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Artículos de revistas sobre el tema "Solid Rocket Motors"

Autor: Grafiati

Publicado: 4 de junio de 2021

Última modificación: 25 de julio de 2025

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1

Abdelraouf, A. M., O. K. Mahmoud, and M. A. Al-Sanabawy. "Thrust termination of solid rocket motor." Journal of Physics: Conference Series 2299, no. 1 (2022): 012018. http://dx.doi.org/10.1088/1742-6596/2299/1/012018.

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Abstract Rocket motors are engines that create the necessary thrust for the rocket motion. There are different types of rocket motors based on the propellant state, such as solid propellant rocket motors, liquid propellant rocket motors, and hybrid propellant rocket motors. One of the biggest disadvantages of solid propellant rocket motors, in comparison to liquid and hybrid propellant rocket motors, is that they are extremely difficult to extinguish, necessitating the use of specific devices. This paper reviews various ways for thrust termination such as fluid injection, rapid increase in thr

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2

Hu, Xiaomei, Yuting Hua, Jiahong Weng, Xianshu Teng, and Mingnan Zhang. "Performance prediction method of solid rocket motor based on the ground test." Journal of Physics: Conference Series 2816, no. 1 (2024): 012053. http://dx.doi.org/10.1088/1742-6596/2816/1/012053.

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Abstract Solid rocket motor (SRM) is a core component of rockets. Considering the high cost of solid rocket motors and the high demand for transportation and storage, there is an urgent need to predict the performance of solid rocket motors before the ground ignition test to lower the cost of tests. Using data mining technology to predict various parameters of rocket motors with historical data has become a new development direction. In order to improve the data fitting effect and prediction accuracy, a novel prediction model was proposed, which tries to combine the Whale Optimization Algorith

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3

Schonberg, W. P. "Energy partitioning in high speed impact of analogue solid rocket motors." Aeronautical Journal 103, no. 1029 (1999): 519–28. http://dx.doi.org/10.1017/s0001924000064277.

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Abstract Modelling the response of solid rocket motors to bullet and fragment impacts is a high priority among the military services from standpoints of both safety and mission effectiveness. Considerable effort is being devoted to characterising the bullet and fragment vulnerability of solid rocket motors, and to developing solid rocket motor case technologies for preventing or lessening the violent responses of rocket motors to these impact loadings. Because full-scale tests are costly, fast-running analytical methods are required to characterise the response of solid rocket motors to ballis

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4

Kessler, D. J. "Explorer 46 Meteoroid Bumper Experiment: Earth Orbital Debris Interpretation." International Astronomical Union Colloquium 85 (1985): 97. http://dx.doi.org/10.1017/s0252921100084414.

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AbstractThe Meteoroid Bumper Experiment on Explorer 46 (launched 1972) was placed in Earth orbit to evaluate the effectiveness of using double-wall structures against meteoroids. This paper re-examines the data from this experiment. Certain sets of sensors were found to be penetrated much more frequently than other sets. The most plausible explanation is that nearly all of the penetrations were from an Earth orbiting population of particulates. In addition, because a large percentage of the penetrations occured soon after solid rocket motors were fired in space, the particulates are most likel

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5

Said, A., A. Maraden, T. M. Elhedery, A. M. abd Elall, and S. Elbasuney. "Propulsion theoretical and experimental analysis of composite propellants motors." Journal of Physics: Conference Series 2616, no. 1 (2023): 012057. http://dx.doi.org/10.1088/1742-6596/2616/1/012057.

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Abstract Rockets have revolutionized space technology and human space exploration. Most rockets and missiles are both propelled by rocket motors that use composite solid propellants. The ICT code and the NSAS CEA code are two programs that can be used to forecast theoretical propulsion parameters for composite solid rocket propellant. Rocket propellant performance is governed by a specific impulse factor, which is calculated theoretical and experiment. In this paper, the theoretical specific impulse for different composite solid propellant formulations at 70 bar combustion pressure and an adap

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6

Mihailescu, Cristina. "Practical Methods of Optimizing the Maximum Range for Rockets." International Journal on Applied Physics and Engineering 2 (October 5, 2023): 137–43. http://dx.doi.org/10.37394/232030.2023.2.13.

