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Journal articles on the topic 'Roket simulation'

Author: Grafiati

Published: 28 May 2022

Last updated: 31 July 2025

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1

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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9

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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10

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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11

Zuo, Tianhao. "Designs, Simulations, and Products for Rocket Engines." Highlights in Science, Engineering and Technology 48 (May 16, 2023): 186–91. http://dx.doi.org/10.54097/hset.v48i.8330.

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As a matter of fact, rocket engine technology has developed rapidly in the last 100 years, which plays a crucial role for stellar travelling and detection for astrophysics usages. To be specific, different models, designs and simulation computer software had been developed in order to investigate and explore the dynamic process of the engines as well as evaluate the effectiveness and ability of the rocket engines. With this in mind, this paper gives a basic description of the designs, simulations, and products for rocket engines. In detail, this study will include description of four basic des

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12

Riyadl, Ahmad, Robertus Heru TriHarjanto, and Pujo Widodo. "Impact Point Dispersion Prediction for 300 mm R-Han 300 Artillery Rocket." Indonesian Journal of Aerospace 21, no. 1 (2023): 51–64. http://dx.doi.org/10.55981/ijoa.2023.27.

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The effectiveness of artillery rocket in battlefield is the determined by its impact point dispersion, which may occur due to manufacturing and measurement inaccuracy, initial launch perturbations and atmospheric conditions. Therefore, the objective of this study is to establish model that could predict the impact point dispersion of R-Han 300 rocket using Monte Carlo method. Generic rocket of 6 Degree-of-Freedom model was implemented to investigate the impact point. Initially two simulations with 1000 iterations were carried out, first to study the effect of value uncertainty of every paramet

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13

AbdelGawad, Alaa R., and Liang Guozhu. "A Numerical Simulation Study for A Dual Thrust Solid Propellant Rocket Motor Nozzle." Journal of Physics: Conference Series 2235, no. 1 (2022): 012010. http://dx.doi.org/10.1088/1742-6596/2235/1/012010.

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Abstract CFD simulation through the rocket motor nozzle is an important issue as it gives a better understanding of the flow behavior and shows the evolution of the parameters along with the nozzle. CFD simulations using ANSYS FLUENT were conducted to model the flow through an experimental dual thrust solid rocket motor nozzle at two pressure values representing the two pressure levels. A two-dimensional axisymmetric numerical simulation was carried out using a pressure-based solver to solve the governing equation and the standard k-ε model to model the turbulence through the motor nozzle. The

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14

Algimantas, FEDARAVIČIUS, RAČKAUSKAS Saulius, and SURVILA Arvydas. "Numerical Study on Internal Ballistics Characteristics of a Solid Propellant Rocket Motor." Mechanics 25, no. 3 (2019): 187–96. http://dx.doi.org/10.5755/j01.mech.25.3.23742.

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The viability of numerical simulations to design a solid propellant rocket motor, as opposed to static testing, is discussed in this paper. The results demonstrate that an objectively more detailed insight into the processes taking place within the motor in active combustion can be gained by employing computer simulations. The abundance of readily available computing power allows complex simulations to be run on personal desktop computers, thus, saving money by eliminating the need for static testing during the design phase of the motor. The computer simulation results are validated by a compa

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15

Liu, Bo, Zhou Fang, Ping Li, and Chuan Chuan Hao. "Takeoff Analysis and Simulation of a Small Scaled UAV with a Rocket Booster." Advanced Materials Research 267 (June 2011): 674–82. http://dx.doi.org/10.4028/www.scientific.net/amr.267.674.

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This paper analyses the takeoff process of a small scaled UAV (unmanned aerial vehicle) with a single rocket booster. Because the thrust provided by the rocket booster is 10 times as large as the thrust provided by the engines, the effects caused by the boosting rocket on total mass, compound centre of gravity and inertia can not be neglected and are all considered. The inertia of the boosting rocket is calculated by the means of finite element method. Based on the analysis, a nonlinear dynamic model of the UAV is built. Several simulations with different takeoff parameters are conducted to te

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16

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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17

Rugescu, Radu D., Alina Bogoi, and Radu Cirligeanu. "Intricacy of the Transit Manifold Concept Paid-off by Computational Accuracy." Applied Mechanics and Materials 325-326 (June 2013): 142–47. http://dx.doi.org/10.4028/www.scientific.net/amm.325-326.142.

