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Relevant bibliographies by topics / Chemical rocket engine

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Academic literature on the topic 'Chemical rocket engine'

Author: Grafiati

Published: 28 May 2022

Last updated: 30 July 2025

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Journal articles on the topic "Chemical rocket engine"

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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Freiherr, Greg. "The Little Rocket Engine That Could." Mechanical Engineering 138, no. 08 (2016): 32–37. http://dx.doi.org/10.1115/1.2016-aug-1.

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This paper highlights advancements of a research team in the field of miniature spacecrafts and development and advantages of CubeStats. CubeSats are space age hitchhikers, that is, miniature spacecraft that fly into orbit aboard rockets whose primary payloads are full-size satellites. Paulo Lozano and his team at MIT’s Space Propulsion Lab have developed a unique kind of rocket engine for these microsatellites. The trick to building a successful ion electrospray propulsion system is to increase thrust density by jamming together as many emitters as possible. Electrospray engines also differ g

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Nae, Catalin, Irina-Carmen Andrei, Gabriela-Liliana Stroe, and Sorin Berbente. "Integration of Fuels Types and Chemical Properties with the Design of the Rocket Engine�s Bell Exhaust Nozzle and Combustion Chamber." Revista de Chimie 71, no. 1 (2020): 436–44. http://dx.doi.org/10.37358/rc.20.1.7872.

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The chemical properties of the fuels are crucial for obtaining the numerical accuracy during the design and performance analysis in case of liquid fuel propelled rocket engines, as well as the trajectory optimization. In this paper, the research was primarly focused on optimizing the numerical accuracy for non-linear two-dimensional approximation the Fuel Combustion Charts; secondarily, the investigation was carried on the design of the bell-nozzle of a liquid propelled rocket engine, taking into account the variation of the coefficients which are significant for expressing the fuels chemical

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Vasiliev, Igor, Boris Kiforenko, and Yaroslav Tkachenko. "COMPARATIVE ANALYSIS OF THE EFFICIENCY OF CONSTANT POWER THROTTLED ROCKET ENGINES FOR INTERORBITAL FLIGHTS TO GEOSTATIONAR." Journal of Automation and Information sciences 6 (November 1, 2021): 66–77. http://dx.doi.org/10.34229/1028-0979-2021-6-7.

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Carrying out low-thrust transfers of spacecrafts in the near-earth space from intermediate elliptic to the geostationary orbit using electric rocket engines seems to be one of the most important tasks of modern cosmonautics. Electric rocket engines, whose specific impulse of the reactive jet is an order of magnitude more than in chemical RD, are preferable for interorbit flights with a maximum payload in the case when a significant increase in the duration of the maneuver is permissible. Ability to throttling the rocket engine thrust is traditionally considered as one of the ways to reduce bot

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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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Vikulov, Aleksey. "Optimal control of propellant consumption during insertion of rocket into a circle orbit of the Earth." Journal of Applied Engineering Science 18, no. 4 (2020): 705–12. http://dx.doi.org/10.5937/jaes0-28127.

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The problem of launching a rocket into the Earth's orbit has already been solved using the regularization method in previous studies. But the regularization method remains relevant for application to solving integral equations of the first kind, which determine the components of speed and acceleration. The problem of optimal control of propellant consumption during the insertion of a rocket into a circle orbit of the Earth is solved using regularized solutions of integral equations of the first kind which are solutions of corresponding Euler equations on discrete-time net. The influence of the

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Huang, Peihao, Huahuang Yu, and Tao Wang. "A Study Using Optimized LSSVR for Real-Time Fault Detection of Liquid Rocket Engine." Processes 10, no. 8 (2022): 1643. http://dx.doi.org/10.3390/pr10081643.

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Health monitoring and fault diagnosis of liquid rocket engine (LRE) are the most important concerning issue for the safety of rocket’s flying, especially for the man-carried aerospace engineering. Based on the sensor measurement signals of a certain type of hydrogen-oxygen rocket engine, this paper proposed a real-time fault detection approach using a genetic algorithm-based least squares support vector regression (GA-LSSVR) algorithm for the real-time fault detection of the rocket engine. In order to obtain effective training samples, the data is normalized in this paper. Then, the GA-LSSVR a

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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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Khan, Sohaib, Muhammad Umer Sohail, Ihtzaz Qamar, Muzna Tariq, and Raees Fida Swati. "Effect of Secondary Combustion on Thrust Regulation of Gas Generator Cycle Rocket Engine." Applied Sciences 12, no. 20 (2022): 10563. http://dx.doi.org/10.3390/app122010563.

