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Journal articles on the topic 'Nuclear rocket engine'

Author: Grafiati

Published: 2 June 2025

Last updated: 31 July 2025

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1

Лазарева, Ю. И., С. В. Клименко, А. В. Кулик та И. В. Лазарев. "АНАЛИЗ СОВРЕМЕННОГО СОСТОЯНИЯ И ПЕРСПЕКТИВЫ РАЗВИТИЯ РАКЕТНЫХ ДВИГАТЕЛЕЙ ДЛЯ ИССЛЕДОВАНИЯ ДАЛЬНЕГО КОСМОСА". System design and analysis of aerospace technique characteristics 27, № 2 (2022): 50–58. http://dx.doi.org/10.15421/471923.

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The article analyzes the current state and development prospects of rocket engines for space exploration. Currently, for flights to other planets, not to mention the stars, the use of liquid-propellant and solid-propellant rocket engines is becoming increasingly unprofitable, although many rocket engines have been developed. Thus, to reach manned planes even the nearest planets, it is necessary to develop rocket launchers on engines operating on principles different from chemical propulsion systems. The most promising in this regard are electric, laser and nuclear rocket engines, as well as hy

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2

Zuo, Tianhao. "Designs, Simulations, and Products for Rocket Engines." Highlights in Science, Engineering and Technology 48 (May 16, 2023): 186–91. http://dx.doi.org/10.54097/hset.v48i.8330.

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As a matter of fact, rocket engine technology has developed rapidly in the last 100 years, which plays a crucial role for stellar travelling and detection for astrophysics usages. To be specific, different models, designs and simulation computer software had been developed in order to investigate and explore the dynamic process of the engines as well as evaluate the effectiveness and ability of the rocket engines. With this in mind, this paper gives a basic description of the designs, simulations, and products for rocket engines. In detail, this study will include description of four basic des

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3

Rawlins, Samantha, and L. Dale Thomas. "Reliability Assessment of Nuclear Thermal Engine Configuration and Health Monitoring System." Journal of the British Interplanetary Society 76, no. 4 (2023): 145–52. http://dx.doi.org/10.59332/jbis-076-04-0145.

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Today’s space nuclear technology programs are often confronted with two fundamental challenges early in the project life cycle: 1) development and testing will be more expensive than a non-nuclear alternative, and 2) the consequences of failure will be more severe. As a result, many space nuclear programs have been designed to minimize testing and maximize their probability of success: their reliability. The United States' Nuclear Engine for Rocket Vehicle Applications Program recognized these facts early on, and by 1961 the program’s primary objective set safety and reliability as the overrid

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4

Berliand, M., and R. Ishchenko. "CALCULATION OF THE EXPANSION PROCESS OF THE FLOW OF WORKING BODY IN THE NOZZLE OF A LIQUID-PHASE NUCLEAR ROCKET ENGINE." Slovak international scientific journal, no. 95 (May 15, 2025): 86–92. https://doi.org/10.5281/zenodo.15427667.

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In this work, flow parameters of the working body (hydrogen) were calculated at the inlet, throat, and exit sections of the liquid-phase nuclear rocket engine nozzle. A method was proposed for determining the specific impulse of thrust while accounting for losses due to scattering, friction, and variations in the specific enthalpy of the working body caused by non-adiabatic effects. The calculated specific impulse exceeded 9500 m/s, significantly surpassing the performance of chemical rocket engines. The evaluation of the thermogasdynamic parameters of the working body expansion confirmed the

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Kotov, V. M., and S. V. Kotov. "SOLAR ROCKET ENGINES IN NEAR-EARTH SPACE." NNC RK Bulletin 1, no. 4 (2019): 86–90. http://dx.doi.org/10.52676/1729-7885-2019-4-86-90.

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At the current stage of space exploration development, missions to the Moon and geostationary orbit are relevant. Enhancing of power supply level of such missions requires innovative technology development. Nuclear rocket engines and engines with use of solar energy are considered among such technologies. In a number of projects, such engines use intermediate heat energy accumulators, which complicates and increases the cost of construction. This embodiment uses a circuit that enables solar engine to operate with any orientation of the thrust direction towards the sun. The dependence of specif

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6

Konyukhov, G. V., and A. I. Petrov. "Heat transfer in a nuclear rocket engine." Journal of Engineering Physics and Thermophysics 67, no. 1-2 (1995): 703–6. http://dx.doi.org/10.1007/bf00853318.