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Despite its intricacy the numerical method applied within the TRANSIT code proved successful in describing discontinuous, non-isentropic flows in rocket engines and solar-gravitational towers for green energy. A number of 0-D approaches are known to render some results in demonstrating the feasibility of the solar tower concept, or in unsteady simulation of transient phases in rocket engines. Computational efficiency is demonstrated by CFD simulation of the starting transients in ADDA solid rocket engines and in the SEATTLER solar mirror tower. The code is exclusively directed to unsteady flow

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18

Lasinta Ari Nendra Wibawa. "Static Stress Analysis and Fatigue Life Prediction of Rocket Motor Test Stand Using Numerical Simulation." R.E.M. (Rekayasa Energi Manufaktur) Jurnal 6, no. 2 (2021): 9–13. http://dx.doi.org/10.21070/r.e.m.v6i2.1533.

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The rocket motor test stand is the equipment used to test the rocket motor's performance under controlled conditions. This equipment is used to measure the thrust of the Dextrose rocket motor and test the ability of components such as the tube, fuel, nozzle and cap of the rocket itself. Before the Dextrose rocket flight test is carried out, it must go through this test. In this study, the variations in the thrust are 2000, 2250, 2500, 2750, and 3000 N. The rocket motor test stands used Aluminum 6063-T6 which has light density and medium strength. Numerical simulations were carried out with Ans

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19

Chen, Si-Yuan, and Qun-Li Xia. "A Multiconstrained Ascent Guidance Method for Solid Rocket-Powered Launch Vehicles." International Journal of Aerospace Engineering 2016 (2016): 1–11. http://dx.doi.org/10.1155/2016/6346742.

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This study proposes a multiconstrained ascent guidance method for a solid rocket-powered launch vehicle, which uses a hypersonic glide vehicle (HGV) as payload and shuts off by fuel exhaustion. First, pseudospectral method is used to analyze the two-stage launch vehicle ascent trajectory with different rocket ignition modes. Then, constraints, such as terminal height, velocity, flight path angle, and angle of attack, are converted into the constraints within height-time profile according to the second-stage rocket flight characteristics. The closed-loop guidance method is inferred by different

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20

Guo, Pengda, Yabin Wang, Donglin Luan, and Shanglin Yang. "Research on Identification of Fire Signal of a Certain Type of Rocket." Journal of Physics: Conference Series 2891, no. 15 (2024): 152012. https://doi.org/10.1088/1742-6596/2891/15/152012.

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Abstract To assess the contradiction between ballistic safety and ignition reliability in traditional rocket projectile inertial initiation mechanisms, this study focuses on the recognition of graze bursting ignition signals for a specific type of rocket projectile. By utilizing a finite element numerical simulation method to model the small-angle impact of the rocket projectile on a target, the overload information can be extracted from the ignition mechanism. The accuracy of the simulation model can be validated by comparing it with data obtained from live ammunition tests. Through a series

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21

Wasilczuk, Filip, Marcin Kurowski, and Paweł Flaszyński. "Test Section Design for Measuring the Drag Coefficient of a Suborbital Rocket Model at Ma 2.45." Transactions on Aerospace Research 2024, no. 3 (2024): 86–100. http://dx.doi.org/10.2478/tar-2024-0018.

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ABSTRACT This study investigates the drag coefficient of three models of suborbital rockets with different nosecones. A test section allowing for force measurement of a 1:50 scale rocket model was designed with the aid of numerical simulations. The velocity obtained in the wind tunnel corresponds with a Mach number of 2.45. RANS simulations were used in verifying operating parameters, as well as testing the support configurations for connecting the model with the bottom wall of the tunnel section. Pressure distribution measurements on the top and bottom walls of the wind tunnel matched simulat

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22

Brask, S. M., S. Marholm, F. Di Mare, et al. "Electron–neutral collisions effects on Langmuir probe in the lower E-region ionosphere." Physics of Plasmas 29, no. 3 (2022): 033511. http://dx.doi.org/10.1063/5.0079761.

