Convex optimization techniques have deterministic convergence properties, do not require an initial guess, and have been tested in real-time environments. These optimization techniques are applied to the trajectory planning problem for orbital rendezvous and proximity operations. Spacecraft rendezvous, inspection, and final approach trajectories are considered. Optional trajectory constraints are considered, including approach corridors, keep-out zones, and maximum thrust acceleration levels. Two linear dynamics models are investigated: Clohessy-Wiltshire dynamics to describe the relative motion in a local-horizontal local-vertical frame, and a new relative orbital motion dynamics model to describe the motion relative to a spinning or uncontrolled spacecraft. In both cases, an algorithm based on a second-order cone program is developed and used to generate optimal rendezvous and proximity operation trajectories. Results for several scenarios are presented and implemented in a nonlinear orbital simulation.

凸优化技术具有确定性的收敛特性，不需要初步猜测，并且已经在实时环境中进行了测试。这些优化技术被应用于轨道交会和接近操作的轨迹规划问题。考虑了航天器的交会，检查和最终进场轨迹。考虑了可选的轨迹约束，包括进近走廊，避让区和最大推力加速度水平。研究了两个线性动力学模型：Clohessy-Wiltshire动力学用于描述局部-水平局部-垂直框架中的相对运动，以及新的相对轨道运动动力学模型来描述相对于旋转或不受控制的航天器的运动。在这两种情况下 开发了基于二阶圆锥程序的算法，并将其用于生成最佳的会合和接近操作轨迹。提出了几种情况的结果，并在非线性轨道仿真中实现了这些结果。