The purpose of this research is to show the potentiality of the rocket with solar heating of working fluid. The study describes design of the heater with tungsten pipes, ensuring full-range application of focusing radiation (95 %) under the hydrogen heating to 2900 К; gives an examples of optimization of rocket engine thrust by the flight time with predetermined fuel weight and specific weight of engine with mirror and payload; illustrates design of the engine and mirrors providing the conjugation between the thrust vector and solar radiation vector; demonstrates design of power-supply source with high-efficient solar energy transformation into electric one and compares various types of the rockets.
| Published in |
American Journal of Aerospace Engineering (Volume 3, Issue 1-1)
This article belongs to the Special Issue Space Laboratories: History, Researches, Prospects |
| DOI | 10.11648/j.ajae.s.2016030101.11 |
| Page(s) | 1-5 |
| Creative Commons |
This is an Open Access article, distributed under the terms of the Creative Commons Attribution 4.0 International License (http://creativecommons.org/licenses/by/4.0/), which permits unrestricted use, distribution and reproduction in any medium or format, provided the original work is properly cited. |
| Copyright |
Copyright © The Author(s), 2024. Published by Science Publishing Group |
Nuclear Rocket Engine (NRE), Working Fluid, Solar-Heated Rocket Engine, Mass of Engine and Mirrors, Open Space, High-Temperature Reactor Components
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| [4] | Koroteev A.S., Akimov V.N., Arkhangelsky V.I., Kuzmin E.P. Solar thermal rocket engine. Patent of Russia No. 2126493 of Feb. 20; 1999. |
| [5] | Fluent version 6.3.26 User Reference. Fluent, Inc.; 2006. |
| [6] | Kotov V.M. High-temperature solar heater. Innovative patent of the Republic of Kazakhstan. No. 22587 of Jun 15, 2010. |
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| [8] | Kotov V.M. Energy source for a solar-heated rocket engine. Innovative patent of the Republic of Kazakhstan. No.22809 of Aug 15, 2010. |
APA Style
V. М. Kotov. (2015). Towards the Capabilities of Rocket Engines with Solar Heating of Working Fluid. American Journal of Aerospace Engineering, 3(1-1), 1-5. https://doi.org/10.11648/j.ajae.s.2016030101.11
ACS Style
V. М. Kotov. Towards the Capabilities of Rocket Engines with Solar Heating of Working Fluid. Am. J. Aerosp. Eng. 2015, 3(1-1), 1-5. doi: 10.11648/j.ajae.s.2016030101.11
AMA Style
V. М. Kotov. Towards the Capabilities of Rocket Engines with Solar Heating of Working Fluid. Am J Aerosp Eng. 2015;3(1-1):1-5. doi: 10.11648/j.ajae.s.2016030101.11
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Download@article{10.11648/j.ajae.s.2016030101.11,
author = {V. М. Kotov},
title = {Towards the Capabilities of Rocket Engines with Solar Heating of Working Fluid},
journal = {American Journal of Aerospace Engineering},
volume = {3},
number = {1-1},
pages = {1-5},
doi = {10.11648/j.ajae.s.2016030101.11},
url = {https://doi.org/10.11648/j.ajae.s.2016030101.11},
eprint = {https://article.sciencepublishinggroup.com/pdf/10.11648.j.ajae.s.2016030101.11},
abstract = {The purpose of this research is to show the potentiality of the rocket with solar heating of working fluid. The study describes design of the heater with tungsten pipes, ensuring full-range application of focusing radiation (95 %) under the hydrogen heating to 2900 К; gives an examples of optimization of rocket engine thrust by the flight time with predetermined fuel weight and specific weight of engine with mirror and payload; illustrates design of the engine and mirrors providing the conjugation between the thrust vector and solar radiation vector; demonstrates design of power-supply source with high-efficient solar energy transformation into electric one and compares various types of the rockets.},
year = {2015}
}
TY - JOUR T1 - Towards the Capabilities of Rocket Engines with Solar Heating of Working Fluid AU - V. М. Kotov Y1 - 2015/07/28 PY - 2015 N1 - https://doi.org/10.11648/j.ajae.s.2016030101.11 DO - 10.11648/j.ajae.s.2016030101.11 T2 - American Journal of Aerospace Engineering JF - American Journal of Aerospace Engineering JO - American Journal of Aerospace Engineering SP - 1 EP - 5 PB - Science Publishing Group SN - 2376-4821 UR - https://doi.org/10.11648/j.ajae.s.2016030101.11 AB - The purpose of this research is to show the potentiality of the rocket with solar heating of working fluid. The study describes design of the heater with tungsten pipes, ensuring full-range application of focusing radiation (95 %) under the hydrogen heating to 2900 К; gives an examples of optimization of rocket engine thrust by the flight time with predetermined fuel weight and specific weight of engine with mirror and payload; illustrates design of the engine and mirrors providing the conjugation between the thrust vector and solar radiation vector; demonstrates design of power-supply source with high-efficient solar energy transformation into electric one and compares various types of the rockets. VL - 3 IS - 1-1 ER -
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