Convex Optimization of Launch Vehicle Ascent Trajectory with Heat-Flux and Splash-Down Constraints

What is it about?

Since present rockets can inject into orbit only a small fraction of their initial mass, trajectory optimization is key to improve the system performance and reduce the cost of access to space. This paper outlines a novel method, based on convex optimization, to formulate and efficiently solve the launch vehicle ascent optimal control problem. Also, the splash-down of the spent stages is taken into account and a sensitivity analysis of the vehicle carrying capacity relative to different splash-down locations is presented.

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