Launch Vehicle First Stage Reusability

a study to compare different recovery options for a reusable launch vehicle

Master thesis (2020)

Authors

M.D. Rozemeijer Aerospace Engineering

Contributors

B.T.C. Zandbergen Space Systems Egineering (supervisor 1)
Faculty
Aerospace Engineering
Copyright: © 2020 Mark Rozemeijer
Surrogate-based optimization Optimisation Algorithms Reusability Launchers
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Published Date

01-12-2020

Language

English

Reuse Rights

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Faculty

Aerospace Engineering

Abstract

In order to make access to space cheaper, the first stage of a launcher can be recovered. For this research, different options are investigated to make the cost per flight cheaper. Two vehicles are investigated going to two different orbits. The results show that recovering the complete stage is better for vehicles that have a lower separation velocity. When the separation velocity is higher, recovering only the engine is better. The best results are obtained when using a Ringsail parachute and a Hypersonic Inflatable Aerodynamic Decelerator. The design for these systems is optimised using a surrogate optimisation algorithm that reduces the computation time. The set target of 30% cost savings could not be achieved, but cost savings of at least 20% were achieved for both vehicles.