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Journal articles on the topic 'Chemical rocket engine'

Author: Grafiati

Published: 28 May 2022

Last updated: 30 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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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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8

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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Dilara Koçak, Türker Erdem Öksüz, Mertcan Koçak, Utku Şentürk, Necdet Özbalta, and Aydoğan Özdamar. "Design, Fabrication and Testing of a Hybrid Rocket Engine Prototype." Defence Science Journal 74, no. 6 (2024): 942–49. https://doi.org/10.14429/dsj.74.19363.

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Rockets are generally used for defense purposes, for civilian purposes, for satellite launching and for orbiting and keeping the satellite in orbit. Chemical fuel rockets are examined in three groups as solid fuel rockets, liquid fuel rockets and hybrid fuel rockets. Due to the cost and complexity of liquid fuel rockets, the explosion hazard and thrust control problems of solid fuel rockets, studies on the use of hybrid rockets have recently become more common, considering the safety advantage. In this study, the thrust-time change was determined for the PVC..................

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Zhuravlev, Viktor Yu, Elvira S. Manokhina, and Matvey A. Shinkarev. "Parameters of rocket engine chambers, obtained by selective laser fusion." Siberian Aerospace Journal 25, no. 1 (2024): 106–14. http://dx.doi.org/10.31772/2712-8970-2024-25-1-106-114.

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When designing and testing a low-thrust rocket engine (SLME), one of the most important tasks is to ensure the quality of materials, which, in turn, affects the reliability of the product. Currently, additive technologies for manufacturing parts from metals are actively developing. This direction is relevant for rocket and space technology products to reduce weight and increase the reliability of products. The article presents the results of studies of the chemical composition and mechanical characteristics of the material of the low-thrust rocket engine demonstrator chamber, manufactured by s

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Tsentis, S. E., V. G. Gkoutzamanis, A. D. Gaitanis, and A. I. Kalfas. "Multi-platform app-embedded model for hybrid air-breathing rocket-cycle engine in hypersonic atmospheric ascent." Aeronautical Journal 125, no. 1291 (2021): 1631–53. http://dx.doi.org/10.1017/aer.2021.3.

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ABSTRACTThis paper presents a performance analysis on a novel engine concept, currently under development, in order to achieve hybrid air-breathing rocket technology. A component-level approach has been developed to simulate the performance of the engine at Mach 5, and the thermodynamic interaction of the different working fluids has been analysed. The bypass ramjet duct has also been included in the model. This facilitates the improved evaluation of performance parameters. The impact of ram drag induced by the intake of the engine has also been demonstrated. The whole model is introduced into

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Ponomarov, O. M., O. O. Dobrodomov, and O. V. Kulyk. "Prospects for the use of nitrogen-containing single-component rocket propellants." Technical mechanics 2022, no. 3 (2022): 85–90. http://dx.doi.org/10.15407/itm2022.03.085.

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The goal of this work is to analyze the possibility of using existing monopropellant compositions based on aqueous solutions of high-energy nitrogen-containing substances as the main propellant for low-thrust engines, for example, for meteorological rockets, for upper-stage engines, and in spacecraft control engine systems. This paper presents an approach that considers the selection and justification of ingredients based on renewable energy sources, the analysis being carried out primarily from standpoint of the availability of propellant components and their safety and energy efficiency. It

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Smolentsev, Vladislav, Nikolay Nenahov, and Natalia Potashnikova. "Investigation of the Properties of Heat-Protective Coatings to Improve the Performance of Products." Materials Science Forum 1037 (July 6, 2021): 516–21. http://dx.doi.org/10.4028/www.scientific.net/msf.1037.516.

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The heat-loaded part of the combustion chamber of a liquid rocket engine are Considered. The proposed coating has several layers: an internal metal coating that contacts the part or substrate, and an external coating made of a mixture of ceramic granules and metal powder. At the same time, to obtain the initial surface for coating with the required surface layer roughness, it is proposed to use the method of sand blasting. The article analyzes possible mechanisms of material formation for "base-coating" transition zones, as well as the influence of their chemical composition on the adhesive st

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Li, Jian-Ling, Wei Fan, Chuan-Jun Yan, Hong-Yan Tu, and Kai-Cheng Xie. "Performance enhancement of a pulse detonation rocket engine." Proceedings of the Combustion Institute 33, no. 2 (2011): 2243–54. http://dx.doi.org/10.1016/j.proci.2010.07.048.

