan AGA. The results showed are for V ∞ , IN of 6 km/s; and the corresponding peak g-load, peak heat rate, and total heat load are 1.5 g, 20 W/cm2, and 5 kJ/cm2 respectively.

中文翻译：

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土星/土卫二任务的泰坦航空重力辅助演习

摘要 本文介绍了使用泰坦航空重力辅助 (AGA) 机动进行的任务分析。考虑到土星到达、泰坦遭遇和不同的后 AGA 轨道，分析使用矢量图来说明所有条件之间的关系以及设计约束。分析侧重于土卫二任务概念，并提供卡西尼型土星系统任务的总结结果。在泰坦上使用 AGA 机动的转向角通过数值模拟进行量化，表明在泰坦入站超速 (V ∞ , IN ) 为 10–20 km/s 的情况下，可以实现 25 度的 AGA 转向角。结果表明，对于土卫二任务，V ∞ , IN 为 10 km/s 是 AGA 机动实现直接到土卫二的出站转移轨道所需的最小速度；相应的峰值重力载荷小于 6 g，峰值热率小于 200 W/cm2，总热负荷约为 25 kJ/cm2。对于卡西尼型土星任务，Titan AGA 可使用最小 V ∞ , IN 5 km/s。结果显示为 V ∞ , IN 为 6 km/s；相应的峰值 g-load、峰值热速率和总热负载分别为 1.5 g、20 W/cm2 和 5 kJ/cm2。