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Journal articles on the topic 'Rocket engine nozzle'

Author: Grafiati

Published: 14 March 2023

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1

Strelnikov, G. A., A. D. Yhnatev, N. S. Pryadko, and S. S. Vasyliv. "Gas flow control in rocket engines." Technical mechanics 2021, no. 2 (2021): 60–77. http://dx.doi.org/10.15407/itm2021.02.060.

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In the new conditions of application of launch vehicle boosters, space tugs, etc., modern rocket engines often do not satisfy the current stringent requirements. This calls for fundamental research into processes in rocket engines for improving their efficiency. In this regard, for the past 5 years, the Department of Thermogas Dynamics of Power Plants of the Institute of Technical Mechanics of the National Academy of Sciences of Ukraine and the State Space Agency of Ukraine has conducted research on gas flow control in rocket engines to improve their efficiency and functionality. Mechanisms of

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2

Jéger, Csaba, and Árpád Veress. "Novell Application of CFD for Rocket Engine Nozzle Optimization." Periodica Polytechnica Transportation Engineering 47, no. 2 (2018): 131–35. http://dx.doi.org/10.3311/pptr.11490.

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Numerical analyses, validation and geometric optimization of a converging-diverging nozzle flows has been established in the present work. The optimal nozzle contour for a given nozzle pressure ratio and length yields the largest obtainable thrust for the conditions and thus minimises the losses. Application of such methods reduces the entry cost to the market, promote innovation and accelerate the development processes. A parametric geometry, numerical mesh and simulation model is constructed first to solve the problem. The simulation model is then validated by using experimental and computat

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3

Guram, Sejal, Vidhanshu Jadhav, Prasad Sawant, and Ankit Kumar Mishra. "Review Study on Thermal Characteristics of Bell Nozzle used in Supersonic Engine." 1 2, no. 1 (2023): 4–14. http://dx.doi.org/10.46632/jame/2/1/2.

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The nozzle is an important component of the rocket motor system, and a rocket’s overall performance is highly reliant on its aerodynamic design. The nozzle contour can be meticulously shaped to improve performance significantly. The design and shape of rocket nozzles have evolved over the last several decades as a result of extensive research. The nozzle design is composed of two components, an integrated throat, an entry and an exit cone, and a thermal protection system. The Bell Nozzle is designed to provide clearance space for placing the ITE and exit cone, with a cone inflection angle of 1

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4

ZAGANESCU, Nicolae-Florin, Rodica ZAGANESCU, and Constantin-Marcian GHEORGHE. "Wernher Von Braun’s Pioneering Work in Modelling and Testing Liquid-Propellant Rockets." INCAS BULLETIN 14, no. 2 (2022): 153–61. http://dx.doi.org/10.13111/2066-8201.2022.14.2.13.

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This paper presents a view on how Dr. Wernher Von Braun laid the basis for realistic modelling and testing liquid-propellants rockets, by his PhD Thesis – a secret document in 1934, which remained classified until 1960. Understanding that better mathematical modelling is needed if these rockets are to become spaceflight vehicles, he clarified in his thesis essential issues like: maximum achievable rocket speed; Laval nozzle thrust gain; polytropic processes in the combustion chamber and nozzle; influence of equilibrium and dissociation reactions; original measurement systems for rockets test s

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5

Bogoi, Alina, Radu D. Rugescu, Valentin Ionut Misirliu, Florin Radu Bacaran, and Mihai Predoiu. "Inviscid Nozzle for Aerospike Rocket Engine Application." Applied Mechanics and Materials 811 (November 2015): 152–56. http://dx.doi.org/10.4028/www.scientific.net/amm.811.152.

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A computational method for the steady 2-D flow in axially symmetrical rocket nozzles with a given profile is developed, in order to determine the Maximum thrust contour of rocket engine nozzles with large expansion ratio. The optimized nozzles proved a more than 10% increase in the integral specific impulse recorded during the variable altitude atmospheric flight of rocket vehicles. The method is well suited for application in the design of the optimum contour for axially-symmetric nozzles for atmospheric rocket ascent, specifically for aerospike type nozzles, as for other similar industrial a

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6

Sultanov, T. S., та G. A. Glebov. "Numerical Computation of Specific Impulse and Internal Flow Parameters in Solid Fuel Rocket Motors with Two-Phase Сombustion Products". Herald of the Bauman Moscow State Technical University. Series Mechanical Engineering, № 3 (138) (вересень 2021): 98–107. http://dx.doi.org/10.18698/0236-3941-2021-3-98-107.