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Cai, Hong-hua, Wan-sheng Nie, Xin-lei Yang, Rui Wu, and Ling-yu Su. "Three-Dimensional Numerical Analysis of LOX/Kerosene Engine Exhaust Plume Flow Field Characteristics." International Journal of Aerospace Engineering 2017 (2017): 1–13. http://dx.doi.org/10.1155/2017/4768376.

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Aiming at calculating and studying the flow field characteristics of engine exhaust plume and comparative analyzing the effects of different chemical reaction mechanisms on the engine exhaust plume flow field characteristics, a method considering fully the combustion state influence is put forward, which is applied to exhaust plume flow field calculation of multinozzle engine. On this basis, a three-dimensional numerical analysis of the effects of different chemical reaction mechanisms on LOX/kerosene engine exhaust plume flow field characteristics was carried out. It is found that multistep c

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18

Beyer, Steffen, Stephan Schmidt, Franz Maidl, Rolf Meistring, Marc Bouchez, and Patrick Peres. "Advanced Composite Materials for Current and Future Propulsion and Industrial Applications." Advances in Science and Technology 50 (October 2006): 174–81. http://dx.doi.org/10.4028/www.scientific.net/ast.50.174.

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Various technology programmes in Europe are concerned with preparing for future propulsion technologies to reduce the costs and increase the life time of components for liquid rocket engine components. One of the key roles to fulfil the future requirements and for realizing reusable and robust engine components is the use of modern and innovative materials. One of the key technologies which concern various engine manufacturers worldwide is the development of fibrereinforced ceramics – CMC's (Ceramic Matrix Composites). The advantages for the developers are obvious – the low specific weight, th

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Belyakov, Vladislav A., Dmitry O. Vasilevsky, Daniil V. Maslov, Artemy A. Kilyashov, and Roman V. Romashko. "Verification of thermodynamic parameters of a mixture of generator gas on oxygen-hydrogen fuel with an excess of one of the fuel components." Siberian Aerospace Journal 25, no. 1 (2024): 56–67. http://dx.doi.org/10.31772/2712-8970-2024-25-1-56-67.

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Liquid gas generators (LGG) are additional firing units in the power system of liquid rocket engines (LPRE). The LGG ensure the operation of the power units of the turbopump unit (TPU) of the engine by feeding combustion products (CP) to the turbine drive. The main criteria for the efficiency of the generator gas is the complex (RT)gg and the thermodynamic properties of the mixture, depending on temperature, pressure, the degree of excess of the oxidizer and the enthalpy of the fuel, attributed to the conditions of supply to the nozzles of the GG. Changing the parameters of the generator gas l

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Sellam, Mohamed, and Amer Chpoun. "Numerical Simulation of Reactive Flows in Overexpanded Supersonic Nozzle with Film Cooling." International Journal of Aerospace Engineering 2015 (2015): 1–15. http://dx.doi.org/10.1155/2015/252404.

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Reignition phenomena occurring in a supersonic nozzle flow may present a crucial safety issue for rocket propulsion systems. These phenomena concern mainly rocket engines which use H2gas (GH2) in the film cooling device, particularly when the nozzle operates under over expanded flow conditions at sea level or at low altitudes. Consequently, the induced wall thermal loads can lead to the nozzle geometry alteration, which in turn, leads to the appearance of strong side loads that may be detrimental to the rocket engine structural integrity. It is therefore necessary to understand both aerodynami

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Hossain, Md Amzad, Austin Morse, Iram Hernandez, Joel Quintana, and Ahsan Choudhuri. "Liquid Rocket Engine Performance Characterization Using Computational Modeling: Preliminary Analysis and Validation." Aerospace 11, no. 10 (2024): 824. http://dx.doi.org/10.3390/aerospace11100824.