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Range extension for artillery projectiles, rockets, and missiles is a problem of trajectory optimization based on a set of constraints aimed at maximizing the range as a measure of performance. Solid Rocket Motors (SRM) are rocket motors that use solid propellants. For higher engine efficiency and cost minimization, optimization of the engine is necessary, which implies a modification of the schematics of the engine. SRM optimization is currently a key topic in aerospace engineering research. Because some input data remain constant, others can be considered as variables, and their influence on

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7

Jadhav, Shruti Dipak, Tapas Kumar Nag, Atri Bandyopadhyay, and Raghvendra Pratap Singh. "Experimental and Computational Investigation of Sounding Solid Rocket Motor." 3 1, no. 3 (2022): 29–38. http://dx.doi.org/10.46632/jame/1/3/5.

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Experimental sounding rockets are important contributors to aerospace engineering research. However, experimental-sounding rockets are rarely used for student research projects by institutes in India. The unavailability of rocket motors, which require complex machining and explosive propellants, is a major barrier to the use of sounding rockets in student research projects. We ran into this problem while developing a sounding rocket motor for project and learning purposes. The project focuses on designing and constructing a solid rocket motor that researchers can use as the primary propulsion

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8

Nagappa, R., M. R. Kurup, and A. E. Muthunayagam. "ISRO's solid rocket motors." Acta Astronautica 19, no. 8 (1989): 681–97. http://dx.doi.org/10.1016/0094-5765(89)90136-7.

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9

Serrano, Dario Donrey. "Applications of Optimization Techniques for Solid Rocket Design." Highlights in Science, Engineering and Technology 38 (March 16, 2023): 716–24. http://dx.doi.org/10.54097/hset.v38i.5936.

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Solid Rocket Motors (SRM) are rocket motors that use solid propellants (fuel/oxidizer). Optimization of the motor’s design is the process to alter the schematics of the engine for higher engine efficiency and cost minimization. Solid Rocket Motor optimization is one of the key topics of aerospace engineering research today. Conventional methods for optimization have fallen obsolete due to the exceedingly large number of design variable in modern rocket engine optimization. This paper will summarize and review some of the related research carried out in this field. Modern methods of optimizatio

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10

Zhang, Yin, Zhensheng Sun, Yu Hu, et al. "Numerical Simulation of the Gas Flow of Combustion Products from Ignition in a Solid Rocket Motor Under Conditions of Propellant Creep." Aerospace 12, no. 2 (2025): 153. https://doi.org/10.3390/aerospace12020153.

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The development of modern solid rocket technology with high-performance and high-loading ratio propellants places higher requirements on the safety and stability of the solid rocket motor. The propellant of the solid rocket motor will creep during long-term vertical storage, which may adversely affect its regular operation. The ignition transient process is a critical phase in the operation of solid rocket motors. The Abaqus v.2022 finite element simulation software is used to analyze the ignition transient under propellant creep conditions and obtain the deformed combustion chamber profile. T

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11

Yang, Huixin, Pengcheng Yu, Yan Cui, Bixuan Lou, and Xiang Li. "Data Augmentation and Deep Learning Methods for Pressure Prediction in Ignition Process of Solid Rocket Motors." Machines 12, no. 12 (2024): 906. https://doi.org/10.3390/machines12120906.

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During the ignition process of a solid rocket motor, the pressure changes dramatically and the ignition process is very complex as it includes multiple reactions. Successful completion of the ignition process is essential for the proper operation of solid rocket motors. However, the measurement of pressure becomes extremely challenging due to several issues such as the enormity and high cost of conducting tests on solid rocket motors. Therefore, it needs to be investigated using numerical calculations and other methods. Currently, the fundamental theories concerning the ignition process have n

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12

Teng, Jian, Zhenlong Wu, Limei Lu, and Yiqing Li. "Rapid prediction of solid rocket ignition transient process using artificial neural networks." Thermal Science, no. 00 (2024): 176. http://dx.doi.org/10.2298/tsci240416176t.

