Relevant bibliographies by topics / Roket simulation

Contents

  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers
  6. Reports

Academic literature on the topic 'Roket simulation'

Author: Grafiati
Published: 28 May 2022
Last updated: 31 July 2025

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Journal articles on the topic "Roket simulation"

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Wibawa, Lasinta Ari Nendra, and Tuswan Tuswan. "Simulasi numerik kekuatan rak roket portabel menggunakan metode elemen hingga." Jurnal Teknik Mesin Indonesia 16, no. 2 (2021): 54–59. https://doi.org/10.36289/jtmi.v16i2.242.

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Makalah ini memaparkan tentang desain rak roket portabel dan analisis tegangan statik menggunakan simulasi numerik. Rangka rak roket portabel didesain untuk mampu membawa 5 unit roket. Pada penelitian ini, beban tiap roket divariasikan 150 kg, 175 kg, 200 kg, dan 225 kg. Material rangka rak roket portabel menggunakan Aluminium 6061-T6. Simulasi numerik dilakukan dengan bantuan perangkat lunak Autodesk Inventor Professional 2017. Hasil analisis tegangan statik menunjukkan tegangan von Mises maksimum rak roket portabel untuk variasi beban 150 kg, 175 kg, 200 kg, dan 225 kg berturut-turut adalah
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Wibawa, Lasinta Ari Nendra, and Tuswan. "Simulasi numerik kekuatan rak roket portabel menggunakan metode elemen hingga." Jurnal Teknik Mesin Indonesia 16, no. 2 (2021): 54–59. https://doi.org/10.5281/zenodo.5910162.

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This paper describes the design of a portable rocket rack and static stress analysis using numerical simulation. The portable rocket rack frame is designed to be able to carry 5 rockets. In this study, the load of each rocket was varied 150 kg, 175 kg, 200 kg, and 225 kg. The frame material for the portable rocket rack uses Aluminum 6061-T6. Numerical simulations were carried out with the help of Autodesk Inventor Professional software. The results of the static stress analysis show that the maximum von Mises stress for portable rocket racks for variations in loads of 150 kg, 175 kg, 200 kg an
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Wibawa, Lasinta Ari Nendra. "Pemodelan umur fatik alat pengangkat roket kapasitas 20 Ton menggunakan Ansys Workbench." Turbulen: Jurnal Teknik Mesin 2, no. 2 (2019): 44–49. https://doi.org/10.36767/turbulen.v2i2.540.

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A rocket lifting device is a tool designed to facilitate the rocket assembly process. The device is mounted on a crane and is equipped with two webbing slings placed at the bottom. The study examines the fatigue life prediction of rocket lifting devices using the finite element method. The design of rocket lifting device using Autodesk Inventor Professional 2017, while finite element analysis using Ansys Workbench. It is subjected to a 20-ton load with a fully-reserved type of loading. The fatigue life prediction using the Gerber mean stress theory. The material for the rocket lifting device i
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Purnami, Ndaru Atmi. "Analisis Bifurkasi Persamaan Longitudinal pada Gerak Roket Tiga Dimensi Tipe RKX-Lapan." AVITEC 3, no. 2 (2021): 149. http://dx.doi.org/10.28989/avitec.v3i2.1060.

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This article discusses about longitudinal equation for the three dimensional rocket motion of RKX-Lapan. The RKX-Lapan’s rocket is guided rocket which was designed using two phases, boosting and sustaining. The rocket has six degrees of freedom movement. The freedom movements consists of three translational motions and three rotational motions which causess unstable rocket movement. Therefore, stable rocket motion system is needed. The rocket motion system is three dimensional of nonlinear equation, thus linearization process of rocket motion equation is requaired. One of this linearization pr
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Wibawa, Lasinta Ari Nendra. "Desain dan Analisis Tegangan Alat Pengangkat Roket Kapasitas 10 Ton Menggunakan Metode Elemen Hingga." Jurnal Energi dan Teknologi Manufaktur (JETM) 2, no. 01 (2019): 23–26. http://dx.doi.org/10.33795/jetm.v2i01.31.