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The need to refuel future missions to Mars and the Moon via in situ resource utilization (ISRU) requires the development of LOX/LCH4 engines, which are complex and expensive to develop and improve. This paper discusses how the use of digital engineering—specifically physics-based modeling (PBM)—can aid in developing, testing, and validating a LOX/LCH4 engine. The model, which focuses on propulsion performance and heat transfer through the engine walls, was created using Siemens’ STAR-CCM+ CFD tool. Key features of the model include Eulerian multiphase physics (EMP), complex chemistry (CC) usin

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Srivastava, Sachin, G. Hamshitha, V. Jagannath, et al. "Numerical Studies of Solid Rocket Propellant PMMA-PBAN-ALF3-Nitrocellulose-Difluoramine." Journal of Physics: Conference Series 2856, no. 1 (2024): 012010. http://dx.doi.org/10.1088/1742-6596/2856/1/012010.

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Abstract The aim of the new investigation is the evaluation of solid rocket Propellant. In which performing numerical analysis of solid rocket propellant and calculating the constraints involved as derived from thrust i.e. velocity involved in the solid rocket propulsion motor usage. This paper aims to show the viability of solid rocket propellant for modern and future applications. Solid rocket motors are simple in design and fabricating. The need for a propellant that produces the same specific impulse as another chemical rocket engine. So it is needed to have a solid rocket motor with an en

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Walter, R. J., D. E. Matejczyk, F. C. Gunderloy, and R. Morinishi. "Methane-Fuel Corrosion in Regeneratively Cooled Rocket-Engine Combustors." CORROSION 45, no. 8 (1989): 685–88. http://dx.doi.org/10.5006/1.3579322.

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Yagodnikov, D. A., A. V. Voronetskii, and N. M. Pushkin. "Electrification of nozzle in a liquid rocket engine." Combustion, Explosion, and Shock Waves 31, no. 4 (1995): 450–54. http://dx.doi.org/10.1007/bf00789365.

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Тymoshenko, V. I., and H. Ye Deshko. "Numerical simulation of efflux of a supersonic multicomponent chemical reacting rocket engine jet." Kosmìčna nauka ì tehnologìâ 23, no. 6 (2017): 3–12. http://dx.doi.org/10.15407/knit2017.06.003.

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Hou, Lingyun, Pengfei Fu, and Yantao Ba. "Chemical Mechanism of MMH/NTO and Simulation in a Small Liquid Rocket Engine." Combustion Science and Technology 191, no. 12 (2018): 2208–25. http://dx.doi.org/10.1080/00102202.2018.1551214.

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Liu, Zheng, Jianxin Nie, Wenqi Fan, et al. "Simulation Analysis of the Safety of High-Energy Hydroxyl-Terminated Polybutadiene (HTPB) Engine under the Impact of Fragments." Crystals 13, no. 3 (2023): 394. http://dx.doi.org/10.3390/cryst13030394.

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The safety of solid rocket engine use seriously affects the survivability and combat effectiveness of weaponries. To study the engine safety against fragment in complex battlefield environments, the fragment impact safety simulation study of a high-energy four-component HTPB propellant solid engine (hereafter referred to as high-energy HTPB propellant engine) was conducted. The equation of state parameters and reaction rate equation parameters of the detonation product of high-energy HTPB propellant were calibrated by using a 50 mm diameter cylinder test and Lagrange test combined with genetic

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T.Vijay, Kumar*1 &. Mohamad Imran2. "DESIGN EVALUTION AND OPTIMIZATION OF NOZZLE USED IN DIESEL ENGINE FUEL INJECTOR." GLOBAL JOURNAL OF ENGINEERING SCIENCE AND RESEARCHES 6, no. 6 (2019): 143–49. https://doi.org/10.5281/zenodo.3252695.

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The nozzle is used to convert the chemical thermal energy generated in the combustion chamber into kinetic energy. The nozzle converts the low velocity, high pressure, high temperature gas in the combustion chamber into high velocity gas of lower pressure and temperature. Nozzle is a device designed to control the rate of flow, speed, direction, mass, shape, and/or the pressure of the stream that exhaust from them. Nozzles come in a variety of shapes and sizes depending on the mission of the rocket, this is very important for the understanding of the performance characteristics of rocket. Conv

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Choi, Suk Min, Sangwoo Jung, Vincent Mario Pierre Ugolini, and Sejin Kwon. "Combustion Visualization and Liquid Jet in Crossflow Analysis of H2O2/Kerosene Bipropellant Thruster." Aerospace 12, no. 2 (2025): 110. https://doi.org/10.3390/aerospace12020110.

