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Статті в журналах з теми "Rockets (Ordnance) Mathematical models"
Berdnyk, M. "Mathematical model and method of solving the generalized Dirichle problem of heat exchange of a cut count." System technologies 1, no. 138 (March 30, 2022): 134–42. http://dx.doi.org/10.34185/1562-9945-1-138-2022-13.
Повний текст джерелаPylypenko, O. V., O. O. Prokopchuk, S. I. Dolgopolov, O. D. Nikolayev, N. V. Khoriak, V. Yu Pysarenko, I. D. Bashliy, and S. V. Polskykh. "Mathematical modelling of start-up transients at clustered propulsion system with POGO-suppressors for CYCLON-4M launch vehicle." Kosmìčna nauka ì tehnologìâ 27, no. 6 (2021): 3–15. http://dx.doi.org/10.15407/knit2021.06.003.
Повний текст джерелаМинай, Александр Николаевич, Игорь Викторович Седых та Ирина Юрьевна Кузьмич. "ПРИМЕНЕНИЕ МЕТОДОВ ЧИСЛЕННОГО МОДЕЛИРОВАНИЯ ПРИ ЭКCПЕРИМЕНТАЛЬНОЙ ОТРАБОТКЕ ЗАБОРНЫХ УСТРОЙСТВ ЦЕНТРАЛЬНОГО ТИПА". Aerospace technic and technology, № 6 (24 грудня 2019): 33–42. http://dx.doi.org/10.32620/aktt.2019.6.05.
Повний текст джерелаФролов, Виктор Петрович, Галина Ивановна Сокол та Владислав Юрьевич Котлов. "ВОЛНОВОЙ ПАРАМЕТР КАК КРИТЕРИЙ В ОСНОВЕ МЕТОДА ИССЛЕДОВАНИЯ АКУСТИЧЕСКИХ ИСТОЧНИКОВ ПРИ СТАРТЕ РАКЕТ". Aerospace technic and technology, № 3 (27 червня 2018): 4–12. http://dx.doi.org/10.32620/aktt.2018.3.01.
Повний текст джерелаLoskutov, A. I., V. I. Kondratyuk, E. A. Ryakhova, and A. V. Stolyarov. "Model of auxiliary identification and technical diagnosis of space vehicles, rockets-rockets, running blocks with the function of error recognition of typical solutions." Nonlinear World, 2021. http://dx.doi.org/10.18127/j20700970-202101-05.
Повний текст джерелаZolla, Paolo Maria, Mario Tindaro Migliorino, Daniele Bianchi, Francesco Nasuti, Rocco Carmine Pellegrini, and Enrico Cavallini. "A Computational Tool for the Design of Hybrid Rockets." Aerotecnica Missili & Spazio, August 24, 2021. http://dx.doi.org/10.1007/s42496-021-00085-3.
Повний текст джерела"The use of models with improved characteristics in the missile control system." Automation. Modern Techologies, 2020. http://dx.doi.org/10.36652/0869-4931-2020-74-12-563-568.
Повний текст джерелаNowak, Piotr R., Tomasz Gajewski, Piotr Peksa, and Piotr W. Sielicki. "Experimental verification of different analytical approaches for estimating underwater explosives." International Journal of Protective Structures, September 25, 2022, 204141962211205. http://dx.doi.org/10.1177/20414196221120511.
Повний текст джерелаДисертації з теми "Rockets (Ordnance) Mathematical models"
Baig, Saood Saeed. "A simple moving boundary technique and its application to supersonic inlet starting /." Thesis, McGill University, 2008. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=112555.
Повний текст джерелаThe developed technique is rather general and can be used with virtually any finite-volume or finite-difference scheme, since the modifications of the schemes themselves are not required. In the present study the proposed technique has been incorporated into a one-dimensional non-adaptive Euler code and a two-dimensional locally adaptive unstructured Euler code.
It is shown that the new approach is conservative with the order of approximation near the moving boundaries. To reduce the conservation error, it is beneficial to use the method in conjunction with local grid adaptation.