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We present the first set of particle-in-cell simulations including Monte Carlo collisions between charged and neutral particles used to simulate a cylindrical Langmuir probe in the electron saturation regime with a collisional electron sheath. We use a setup focused on the E-region ionosphere; however, the results of these simulations are analyzed in a general sense using dimensionless values. We find that the electron currents get enhanced as the collision frequency for electrons increases and the values of [Formula: see text], where λe is the electron mean free path and λD is the electron De

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23

Busygin, A. S., and А. V. Shumov. "MULTISTAGE ROCKET FLIGHT SIMULATION." Issues of radio electronics, no. 3 (March 20, 2019): 105–7. http://dx.doi.org/10.21778/2218-5453-2019-3-105-107.

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The paper considers a method for simulating the flight of a multistage rocket in Matlab using Simulink software for control and guidance. The model takes into account the anisotropy of the gravity of the Earth, changes in the pressure and density of the atmosphere, piecewise continuous change of the center of mass and the moment of inertia of the rocket during the flight. Also, the proposed model allows you to work out various targeting options using both onboard and ground‑based information tools, to load information from the ground‑based radar, with imitation of «non‑ideality» of incoming ta

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24

Wang, Chen, Jinbao Chen, Shan Jia, and Heng Chen. "Parameterized Design and Dynamic Analysis of a Reusable Launch Vehicle Landing System with Semi-Active Control." Symmetry 12, no. 9 (2020): 1572. http://dx.doi.org/10.3390/sym12091572.

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Reusable launch vehicles (RLVs) are a solution for effective and economic transportation in future aerospace exploration. However, RLVs are limited to being used under simple landing conditions (small landing velocity and angle) due to their poor adaptability and the high rocket acceleration of current landing systems. In this paper, an adaptive RLV landing system with semi-active control is proposed. The proposed landing system can adjust the damping forces of primary strut dampers through semi-actively controlled currents in accordance with practical landing conditions. A landing dynamic mod

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TANG, Jingyuan, Yongjie GOU, Yangyang MA, and Binfeng PAN. "Rocket landing guidance based on second-order Picard-Chebyshev-Newton type algorithm." Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University 42, no. 1 (2024): 98–107. http://dx.doi.org/10.1051/jnwpu/20244210098.

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This paper proposes a rocket substage vertical landing guidance method based on the second-order Picard-Chebyshev-Newton type algorithm. Firstly, the continuous-time dynamic equation is discretized based on the natural second-order Picard iteration formulation and the Chebyshev polynomial. Secondly, the landing problem that considers terminal constraints is transformed into a nonlinear least-squares problem with respect to the terminal constraint function and solved with the Gauss-Newton method. In addition, the projection method is introduced to the iteration process of the Gauss-Newton metho

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Su, Qingdong, Bailin Zha, Jinjin Wang, et al. "Simulation and Application of a New Multiphase Flow Ablation Test System for Thermal Protection Materials Based on Liquid Rocket Engine." Aerospace 9, no. 11 (2022): 701. http://dx.doi.org/10.3390/aerospace9110701.

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Internal flow field ablation is an important issue in thermal protection materials for rocket engines and hypersonic vehicles. In this paper, a new multiphase flow ablation test system, with an Al2O3 particle delivery device based on an oxygen-kerosene liquid rocket engine, is designed and manufactured. A general variable-precision modular system simulation method is proposed to analyze the dynamic characteristics of the system. In addition, a unique internal flow field ablation test was performed on the 4D C/C composite simulating the working conditions of the SRM. The results show that the s

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27

Воронин, С. Т. "Численное моделирование сверхзвукового потока газов в коническом сопле с локальным подогревом плазмой". Письма в журнал технической физики 48, № 10 (2022): 40. http://dx.doi.org/10.21883/pjtf.2022.10.52556.19175.