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Thrust regulation is applied to maintain the performance of the liquid propellant rocket engine. The thrust level of a rocket engine can be readily controlled by adjusting the number of propellants introduced into the combustion chamber. In this study, a gas generator design is proposed in which thrust regulation is maintained by performing secondary combustion in the divergent section of the nozzle of a gas generator. Tangential and normal injection techniques have also been studied for better combustion analyses. A normal injection technique is used for the experiment and CFD results are val

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Золотько, Олександр Євгенович, Олена Василівна Золотько, Олександра Валеріївна Сосновська, Олександр Сергійович Аксьонов та Ірина Сергіївна Савченко. "ОСОБЛИВОСТІ КОНСТРУКТИВНИХ СХЕМ ДВИГУНІВ З ІМПУЛЬСНИМИ ДЕТОНАЦІЙНИМИ КАМЕРАМИ". Aerospace technic and technology, № 2 (27 квітня 2020): 4–10. http://dx.doi.org/10.32620/aktt.2020.2.01.

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The pressure of the products of chemical reactions in the chamber of a rocket engine increases significantly if the rocket fuel components burn in the detonation mode. In this case, it can get to a simpler and more reliable expulsion propellant feed system instead of a turbopump feed system. The value of heat release power (MW / liter) of detonation engines is several orders of magnitude larger than that of aircraft and rocket engines operating in the Brighton cycle. The high rate of energy released in the detonation mode can significantly reduce the mass, the inertia, and overall dimensions o

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Dissertations / Theses on the topic "Chemical rocket engine"

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Черненко, В. В., та М. А. Погорєлий. "Різновиди космічних двигунів". Thesis, Сумський державний університет, 2018. http://essuir.sumdu.edu.ua/handle/123456789/67086.

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Rocchi, Jean-Philippe. "Simulations aux grandes échelles de la phase d'allumage dans un moteur fusée cryotechnique." Phd thesis, Toulouse, INPT, 2014. http://oatao.univ-toulouse.fr/14667/1/rocchi.pdf.

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À ses débuts, la conquête spatiale a pu bénéficier des rivalités politiques de la Guerre Froide pour se développer rapidement sans réellement se soucier des efforts économiques à fournir. Aujourd’hui, de nombreux pays subissent le revers de la médaille de cette course effrénée : pour maintenir une flotte de lanceurs viable économiquement, les différentes agences spatiales doivent faire face à un dilemme opposant la minimisation des coûts de lancement à la maximisation de leur fiabilité. Dans cette logique d’optimisation, les industriels présents dans ce processus de réflexion se tournent vers

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Luanje, Appolinaire Tifang. "INTEGRATED OPTICAL FIBER RAMAN SENSOR FOR CRYOGENIC APPLICATION." MSSTATE, 2008. http://sun.library.msstate.edu/ETD-db/theses/available/etd-04042008-155057/.

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An integrated fiber optical Raman sensor was designed for real-time, non intrusive detection of liquid and gaseous mixtures at high pressure and high flow rates. The integrated sensor employs a high-power solid-state pumped Nd:YAG frequency doubled (532nm) laser (3W), a modified In Photonics Raman probe which has built-in Raman signal filter optics, and two high-resolution spectrometers and photomultiplier tubes (PMT) with selected bandpass filters to collect both N2 and O2 Raman signals. The detection unit was also integrated with Lab View software interfaced PMT modules for fast data acquisi

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(7043039), Jacob M. McCormick. "Design and Characterization of an Altitude Chamber for Chemical Rocket Engines." Thesis, 2019.