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Solid rocket motors (SRMs) have been a critical component of space exploration, military operations, and numerous other applications for decades. The ability to accurately predict the ignition transient behavior of solid rocket motors is crucial for ensuring safe and reliable operations. In this study, artificial neural networks (ANNs) are employed to predict the ignition transient process of a model solid rocket motor. The training and validation data for the ANNs are obtained through simulations of a validated quasi-one-dimensional model. Results show that with the inputs of axial coordinate

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13

Muhammed, Safna K., and Prof Indu Susan Raj. "A Review on the Influence of Test Bed Dynamic Characteristics on Thrust measured during Static Fire Testing of Solid Rocket Motor case." International Journal for Research in Applied Science and Engineering Technology 11, no. 5 (2023): 505–8. http://dx.doi.org/10.22214/ijraset.2023.51564.

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Abstract: Solid propelled rocket motors (SRMs) static firing tests are crucial tests in the aerospace industry while developing new motors as well as to ensure the quality of a motor batch. The operator can use this sort of test to determine whether the motor performance meets the project criteria by obtaining the measured "thrust versus time of burning" graphic the motor produces while burning. In this paper over all thrust measurement uncertaintyof a solid propellant rocket motor test bed is studied. During static test of solid motors requires the dynamic characteristics of the Static test c

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14

Kitinirunkul, Thirapat, Prakob Kitchaiya, Chesda Kiriratnikom, Paisarn Boonyarat, and Suchuchchai Nuanklai. "Effect of Antimony Trioxide and Carbon Black on the Mechanical Properties and Ablation Properties of Liner Insulation in Rocket Motors." Key Engineering Materials 877 (February 2021): 108–13. http://dx.doi.org/10.4028/www.scientific.net/kem.877.108.

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This study focused on the mechanical properties and ablation properties of liner insulation in rocket motors for improving rocket performance by means of tensile strength, elongation, ablation rate and density. The following parameters were varied: amount of zinc oxide, antimony trioxide and carbon black (N550). It was found that the insulation of the rocket motors with antimony trioxide and carbon black provided higher the elongation and ablation rate. Thus, it was able to endure more heat from hot gas in combustion chamber. The result suggests that use of antimony trioxide and carbon black a

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15

Viganò, Davide, Adriano Annovazzi, and Filippo Maggi. "Monte Carlo Uncertainty Quantification Using Quasi-1D SRM Ballistic Model." International Journal of Aerospace Engineering 2016 (2016): 1–8. http://dx.doi.org/10.1155/2016/3765796.

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Compactness, reliability, readiness, and construction simplicity of solid rocket motors make them very appealing for commercial launcher missions and embarked systems. Solid propulsion grants high thrust-to-weight ratio, high volumetric specific impulse, and a Technology Readiness Level of 9. However, solid rocket systems are missing any throttling capability at run-time, since pressure-time evolution is defined at the design phase. This lack of mission flexibility makes their missions sensitive to deviations of performance from nominal behavior. For this reason, the reliability of predictions

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16

Wang, Zhuopu, Wenchao Zhang, and Yuanzhe Liu. "A Phenomenological Model for the Unsteady Combustion of Solid Propellants from a Zel’dovich-Novzhilov Approach." Aerospace 10, no. 9 (2023): 767. http://dx.doi.org/10.3390/aerospace10090767.

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Solid rocket motors are prone to combustion instabilities, which may lead to various problems for the rockets, from unexpected oscillations, precision decreasing, to explosion. The unsteady combustion dynamics of the propellants play a crucial role in most solid rocket motors experiencing combustion instabilities. A modeling framework for the unsteady combustion of the solid propellant is constructed via the Zel’dovich-Novozhilov (ZN) phenomenological perspective. The overall unsteady combustion features of a quasi-steady homogeneous one-dimensional (QSHOD) model are investigated. The phenomen

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17

Cobbald, T. J. "Technical Note — The impingement of underexpanded axisymmetric rocket motor exhausts and cold jets on flat plates." Aeronautical Journal 96, no. 951 (1992): 27–28. http://dx.doi.org/10.1017/s0001924000024441.