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Eulerian --- Lagrangian method was used in the Fluent computational fluid dynamics system to calculate motion of the two-phase combustion products in the solid fuel rocket motor combustion chamber and nozzle. Condensed phase is assumed to consist of spherical particles with the same diameter, which dimensions are not changing along the motion trajectory. Flows with particle diameters of 3, 5, 7, 9, and 11 μm were investigated. Four versions of the engine combustion chamber configuration were examined: with slotted and smooth cylindrical charge channels, each with external and submerged nozzles

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7

Bruce Ralphin Rose, J., and J. Veni Grace. "Performance analysis of lobed nozzle ejectors for high altitude simulation of rocket engines." International Journal of Modeling, Simulation, and Scientific Computing 05, no. 04 (2014): 1450019. http://dx.doi.org/10.1142/s1793962314500196.

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Ejectors are used in high altitude testing of rocket engines to create vacuum for simulating the engine test in vacuum conditions. The performance of an ejector plays a vital role in creating vacuum at the exit of the engine nozzle and the nozzle design exit pressure at the time of ignition. Consequently, the performance of ejectors has to be improved to reduce the consumption of active fluid. In this investigation, the performance of an ejector has been improved by changing the exit shear plane of the nozzle. Conventionally, conical nozzles are used for creating the required momentum. Lobes o

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8

Shustov, S. A., I. E. Ivanov, and I. A. Kryukov. "Numerical study of the separation of a turbulent boundary in rocket engine nozzles with an optimized supersonic part." Journal of Physics: Conference Series 2308, no. 1 (2022): 012015. http://dx.doi.org/10.1088/1742-6596/2308/1/012015.

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Abstract At present, propulsion systems are being developed for flights of aerospace vehicles both in the Earth’s atmosphere and beyond. At the stage of the propulsion system design, it is necessary to be able to reliably determine the energy and thrust characteristics of rocket engines in regimes with flow separation in the nozzle for a wide range of nozzle pressure ratio (NPR) (1 ≤ m ≤ 30, m = ph /pa , p—pressure, indices h and a refer, respectively, to the parameters of the external environment and at the nozzle exit) characterizing the flow in nozzles and jets. In this case, the nozzle, as

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9

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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10

Kumar, S. Senthil, and M. Arularasu. "Advanced Computational Flow Analysis - Rocket Engine Nozzle." Asian Journal of Research in Social Sciences and Humanities 6, no. 11 (2016): 1219. http://dx.doi.org/10.5958/2249-7315.2016.01265.x.

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11

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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12

O¨stlund, J., and B. Muhammad-Klingmann. "Supersonic Flow Separation with Application to Rocket Engine Nozzles." Applied Mechanics Reviews 58, no. 3 (2005): 143–77. http://dx.doi.org/10.1115/1.1894402.

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The past decade has seen a qualitative advancement of our understanding of physical phenomena involved in flow separation in supersonic nozzles; in particular, the problem of side loads due to asymmetrical pressure loads, which constitutes a major restraint in the design of nozzles for satellite launchers. The development in this field is to a large extent motivated by the demand for high-performance nozzles in rocket engineering. The present paper begins with an introduction to the physical background of shock-boundary-layer interactions in basic 2D configurations, and then proceeds to intern

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13

Abada, Omar, Abderahim Abada, and Ahmed Abdallah El-Hirtsi. "Effect of bipropellant combustion products on the rocket nozzle design." Mechanics & Industry 21, no. 5 (2020): 515. http://dx.doi.org/10.1051/meca/2020064.

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The focus of this research work is to investigate numerically the effect of adding the gas on the design and performance of axisymmetric MLN nozzles. A FORTRAN code was developed to design this nozzle using the characteristics method (MOC) at high temperature. The thermochemical and combustion studies of the most used liquid propellants on the satellites and launch vehicles allow to known all gases. Four engines are investigated: Ariane 5 (Vulcain 2), Ariane-5 upper stage engine (Aestus), Zenit first stage (RD-170) and Falcon 9 upper stage (Raptor). Thermodynamic analysis of parameters design

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14

Wang, Yan Dong, and Hong Guang Jia. "Numerical Simulation of Laval Nozzle." Applied Mechanics and Materials 397-400 (September 2013): 266–69. http://dx.doi.org/10.4028/www.scientific.net/amm.397-400.266.