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In the H2O2/Kerosene bipropellant thruster, a liquid fuel jet is transversely injected into a crossflow of hot oxygen and water vapor, catalytically decomposed from a liquid oxidizer. Due to the high temperature and oxygen-rich environment, kerosene is auto-ignited without the need for an additional ignition source. Hence, fuel trajectory and breakup processes play a significant role in determining the performance of the rocket engine. However, little effort has been made to analyze these characteristics during actual rocket engine operation, mainly due to its harsh operating conditions of hig

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Sekar, T. Chandra, and A. M. Pradeep. "Selected Papers from 4th National Aerospace Propulsion Conference NAPC 2022." Defence Science Journal 74, no. 2 (2024): 161–62. http://dx.doi.org/10.14429/dsj.74.20002.

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The National Aerospace Propulsion Conference (NAPC) is a national conference dedicated to aerospace propulsion technologies. Two erstwhile popular conference series, the National Propulsion Conference (NPC) and the National Conference on Air-Breathing Engines (NCABE) were merged to result in NAPC. This biennial conference is intended to bring together the entire propulsion community spanning the industry, academia and the research labs nationwide. The aerospace propulsion-centred conference is considered an ideal opportunity to showcase one’s research activities with peers and foster future co

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Senchev, M. N., I. A. Zubrilin, A. A. Yurtaev, М. A. Benedyuk, and Yu V. Komisar. "Simulation of the processes of spraying and combustion of kerosene and liquid oxygen in the chamber of a liquid-propellant rocket engine." VESTNIK of Samara University. Aerospace and Mechanical Engineering 23, no. 4 (2024): 167–79. https://doi.org/10.18287/2541-7533-2024-23-4-167-179.

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The paper presents the results of simulation of spray and combustion processes in the liquid-propellant rocket engine chamber using the z77 reduced kinetic mechanism of chemical reactions and a hybrid method for determining spray parameters of a swirl atomizer. Simulation was carried out for the nominal operational conditions in a three-dimensional domain using the ANSYS Fluent software. The process of spraing liquid fuel components (T-1 kerosene and oxygen) by monopropellant injectors was simulated using a model of discontinuous phases. The simulation results (pressure, temperature and veloci

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Igor, Trofimov, Boichenko Sergii, and Shamanskyi Sergii. "Analysis of rocket fuels and problems of their application on the example of Ukraine." TECHNOLOGY AUDIT AND PRODUCTION RESERVES 6, no. 1(56) (2020): 19–27. https://doi.org/10.15587/2706-5448.2020.218358.

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<em>The object of research is the problems of rocket fuel application, the state of art and prospects. These problems are characteristic of almost the entire range of brands of modern rocket fuels suitable for application. These are problems with the basic physic-chemical and operational properties, technical requirements for the quality of rocket fuel, problems with the functioning of the refueling infrastructure, as well as ensuring the purity of rocket fuels.</em> <em>Given the ban on the use of highly toxic poisonous rocket fuels based on nitric acid, there is a problem of replacing them w

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Zhu, Chengfeng, Yanzhong Li, Fushou Xie, Lei Wang, and Yuan Ma. "The Mechanism Research of Low-Frequency Pressure Oscillation in the Feeding Pipe of Cryogenic Rocket Propulsion System." Processes 10, no. 11 (2022): 2448. http://dx.doi.org/10.3390/pr10112448.

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In the propulsion system of cryogenic liquid rockets, low-frequency pressure oscillation is a long-standing issue occurring in its feeding pipe, and is not conducive to the normal operation of the rocket. Its mechanism and excitation process are not very clear due to the limitation of the existing numerical method and the difficulty of the real dynamic experiment. Inspired by the periodic suck-back flow phenomenon of steam condensation, the fluctuation of the two-phase interface might be the crucial factor to initiate the low-frequency pressure oscillation. To simulate this interfacial charact

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Bykovskaya, Galina Alekseevna Chernykh Vladimir Dmitrievich. "HISTORICAL ASPECTS OF COSMONAUTICS: VORONEZH SPACE PROGRAMS." Bulletin Social-Economic and Humanitarian Research 10 (12), 2021 (April 12, 2021): 14–26. https://doi.org/10.5281/zenodo.4500880.

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The article describes the history of the aerospace industry in Russia at its present stage, identifies the critical points of development of the KBKhA (Voronezh), which is one of the world leaders in engine building for rocket systems.