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7

Pilger, Christoph, Patrick Hupe, and Peter Gaebler. "Worldwide detection of rocket launches for space missions using International Monitoring System infrasound arrays." Journal of the Acoustical Society of America 154, no. 4_supplement (2023): A347. http://dx.doi.org/10.1121/10.0023754.

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The signals of rocket launches can be detected at infrasound arrays in thousands of kilometers distance. We use microbarometer arrays, which are part of the International Monitoring System (IMS) for the Comprehensive Nuclear-Test-Ban Treaty (CTBT), to identify and characterize rocket launches all over the world. We studied more than 1000 launch events for space missions and their infrasonic signatures. Even small-lift launch vehicles such as Electron rockets starting from New Zealand with payloads of only a few hundreds of kilograms, e.g., for small satellites, can regularly be detected by one

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8

Vadim, Zakirov, and Pavshook Vladimir. "Russian nuclear rocket engine design for mars exploration." Tsinghua Science and Technology 12, no. 3 (2007): 256–60. http://dx.doi.org/10.1016/s1007-0214(07)70038-x.

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9

Brockmeyer, J. W. "Ceramic Matrix Composite Applications in Advanced Liquid Fuel Rocket Engine Turbomachinery." Journal of Engineering for Gas Turbines and Power 115, no. 1 (1993): 58–63. http://dx.doi.org/10.1115/1.2906686.

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Hot gas path components of current generation, liquid fuel rocket engine turbopumps (T/P) are exposed to severe thermal shock, extremely high heat fluxes, corrosive atmospheres, and erosive flows. These conditions, combined with high operating stresses, are severely degrading to conventional materials. Advanced turbomachinery (T/M) applications will impose harsher demands on the turbine materials. These demands include higher turbine inlet temperature for improved performance and efficiency, lower density for improved thrust-to-weight ratio, and longer life for reduced maintenance of re-usable

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10

Lanin, Anatolii G., and Ivan I. Fedik. "Selecting and using materials for a nuclear rocket engine reactor." Physics-Uspekhi 54, no. 3 (2011): 305–18. http://dx.doi.org/10.3367/ufne.0181.201103f.0319.

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11

Lanin, A. G., and I. I. Fedik. "Selecting and using materials for a nuclear rocket engine reactor." Uspekhi Fizicheskih Nauk 181, no. 3 (2011): 319. http://dx.doi.org/10.3367/ufnr.0181.201103f.0319.

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12

Vasyliv, S. S., and H. O. Strelnykov. "Rocket engine thrust vector control by detonation product injection into the supersonic portion of the nozzle." Technical mechanics 2020, no. 4 (2020): 29–34. http://dx.doi.org/10.15407/itm2020.04.029.

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For solving non-traditional problems of rocket flight control, in particular, for the conditions of impact of a nuclear explosion, non-traditional approaches to the organization of the thrust vector control of a rocket engine are required. Various schemes of gas-dynamic thrust vector control systems that counteract impact actions on the rocket were studied. It was found that the dynamic characteristics of traditional gas-dynamic thrust vector control systems do not allow one to solve the problem of counteracting impact actions on the rocket. Appropriate dynamic characteristics can provide a pe

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13

Konkashbaev, I. K., V. V. Sidnev, Yu V. Skvortsov, and V. E. Cherkovets. "The Nuclear Powered Electrodynamic Plasma Accelerator as a Rocket Engine for Interplanetary Spacecraft." Fusion Technology 20, no. 4P2 (1991): 710–13. http://dx.doi.org/10.13182/fst91-a11946923.

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14

Taylor, B., J. Cassibry, and R. Adams. "Ignition and Burn in a Hybrid Nuclear Fuel for a Pulsed Rocket Engine." Acta Astronautica 175 (October 2020): 465–75. http://dx.doi.org/10.1016/j.actaastro.2020.04.007.