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The results of calculations and experiments on plasma heating of the supersonic flow of gases in the conical nozzle by an external high-frequency inductor are given. The simulation was carried out in order to increase the specific impulse and efficiency of the liquid rocket engine. The results of numerical simulations are qualitatively consistent with the experiments conducted in a water-cooled quartz reactor.

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Zhao, Tuan, Hongzhi Yao, Xiangfei Ji, and Jiao Li. "Simulation Analysis on Shielding Effectiveness of Rocket Projectile." Journal of Physics: Conference Series 2478, no. 3 (2023): 032025. http://dx.doi.org/10.1088/1742-6596/2478/3/032025.

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Abstract In order to analyze the shielding effectiveness of the rocket projectile in the electromagnetic environment, the electromagnetic simulation model of the rocket motor was established by using the ANSYS HFSS electromagnetic simulation software, the shielding effectiveness of the rocket projectile motor was calculated, and the influence of the structural charactetristic parameters of the rocket projectile motor on the shielding effectiveness was analyzed, the distribution law of shielding effectiveness with frequency parameters and position parameters were obtained, which provided suppor

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Singh, Sunayna, Martin Sippel, and Sven Stappert. "Full-scale simulations of ‘In-Air Capturing’ return mode for winged reusable launch vehicles." Journal of Physics: Conference Series 2526, no. 1 (2023): 012114. http://dx.doi.org/10.1088/1742-6596/2526/1/012114.

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Abstract The recent success of reusable launchers has become a driving force for sustainable launch technologies. An innovative approach proposed by DLR, involves winged rocket stages captured mid air and towed back to the launch site by an aircraft. This recovery concept known as ‘In-Air Capturing (IAC)’, shows potential for substantial cost reduction, when compared to existing return modes. In the light of the Horizon 2020 project FALCon, full-scale simulations and sub-scale flight testing were carried out for further development of the technology. The paper summarizes the full-scale studies

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Tao, Ru Yi, Yun Liu, Peng Li, and Ming Huang. "Micro-Rocket System of Small Object Release Process Simulation." Advanced Materials Research 875-877 (February 2014): 994–97. http://dx.doi.org/10.4028/www.scientific.net/amr.875-877.994.

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To study the release process of micro-rocket system of small object, a novel model and numerical simulation is proposed. The structure and the work principle of the micro-rocket release system are explored. The release model is constructed using solid rocket theory, and including gap between objects and project canal. The theoretical methods are presented for the constructional design of micro-rocket releasing system of small object.

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Citarella, Roberto, Michele Ferraiuolo, Michele Perrella, and Venanzio Giannella. "Thermostructural Numerical Analysis of the Thrust Chamber of a Liquid Propellant Rocket Engine." Materials 15, no. 15 (2022): 5427. http://dx.doi.org/10.3390/ma15155427.

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The numerical simulation of rocket engine thrust chambers is very challenging as several damaging phenomena, such as plasticity, low-cycle-fatigue (LCF) and creep occur during its service life. The possibility of simulating the thermostructural behavior of the engine, by means of non-linear finite element analyses, allows the engineers to guarantee the structural safety of the structure. This document reports the numerical simulations developed with the aim of predicting the thermostructural behaviour and the service life of the thrust chamber of a liquid-propellant rocket engine. The work rep

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Viscor, Tor, Hikaru Isochi, Naoto Adachi, and Harunori Nagata. "Burn Time Correction of Start-Up Transients for CAMUI Type Hybrid Rocket Engine." Aerospace 8, no. 12 (2021): 385. http://dx.doi.org/10.3390/aerospace8120385.

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Burn time errors caused by various start-up transient effects have a significant influence on the regression modelling of hybrid rockets. Their influence is especially pronounced in the simulation model of the Cascaded Multi Impinging Jet (CAMUI) hybrid rocket engine. This paper analyses these transient burn time errors and their effect on the regression simulations for short burn time engines. To address these errors, the equivalent burn time is introduced and is defined as the time the engine would burn if it were burning at its steady-state level throughout the burn time to achieve the meas

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Jian, Shen, Han Feng, Chen Fang, Zhou Qiao, and Pavel M. Trivailo. "Dynamics and modeling of rocket towed net system." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 232, no. 1 (2016): 185–97. http://dx.doi.org/10.1177/0954410016673090.