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Laval nozzle is the commonly used device in rocket engine and aero engine. this paper, the numerical model is derived. The convergent section subsonic flow and divergent section hypersonic flow are simulated in dimensionless method. Reverting the dimension, the result can be seen that the analytical solution, the CFX simulation solution and the numerical are in uniform.

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15

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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16

Zieliński, Mateusz, Piotr Koniorczyk, Janusz Zmywaczyk, and Marek Preiskorn. "Numerical simulations of temperature fields in the uncooled nozzle of a short-range anti-aircraft rocket engine with an insert in the critical section made of various materials." Bulletin of the Military University of Technology 70, no. 1 (2021): 15–30. http://dx.doi.org/10.5604/01.3001.0015.6955.

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Abstract. The paper presents numerical simulations of transient heat conduction in the uncooled nozzle of a short-range anti-aircraft rocket engine. The calculations were made for the configuration of the nozzle with an insert in the critical section made of various materials. The inserts used were: POCO graphite, Al2O3 ceramics, ZrO2-3Y2O3 ceramics. For comparison, numerical simulations of the heat transfer in a nozzle made entirely of St 45 steel, the melting point of which is 1700K, were also carried out. The engine's working time was in the order of 3 s. Numerical simulations were performe

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17

Sabirzyanov, A. N., A. I. Glazunov, A. N. Kirillova, and K. S. Titov. "Simulation of a Rocket Engine Nozzle Discharge Coefficient." Russian Aeronautics 61, no. 2 (2018): 257–64. http://dx.doi.org/10.3103/s1068799818020150.

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18

Semenov, Vasiliy, Igor Ivanov, and Igor Kryukov. "Dual bell slot nozzle of a rocket engine." Perm National Research Polytechnic University Aerospace Engineering Bulletin, no. 46 (2016): 56–72. http://dx.doi.org/10.15593/2224-9982/2016.46.03.

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19

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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20

Sun, Dechuan, Tianyou Luo, and Qiang Feng. "New Contour Design Method for Rocket Nozzle of Large Area Ratio." International Journal of Aerospace Engineering 2019 (December 20, 2019): 1–8. http://dx.doi.org/10.1155/2019/4926413.

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A rocket engine for space propulsion usually has a nozzle of a large exit area ratio. The nozzle efficiency is greatly affected by the nozzle contour. This paper analysed the effect of the constant capacity ratio in Rao’s method through the design process of an apogee engine. The calculation results show that increasing the heat capacity ratio can produce an expansion contour of smaller expansion angle and exit area ratio. A simple modification of Rao’s method based on thermally perfect gas assumption was made and verified to be more effective. The expansion contour designed by this method has

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21

Bhupendra Kumar, Mohd Shoaib, Ramanan G, and Radhakrishnan P. "Design and Computational Flow Analysis of Different Rocket Nozzle Profile." ACS Journal for Science and Engineering 2, no. 2 (2022): 49–60. http://dx.doi.org/10.34293/acsjse.v2i2.38.

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In recent days the launching value of increasing the industrial business starts with lowering prices related to the launch vehicle operation. Reducing the price begins with rising the propulsion systems, creating these vehicles a lot of economical with a restricted fuel amount. The Linear Aerospike engine has incontestable bigger thrust potency over this engines used on launch vehicles. However, unresolved problems with warming plague this standard. This study proposes an approach amendment to the rocket motor that explores a way to increase the performance of the nozzle body, and lower the ch

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22

Cunningham, Carson F., Mark C. Anderson, Levi T. Moats, et al. "Acoustical measurement and analysis of an Atlas V launch without solid rocket boosters." Journal of the Acoustical Society of America 151, no. 4 (2022): A83. http://dx.doi.org/10.1121/10.0010730.

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In September 2021, an Atlas V rocket without solid rocket boosters was launched from Vandenberg Space Force Base, California, carrying the NASA/USGS Landsat 9 satellite. In this launch configuration, the plumes from the RD-180 engine’s two nozzles are unobstructed, providing the opportunity to analyze the sound generated by a liquid-fuel rocket engine with an azimuthally asymmetric nozzle geometry. Acoustical data were collected at various locations surrounding the launch pad, ranging from a few hundred meters to several kilometers. This paper discusses an overview of the measurement logistics

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23

Brykov, N. A., and K. A. Tischenko. "Computational study of gas flow characteristics when using intra-nozzle interceptors for thrust vector control." Journal of Physics: Conference Series 2388, no. 1 (2022): 012098. http://dx.doi.org/10.1088/1742-6596/2388/1/012098.

