Optimal Lunar Lander

This paper presents optimal trajectory solutions for guiding the Apollo Lunar Excursion Module (LEM) to and from the Moon's surface. GPOPS II was used to solve the nonlinear control problem, providing full state and control histories for optimal ascent, descent and abort scenarios. Although historically Apollo did not follow an optimal trajectory due to terrain and navigation constraints, the methods presented here can be used by future mission planners to quantify mission risk and potentially adapt the concept of operations for optimal astronaut safety.

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