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This study examines the design and stress analysis of a 10 ton capacity rocket lifting device using the finite element method. The material used is Aluminum alloy 7075. Finite element analysis is done numerically by using Autodesk Inventor Professional 2017. software The simulation results show that the structure of the rocket lift has Von Mises stress, deformation, mass, and safety factors of 46.34 MPa, 0.7947 mm, 186.75 kg, and 3.13.
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Nugraha, Alpi Mahisha, and Nurullaeli Nurullaeli. "Blast-off simulation sebagai alternatif media pembelajaran siswa dalam mempelajari mekanika gerak roket berbasis matlab." Navigation Physics : Journal of Physics Education 1, no. 1 (2020): 6–11. http://dx.doi.org/10.30998/npjpe.v1i1.190.

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Blast-off or rocket launcher is a physics phenomena about mechanical of motion specially momentum principal. Unlike other flying objects like blimps and airplanes, blass-off uses the principle of changing momentum as a driving force to able fly in the air. The definition of force is a rate of changing momentum, the definition is illustrated by first-order differential equation which can be solved analytically or numerically. Unfortunately, during class learning, the equation is only used to solve collision problems instead of being used to explain blast-off phenomena which is very interesting
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Wibawa, Lasinta Ari Nendra. "DESAIN DAN ANALISIS TEGANGAN STRUKTUR CRANE KAPASITAS 10 TON MENGGUNAKAN METODE ELEMEN HINGGA." Jurnal Muara Sains, Teknologi, Kedokteran dan Ilmu Kesehatan 4, no. 2 (2020): 201. http://dx.doi.org/10.24912/jmstkik.v4i2.7006.

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Crane is one of the heavy equipment that is widely used in the industry. The crane functions as a tool for lifting heavy loads and moving them from one place to another vertically and horizontally. In the LAPAN Garut office, it is used for the rocket assembly process. The study investigates the design and analysis of von Mises stress of crane structure with a capacity of 10 tons using mild steel material. The investigation was carried out numerically using Autodesk Inventor Professional 2017. The simulation results showed the Crane structure had a von Mises stress, deformation, mass, and safet
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Setiawan, Ahmad Yudi, Nurul Iman Supardi, and Yulia Azatil Ismah. "DESAIN DAN SIMULASI KEGAGALAN STIK MANDRIL ROKET RX-100 PADA PROSES DECORING MENGGUNAKAN SOFTWARE SOLIDWORK." Rekayasa Mekanika 8, no. 2 (2024): 61–68. https://doi.org/10.33369/rekayasamekanika.v8i2.39390.

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The substances used in rocket propellant have the ability to produce molecular gas at very high pressure and temperature during combustion. This material has great energy, and can explode so it is widely used in firearms, explosives and rockets. During the process of making rocket propellant, there is a process, namely the decorating process, which is the process of withdrawing the mandril stick from the propellant mold tube. The mandril stick is a component found at the end of the mandril itself, used as a link between the electric pulley and the mandril which is useful for pulling the mandri
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Kurihara, J., K. I. Oyama, N. Iwagami, and T. Takahashi. "Numerical simulation of 3-D flow around sounding rocket in the lower thermosphere." Annales Geophysicae 24, no. 1 (2006): 89–95. http://dx.doi.org/10.5194/angeo-24-89-2006.

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Abstract. Numerical simulations using the Direct Simulation Monte Carlo (DSMC) method are known to be useful for analyses of aerodynamic effects on in-situ rocket measurements in the lower thermosphere, but the DSMC analysis of a spin modulation caused by an asymmetric flow around the rocket spin axis has been restricted to the two-dimensional and axially symmetric simulations in actual sounding rocket experiments. This study provides a quantitative analysis of the spin modulation using a three-dimensional (3-D) simulation of the asymmetric flow with the DSMC method. Clear spin modulations in
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Salehian, Saman, and Reda R. Mankbadi. "Simulations of rocket launch noise suppression with water injection from impingement pad." International Journal of Aeroacoustics 19, no. 3-5 (2020): 207–39. http://dx.doi.org/10.1177/1475472x20930653.

