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Seuring, Stefan |
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Nor Azizi, S. |
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Pato, Margarida Vaz |
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Kölker, Katrin |
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Huber, Oliver |
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Király, Tamás |
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Spengler, Thomas Stefan |
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Al-Ammar, Essam A. |
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Dargahi, Fatemeh |
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Mota, Rui |
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Mazalan, Nurul Aliah Amirah |
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Macharis, Cathy | Brussels |
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Arunasari, Yova Tri |
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Nunez, Alfredo | Delft |
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Bouhorma, Mohammed |
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Bonato, Matteo |
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Fitriani, Ira |
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Autor Correspondente Coelho, Sílvia. |
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Pond, Stephen |
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Okwara, Ukoha Kalu |
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Toufigh, Vahid |
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Campisi, Tiziana | Enna |
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Ermolieva, Tatiana |
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Sánchez-Cambronero, Santos |
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Agzamov, Akhror |
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Agzamov, Akhror
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document
Microwave Thermal Rocket Engine-Based Orbital Launch System Implementation
Abstract
Chemical rocket engines’ specific impulse (Isp) limitations hinder the introduction of fully reusable single-stage launch vehicles with high payload mass-fraction. Modern launchers rely on multi-staging, face reusability difficulties, and resulting in a low payload mass-fraction compared to other vehicles. Microwave Thermal Rocket (MTR) method was explored as a more efficient solution but was abandoned due development cost risks. There are three types of rocket engines for orbital launch: (1) Chemical engines, (2) nuclear thermal rocket (NTR) engine, and (3) beam-powered engines (microwave or laser). Chemical engines provide low Isp, but high thrust-to-weight ratio (T/W). NTR engines offer high Isp but have low T/W and cause radiation pollution. MTR engines provide similar to NTR Isp and T/W similar to chemical engines without radiation pollution. MTR differ from conventional rockets as the power source is ground-based. The engine and ground-based beam director communicate to adjust power intensity and guidance parameters for autonomous ascent. This communication is to be done without human interaction, which is the ability of autonomy. However, as strong interference may put the viability of this essential feature in doubt. We propose a solution to address this problem. Research also proposes a commercially viable microwave-powered launch method utilizing reduced frequency Gyrotrons, air-launch method, and direct methane heating design to reduce research, development, and infrastructure costs. MTR engines can provide high Isp, enabling fully reusable single-stage vehicles with higher payload mass-fraction. Our approach trades off maximum performance for cost reduction, aligning with private investing market needs and supporting the trend of commercial space expansion.
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