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15

Yang, Si, Hangbin Zhao, Nailiang Zhuang, and Xiaobin Tang. "Thermal protection of the nuclear rocket engine nozzle based on regenerative cooling method." International Journal of Thermal Sciences 204 (October 2024): 109201. http://dx.doi.org/10.1016/j.ijthermalsci.2024.109201.

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16

Herbell, T. P., and A. J. Eckel. "Ceramic Matrix Composites for Rocket Engine Turbine Applications." Journal of Engineering for Gas Turbines and Power 115, no. 1 (1993): 64–69. http://dx.doi.org/10.1115/1.2906687.

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A program to establish the potential for introducing fiber-reinforced ceramic matrix composites (FRCMC) in future rocket engine turbopumps was instituted in 1988. A brief summary of the overall program (both contract and in-house research) is presented. Tests at NASA Lewis include thermal upshocks in a hydrogen/oxygen test rig capable of generating heating rates up to 2500°C/s. Post-thermal upshock exposure evaluation includes the measurement of residual strength and failure analysis. Test results for monolithic ceramics and several FRCMCs are presented. Hydrogen compatibility was assessed by

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17

Labib, Satira, and Jeffrey King. "Design and analysis of a single stage to orbit nuclear thermal rocket reactor engine." Nuclear Engineering and Design 287 (June 2015): 36–47. http://dx.doi.org/10.1016/j.nucengdes.2015.02.006.

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18

Fishbach, L. H., and S. Gordon. "NNEPEQ—Chemical Equilibrium Version of the Navy/NASA Engine Program." Journal of Engineering for Gas Turbines and Power 111, no. 1 (1989): 114–16. http://dx.doi.org/10.1115/1.3240205.

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The Navy NASA Engine Program, NNEP, developed in 1975, currently is in use at a large number of government agencies, commercial companies, and universities. This computer code has been used extensively to calculate the design and off-design (matched) performance of a broad range of turbine engines, ranging from subsonic turboprops to variable cycle engines for supersonic transports. Recently, there has been increased interest in applications that NNEP was not capable of simulating, namely, high Mach applications, alternate fuels including cryogenics, and cycles such as the gas generator air-tu

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19

Khatry, Jivan, and Fatih Aydogan. "Modeling Loss-of-Flow Accidents and Their Impact on Radiation Heat Transfer." Science and Technology of Nuclear Installations 2017 (2017): 1–15. http://dx.doi.org/10.1155/2017/1345938.

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Long-term high payload missions necessitate the need for nuclear space propulsion. The National Aeronautics and Space Administration (NASA) investigated several reactor designs from 1959 to 1973 in order to develop the Nuclear Engine for Rocket Vehicle Application (NERVA). Study of planned/unplanned transients on nuclear thermal rockets is important due to the need for long-term missions. In this work, a system model based on RELAP5 is developed to simulate loss-of-flow accidents on the Pewee I test reactor. This paper investigates the radiation heat transfer between the fuel elements and the

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20

Mkrtychev, Oleg V., Yury V. Novozhilov, and Anton Yu Savenkov. "The impact of heavy object on an underground structure when falling onto the ground surface." Structural Mechanics of Engineering Constructions and Buildings 17, no. 4 (2021): 425–38. http://dx.doi.org/10.22363/1815-5235-2021-17-4-425-438.

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At the objects of space infrastructure and at nuclear power facilities there are industrial structures, the main task of which is to protect a person, equipment or machinery from emergencies such as, for example, explosions, falling of various objects, fragments. In accordance with the requirements of the Federal Law On the Protection of the Population and Territories from Natural and Technogenic Emergencies, when calculating such structures, all types of loads corresponding to their functional purpose must be taken into account. So, for structures located in the area of a possible accident an

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21

Wurden, G. A., T. E. Weber, P. J. Turchi, et al. "A New Vision for Fusion Energy Research: Fusion Rocket Engines for Planetary Defense." Journal of Fusion Energy 35, no. 1 (2015): 123–33. http://dx.doi.org/10.1007/s10894-015-0034-1.

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Abstract We argue that it is essential for the fusion energy program to identify an imagination-capturing critical mission by developing a unique product which could command the marketplace. We lay out the logic that this product is a fusion rocket engine, to enable a rapid response capable of deflecting an incoming comet, to prevent its impact on the planet Earth, in defense of our population, infrastructure, and civilization. As a side benefit, deep space solar system exploration, with greater speed and orders-of-magnitude greater payload mass would also be possible.