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The focus of this work is on understanding the effect of water injection from the launch pad on the noise generated during rocket’s lift-off. To simplify the problem, we consider a supersonic jet impinging on a flat plate with water injection from the impingement plate. The Volume of Fluid model is adopted in this work to simulate the two-phase flow. A Hybrid Large Eddy Simulation – Unsteady Reynolds Averaged Simulation approach is employed to model turbulence, wherein Unsteady Reynolds Averaged Simulation is used near the walls, and Large Eddy Simulation is used elsewhere in the computational
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Dissertations / Theses on the topic "Roket simulation"

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Анікушин, Д. Р., М. Ф. Лук’янова та Є. В. Небилиця. "Конструювання та виготовлення моделі ракети для розкидання харчових вакцинованих брикетів для тварин". Thesis, Сумський державний університет, 2018. http://essuir.sumdu.edu.ua/handle/123456789/67494.

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Актуальність теми – залучення гуртків технічної творчості до співпраці та допомоги різним галузям господарства України, зокрема лісовому господарству у вирішенні проблеми проведення вакцинації диких тварин шляхом розробки та виготовлення моделі ракети з корисним вантажем.
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Elfving, Filip. "Simulation of laser welding in sandwich rocket nozzle." Thesis, Karlstads universitet, Avdelningen för maskin- och materialteknik, 2015. http://urn.kb.se/resolve?urn=urn:nbn:se:kau:diva-36830.

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This bachelor thesis has been carried out at GKN Aerospace. GKN is a member of European Space Agency, designing and manufacturing rocket-nozzles for the Ariane rockets. The manufacturing process entails many welds. Weld-simulations have been made to investigate stresses and plastic strains on simplified geometries. Plastic strains have been evaluated parallel and normal to the weld for plate geometries of shell-elements with rectangular cross-section and sandwich-cross-section, using the FEM-program MSC.marc. Results shows that plate width and length have negligible effect on the plastic strai
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Brock, Andrew. "Aerospike Rocket Motor Structural Webbing." DigitalCommons@CalPoly, 2015. https://digitalcommons.calpoly.edu/theses/1355.

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A labscale hybrid rocket motor test stand has been developed for research at Cal Poly. The primary focus of research using this rig has been the development of regenerative cooling techniques using nitrous oxide as coolant and oxidizer, as well as validation of technologies relating to the annular aerospike nozzle. In order to prevent undesirable deflection of the cantilevered spike, a structural stiffening web, referred to as “The Spider,” is proposed. The Spider resembles a three-spoked wheel, with the aerospike held by the inner hub and the chamber walls abutting the outer radius. The Spide
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Gomes, Marc Faria. "Internal ballistics simulation of a solid propellant rocket motor." Master's thesis, Universidade da Beira Interior, 2013. http://hdl.handle.net/10400.6/1980.

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In the design and development of solid propellant rocket motors, the use of numerical tools able to simulate, predict and reconstruct the behaviour of a given motor in all its operative conditions is particularly important in order to decrease all the planning and costs. This study is devoted to present an approach to the numerical simulation of a given SPRM internal ballistics, NAWC no. 13, during the quasi steady state by means of a commercial numerical tool, ANSYS FLUENT. The internal ballistics model constructed in this study is a 2-D axisymmetric model, based on several assumption
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Ruiz, Anthony. "Unsteady Numerical Simulations of Transcritical Turbulent Combustion in Liquid Rocket Engines." Thesis, Toulouse, INPT, 2012. http://www.theses.fr/2012INPT0009/document.

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Ces cinquantes dernières années, la majorité des paramètres de conception des moteurs cryotechniques ont été ajustés en l'absence d'une compréhension détaillée des phénomènes de combustion, en raison des limites des diagnostiques expérimentaux et des capacités de calcul. L'objectif de cette thèse est de réaliser des simulations numériques instationnaires d'écoulements réactifs transcritiques de haute fidélité, pour permettre une meilleure compréhension de la dynamique de flamme dans les moteurs cryotechniques et finalement guider leur amélioration. Dans un premier temps, la thermodynamique gaz
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Modin, Emelie. "Estimating Charging on a Sounding Rocket Experiment Using Plasma Simulation." Thesis, KTH, Skolan för elektroteknik och datavetenskap (EECS), 2020. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-293892.