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Abstract This article proposes the use of cylindrical nozzle interceptors (probes) as an alternative method of rocket engine thrust vector control, which can replace traditional thrust vector control systems. The objective of this paper was to perform a three-dimensional CFD simulation of the gas flow in a rocket engine nozzle with a rod interceptor taken out of the wall without secondary injection, analyzing the calculated flow data and estimating the lateral force. The simulations will be performed in steady-state mode. In the CFD simulations, velocity distribution contours were obtained on

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24

Leto, Angelo. "Investigation of a Radial Turbines Compatibility for Small Rocket Engine." E3S Web of Conferences 197 (2020): 11009. http://dx.doi.org/10.1051/e3sconf/202019711009.

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In the radial turbine preliminary design for an expander rocket engine, a comparison was made with axial turbine used in Pratt & Whitney RL10 engine. One of the primary requirements of a liquid propellant rocket engine is the generation of a high thrust, which depends on both the mass flow rate of the propellant and the pressure in the thrust chamber. In expander-cycle engines, which are the subject of the present study, the liquid propellant is first compressed using centrifugal turbo-pumps, then it is used to cool the combustion chamber and the nozzle and, once vaporized, it flows throug

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25

Manski, Detlef, and Gerald Hagemann. "Influence of rocket design parameters on engine nozzle efficiencies." Journal of Propulsion and Power 12, no. 1 (1996): 41–47. http://dx.doi.org/10.2514/3.23988.

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26

Cai, Guobiao, Jie Fang, Xu Xu, and Minghao Liu. "Performance prediction and optimization for liquid rocket engine nozzle." Aerospace Science and Technology 11, no. 2-3 (2007): 155–62. http://dx.doi.org/10.1016/j.ast.2006.07.002.

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27

Bennewitz, John W., Blaine R. Bigler, Mathias C. Ross, Stephen A. Danczyk, William A. Hargus, and Richard D. Smith. "Performance of a Rotating Detonation Rocket Engine with Various Convergent Nozzles and Chamber Lengths." Energies 14, no. 8 (2021): 2037. http://dx.doi.org/10.3390/en14082037.

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A rotating detonation rocket engine (RDRE) with various convergent nozzles and chamber lengths is investigated. Three hundred hot-fire tests are performed using methane and oxygen ranging from equivalence ratio equaling 0.5–2.5 and total propellant flow up to 0.680 kg/s. For the full-length (76.2 mm) chamber study, three nozzles at contraction ratios ϵc = 1.23, 1.62 and 2.40 are tested. Detonation is exhibited for each geometry at equivalent conditions, with only fuel-rich operability slightly increased for the ϵc = 1.62 and 2.40 nozzles. Despite this, counter-propagation, i.e., opposing wave

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28

Dîrloman, F.-M., L.-C. Matache, T. Rotariu, et al. "Computational fluid dynamics simulations for composite rocket propellant optimization." IOP Conference Series: Materials Science and Engineering 1182, no. 1 (2021): 012017. http://dx.doi.org/10.1088/1757-899x/1182/1/012017.

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Abstract When designing a rocket engine configuration, both in terms of propellant grain, combustion chamber and nozzle geometry, one of the most convenient approach is using Computational Fluid Dynamics (CFD) Simulation. Numerical simulation is an alternative method of scientific investigation, which substitutes large number of experiments that often imply high financial burden and are also dangerous for the personnel involved. The numerical approach is often more useful than consecrated experimental method because it provides complete data that cannot be directly observed or measured, or it

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29

Hasegawa, Keiichi, Akinaga Kumakawa, Kazuo Kusaka, et al. "Fundamental Study of Extendible Nozzle and Dual-Bell Nozzle for Reusable Rocket Engine." SPACE TECHNOLOGY JAPAN, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 2 (2003): 25–34. http://dx.doi.org/10.2322/stj.2.25.

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30

Zhao, Na, Yong Gang Yu, and Yu Qiang Wang. "Numerical Simulation of the Spray Characteristics in Small Scale Liquid Rocket Engine Combustion Chamber." Advanced Materials Research 383-390 (November 2011): 7729–33. http://dx.doi.org/10.4028/www.scientific.net/amr.383-390.7729.