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<p>This thesis focuses on the development of reduced pressure testing capabilities at Zucrow Laboratories. A two-stage ejector on loan from NASA Marshall is used in series with a supersonic diffuser to allow for the testing of up to100 lb<sub>f</sub> rocket engines at equivalent altitudes of up to 100,000 ft. The objective of this research is to implement a one-dimensional (1-D) model which accurately predicts the performance of the two-stage ejector in real time, informing the maximum thrust and simulated altitude capabilities within the altitude chamber located in room 134A of ZL3 during e

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(9505169), Kevin James Dille. "Transient Response of Gas-Liquid Injectors Subjected to Transverse Detonation Waves." Thesis, 2020.

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<p>A series of experimental tests were performed to study the transient response of gas/liquid injectors exposed to transverse detonation waves. A total of four acrylic injectors were tested to compare the response between gas/liquid and liquid only injectors, as well as compare the role of various geometric features of the notional injector design. Detonation waves are produced through the combustion of ethylene and oxygen, at conditions to produce average wave pressures between 128 and 199 psi. The injectors utilize water and nitrogen to simulate the injection of liquid and gaseous propellan

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Books on the topic "Chemical rocket engine"

1

United States. National Aeronautics and Space Administration., ed. Pretest uncertainty analysis for chemical rocket engine tests. National Aeronautics and Space Administration, 1987.

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2

A, Krishnan, Przekwas A. J, and United States. National Aeronautics and Space Administration., eds. Computational analysis of variable thrust engine (VTE) performance: Final report. CFD Research Corp., 1993.

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United States. National Aeronautics and Space Administration., ed. Robotic planetary science missions enabled with small NTR engine/stage technologies. National Aeronautics and Space Administration, 1995.

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Leone, D. M. Active chlorine and nitric oxide formation from chemical rocket plume afterburning. National Aeronautics and Space Administration, 1994.

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L, Gage Mark, and United States. National Aeronautics and Space Administration., eds. Advanced small rocket chambers option 1 - 14 Lbf Ir-Re rocket: Final report. National Aeronautics and Space Administration, 1992.

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Southern Research Institute (Birmingham, Ala.) and United States. National Aeronautics and Space Administration., eds. SRB thermal curtain design support: October 1990 interim report to U.S. Polymeric, B.P. Chemicals. Southern Research Institute, 1990.

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Lundblad, Wayne E. SRB thermal curtain design support: October 1990 interim report to U.S. Polymeric, B.P. Chemicals. Southern Research Institute, 1990.

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United States. National Aeronautics and Space Administration., ed. Calculation of propulsive nozzle flowfields in multidiffusing chemically recating environments. National Aeronautics and Space Administration, 1994.

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9

Gordon, Sanford. Computer program for calculation of complex chemical equilibrium compositions and applications. National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1996.

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Gordon, Sanford. Computer program for calculation of complex chemical equilibrium compositions and applications. National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1994.

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Book chapters on the topic "Chemical rocket engine"

1

Haeseler, Dietrich, and Oskar J. Haidn. "Russian Engine Technologies." In Chemical Rocket Propulsion. Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-27748-6_18.

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Yoshida, Makoto, Toshiya Kimura, Tomoyuki Hashimoto, Shinichi Moriya, and Satoshi Takada. "Overview of Research and Development Status of Reusable Rocket Engine." In Chemical Rocket Propulsion. Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-27748-6_38.

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Platov, Yulii V., and Sergey Sh Nikolayshvili. "Physical Mechanisms of Upper Atmosphere Optical Phenomena Associated with Rocket Engine Operation." In Chemical Rocket Propulsion. Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-27748-6_34.

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Huang, Minchao, Yuqiang Cheng, Jia Dai, and Jian Li. "Simulation Analysis of the Starting Process of the Pump-Fed Liquid Rocket Engine." In Performance Analysis of a Liquid/Gel Rocket Engine During Operation. Springer Nature Singapore, 2024. http://dx.doi.org/10.1007/978-981-97-6485-3_8.

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AbstractFor the operation of a large pump-fed liquid rocket engine, the most important and critical working process is the starting process of the liquid rocket engine system. The success of starting is directly related to the success or failure of the launch of a space vehicle. During the starting process of a liquid rocket engine, very complex chemical and physical changes occur in the propellant components, and the engine system parameters change rapidly within a large range. Therefore, it is obviously important to conduct an in-depth simulation study on the starting process of a liquid roc

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Huang, Minchao, Yuqiang Cheng, Jia Dai, and Jian Li. "Mathematical Model of the Operation of a Pump-Fed Liquid Rocket Engine." In Performance Analysis of a Liquid/Gel Rocket Engine During Operation. Springer Nature Singapore, 2024. http://dx.doi.org/10.1007/978-981-97-6485-3_7.