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The aim of this project is to model current volt-age characteristic curves for different plasma conditions (i.eelectron density, electron temperature, ion temperature andplasma potential) that can be found in active auroras. This isdone by simulating the charging of a FFU with a connectedLangmuir probe in the software SPIS. These I-V curves wereused to determine the plasma properties of the auroras in whichthe sounding rockets SPIDER-1 and SPIDER-2 were launched.Through the simulations it was also studied how the differentparameters effects the I-V curves.The results showed that the plasma SPI
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MacLean, Steven M. "Modeling and Simulation of a Sounding Rocket Active Stabilization System." DigitalCommons@CalPoly, 2017. https://digitalcommons.calpoly.edu/theses/1735.

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The Horizon Simulation Framework is a modeling and simulation framework developed to verify system level requirements. In this thesis, the framework is extended to include the Dynamic position type that existed in the early development phase of the framework. The Dynamic position type is tested through the modeling and simulation of a sounding rocket. An active control system based on linear-quadratic regulator (LQR) control theory is implemented and tested in the simulation to determine the overall effect on altitude. A first order aerodynamics and aeroprediction model are created within the
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Corvatta, Sarah. "Propellant casting process simulation in a small-scale solid rocket booster." Master's thesis, Alma Mater Studiorum - Università di Bologna, 2020.

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Small-scale solid rocket motors have been extremely successful among propulsion industries in the last decades for improving the accuracy of thrust-time prediction in new motors in order to reduce the amount of experimental tests needed for the characterization of their internal ballistics behaviour. It is of common knowledge the fact that the ballistic response of solid rocket motors depends on several factors, among which the manufacturing process stands out. It is the grain that defines the quality of the propellant. Therefore, the thrust performance can be affected by heterogeneity of gra
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Witter, Jonathan Keay. "Modeling for the simulation and control of nuclear reactor rocket systems." Thesis, Massachusetts Institute of Technology, 1993. http://hdl.handle.net/1721.1/12755.

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Samee, Lal Rejish Lal Johnson. "Thermal gas radiation modelling for CFD simulation of rocket thrust chamber." Thesis, KTH, Kraft- och värmeteknologi, 2019. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-261230.

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Methane and oxygen are a promising propellant combination in future rocket propulsion engines mainly due to its advantages like reusability and cost reduction. In order to have a comprehensive understanding of this propellant combination extensive research work is being done. Especially, for reusable rocket engines the thermal calculations become vital as an effective and efficient cooling system is crucial for extending the engine life. The design of cooling channels may significantly be influenced by radiation. Within the framework of this thesis, the gas radiation heat transfer is modelled
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Books on the topic "Roket simulation"

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United States. National Aeronautics and Space Administration., ed. Solid rocket combustion simulator technology (using the hybrid rocket for simulation): Final report. University of Arizona, Engineering Experiment Station, College of Engineering and Mines, 1994.

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Hirshorn, Jessica. Rocket: A simulation on intercultural teamwork. Intercultural Press, 2010.

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Hirshorn, Jessica. Rocket: A simulation on intercultural teamwork. Intercultural Press, 2010.

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Hirshorn, Jessica. Rocket: A simulation on intercultural teamwork. Intercultural Press, 2010.

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Stuart, Thomas A. A study of ignition and simulation circuits for arcjet thrusters. U.S. National Aeronautics and Space Administration, 1991.

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Stuart, Thomas A. A study of ignition and simulation circuits for arcjet thrusters. U.S. National Aeronautics and Space Administration, 1991.

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D, Southwick R., and United States. National Aeronautics and Space Administration., eds. Large liquid rocket engine transient performance simulation system. Pratt & Whitney, 1989.

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D, Southwick R., and United States. National Aeronautics and Space Administration., eds. Large liquid rocket engine transient performance simulation system. United Technologies, Pratt & Whitney ; [Washington, DC, 1989.

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United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., ed. Thermal stratification potential in rocket engine coolant channels. National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992.

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United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., ed. Thermal stratification potential in rocket engine coolant channels. National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992.

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Book chapters on the topic "Roket simulation"

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Traxinger, Christoph, Julian Zips, Christian Stemmer, and Michael Pfitzner. "Numerical Investigation of Injection, Mixing and Combustion in Rocket Engines Under High-Pressure Conditions." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design. Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-53847-7_13.