The technique is verified for a number of one and two dimensional test cases with analytical solutions. It is applied to the problem of supersonic inlet starting via variable geometry approach. At first, a classical starting technique of changing exit area by a moving wedge is numerically simulated. Then, the feasibility of some novel ideas such as a collapsing frontal body and "tractor-rocket" are explored.
Anthoine, Jérôme P. L. R. "Experimental and numerical study of aeroacoustic phenomena in large solid propellant boosters." Doctoral thesis, Universite Libre de Bruxelles, 2000. http://hdl.handle.net/2013/ULB-DIPOT:oai:dipot.ulb.ac.be:2013/211712.
Повний текст джерелаLarge SRM are composed of a submerged nozzle and segmented propellant grains separated by inhibitors. During propellant combustion, a cavity appears around the nozzle. Vortical flow structures may be formed from the inhibitor (Obstacle Vortex Shedding OVS) or from natural instability of the radial flow resulting from the propellant combustion (Surface Vortex Shedding SVS). Such hydrodynamic manifestations drive pressure oscillations in the confined flow established in the motor. When the vortex shedding frequency synchronizes acoustic modes of the motor chamber, resonance may occur and sound pressure can be amplified by vortex nozzle interaction.
Original analytical models, in particular based on vortex sound theory, point out the parameters controlling the flow-acoustic coupling and the effect of the nozzle design on sound production. They allow the appropriate definition of experimental tests.
The experiments are conducted on axisymmetric cold flow models respecting the Mach number similarity with the Ariane 5 SRM. The test section includes only one inhibitor and a submerged nozzle. The flow is either created by an axial air injection at the forward end or by a radial injection uniformly distributed along chamber porous walls. The internal Mach number can be varied continuously by means of a movable needle placed in the nozzle throat. Acoustic pressure measurements are taken by means of PCB piezoelectric transducers. A particle image velocimetry technique (PIV) is used to analyse the effect of the acoustic resonance on the mean flow field and vortex properties. An active control loop is exploited to obtain resonant and non resonant conditions for the same operating point.
Finally, numerical simulations are performed using a time dependent Navier Stokes solver. The analysis of the unsteady simulations provides pressure spectra, sequence of vorticity fields and average flow field. Comparison to experimental data is conducted.
The OVS and SVS instabilities are identified. The inhibitor parameters, the chamber Mach number and length, and the nozzle geometry are varied to analyse their effect on the flow acoustic coupling.
The conclusions state that flow acoustic coupling is mainly observed for nozzles including cavity. The nozzle geometry has an effect on the pressure oscillations through a coupling between the acoustic fluctuations induced by the cavity volume and the vortices travelling in front of the cavity entrance. When resonance occurs, the sound pressure level increases linearly with the chamber Mach number, the frequency and the cavity volume. In absence of cavity, the pressure fluctuations are damped.
Doctorat en sciences appliquées
info:eu-repo/semantics/nonPublished
Книги з теми "Rockets (Ordnance) Mathematical models"
Ye ti huo jian fa dong ji ran shao guo cheng jian mo yu shu zhi fang zhen: Modeling and numerical simulations of internal combustion process of liquid rocket engines. Beijing: Guo fang gong ye chu ban she, 2012.
Знайти повний текст джерелаZhijun, Yao, ed. Huo pao shi yan yu dong li xue xing neng she ji ji suan xin fang fa. Beijing: Guo fang gong ye chu ban she, 2013.
Знайти повний текст джерелаRocker, M. Modeling on nonacoustic combustion instability in simulations of hybrid motor tests. Marshall Space Flight Center, Ala: National Aeronautics and Space Administration, Marshall Space Flight Center, 2000.
Знайти повний текст джерелаYe ti huo jian fa dong ji ran shao dong li xue mo xing yu shu zhi ji suan. Beijing Shi: Guo fang gong ye chu ban she, 2011.
Знайти повний текст джерелаBackyard rockets: Learn to make and launch rockets, missiles, cannons and other projectiles. 2013.
Знайти повний текст джерелаKratt, Aaron T. Numerical simulation of the ejector flowfield in a ram rocket engine with multiple rockets. 2004.
Знайти повний текст джерела