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Zhao, Ting, Jianguo Xu, and Yuanding Wang. "Modeling of Spray Combustion and Heat Transfer of MMH/N2O4 in a Small Rocket Engine Using Different Mechanisms." Energies 17, no. 19 (2024): 4781. http://dx.doi.org/10.3390/en17194781.

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Although various hypergolic propellants like MMH/N2O4 (monomethylhydrazine/dinitrogen tetroxide) are widely used in small rocket engines, there remains a lack of in-depth study conducted on their chemical reactions and spray combustion behaviors. To fill this research gap, a simplified chemical kinetic model that is suitable for three-dimensional simulation was proposed in this paper for MMH/N2O4. Then, numerical investigation was conducted using the Volume of Fluid (VOF) model to explore the transient injection and atomization of MMH/N2O4 impinging jets in a small bipropellant thruster. Also,

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Lentini, D. "Identification of chemical and vibrational relaxation regimes in rocket nozzle flow via a quasi-linear formulation." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 215, no. 2 (2001): 79–87. http://dx.doi.org/10.1243/0954410011531781.

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A quasi-linear formulation is proposed for high-speed finite-rate chemically reacting mixtures of imperfect gases, i.e. thermally perfect gases with specific heat varying with temperature, as an extension of a previously developed formulation for perfect gases. The form is suitable for application of accurate and fast algorithms. In particular, the resulting equations keep the same formalism already derived for reacting mixtures of perfect gases, thus indicating the potential for a straightforward extension of existing computational algorithms. In order to assess the applicability of the appro

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Gidaspov, V. Yu, F. T. Kuli-Zade, and N. S. Severina. "One-Dimensional Model for Calculating Losses due to Chemical Nonequilibrium in a Rocket Engine Nozzle." Russian Aeronautics 67, no. 3 (2024): 601–9. https://doi.org/10.3103/s1068799824030152.

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38

Egorov, Mikhail, Vitaliy Gorodnev, Dmitry Egorov, and Sergey Egorov. "NUMERICAL STUDY OF THE DYNAMICS OF INTRA-CHAMBER PROCESSES IN A ROCKET ENGINE FOR MOBILE COMPLEXES WITH A MULTI-TURRET POWDER CHARGE." Perm National Research Polytechnic University Aerospace Engineering Bulletin, no. 60 (2020): 55–63. http://dx.doi.org/10.15593/2224-9982/2020.60.06.

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A solid-fuel rocket engine is a complex technical system in which a number of interrelated non – stationary and substantially nonlinear physical and chemical processes simultaneously occur. The type of SFRE under consideration has its own problems and design features. To optimize the parameters of a rocket engine, we study the dynamics of its internal processes. The research method is to set up a computational experiment. We consider the conjugate statement of the problem, which includes: triggering of the ignition device; – heating, ignition and subsequent unsteady and turbulent combustion of

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39

Pietrykowski, Konrad, Paweł Karpiński, and Radosław Mączka. "Computational Fluid Dynamics Model of Various Types of Rocket Engine Nozzles." International Review on Modelling and Simulations (IREMOS) 13, no. 1 (2020): 1. http://dx.doi.org/10.15866/iremos.v13i1.18068.

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Zhou, Shengbing, Yuan Ma, Feng Liu, and Ning Hu. "Experimental investigation on pulse operation characteristics of rotating detonation rocket engine." Fuel 354 (December 2023): 129408. http://dx.doi.org/10.1016/j.fuel.2023.129408.

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41

Gorskiy, V. V., M. G. Kovalsky, and V. G. Resh. "Method of Calculating Carbon Ablation in the Jet of Liquid Rocket Engine Combustion Products." Herald of the Bauman Moscow State Technical University. Series Mechanical Engineering, no. 5 (128) (October 2019): 4–21. http://dx.doi.org/10.18698/0236-3941-2019-5-4-21.

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Nowadays carbon materials are widely used as ablating thermal protection for high-temperature structural elements in aerospace technology. Prediction of changes in the shape of the external surfaces of these elements, due to the burning of thermal protection, is closely related to the use of computational-theoretical methods describing the flow of various physicochemical and mechanical processes associated with the occurrence of the phenomenon under consideration. At the same time, it is crucial to test such methods on the results of experimental studies conducted under conditions which are im

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42

Belov, G. V. "Development of Tools for Thermodynamic Calculation of Rocket Engine Characteristics using the Julia Programming Language." Herald of the Bauman Moscow State Technical University. Series Mechanical Engineering, no. 4 (139) (December 2021): 80–93. http://dx.doi.org/10.18698/0236-3941-2021-4-80-93.