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Abstract The design and development of future rocket engines severely relies on accurate, efficient and robust numerical tools. Large-Eddy Simulation in combination with high-fidelity thermodynamics and combustion models is a promising candidate for the accurate prediction of the flow field and the investigation and understanding of the on-going processes during mixing and combustion. In the present work, a numerical framework is presented capable of predicting real-gas behavior and nonadiabatic combustion under conditions typically encountered in liquid rocket engines. Results of Large-Eddy S
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Perakis, Nikolaos, and Oskar J. Haidn. "Experimental and Numerical Investigation of CH$$_4$$/O$$_2$$ Rocket Combustors." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design. Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-53847-7_23.

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Abstract The experimental investigation of sub-scale rocket engines gives significant information about the combustion dynamics and wall heat transfer phenomena occurring in full-scale hardware. At the same time, the performed experiments serve as validation test cases for numerical CFD models and for that reason it is vital to obtain accurate experimental data. In the present work, an inverse method is developed able to accurately predict the axial and circumferential heat flux distribution in CH$$_4$$/O$$_2$$ rocket combustors. The obtained profiles are used to deduce information about the i
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Auweter-Kurtz, Monika, Cristian Coclici, Jörg Heiermann, Claus-Dieter Munz, and Christian Sleziona. "Magnetoplasmadynamic Rocket Thruster Simulation." In Hyperbolic Problems: Theory, Numerics, Applications. Birkhäuser Basel, 2001. http://dx.doi.org/10.1007/978-3-0348-8370-2_11.

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Ma, Qingtian, Cungui Yu, Guanglei Li, Cheng Zhou, Shuang Liu, and Junyi Ma. "Simulation Study on Driving Dynamic Characteristics of a Light Rocket Launcher." In Lecture Notes in Mechanical Engineering. Springer Nature Singapore, 2024. http://dx.doi.org/10.1007/978-981-97-1876-4_26.

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AbstractTaking a light rocket launcher as the research object, based on random road excitation and applying the theory of multi-rigid-body system dynamics, the multi-body dynamics model of a light rocket launcher is established, and its driving dynamic characteristics are studied. Considering the load-bearing characteristics of leaf spring and the use of tires, the driving dynamics simulation of light rocket launcher on C-class virtual road is carried out. Considering the vibration impact of the road surface on the rocket launcher, the vibration characteristic results of the rocket launcher ar
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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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Li, Pengcheng, Zhi Zhu, Haidong Chen, and Shipeng Li. "Motion Simulation of Rocket Based on Simulink." In Simulation Tools and Techniques. Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-72795-6_43.

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Kitsche, Wolfgang. "Simulation of Flight Conditions." In Operation of a Cryogenic Rocket Engine. Springer Berlin Heidelberg, 2010. http://dx.doi.org/10.1007/978-3-642-10565-4_6.

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Barfusz, Oliver, Felix Hötte, Stefanie Reese, and Matthias Haupt. "Pseudo-transient 3D Conjugate Heat Transfer Simulation and Lifetime Prediction of a Rocket Combustion Chamber." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design. Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-53847-7_17.

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Abstract Rocket engine nozzle structures typically fail after a few engine cycles due to the extreme thermomechanical loading near the nozzle throat. In order to obtain an accurate lifetime prediction and to increase the lifetime, a detailed understanding of the thermomechanical behavior and the acting loads is indispensable. The first part is devoted to a thermally coupled simulation (conjugate heat transfer) of a fatigue experiment. The simulation contains a thermal FEM model of the fatigue specimen structure, RANS simulations of nine cooling channel flows and a Flamelet-based RANS simulatio
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Shyji, S., N. Asok Kumar, T. Jayachandran, and M. Deepu. "Reacting Flow Simulation of Rocket Nozzles." In Fluid Mechanics and Fluid Power – Contemporary Research. Springer India, 2016. http://dx.doi.org/10.1007/978-81-322-2743-4_142.

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Sun, Yutian, Guoping Wang, Yu Zhang, Youyu Wang, and Lilin Gu. "Airdrop Landing Rocket Dynamics Simulation in Multiple Rocket Storage-Transportation Box." In Lecture Notes in Mechanical Engineering. Springer Nature Singapore, 2024. http://dx.doi.org/10.1007/978-981-99-8048-2_15.