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22

Kanareykin, Aleksandr. "Determination of the optimal size of the fuel element of the elliptical cross-section of a nuclear reactor." E3S Web of Conferences 376 (2023): 01066. http://dx.doi.org/10.1051/e3sconf/202337601066.

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The work is devoted to the process of heat exchange of a nuclear reactor. Attention was paid to improving the reliability of the fuel rods of the nuclear reactor. At the same time, two cases of the cross section of the rod shell were considered: cylindrical and elliptical. Based on the application of the differentiation method, it was shown that the level of thermal stresses arising during the transition from a circular cross-section to an elliptical one decreases. Which confirms the choice of the section of the reduced elements in the form of an ellipse. The optimal size of the section itself

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23

Cavalier, Jean Claude, Isabelle Berdoyes, and Eric Bouillon. "Composites in Aerospace Industry." Advances in Science and Technology 50 (October 2006): 153–62. http://dx.doi.org/10.4028/www.scientific.net/ast.50.153.

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Since more than twenty five years, composite materials have been with continuously increasing spatial and aeronautical applications requirements. The thermostructural composites materials are of utmost importance for satisfying the needs of mechanical and thermal characteristics at very high temperature and in severe environments. This paper deals with a large variety of applications concerning the aerospace and nuclear applications like nozzles and hot gas valves for Solid Rocket Motor (SRM), brake disks for planes, aerospace turbine engine exhaust nozzles, thermal protection system for reent

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24

Grozdanov, D. N., N. A. Fedorov, F. A. Aliev, et al. "Elemental Analysis of Engine Parts of the Proton Rocket Carrier with Resonance Neutrons." Physics of Particles and Nuclei Letters 15, no. 5 (2018): 537–40. http://dx.doi.org/10.1134/s1547477118050102.

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25

Wu, Xunliang, Mingxue Shao, Kaiyuan Cai, Xiaoliang Li, and Songjiang Feng. "Effect of finned configuration of circular tube based on fluid-structure coupling on hydrogen flow characteristics." Journal of Physics: Conference Series 2730, no. 1 (2024): 012058. http://dx.doi.org/10.1088/1742-6596/2730/1/012058.

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Abstract Nuclear thermal propulsion has the characteristics of high specific impulse, large thrust, green and efficient, and is the primary choice of manned deep space exploration propulsion system. Because the circulating flow of propellant hydrogen in the internal pipeline of the engine is always affected by the harsh environment of high temperature and high pressure, it is very important to study the flow characteristics of hydrogen in the pipeline, the heat exchange characteristics of hydrogen and pipeline and the deformation characteristics of pipeline under heat stress. In this paper, th

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26

Bai, Xiao, Peng Cheng, Qinglian Li, Liyong Sheng, and Zhongtao Kang. "Effects of self-pulsation on combustion instability in a liquid rocket engine." Experimental Thermal and Fluid Science 114 (June 2020): 110038. http://dx.doi.org/10.1016/j.expthermflusci.2019.110038.

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27

Lancelle, Daniel-Maurice, O. Bozic, and H. Koke. "Flight Test Results of the Investigation of Acceleration Effects on a Gun-Launched Rocket Engine." IEEE Transactions on Plasma Science 41, no. 5 (2013): 1364–69. http://dx.doi.org/10.1109/tps.2013.2249532.

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28

Litovko, Irina V., Alexy A. Goncharov, Andrew N. Dobrovolskiy, Lily V. Naiko, and Irina V. Naiko. "Modelling of new generation plasma optical devices." Nukleonika 61, no. 2 (2016): 207–12. http://dx.doi.org/10.1515/nuka-2016-0035.

