Laser Propulsion for ESA Missions: Ground to Orbit Launch Project Overview — Part 1

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Laser Propulsion for ESA Missions: Ground to Orbit Launch Project Overview — Part 1

Conference Paper (2006)

Author(s)

David Resendes (Universidade Técnica de Lisboa)

José Mendonça (Universidade Técnica de Lisboa)

Berry Sanders (TNO)

J. De Teixeira Da Encarnação (Student TU Delft)

Jose Gonzalez del Amo (European Space Agency (ESA))

Leik Myrabo (Rensselaer Polytechnic Institute)

DOI related publication

https://doi.org/10.1063/1.2203299 Final published version

To reference this document use

https://resolver.tudelft.nl/uuid:dd62597b-6633-40a4-9e58-4b765b6c200d

More Info

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Publication Year

2006

Language

English

Volume number

830

Pages (from-to)

576-587

Event

4th International Symposium on Beamed Energy Propulsion (2005-11-15 - 2005-11-18), Nara, Japan

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109

Abstract

A thermal laser thruster depends on introduction of a high energy laser beam, absorption by the fluid propellant, confinement of the hot propellant gas with minimal losses, and conversion of thermal to kinetic energy in the nozzle. Based on thermodynamic constraints, efficient energy conversion is possible in either the subsonic Laser Supported Combustion (LSC) wave in a converging diverging nozzle or the supersonic Laser Supported Detonation (LSD) wave in a diverging nozzle configuration. A short discussion of both mechanisms is presented. Thruster modeling was performed. The results of steady laser heated LSD flows using LiH as propellant assuming finite rate chemistry are presented.