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

David Resendes, José Mendonça, Berry Sanders, J. De Teixeira Da Encarnação, Jose Gonzalez del Amo, Leik Myrabo

Research output: Chapter in Book/Conference proceedings/Edited volumeConference contributionScientificpeer-review

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.
Original languageEnglish
Title of host publicationAIP Conference Proceedings
EditorsK. Komurasaki, T. Yabe, S. Uchida, A. Sasoh
Pages576-587
Number of pages13
Volume830
DOIs
Publication statusPublished - 2006
Externally publishedYes
Event4th International Symposium on Beamed Energy Propulsion - Nara, Japan
Duration: 15 Nov 200518 Nov 2005
Conference number: 4

Conference

Conference4th International Symposium on Beamed Energy Propulsion
CountryJapan
CityNara
Period15/11/0518/11/05

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