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Conference papers on the topic "Roket simulation"

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Tomporowski, Michal, Olgierd Skromak, Mateusz Sochacki, et al. "Development and Validation of Rocket Motor Simulation Software." In IAF Space Propulsion Symposium, Held at the 75th International Astronautical Congress (IAC 2024). International Astronautical Federation (IAF), 2024. https://doi.org/10.52202/078371-0116.

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Berg, Paige. "Hybrid Rocket Simulation Using CEQUEL for Thermochemistry Calculations." In IAF Space Propulsion Symposium, Held at the 75th International Astronautical Congress (IAC 2024). International Astronautical Federation (IAF), 2024. https://doi.org/10.52202/078371-0184.

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Steppert, Michael, Philipp Epple, and Michael Steber. "Calculation of the Maximal Flight Altitude of the Historical HW2 Rocket Using CFD." In ASME 2018 5th Joint US-European Fluids Engineering Division Summer Meeting. American Society of Mechanical Engineers, 2018. http://dx.doi.org/10.1115/fedsm2018-83379.

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The historical HW2 rocket was a liquid propulsion rocket, designed by the German rocket pioneer Johannes Winkler in 1932. With this rocket, Winkler tried to reach a much higher altitude than with his first model, the HW1, which was the first liquid propulsion rocket in Europe and reached an altitude of 60 meters. Because of technical problems, the HW2 exploded immediately after the launch on October 6th in 1932 [1] [2]. To estimate the performance of this historical liquid propulsion rocket its maximum flight altitude was computed with the use of CFD. The equation of the vertical flight trajec
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Gori, Fabio, Riccardo Pecorari, and Marco Mastrapasqua. "Numerical Simulation of the Coupling Between Vortex Shedding and Acoustic Field in a Solid Propellant Engine." In ASME 2003 International Mechanical Engineering Congress and Exposition. ASMEDC, 2003. http://dx.doi.org/10.1115/imece2003-42680.

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The paper investigates the numerical simulation of vortex shedding in the flow field of solid-propellant rocket motors. This phenomenon, resulting from the strong coupling between shear-layer instability and acoustic waves in the chamber, produces thrust and pressure oscillations. Numerical simulations are performed on the combustion chamber of the Ariane 5 MPS P230 (Solid Rocket Motor) with the commercial code Fluent CFD for conditions corresponding to 89 s of combustion time. The objective of the study is to reproduce the pressure oscillations frequencies and magnitudes, to compare the avail
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de Oliveira Junior, Wilson Luiz, Heloise Assis Fazzolari, Cesar Monzu Freire, and Carlos Alberto de Paiva Carvalho. "6 degrees of freedom simulation of an unguided sounding rocket using Matlab/Simulink." In SAE Brasil 2023 Congress. SAE International, 2024. http://dx.doi.org/10.4271/2023-36-0095.

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<div class="section abstract"><div class="htmlview paragraph">Unguided sounding rockets, also known as sub-orbital rockets, are vehicles that carry scientific experiments and/or sensors to collect data during their trajectory. These rockets lack active control but are capable of traversing the Earth’s atmosphere. It is crucial to thoroughly analyze the flight parameters during the preliminary design phase.</div><div class="htmlview paragraph">The Open Rocket flight simulation software, developed by Sampo Niskanen, is a widely used open-source project. However, it has so
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Rollin, Bertrand, and Malcolm J. Andrews. "Simulation of the Tilted Rig Experiment." In ASME 2012 Fluids Engineering Division Summer Meeting collocated with the ASME 2012 Heat Transfer Summer Conference and the ASME 2012 10th International Conference on Nanochannels, Microchannels, and Minichannels. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/fedsm2012-72320.

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The tilted rig experiment is a derivative of the rocket rig experiment designed to study mixing of fluids by the Rayleigh-Taylor instability. In the latter experiment, a tank containing two fluids of different densities is accelerated downwards between two parallel guide rods by a rocket motor. Misalignment between density and pressure gradients trigger the instability leading turbulence and mixing of the fluids. In the tilted rig experiment, the rocket rig is inclined by few degrees off the vertical before firing, creating a slanted initial perturbation interface. The purpose of the tilted ri
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Burkardt, Leo A., and Leo C. Franciscus. "RAMSCRAM: A Flexible RAMJET/SCRAMJET Engine Simulation Program." In ASME 1990 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1990. http://dx.doi.org/10.1115/90-gt-323.

