A performance analysis for aerocapture at Uranus and Neptune is presented and considers entry corridor width, peak deceleration, peak heat rate, total heat load, and the effect of postcapture orbit on the design parameters. Aerocapture mass benefit vs chemical capture is also quantified. Design relationships are found that can be used in flight system sizing for future studies involving aerocapture. Results are obtained for interplanetary trajectories for launch years from 2025 to 2036, including both chemical capture and high arrival $V_{\infty }$. The results show that based on the current assumption for errors and uncertainties aerocapture at Uranus and Neptune requires a mid-lift-to-drag ratio between 0.6 and 0.8. Technology recommendations are made for aerocapture missions to Uranus and Neptune.

提出了对天王星和海王星航空捕获的性能分析，并考虑了入口走廊的宽度，峰值减速度，峰值热率，总热负荷以及捕获后轨道对设计参数的影响。航空捕集质量收益与化学捕集的关系也得以量化。发现可以在飞行系统尺寸确定中用于未来涉及航空捕获的研究的设计关系。获得了从2025年到2036年发射年的行星际轨迹的结果，包括化学捕获和高到达$V_{\infty }$。结果表明，基于当前对误差和不确定性的假设，天王星和海王星的航空捕获需要将升力与阻力之比控制在0.6到0.8之间。为前往天王星和海王星的航空飞行任务提出了技术建议。