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The mathematical and physical model of the liquid propellant spray in straight nozzle was proposed for studying the performance characteristics of the small-scale liquid rocket engine. With the Fluent software, the numerical simulation was carried out. Sauter mean diameter (SMD) of the HAN-based liquid propellant (LP1846) in the engine combustor changing with spray pressure, nozzle diameter and the liquid surface tension were analyzed. The results indicate that: in the spray pressure region of 1.8MPa~3.0MPa, at a fixed spray pressure, the smaller is the nozzle diameter, the smaller is the drop

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31

LEE, YOUNG-SHIN, JAE-HOON KIM, HYUN-SOO KIM, DUCK-HOI KIM, SEONG-HOI KU, and SOON-IL MOON. "A STUDY ON THE THERMAL VIBRATION ANALYSIS OF THE GRAPHITE DISK UNDER THERMAL SHOCK." International Journal of Modern Physics B 20, no. 25n27 (2006): 4105–10. http://dx.doi.org/10.1142/s0217979206040933.

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Graphite is applied to structural material of the high temperature reactor and nozzle of high energy rocket engine. The excessive vibration and stress field can be occurred for this material due to the severe thermal condition. In this study, the thermal stress and vibration characteristics of ATJ graphite under high temperature condition are investigated by finite element analysis (FEA). The specimen is designed as a disk shape in order to simulate the rocket nozzle combustion condition. The experiment of thermal heat is also conducted using by CO 2 laser.

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32

Arzhannikov, Andrey, and Alexey Beklemishev. "An Electro-Jet Rocket Engine With Big Thrust At Helical Corrugated Magnetic Field." Siberian Journal of Physics 11, no. 1 (2016): 107–18. http://dx.doi.org/10.54362/1818-7919-2016-11-1-107-118.

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A fundamentally new electro-jet rocket engine having a big thrust with a high specific impulse is described in this paper. The acceleration mechanism of magnetized plasma along the axis of a cylindrical chamber with a helical corrugated magnetic field is put in the basis of such engine. The plasma acceleration is achieved during its drift motion by applying a radial electric field. The analytical description of the plasma motion process gives a visual representation of how the diamagnetic forces provide the process of the continuous acceleration of plasma ions along the axis of the helical cor

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33

Zhao, Wei Guo, Ji Hong Dong, Wei Li, Hai Ping Wang, and Quan Feng Guo. "Research on Defect Detection Technology of C/C Composite." Advanced Materials Research 295-297 (July 2011): 264–69. http://dx.doi.org/10.4028/www.scientific.net/amr.295-297.264.

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Carbon matrix/Carbon fibre reinforced composite(C/C composite) has many special characteristics such as high strength, high elastic modulus, high temperature resistance and ablation resistance. So it is used to manufacture rocket engine nozzle in aerospace filed. But its security will be seriously effected during rocket engine working due to the manufacturing defects. Based on analyzing defect types and structure characteristic of C/C composite, the ultrasonic and infrared testing methods on C/C composite are further studied in this thesis. And effective defect detection has been achieved.

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Ryzhkov, V. V., and I. I. Morozov. "Technology of computational analysis of the working process parameters of low-thrust rocket engines running on gaseous oxygen-hydrogen fuel with the use of ANSYS CFD." VESTNIK of Samara University. Aerospace and Mechanical Engineering 18, no. 2 (2019): 62–74. http://dx.doi.org/10.18287/2541-7533-2019-18-2-62-74.

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The paper presents the description of a mathematical model of the working process of a low-thrust rocket engine operating on gaseous oxygen-hydrogen fuel and some fragments of the technology of computational analysis of distribution of gas-dynamic parameters in the engine duct. We present the results of calculating the stream line distribution, the distribution of total temperature profile along the flow path of the engine chamber and at its characteristic cross sections, the axial component of (total) speed of combustion products in the Laval nozzle output section. The results of calculating

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35

Verma, S. B., and Oskar Haidn. "Unsteady Side-Load Evolution in a Liquid Rocket Engine Nozzle." Journal of Spacecraft and Rockets 57, no. 2 (2020): 391–97. http://dx.doi.org/10.2514/1.a34556.

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Forde, Scott, Mel Bulman, and Todd Neill. "Thrust augmentation nozzle (TAN) concept for rocket engine booster applications." Acta Astronautica 59, no. 1-5 (2006): 271–77. http://dx.doi.org/10.1016/j.actaastro.2006.02.052.

