A preliminary study of pulse-laser powered orbital launcher |
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| Authors: | Hiroshi Katsurayama Kimiya Komurasaki Yoshihiro Arakawa |
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| Institution: | aInstitute of Space and Astronautical Science, Japan Aerospace Exploration Agency, 3-1-1 Yoshinodai, Sagamihara, Kanagawa 229-8510, Japan;bThe University of Tokyo, Department of Advanced Energy, 5-1-5 Kashiwanona, Kashiwa, Chiba 277-8561, Japan;cThe University of Tokyo, Department of Aeronautics and Astronautics, 7-3-1 Hongo Bunkyo-ku, Tokyo 133-8656, Japan |
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| Abstract: | An air-breathing pulse-laser powered orbital launcher has been proposed as an alternative to conventional chemical launch systems. The aim of the present study is to assess its feasibility through the estimation of its achievable payload mass per unit beam power and launch cost. A transfer trajectory from the ground to a geosynchronous Earth orbit (GEO) is proposed, and the launch trajectory to its geosynchronous transfer orbit (GTO) is computed using the realistic performance modeled in the pulsejet, ramjet, and rocket flight modes of the launcher. Results show that the launcher can transfer 0.084 kg of payload per 1 MW beam power to a geosynchronous earth orbit. The cost becomes a quarter of existing systems if one can divide a single launch into 24,000 multiple launches. |
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| Keywords: | Laser propulsion Space transportation Launch cost |
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