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Abstract The paper presents new generation plasma optical devices based on the electrostatic plasma lens configuration that opens a novel attractive possibility for effective high-tech practical applications. Original approaches to use of plasma accelerators with closed electron drift and open walls for the creation of a cost-effective low-maintenance plasma lens with positive space charge and possible application for low-cost, low-energy rocket engine are described. The preliminary experimental, theoretical and simulation results are presented. It is noted that the presented plasma devices ar

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29

Budur, О., S. Nikul, M. Petrushenko, V. Holovan, O. Serheyev, and S. Tarasenko. "DEVELOPMENT OF RECOMMENDATIONS FOR CALCULATING THE MECHANISM OF SEPARATION OF PERSPECTIVE SOLID PROPELLANT ROCKETS WITH A NEGATIVE IN-FLIGHT WARHEAD AND MECHANISM OF SEPARATION." Collection of scientific works of Odesa Military Academy 1, no. 12 (2019): 81–88. http://dx.doi.org/10.37129/2313-7509.2019.12.1.81-88.

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In today's difficult international environment, especially in view of the situation in which Ukraine finds itself, it is necessary to note that each of the states with different social structures makes a titanic effort to prevent a nuclear war, to preserve and strengthen the peace. Engaging in peaceful construction, it is necessary to protect the defense capability of the Ukrainian state, where we have no right to allow the weakening for a second. The prospect of solving such problems lies to some extent on missile systems, as they are high-precision weapons. To accomplish these missiles, it i

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30

Dhanasekar, S., Arul Thayammal Ganesan, Taneti Lilly Rani, et al. "A Comprehensive Study of Ceramic Matrix Composites for Space Applications." Advances in Materials Science and Engineering 2022 (September 8, 2022): 1–9. http://dx.doi.org/10.1155/2022/6160591.

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Ceramic matrix composites (CMCs) have grown in popularity as a material for a range of high as well as protection components, increasing the need to better understand the impacts of multiple machining methods. It is primarily composed of ceramic fibers embedded in the matrix. Ceramic materials, especially carbon fibers and carbon were used to create the matrix and fibers. These ceramics include a huge variety of non-metallic inorganic materials that are regularly utilized under high temperatures. The aircraft industry became revolutionized by this unique combination of materials, which made pa

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31

Wang, Ke, Wei Fan, Xu-dong Zhu, Yu Yan, and Zhan Gao. "Experimental investigations on effects of wall-temperature on performance of a pulse detonation rocket engine." Experimental Thermal and Fluid Science 48 (July 2013): 230–37. http://dx.doi.org/10.1016/j.expthermflusci.2013.03.005.

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32

Glazunov, A. A., N. N. Dyachenko, and L. I. Dyachenko. "Numerical investigation of the flow of ultradisperse particles of the aluminum oxide in the solid-fuel rocket engine nozzle." Thermophysics and Aeromechanics 20, no. 1 (2013): 79–86. http://dx.doi.org/10.1134/s0869864313010071.

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33

ZHUGAN, O., and M. DEGTYAREV. "VERSION OF LOITERING MUNITIONS CLASSIFICATION BASED ON THE STATE-OF-THE-ART AND TRENDS ANALYSIS." Kosmìčna nauka ì tehnologìâ 30, no. 3 (2024): 31–39. http://dx.doi.org/10.15407/knit2024.03.031.

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At present, objects of the rocket and space industry and strategic nuclear forces of the leading countries of the world, as well as other expensive infrastructure objects, can be attacked by air attack units belonging to the newest class of weapon — loitering munitions. This type of weapons combines low cost and easy development and production, which makes them available for illegal armed formations and the conduct of hybrid warfare. According to their design features and performance characteristics, loitering munitions occupy a place between cruise missiles and unmanned aerial vehicles. To an

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34

Nerubailo, B. V. "On the Problem of Designing the Anisotropic Material of Shell Sleeves with a Free Edge in the Core of a Nuclear Rocket Engine." Journal of Engineering Physics and Thermophysics 94, no. 1 (2021): 247–53. http://dx.doi.org/10.1007/s10891-021-02293-x.

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35

Ng, Ching Tai, and Aseem Ahmed. "Effect of high temperature on nonlinear guided wave in reinforced concrete structures." Journal of the Acoustical Society of America 154, no. 4_supplement (2023): A261. http://dx.doi.org/10.1121/10.0023467.