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Hu, Songqi, Wu Guanjie, and Noor Fatima Rashid. "Performance Analysis of Paraffin Fuels for Hybrid Rocket Engines." In Chemical Rocket Propulsion. Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-27748-6_24.

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Asakawa, Hiroya, Hideaki Nanri, Kenji Aoki, et al. "The Status of the Research and Development of LNG Rocket Engines in Japan." In Chemical Rocket Propulsion. Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-27748-6_19.

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Aliev, A. V., O. A. Voevodina, and E. S. Pushina. "Non-Stationary Thermodynamic Processes in Rocket Engines of Solid Fuels: Chemical Equilibrium of Combustion Products." In Nanoscience and Nanoengineering. Apple Academic Press, 2018. http://dx.doi.org/10.1201/9781351138789-4.

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"Pressurization of Liquid Propellant Rocket Engine Tanks." In Chemical Kinetics in Combustion and Reactive Flows. Cambridge University Press, 2019. http://dx.doi.org/10.1017/9781108581714.009.

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Gao, Yi, Fei Qin, Shaohua Zhu, Bing Liu, and Xingliang Chen. "Numerical Simulation of Kerosene-Fueled Rocket-Based Combined Cycle Engine Based on Skeletal Mechanism." In Advances in Transdisciplinary Engineering. IOS Press, 2025. https://doi.org/10.3233/atde250339.

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Accurate numerical simulation results of turbulent combustion are crucial for combustion organization and performance prediction studies of rocket-based combined cycle engine. However, there are few relevant lightweight chemical kinetic mechanisms available for kerosene. In this study, the two different kerosene detailed mechanisms were reduced, and six kinds of skeletal mechanisms were obtained, namely: 59 species/410 reactions (abbreviated as 59s/410r), 38s/180r, 27s/98r, and 64s/460r, 36s/191r, and 21s/70r. In order to validate the accuracy of the reduced mechanisms, these mechanisms were f

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Conference papers on the topic "Chemical rocket engine"

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Jung, Taekyu. "Pressure Pulsator to Study the Low-Frequency Characteristics of a Liquid Rocket Engine." In The 4th World Congress on Mechanical, Chemical, and Material Engineering. Avestia Publishing, 2018. http://dx.doi.org/10.11159/icmie18.108.

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Hutcherson, Wesley, Russell Gaerlan, Carlos Fernandez, and Shyam Menon. "Design and Development of A Hybrid Rocket Engine Test Stand to Study Exhaust Flow Gas Dynamics and Chemical Kinetics." In 2024 Regional Student Conferences, Region I - North East. American Institute of Aeronautics and Astronautics, 2024. http://dx.doi.org/10.2514/6.2024-85669.

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Sannino, A. "Fast reconfiguration maneuvers of a micro-satellite constellation based on a hybrid rocket engine." In Aeronautics and Astronautics. Materials Research Forum LLC, 2023. http://dx.doi.org/10.21741/9781644902813-142.

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Abstract. In this work, the formation flight of the CubeSat cluster RODiO (Radar for Earth Observation by synthetic aperture DIstributed on a cluster of cubesats equipped with high-technology micro-propellers for new Operative services [1]) with respect to a small satellite in LEO (Low Earth Orbit) has been analyzed. RODiO is an innovative mission concept funded by the Italian Space Agency (ASI) in the context of the Alcor program [2]. The small satellite is equipped with an antenna that allows it to function as a transmitter, whereas RODiO functions as a receiver. The extension of the virtual

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MUNGIGUERRA, STEFANO, ANSELMO CECERE, and RAFFAELE SAVINO. "AERO-THERMO-DYNAMIC STUDY OF ULTRA-HIGH- TEMPERATURE CERAMIC COMPOSITES FOR THERMAL PROTECTION SYSTEMS AND ROCKET NOZZLES." In Thirty-sixth Technical Conference. Destech Publications, Inc., 2021. http://dx.doi.org/10.12783/asc36/35774.