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Rocket motors are used to provide propulsive thrust for various types of aerospace vehicle. The thrust is developed by the supersonic jets of hot gas emitted through the rocket motor exhaust nozzles. Usually, for most flight trajectories of rocket-propelled aerospace vehicles, the exhaust jets expand freely into the ambient medium. There are, however, instances where the exhaust jets impinge on solid obstacles which are either unavoidably or deliberately positioned in the vicinity of the rocket motor exhaust nozzles. In these cases, the exhaust jets are deflected from their normal paths. When

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18

Dominiak, Adam, Michał Rąpała, Roman Domański, Bartosz Bartkowiak, and Piotr Darnowski. "Solid-fuel Rocket Engines: Layered Composite Materials Manufacturing and Thermal Diffusivity Measurements." High Temperature Materials and Processes 33, no. 2 (2014): 171–77. http://dx.doi.org/10.1515/htmp-2013-0054.

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AbstractThis communication presents thermal diffusivity measurements of fourteen layered insulating composite materials. Composite materials that were taken under investigation contained matrixes based on epoxy and phenol-formaldehyde resins and reinforcements, such as glass, basalt fiber and wrapping or ceramic paper. They were all prepared by the Rocket Section of the Students Space Association (RS-SSA). Manufacturing process of samples is described. Additional objective of this research was to obtain the quality of such prepared materials and if they are reliable enough to be used in solid-

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19

Soe, Hlaing Tun, and Hong Jun Xiang. "Star Grain Regression under Spin Induced Acceleration Effect." Applied Mechanics and Materials 110-116 (October 2011): 451–56. http://dx.doi.org/10.4028/www.scientific.net/amm.110-116.451.

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Spinning is used in some of solid rocket motors to increase the flight trajectory precision or for stability requirements. The angular acceleration due to the spin effect increases the burning rate of solid propellant and changes the motor performance by increasing the operating pressure and decreasing the burning time. So it is important to know the grain regression taken place in the solid propellant rocket motor in the acceleration field. In this study, we represent the grain regression analysis of two-dimensional axis-symmetric star grain configuration of the solid propellant rocket motor

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20

BANACKA, Natalia, Dariusz SOKOŁOWSKI, and Mirosław SZCZEPANIK. "TESTING PROPERTIES OF SELECTED POLYMER MATERIALS FOR ABLATIVE LAYERS IN ROCKET SOLID FUEL MOTORS." PROBLEMY TECHNIKI UZBROJENIA 168, no. 1 (2024): 113–31. http://dx.doi.org/10.5604/01.3001.0054.4796.

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The article presents basic information about using thermal insulation in rocket solid fuel motors. A breakdown of the insulating material is given with examples of polymers used to protect motor internal surface at combustion of fuel and its hightemperature products. Tests were carried out in the work for selected polymer materials used at production of rocket solid fuel motors, and the polymer was indicated with the best ablative properties. The method of testing consisted of physicochemical and mechanical tests. Performing DSC and TG measurements made it possible to observe the phase transfo

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21

Hart, Grant W., Kent L. Gee, and Mylan R. Cook. "Updated frequency-dependent directivity indices for large solid rocket motors." Journal of the Acoustical Society of America 153, no. 3_supplement (2023): A41. http://dx.doi.org/10.1121/10.0018084.

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For many years, empirical models for rocket noise radiation relied on the directivity indices published in NASA SP-8072 (K. Eldred, 1971). Because these indices had known issues, NASA led a campaign to update the indices using a Space Shuttle reusable solid rocket motor (RSRM). The RSRM measurements, involving a polar arc at a radius of about 80 nozzle exit diameters, resulted in updated directivity indices (Haynes and Kenny, AIAA 2009–3160). However, because the arc origin was placed at the nozzle exit plane, James et al. [Proc. Mtgs. Acoust., 18, 040008 (2012)] corrected the low-frequency in

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22

Grythe, Kai Frode, Finn Knut Hansen, and Torbj⊘rn Olsen. "Adhesion in Solid Propellant Rocket Motors." Journal of Adhesion 83, no. 3 (2007): 223–54. http://dx.doi.org/10.1080/00218460701239059.