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The experience in developing an algorithm and a program for the thermal-chemical calculation of the characteristics of a rocket engine is presented. The program is written in Julia. To calculate the equilibrium composition of combustion products the freely distributed library Ipopt is used. The program is interfaced to the database on thermodynamic properties of individual substances IVTANTERMO. For the convenience of processing, the information on thermodynamic properties is stored in two text files of a special form. The program has been developed using the simplest working process model acc

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Seidl, Martin J., Manfred Aigner, Roman Keller, and Peter Gerlinger. "CFD simulations of turbulent nonreacting and reacting flows for rocket engine applications." Journal of Supercritical Fluids 121 (March 2017): 63–77. http://dx.doi.org/10.1016/j.supflu.2016.10.017.

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44

Ahn, Kyubok, and Hwan-Seok Choi. "A STUDY ON DISCHARGE COEFFICIENTS OF CLOSED-TYPE SWIRL INJECTORS FOR A LIQUID ROCKET ENGINE." Atomization and Sprays 27, no. 7 (2017): 569–78. http://dx.doi.org/10.1615/atomizspr.2017019096.

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45

Palacz, Tomasz, and Jacek Cieślik. "Testing of the N2O/HDPE Vortex Flow Pancake Hybrid Rocket Engine with Augmented Spark Igniter." Aerospace 10, no. 8 (2023): 727. http://dx.doi.org/10.3390/aerospace10080727.

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The paper is part of the research aimed at determining if the vortex flow pancake (VFP) hybrid rocket engine is feasible as green in-space chemical propulsion. The objective of this study is to test an N2O/HDPE VFP hybrid ignited with N2O/C3H8 torch igniter. The N2O is used in self-pressurizing mode, which results in two-phase flow and varying inlet conditions, thus better simulating real in-space behavior. The study begins with characterizing the torch igniter, followed by hot-fire ignition tests of the VFP. The results allow for the improved design of the torch igniter and VFP hybrid. The ax

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Petrenko, V. I., and V. L. Popov. "A variable-thrust solid-propellant rocket engine with local combustion boosting." Combustion, Explosion, and Shock Waves 32, no. 3 (1996): 327–30. http://dx.doi.org/10.1007/bf01998464.

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Lucchese, L., J. Liberatori, D. Cavalieri, et al. "Impact of chemical modeling on the numerical analysis of a LOx/GCH4 rocket engine pintle injector." Acta Astronautica 218 (May 2024): 240–50. http://dx.doi.org/10.1016/j.actaastro.2024.02.038.

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Srivastava, Srikant, P. N. Dwivedi, and D. M. Vinod Kumar. "3 Loop Structure based Fuel Flow Controller Design for Robust Operation of Ducted Ramjet Rocket." Defence Science Journal 71, no. 4 (2021): 571–77. http://dx.doi.org/10.14429/dsj.71.16397.

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This paper is about the designing of 3-loop structure based fuel flow controller (FFC) for efficient operation of supersonic ramjet based propulsion system. The main objective of the control design is to vary appropriately the engine controllable parameters (throttle value area) such that commanded thrust is achieved by ramjet engine without endangering the engine stability and performance. Various factors such as combustion-intake interaction, atmospheric disturbance and other flight conditions have a significant impact on the air intake operation which lead to effect on engine performance. D

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Nasuti, Francesco, and Marco Pizzarelli. "Pseudo-boiling and heat transfer deterioration while heating supercritical liquid rocket engine propellants." Journal of Supercritical Fluids 168 (February 2021): 105066. http://dx.doi.org/10.1016/j.supflu.2020.105066.

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Santos, Emerson Andrade, Wilton Fernandes Alves, André Neves Almeida Prado, and Cristiane Aparecida Martins. "Development of test stand for experimental investigation on of chemical and physical phenomena in Liquid Rocket Engine." Journal of Aerospace Technology and Management 3, no. 2 (2011): 159–70. http://dx.doi.org/10.5028/jatm.2011.03021111.

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