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There are some ations that reinforced concrete (RC) structures may be subjected high temperatures, e.g., building fires, rocket and jet aircraft engine blasts, and nuclear power reactors. It is crucial to ensure the integrity and safety of these RC structures. This study investigates the effects of high temperature on the behavior of nonlinear guided wave, which can potentially be used for non-destructive evaluation, in reinforced concrete structures. In this study, the reinforced concrete specimens are heated from 100 to 800°C. Two sets of experimental studies are considered. At temperatures

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36

Wang, Jian, Meisheng An, Bifeng Yin, Bin Wang, Pei Chen, and Wangzhao He. "Combustion and Emission Characteristics of a Diesel Engine Fueled with Diesel–Rocket Propellant-3 Wide Distillation Blended Fuels." Journal of Energy Engineering 146, no. 4 (2020): 04020025. http://dx.doi.org/10.1061/(asce)ey.1943-7897.0000679.

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37

Kuzmin, V. A., I. A. Zagrai, and E. I. Maratkanova. "Model of solid fuel rocket engine: thermal emission characteristics from a plume calculated with account for temperature and speed non-equilibrium between gas and particle flows." Thermophysics and Aeromechanics 26, no. 1 (2019): 69–77. http://dx.doi.org/10.1134/s0869864319010074.

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38

Peralta, Stephen F., Keisa R. Rosales, Joel M. Stoltzfus, H. Barthelemy, and S. W. Dean. "Liquid Oxygen Rotating Friction Ignition Testing of Aluminum and Titanium with Monel® and Inconel® for Rocket Engine Propulsion System Contamination Investigation." Journal of ASTM International 6, no. 10 (2009): 102342. http://dx.doi.org/10.1520/jai102342.

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Wu, M. K., and A. Ray. "Damage-Mitigating Control of Power Systems for Structural Durability and High Performance." Journal of Engineering for Gas Turbines and Power 117, no. 2 (1995): 307–13. http://dx.doi.org/10.1115/1.2814095.

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A major goal in the control of complex power systems such as advanced aircraft, spacecraft, and electric power plants is to achieve high performance with increased reliability, availability, component durability, and maintainability. The state of the art in the synthesis of control systems for complex mechanical processes focuses on improving performance and diagnostic capabilities under constraints that do not often adequately represent the dynamic properties of the materials. The reason is that the traditional design is based upon the assumption of conventional materials with invariant chara

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40

Beveridge, J. H. "Development Problems of Nuclear Rocket Engines." Annals of the New York Academy of Sciences 134, no. 1 (2008): 304–16. http://dx.doi.org/10.1111/j.1749-6632.1965.tb56163.x.

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41

Kamennov, P. B. "PRC’S MILITARY-INDUSTRIAL COMPLEX UNDER XI JINPING." Outlines of global transformations: politics, economics, law 10, no. 5 (2017): 135–51. http://dx.doi.org/10.23932/2542-0240-2017-10-5-135-151.

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The article is dedicated to the achievements and problems of the Chinese military-industrial complex and its role in the economy building during the Xi Jinping` s term (2012–2017). The evolution of the problem is particularly interesting in the context of the realization of the National Security modernization Program of China 2050. The author provides a description of the current state of military-industrial complex fields. Chinese atomic industry has been growing rapidly during the last years. There are significant achievements in the field of the rocket and space industry. Aviation industry,

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42

Brockmeyer, J. W., A. C. Straub, and E. J. Krieg. "Ceramic Composite Attachments for Transmission of High-Torque Loads." Journal of Engineering for Gas Turbines and Power 116, no. 3 (1994): 611–15. http://dx.doi.org/10.1115/1.2906863.

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The use of fiber-reinforced ceramic matrix composites (FRCMC) for advanced turbopump (T/P) hot-section components offers a number of potential advantages relative to the use of “conventional” materials. Among these advantages are reduced weight, enhanced life with reduced maintenance, and improved performance achievable by increasing the turbine inlet temperature. FRCMC are, however, emerging materials, and their design and analysis present unique challenges. These composites have relatively low thermal expansion coefficients and low strain-to-failure characteristics, and they have nonlinear,

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43

Arakere, N. K. "High-Temperature Fatigue Properties of Single Crystal Superalloys in Air and Hydrogen." Journal of Engineering for Gas Turbines and Power 126, no. 3 (2004): 590–603. http://dx.doi.org/10.1115/1.1501075.