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37

Vinod, G., S. Renjith, and V. Thaddeus Basker. "Thermo Structural Analysis of Carbon-Carbon Nozzle Exit Cone for Rocket Cryo Engines." Applied Mechanics and Materials 877 (February 2018): 320–26. http://dx.doi.org/10.4028/www.scientific.net/amm.877.320.

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Launch and space vehicle structures are required to be extremely weight efficient. The need to achieve the performance required for the engine in the upper stage of a launch vehicle, increase the payload capacity drives rocket engine manufacturers to seek higher thrust level, specific impulse and thrust to weight ratio. The use of high temperature C-C composite materials is an efficient way to reach these objectives by allowing use of high expansion ratio. Nozzle extensions benefiting of the outstanding thermal, mechanical and fatigue resistance of these materials to decrease mass and featurin

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38

KOSTYUSHIN, Kirill V. "NUMERICAL INVESTIGATION OF UNSTEADY GASDYNAMIC PROCESSES AT THE LAUNCH OF SOLID-PROPELLANT ROCKETS." Vestnik Tomskogo gosudarstvennogo universiteta. Matematika i mekhanika, no. 67 (2020): 127–43. http://dx.doi.org/10.17223/19988621/67/12.

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The paper presents the results of the methodology developed for calculating unsteady gasdynamic processes occurring at the launch of missiles, in the gas-dynamic paths of rocket engines, and in the external regions. The method accounts for the variation in the geometry of the solidpropellant charge in the course of solid-propellant rocket engine operation and in the geometry of the computational domain at the rocket launch. The analysis of the unsteady force impact of the supersonic jet on the launch surface is carried out. It is shown that the maximum force action is located in the vicinity o

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39

Mironov, Daniil, and Aleksey Salnikov. "DYNAMIC BEHAVIOR OF SOLID FUEL ROCKET ENGINE DURING OPERATION (REVIEW)." Perm National Research Polytechnic University Aerospace Engineering Bulletin, no. 70 (2022): 7–17. http://dx.doi.org/10.15593/2224-9982/2022.70.01.

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One of the problems that has been solved for more than 80 years is the dynamic behavior both during the development of a rocket engine and during operation, these are oscillations that occur in the combustion chamber. Gas vibrations and mechanical vibrations of the rocket engine elements can cause vibration loads, which, under certain conditions, leads to resonance phenome-na. This can cause engine failures. An analysis of the behavior of a rocket engine as a dynamic system with an assessment of frequency interactions over the entire time of its operation has not been completely resolved today

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Somov, V. V. "DETERMINATION OF THE TYPE OF A SINGLE-USE GRENADE LAUNCHER BASED ON ITS COMPOSITE PARTS AND FRAGMENTS OF REACTIVE GRENADE FOUND AT THE PLACE OF ACCIDENT." Theory and Practice of Forensic Science and Criminalistics 17 (November 29, 2017): 245–52. http://dx.doi.org/10.32353/khrife.2017.31.

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In carrying out an investigation into the explosion, among others, the investigative version of the use of a single-use reactive grenade launcher is being considered. The most common for criminal explosions are applied grenade launchers RPG-18, RPG-22, RPG-26. Their use is due to a number of such properties as small size and weight, which makes it possible to transfer them covertly, the range of the shot significantly exceeding the range of the hand grenade throw, the high detonating effect of the rocket grenade explosion. The single-use rocket launchers are generally of the same design. Their

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Wolański, P. "RDE research and development in Poland." Shock Waves 31, no. 7 (2021): 623–36. http://dx.doi.org/10.1007/s00193-021-01038-2.

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AbstractA very short survey of research conducted in Poland on the development of the rotating detonation engine (RDE) is presented. Initial studies conducted in cooperation with Japanese partners lead to development of a joint patent on RDE. Then, an intensive basic and applied research was started at the Institute of Heat Engineering of the Warsaw University of Technology. One of the first achievements was the demonstration of performance of the rocket engine with an aerospike nozzle utilizing continuously rotating detonation (CRD), and research was directed into development of a small turbo

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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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Gao, Yuhang, and Jian Zheng. "Noise simulation of wake field of solid rocket motor." Journal of Physics: Conference Series 2364, no. 1 (2022): 012004. http://dx.doi.org/10.1088/1742-6596/2364/1/012004.