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The most extreme aero-thermo-dynamic conditions encountered in aerospace applications include those of atmospheric re-entry, characterized by hypersonic Mach numbers, high temperatures and a chemically reacting environment, and of rocket propulsion, in which a combusting, high-pressure, supersonic flow can severely attack the surfaces of the motor internal components (particularly nozzle throats), leading to thermo-chemical erosion and consequent thrust decrease. For these applications, Ultra-High-Temperature Ceramics (UHTC), namely transition metal borides and carbides, are regarded as promis

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Barato, F. "Update on green chemical propulsion activities and achievements by the University of Padua and its spin-off T4I." In Aeronautics and Astronautics. Materials Research Forum LLC, 2023. http://dx.doi.org/10.21741/9781644902813-140.

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Abstract. In recent years, there has been a great research interest on green propulsion, both for environmental, cost and ease-of-use considerations, further accelerated by the needs of the NewSpace Economy. Hydrogen peroxide is a green and versatile propellant that is suitable for a lot of different uses in space applications. Following a previous AIDAA publication of 2019, this paper updates the research performed on hydrogen peroxide-based propulsion by the University of Padua and its spin-off T4i with the latest achievements. Starting from the simplest propulsion systems, several monoprope

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Masseni, Filippo. "ANN-based chemical model for hybrid rocket engines." In INTERNATIONAL CONFERENCE OF NUMERICAL ANALYSIS AND APPLIED MATHEMATICS: ICNAAM2022. AIP Publishing, 2024. http://dx.doi.org/10.1063/5.0210170.

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Shanov, Vesselin, Widen Tabakoff, and J. A. Gunaraj. "Study of CVD Coated and Uncoated INCO 718 Exposed to Particulate Flow." In ASME 1996 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 1996. http://dx.doi.org/10.1115/imece1996-1050.

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Abstract The major problem confronting developers of coal burning boilers, fluidized beds, and gas and steam turbines, is the serious erosion of the systems’ components by the suspension of fly ash or other solid particles in the flow. A permanent loss of performance is associated with surface erosion, which is caused by particle surface impacts. To improve the resistance of hot erosion and corrosion, new alloys and coatings are investigated. The objective of this research work is to investigate the basic erosion process and fluid mechanics associated with material degradation in coated and un

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Sá Gontijo, Maurício, Gustavo Alexandre Achilles Fischer, and FERNANDO DE SOUZA COSTA. "Characteristic Lengths of Liquid Propellant Rocket Engines and the Influence of Chemical Reactions." In 26th International Congress of Mechanical Engineering. ABCM, 2021. http://dx.doi.org/10.26678/abcm.cobem2021.cob2021-2105.

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Haynes, J., and J. Karthikeyan. "Cold Spray Copper Application for Upper Stage Rocket Engine Design." In ITSC2003, edited by Basil R. Marple and Christian Moreau. ASM International, 2003. http://dx.doi.org/10.31399/asm.cp.itsc2003p0079.

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Abstract Pratt & Whitney's upper stage rocket engine development program, designated "RL60", has incorporated cold-sprayed copper to improve the design and function of this new engine. Combustion chamber designs contain two stainless steel manifolds connected by a series of copper tubes. The manifold where the hydrogen fuel exits is located near the injector face. The combustion gases from the injector would cause over-heating of this manifold. Thick copper application was needed to actively cool this manifold by conducting the cold temperatures from the hydrogen fuel inside the copper tub

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Taran, J. P. "CARS from Lift-Off to Re-Entry." In Laser Applications to Chemical Analysis. Optica Publishing Group, 1990. http://dx.doi.org/10.1364/laca.1990.mb1.

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Coherent Anti-Stokes Raman Scattering (CARS) has been particularly useful for making temperature measurements in flames. A majority of the CARS instruments is used in studies of small-scale burners, piston engines, and even furnaces and boilers of industrial size. Occasional investigations of species concentrations and rotational and vibrational temperatures in rarefied gases have also been conducted. In the area of aerospace research, one must tackle very delicate problems in all of these fields. For instance, it is particularly difficult to investigate cryogenic rocket motor combustion, hype

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