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With the resurgence of interest in high supersonic and hypersonic flight there is a need to simulate airbreathing engines which may be used in this flight regime. To meet this requirement the RAMSCRAM code was developed. The code calculates one-dimensional flow properties at each component interface and the overall performance of the engine. It uses equilibrium thermodynamics which accounts for dissociation and allows for any fuel or combination of fuels. The program can simulate ramjet, scramjet, rocket, and ducted rocket engines.
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Zyśk, Krystian, Michał Hałoń, Kacper Kaczmarek, et al. "Generation of Artificial Infrared Camera Images for Visual Navigation Simulation." In ESA 12th International Conference on Guidance Navigation and Control and 9th International Conference on Astrodynamics Tools and Techniques. ESA, 2023. http://dx.doi.org/10.5270/esa-gnc-icatt-2023-091.

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Visual navigation is a cornerstone of many modern navigation systems, from computer mice sensors through cars, guided missiles, spacecraft proximity operations and landers. Since 2017 the Students’ Space Association at Warsaw University of Technology has been developing the FOK rocket - a guidance, navigation and control research and development platform. The rocket is aerodynamically controlled using canards and is capable of reaching an apogee of about 1700 metres, a speed of Mach 0.6. It is fully reusable thanks to a parachute recovery system. Currently, the team is developing a vision-base
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de Celis, Raul, Pablo Solano-Lopez, and Luis Cadarso. "A Neural Network for Sensor Hybridization in Rocket Guidance." In 2020 Winter Simulation Conference (WSC). IEEE, 2020. http://dx.doi.org/10.1109/wsc48552.2020.9384129.

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Akcal, Ugur, Burak Yuksek, and Nazim K. Ure. "Modeling and Simulation of Aerobee-150A Sounding Rocket." In AIAA Modeling and Simulation Technologies Conference. American Institute of Aeronautics and Astronautics, 2017. http://dx.doi.org/10.2514/6.2017-1557.

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Reports on the topic "Roket simulation"

1

Resendiz Lira, Pedro, and Gian Delzanno. Rocket 3D CPIC Simulations. Office of Scientific and Technical Information (OSTI), 2025. https://doi.org/10.2172/2568632.

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Candler, Graham V. Simulation of Nonequilibrium Rocket Motor Plumes. Defense Technical Information Center, 2001. http://dx.doi.org/10.21236/ada394241.

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Karagozian, Ann R. Numerical Simulation of Pulse Detonation Rocket-Induced MHD Ejector (PDRIME) Concepts for Advanced Propulsion Systems. Defense Technical Information Center, 2012. http://dx.doi.org/10.21236/ada608775.

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Shkurupiy, V. A., and N. L. Budnyi. Simulation of the dynamics of the stand for measuring the thrust of an electric rocket engine. Baltic State Technical University “VOENMEH” named after D.F.Ustinov, 2022. http://dx.doi.org/10.12731/edn:jmtccs.

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Greenough, J., and M. Wickett. Simulations of the Tilted Rocket Rig Experiment using the K-L RANS Model in the Ares Hydrodynamics Code. Office of Scientific and Technical Information (OSTI), 2012. http://dx.doi.org/10.2172/1057710.

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METHOD OF IMPERFECTION RANDOM FIELD CONSTRUCTION FOR WELDED CYLINDRICAL SHELL BASED ON SMALL SAMPLE. The Hong Kong Institute of Steel Construction, 2025. https://doi.org/10.18057/ijasc.2025.21.1.6.

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The initial geometrical imperfections of thin-walled cylindrical shell structures are important factors that cause the actual bearing capacity of such products to deviate from the theoretical value. In recent years, with the development of digital image measurement technology, it is possible to obtain geometric imperfections(GIs) through the measurement of the real geometric shape of the product, and it is possible to accurately predict the structural load-bearing capacity by considering the imperfections. On this basis, the initial GIs random field can then be considered to carry out thin-wal
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