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Abstract When the rocket engine works, it will produce high-temperature and high-speed gas, which will be rapidly mixed with the surrounding medium, and will produce huge jet noise. This paper studies jet flow field and sound field of rocket engine using Fluent. The broadband noise simulation shows that the noise distribution is related to the nozzle jet. The sound pressure data of transient FW-H observation points show that the noise frequency distribution is wide. At the same time, the size of the noise will increase with the increase of the inlet pressure, and the influence range will becom

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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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Mosolov, S. V., I. G. Lozino-Lozinskaya, D. M. Pozvonkov, and D. F. Slesarev. "Test Results of a Model Additively Manufactured Oxygen-Methane Combustion Chamber of a Liquid Rocket Engine." Herald of the Bauman Moscow State Technical University. Series Mechanical Engineering, no. 3 (138) (September 2021): 60–79. http://dx.doi.org/10.18698/0236-3941-2021-3-60-79.

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The paper focuses on an experimental unit developed for modeling combustion characteristics in a model oxygen-methane combustion chamber of a liquid rocket engine. The key components of the unit, i.e., the mixing head of the combustion chamber and the regeneratively cooled nozzle, were manufactured using advanced methods of additive manufacturing. The paper emphasizes the specific character of the combustion chamber components made with the use of additive technology and introduces hot-fire test results of the model combustion chamber as part of the experimental unit. The study shows the durab

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Simmons, J., and Richard Branam. "Parametric Study of Dual-Expander Aerospike Nozzle Upper-Stage Rocket Engine." Journal of Spacecraft and Rockets 48, no. 2 (2011): 355–67. http://dx.doi.org/10.2514/1.51534.

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Otsubo, Naoyuki, Kunio Hirata, and Hirotaka Otsu. "659 Enhancement of Rocket Engine Thrust using Variable Area Ratio Nozzle." Proceedings of Conference of Tokai Branch 2008.57 (2008): 439–40. http://dx.doi.org/10.1299/jsmetokai.2008.57.439.

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Trzun, Zvonko, Milan Vrdoljak, and Hrvoje Cajner. "The Effect of Manufacturing Quality on Rocket Precision." Aerospace 8, no. 6 (2021): 160. http://dx.doi.org/10.3390/aerospace8060160.

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The effect of manufacturing quality on rocket impact point dispersion is analyzed. The approach presented here applies to any type of rocket. Here, manufacturing quality is demonstrated for the unguided rocket, and by simulating four typical manufacturing errors: erroneously manufactured warhead, misalignment between the warhead and engine chamber, asymmetrically installed propellant, and error in nozzle manufacturing. A new methodology is proposed, which combines a 3D CAD model of the asymmetrical projectile (due to manufacturing errors) and the improved Six-degrees-of-freedom (6DOF) model of

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Ma, Yarui, Jiwen Cui, Hui Wang, and Jiubin Tan. "Impacts of Micro-Deviations of Aperture on the Characteristics of Collision Atomization Field." Applied Sciences 12, no. 9 (2022): 4685. http://dx.doi.org/10.3390/app12094685.

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As the final flow channel of the liquid rocket engine, the manufacturing of impinging atomization nozzles has become a critical link in the manufacture of impinging atomization components. At present, the high-precision machining of millimeter nozzles in large-scale production is quite difficult, which inevitably leads to the diversity of internal flow field and atomization field parameters. In this investigation, the influence of the diameter deviation of impinging nozzles on the atomization field is analyzed by experiment. The transparent nozzle is installed in a typical colliding atomizer.

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Lin, Binbin, Hongliang Pan, Lei Shi, and Jinying Ye. "Effect of Primary Rocket Jet on Thermodynamic Cycle of RBCC in Ejector Mode." International Journal of Turbo & Jet-Engines 37, no. 1 (2020): 61–70. http://dx.doi.org/10.1515/tjj-2017-0013.

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AbstractThrust augmentation in ejector mode is important to improve engine performance so as to enable more propulsion applications of RBCC. Usually, the internal flow-path is configured mainly for combustion organization in ramjet and scramjet modes, thus the RBCC performance in ejector mode will mainly depend on the primary rocket operating parameters and jet expansion state. Considering such restrictions and requirements on the primary rocket, this paper studies the effects of the primary rocket jet on the thermodynamic cycle performance of ejector mode, in which incoming air is dominated b

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