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In order to study the complex dynamical behavior of the rocket towed net system, a three-dimensional model consisting of a rigid rocket model and a lumped mass net model is built based on the aerodynamics theory. The rocket towed net system model is solved by the fourth-order Runge–Kutta method in simulation. Simulation and experimental results show that the accuracies of rocket towed net system expanding distance were about 90% of the system length. With the comparison of simulation, a rigid multibody model and experimental results in rocket mass center trajectory, velocity, and pitch angle,

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Dziczkaniec, Rafał, Tomasz Noga, Krzysztof Matysek, and Piotr Umiński. "A Study of the Trajectory of an Aerobalistic Rocket Based on the 9m723 Missile." Safety & Defense 10, no. 2 (2024): 8–22. https://doi.org/10.37105/sd.231.

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This article presents the modeling of and research on the flight trajectory of an aeroballistic missile using MATLAB/Simulink software. This article adopts the 9M723 rocket as a focus of research because the Iskander system missile is an ideal example of an SRBM (Short-range ballistic missile), which, due to the shape of its flight trajectory, is quite a challenge for the defending side. The research was carried out by performing a series of computer simulations of the 9M723 rocket model in six degrees of freedom, where flight parameters were examined for the boost, mid-course and terminal pha

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Lastomo, Dwi, Herlambang Setiadi, and Muhammad Ruswandi Djalal. "Optimization pitch angle controller of rocket system using improved differential evolution algorithm." International Journal of Advances in Intelligent Informatics 3, no. 1 (2017): 27. http://dx.doi.org/10.26555/ijain.v3i1.83.

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Pitch angle of rocket system is the important parts of the rocket. This part corresponds to the movement of the rocket system. Rocket system is fell into multi-input and multi-output (MIMO) system. The most challenge factor in MIMO system is designing the controller, if the design is not appropriate, it may lead to the unstable condition. Hence, appropriate and robust control design is inevitable. This paper introduces PID controller as pitch angle control of rocket system. Furthermore, PID controller parameter is optimized using improved differential evolution algorithm (IDEA). To analyze the

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Siddiq, Muhammad Kashif, Jian Cheng Fang, and Wen Bo Yu. "SDRE Based Integrated Roll, Yaw and Pitch Controller Design for 122mm Artillery Rocket." Applied Mechanics and Materials 415 (September 2013): 200–208. http://dx.doi.org/10.4028/www.scientific.net/amm.415.200.

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State-dependent Riccati equation (SDRE) based controller design is an emerging trend in real world applications. This paper describes the design of an integrated roll, yaw and pitch attitude controller for a fin stabilized and canard controlled 122mm artillery rocket using SDRE technique. The rocket configuration considered is with front canards and foldable straight tail fins, and is given initial spin at the time of launch. Tails fins are deployed immediately after launch and offer high roll damping moment thereby reducing the spin rate to zero within six seconds of flight. The canards are t

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Voronin S. T. "Numerical simulation of supersonic gas flow in a conical nozzle with local plasma heating." Technical Physics Letters 48, no. 5 (2022): 63. http://dx.doi.org/10.21883/tpl.2022.05.53485.19175.

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The results of calculations and experiments on plasma heating of the supersonic flow of gases in the conical nozzle by an external high-frequency inductor are given. The simulation was carried out in order to increase the specific impulse and efficiency of the liquid rocket engine. The results of numerical simulations are qualitatively consistent with the experiments conducted in a water-cooled quartz reactor. Keywords: Low-temperature plasma, specific high-frequency power, skin layer.

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Adzan, Muhammad Ichsanul, Yayat Ruyat, and Heri Budi Wibowo. "Thrust Analysis of the RX-70 Rocket Using Burnsim Simulation with Variations in RDX Content and Grain Geometry." Jurnal Pijar Mipa 20, no. 4 (2025): 762–70. https://doi.org/10.29303/jpm.v20i4.9194.