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Hot section components in high-performance aircraft and rocket engines are increasingly being made of single crystal nickel superalloys such as PWA1480, PWA1484, CMSX-4, and Rene N-4 as these materials provide superior creep, stress rupture, melt resistance, and thermomechanical fatigue capabilities over their polycrystalline counterparts. Fatigue failures in PWA1480 single crystal nickel-base superalloy turbine blades used in the space shuttle main engine fuel turbopump are discussed. During testing many turbine blades experienced stage II noncrystallographic fatigue cracks with multiple orig

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44

Corfield, Richard. "Nuclear spacecraft: from dream to reality." Physics World 37, no. 3 (2024): 32–35. http://dx.doi.org/10.1088/2058-7058/37/03/30.

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Launching rockets into space with atomic bombs is a crazy idea that was thankfully discarded many decades ago. But as Richard Corfield discovers, the potential of using the energy from nuclear-powered engines to drive space travel is back on NASA’s agenda.

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45

Kharitonov, Alexey M. "Optimization of Interplanetary Trajectories of Space Vehicles with Bi-modal Nuclear Rocket Engines." Journal of Automation and Information Sciences 41, no. 8 (2009): 71–86. http://dx.doi.org/10.1615/jautomatinfscien.v41.i8.70.

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46

Wang, Xue Feng, Shi Gang Wang, and Zi Jing Wu. "High Temperature Alloy of Turning Processing Characteristic and Process Analysis." Materials Science Forum 800-801 (July 2014): 71–75. http://dx.doi.org/10.4028/www.scientific.net/msf.800-801.71.

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High temperature alloy is the key hot end parts' material, which is often used in the modern aircraft, spacecraft and the rocket engines, as well as naval vessels and industry gas turbine. And it's also used in the nuclear reactor, chemical equipment, coal conversion technologies etc. as the very important high temperature structural materials. High temperature alloy of turning processing is the technical difficulties in mechanical cutting work, this paper introduces the high temperature alloy turning processing features, turning processing tool, cutting parameters, the choice of the cutting f

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Kharitonov, Alexey M. "Computation of Interplanetary Trajectories of Spacecrafts with Nuclear Rocket Engines of High-Limited Thrust." Journal of Automation and Information Sciences 41, no. 6 (2009): 58–69. http://dx.doi.org/10.1615/jautomatinfscien.v41.i6.40.

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Onufriev, A. V., V. V. Onufriev, V. V. Perevezentsev, and S. N. Dmitriev. "On the effect of the specific heat release of a mixture of radionuclides on the relative mass transported in the “self-delivery” of spent nuclear fuel mode during space burial." Izvestiâ Akademii nauk SSSR. Ènergetika, no. 3 (November 12, 2024): 110–24. http://dx.doi.org/10.31857/s0002331024030077.

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The issues of disposal of radioactive waste (RW) are currently one of the serious environmental challenges. One of the ways of disposal can be the space burial of radioactive waste, which reduces the pollution of the Earth. The paper considers the issues of transportation of radioactive waste, representing a mixture of isotopes of spent nuclear fuel (SNF), estimates of the mass-energy costs of SNF transportation using electric rocket engines (ERD). A variant is considered in which the transported mixture of SNF isotopes is both a payload and an energy source – “self-delivery”. The relations fo

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Klimovskii, K. K. "Cavitation stability characteristics of turbine-driven pump units for rocket engines." Thermal Engineering 53, no. 12 (2006): 989–92. http://dx.doi.org/10.1134/s0040601506120081.

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Way, S. "Comments on the Development of the Early Westinghouse Turbojets, 1941-1946." Journal of Engineering for Gas Turbines and Power 116, no. 2 (1994): 315–21. http://dx.doi.org/10.1115/1.2906822.

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The early thinking leading to the American Turbojet engine is reviewed. This included ideas pertaining to ramjets and rockets, and culminated in the axial flow turbojet engine concept. The role of the NACA Subcommittee on Jet Propulsion under the leadership of Dr. W. F. Durand is stressed. Early problems with the new engine are mentioned, including flame tube light-off, interconnecting tubes, and fuel injection problems. An early major design innovation was the change to a single annular combustion chamber, replacing the 24 cans. This change culminated in the 19XB engine. The purposes of this

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