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23

Suksila, Thada. "Experimental investigation of solid rocket motors for small sounding rockets." IOP Conference Series: Materials Science and Engineering 297 (January 2018): 012009. http://dx.doi.org/10.1088/1757-899x/297/1/012009.

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24

Aswin, C., S. Srichand Vishnu, D. Aravind Kumar, et al. "Studies on Ignition Delay and Flame Spread in High-Performance Solid Rocket Motors." Applied Mechanics and Materials 232 (November 2012): 316–21. http://dx.doi.org/10.4028/www.scientific.net/amm.232.316.

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Accurate prediction of ignition delay and flame spread rate in solid propellant rocket motors is of great topical interest. In this paper using a standard k-ω turbulence model numerical studies have been carried out to examine the influence of solid rockets port geometry on ignition delay and the flame spread pattern. We observed that with the same inflow conditions and propellant properties heat flux histories and ignition time sequence are different for different port geometries. We conjectured from the numerical results that in solid rocket motors with highly loaded propellants, mass flux o

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25

Abyan, Muhammad Ihsan, Aang Nuryaman, Bagus Hayatul Jihad, Soleh Fajar Junjunan, and Asmiati Asmiati. "Design Optimization of Propellant Grain and Nozzle Contour to Improve Performance of Solid Rocket Propulsion." Journal of Engineering and Technological Sciences 54, no. 5 (2022): 220508. http://dx.doi.org/10.5614/j.eng.technol.sci.2022.54.5.8.

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A rocket is a spacecraft, guided missile, or flying vehicle that boosted by a chemical reaction resulting from the combustion of propellant in the rocket motor. One of the essential parameters in the development of rocket motors is design optimization to improve the propulsion performance of the rocket. Increasing the propulsion performance of the rocket will increase the flight performance of the rocket, in terms of its maximum range or the altitude of the rocket trajectory. This study examined the determination of the design parameter values of a rocket motor by looking at it as an optimizat

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26

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

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

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27

Abdelaziz, Almostafa, Liang Guozhu, and Anwer Elsayed. "Parameters Affecting the Erosive Burning of Solid Rocket Motor." MATEC Web of Conferences 153 (2018): 03001. http://dx.doi.org/10.1051/matecconf/201815303001.

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Increasing the velocity of gases inside solid rocket motors with low port-to-throat area ratios, leading to increased occurrence and severity of burning rate augmentation due to flow of propellant products across burning propellant surfaces (erosive burning), erosive burning of high energy composite propellant was investigated to supply rocket motor design criteria and to supplement knowledge of combustion phenomena, pressure, burning rate and high velocity of gases all of these are parameters affect on erosive burning. Investigate the phenomena of the erosive burning by using the 2’inch rocke

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28

Man’ko, Tamara Antonovna, and Kristina Viktorovna Коzis. "THE ISSUES OF CHEMISTRY AND TECHNOLOGIES OF RESIN MIXTURES FABRICATION FOR INTERNAL HEAT-PROTECTIVE COATING OF ROCKET SOLID FUEL ENGINE." Journal of Rocket-Space Technology 27, no. 4 (2019): 13–20. http://dx.doi.org/10.15421/451903.

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One of specific features of rocket engineering – is the high rate of sophistication and renewal of structures due to constantly growing operational and technical specifications imposed to them. Every generation of rocket and space products features a new complex of design and processing parameters and new materials possessing higher properties. It is impossible to resolve the entire scope of design and processing tasks in course of development, creation and operation of spacecraft without extend development and infusion of new materials which possess a number of required characteristics impose

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29

Santos, L. M. C., L. A. R. Almeida, A. M. Fraga, and C. A. G. Veras. "EXPERIMENTAL INVESTIGATION OF A PARAFFIN BASED HYBRID ROCKET." Revista de Engenharia Térmica 5, no. 1 (2006): 08. http://dx.doi.org/10.5380/reterm.v5i1.61658.