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Indonesia, as the largest archipelagic country in the world with a strategic geographical position, has an urgent need to develop a reliable defence system, one of which is through rocket technology. The RX-70 rocket is one of the national rocket development programs designed to strengthen domestic defence capabilities. This study aims to analyze the thrust performance of the RX-70 rocket motor with a numerical simulation approach using BurnSim software. The main focus of this study is to evaluate the effect of variations in Cyclotrimethylenetrinitramine (RDX) content and star grain geometry c

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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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Li, Yilin. "Designing and Modeling of Saturn V base on Juno New Origins." Transactions on Computer Science and Intelligent Systems Research 5 (August 12, 2024): 672–77. http://dx.doi.org/10.62051/jypx3f91.

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Saturn V, utilized by NASA during the 1960s Apollo program, stands as a pivotal heavy-lift rocket in space exploration history. Its design and fabrication mark a significant chapter in spaceflight history. Through an amalgamation of Saturn V's authentic design parameters and Juno New Origins' sophisticated modeling tools, we proficiently resurrected this emblematic rocket system. This investigation delves into design methodology, model validation, and the advantages of Juno New Origins for Saturn V spacecraft modeling, offering a fresh vantage point for spacecraft design and simulation researc

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Dyrud, L., B. Krane, M. Oppenheim, H. L. Pécseli, J. Trulsen, and A. W. Wernik. "Structure functions and intermittency in ionospheric plasma turbulence." Nonlinear Processes in Geophysics 15, no. 6 (2008): 847–62. http://dx.doi.org/10.5194/npg-15-847-2008.

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Abstract. Low frequency electrostatic turbulence in the ionospheric E-region is studied by means of numerical and experimental methods. We use the structure functions of the electrostatic potential as a diagnostics of the fluctuations. We demonstrate the inherently intermittent nature of the low level turbulence in the collisional ionospheric plasma by using results for the space-time varying electrostatic potential from two dimensional numerical simulations. An instrumented rocket can not directly detect the one-point potential variation, and most measurements rely on records of potential dif

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Srinivas, G., and Srinivasa Rao Potti. "Numerical Simulation of Rocket Nozzle." Advanced Materials Research 984-985 (July 2014): 1210–13. http://dx.doi.org/10.4028/www.scientific.net/amr.984-985.1210.

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The vent or opening is called nozzle. The objectives are to measure the flow rates and pressure distributions within the converging and diverging nozzle under different exit and inlet pressure ratios. Analytic results will be used to contrast the measurements for the pressure and normal shock locations. In this paper computational Fluid Dynamics (CFD) Analysis of various performance parameters like static pressure, the Mach number, intensity of turbulence, the area ratio are studied in detail for a rocket nozzle from Inlet to exit by using Ansys Fluent software. From the public literature surv

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Pegov, V. I., I. Yu Moshkin, E. S. Merkulov, and A. D. Cheshko. "Numerical simulation of hydrodynamic loads on starting rocket and submarine." Journal of «Almaz – Antey» Air and Space Defence Corporation, no. 3 (September 30, 2016): 30–35. http://dx.doi.org/10.38013/2542-0542-2016-3-30-35.

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The paper proposes a solution to the problem of determining hydrodynamic loads on the rocket and submarine using numerical simulation based on the control volume method in a three-dimensional non-stationary problem statement. We took into consideration contours, rocket and submarine velocity, medium two-phase state (gas liquid), viscosity and gravity. We calculated the start effects on the rocket and submarine for two cases: when the submarine is moving and stationary. The reliability and accuracy of the calculations were confirmed by comparing them with the results of the tests on a model in

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Zivkovic, Sasa, Momcilo Milinovic, Predrag Stefanovic, Pavle Pavlovic, and Nikola Gligorijevic. "Experimental and simulation testing of thermal loading in the jet tabs of a thrust vector control system." Thermal Science 20, suppl. 1 (2016): 275–86. http://dx.doi.org/10.2298/tsci150914208z.

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The paper discusses the temperature changes in mechanical jet tabs in a system of rocket motor thrust vector control, estimated by the simulation and experimental tests methodology. The heat transfer calculation is based on complex computational fluid dynamics simulations of both the nozzle and external tab flows, as the comprehensive integral flow zones with high flow parameters gradients. Due to a complexity of the model for flow calculations, the experimental estimation of the calculated results is carried out. The temperature is measured by jet tabs embedded thermocouples, and conducted th

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Longmire, Nelson P., and Daniel T. Banuti. "Limits of Fluid Modeling for High Pressure Flow Simulations." Aerospace 9, no. 11 (2022): 643. http://dx.doi.org/10.3390/aerospace9110643.

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Flows in liquid propellant rocket engines (LRE) are characterized by high pressures and extreme temperature ranges, resulting in complex fluid behavior that requires elaborate thermo-physical models. In particular, cubic equations of state and dedicated models for transport properties are firmly established for LRE simulations as a way to account for the non-idealities of the high-pressure fluids. In this paper, we review some shortcomings of the current modeling paradigm. We build on the common study of property errors, as a direct measure of the density or heat capacity accuracy, to evaluate

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Yue, Chun Guo, Xin Long Chang, Shu Jun Yang, and You Hong Zhang. "Numerical Simulation of Interior Flow Field of a Variable Thrust Rocket Engine." Advanced Materials Research 186 (January 2011): 215–19. http://dx.doi.org/10.4028/www.scientific.net/amr.186.215.

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With the support of powerful calculation ability of computer and Fluent of CFD software, integrative simulation research of the variable thrust liquid propellant rocket engine was developed. Numerical simulation of interior flow field of a variable thrust rocket engine with flux-oriented injector was done. The distributions of pressure, temperature, molar fraction of product and flow mach numbers were attained. By the contrast of the calculation results, the effects of structure parameters and working condition etc. on total whole performance of variable thrust rocket engine were analyzed. The

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Costa, B. P., A. C. Goulart, G. L. Yamato, et al. "SIMULATION AND PERFORMANCE ANALYSIS OF A HYBRID ROCKET ENGINE WITH SELF-PRESSURIZING OXIDIZER." Revista de Engenharia Térmica 21, no. 2 (2022): 37. http://dx.doi.org/10.5380/reterm.v21i2.87920.

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There are many challenges to simulate and design a hybrid engine, such as the dimensioning of the feed lines and tanks, propulsive performance calculations, and simulations of the expected behavior in the combustion chamber and the oxidizer tank during the engine operation. In this work, methods are assembled in a concise and complete analysis of the Gluon hybrid rocket engine, developed by PION Labs, with a blowdown pressurization system, using N2O as oxidizer and a paraffin-based fuel. For that, a study will be presented on the peculiar characteristics of the oxidizer and its behavior during

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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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Yunpeng, Du, Li Zhaoyong, Wang Ziqiang, et al. "Optimization design of cartridge adapter based on launch dynamics." Journal of Physics: Conference Series 2478, no. 12 (2023): 122077. http://dx.doi.org/10.1088/1742-6596/2478/12/122077.

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Abstract To study the influence of the cartridge adapter on the initial disturbance of the rocket shell launch, the dynamic simulation model of the interaction between the cartridge and the storage and distribution box during the rocket shell launch is established. With the aim of reducing the initial disturbance, the structure optimization and design parameters of the cartridge adapter are obtained fro m the dynamics simulation optimization analysis of rocket shell launch. The optimization results suggest that the number and layout of the cartridge adapter can greatly reduce the initial distu

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Zhong, Kun, Zhong Hua Du, Liang Zhou, and Li Li Song. "Numerical Simulation of Intercepting Efficiency on Airbag Active Protection System." Advanced Materials Research 156-157 (October 2010): 360–66. http://dx.doi.org/10.4028/www.scientific.net/amr.156-157.360.

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Based on the advantages and disadvantages of existing active protection system, this paper proposes a new type of airbag active protection system. The components and working process of the system is introduced. Then taking the physical process of airbag active protection system against a rocket projectile as an example, a 3D finite element model (FEM) of airbag and rocket projectile is set up. With the assistance of the software LS-DYNA3D, through performing the simulation when the rocket projectile touched the airbag with an angle 30° from the normal interface, the intercepting efficiency is

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