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Hybrid rockets are known to be simpler, safer, environmentally friend, and, more importantly, cheaper than most of the technologies for propulsion devices used today. Hybrid rockets can be applied as the propulsion system in satellites launch vehicles, micro-satellites and tactical missiles. This paper deals with combustion of ultra-high molecular weight polyethylene (UHMWPE) and paraffin as the solid fuels burning with gaseous oxygen (GOX) as well as N O as the oxidizer in lab scale hybrid rocket motors. A test 2 stand was built to carry out the experiments. The main objectives were to invest

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30

He, Kai-le, and Xiao-chun Xue. "Cook-off Characteristics of Solid Rocket Motor with AP/HTPE Propellant Charge." Journal of Physics: Conference Series 2478, no. 3 (2023): 032014. http://dx.doi.org/10.1088/1742-6596/2478/3/032014.

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Abstract Conducting thermal safety research on solid rocket motors is a method to effectively improve the battlefield survivability of rockets and missile weapons. Based on the AP-based cock-off reaction mechanism, a 2-D unsteady axial symmetrical model of solid rocket motor is developed. The software Fluent is used to calculate the numerical value of the rocket motor under thermal stimulation conditions of different heating rates. The results indicate that the heating rate of cook-off is negatively correlated with the ignition delay time of the motor, and there is no significant connection be

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31

Castor, Fernando de Paula Leite, Carlos Roberto Hall Barbosa, and Elcio Cruz de Oliveira. "Assessing the Metrological Reliability of Static Firing Tests of Rocket Motors Through the Evaluation of Thrust and Total Impulse Measurement Uncertainty." Applied Sciences 15, no. 8 (2025): 4280. https://doi.org/10.3390/app15084280.

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A solid propellant rocket motor is a propulsion system used in missiles and rockets that burns a propellant, typically composed of a mixture of fuel and an oxidizer, to generate the thrust necessary to propel the vehicle. During both the development and quality assurance phases, static firing tests of rocket motors are conducted to verify whether the system requirements meet the product specifications. These tests aim to produce two main types of graphs, “thrust versus burn time” and “pressure versus burn time,” both generated by the rocket motor during the burn. While thrust and pressure are

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32

Timarov, A. G., I. O. Eliseev, D. M. Borisov, and V. V. Mironov. "ANALYSIS OF FOREIGN EXPERIENCE OF DUAL USE SOLID ROCKET MOTORS." Вестник Российской академии наук 93, no. 12 (2023): 1151–61. http://dx.doi.org/10.31857/s0869587323120083.

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In countries, such as the United States, China, India, France, Israel and many others, solid-propellant rocket engine technologies are used not only in military missiles, but also in launch vehicles of the rocket and space industry. Such an approach of dual application of technologies makes it possible to introduce and develop new innovative solutions to increase the degree of unification of related technologies. One of the most important factors influencing the efficiency of using solid propellant rocket engines in space programs is the cost of solid rocket propellants and propulsion system c

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Guo, Xufei, Yanwei Yang, and Xingcheng Han. "Classification and Inspection of Debonding Defects in Solid Rocket Motor Shells Using Machine Learning Algorithms." Journal of Nanoelectronics and Optoelectronics 16, no. 7 (2021): 1082–89. http://dx.doi.org/10.1166/jno.2021.3055.

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Debonding problems along the propellant/liner/insulation interface are a critical factor affecting the integrity of solid rocket motors and one of the major causes of their structural failure. Due to the complexity of interface debonding detection and its low accuracy, a method of wavelet packet transform (WPT) combined with machine learning is proposed. In this research, multi-layer structure specimens were prepared to simulate the structure of a solid rocket motor. First, ultrasonic non-destructive testing technology was used to obtain defect data. Then, WPT algorithm was employed to extract

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Novozhilov, B. V. "NONLINEAR COMBUSTION IN SOLID PROPELLANT ROCKET MOTORS." International Journal of Energetic Materials and Chemical Propulsion 5, no. 1-6 (2002): 793–802. http://dx.doi.org/10.1615/intjenergeticmaterialschemprop.v5.i1-6.830.

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35

Vuillot, Francois. "Vortex-shedding phenomena in solid rocket motors." Journal of Propulsion and Power 11, no. 4 (1995): 626–39. http://dx.doi.org/10.2514/3.23888.

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36

Kourta, A. "Vortex shedding in segmented solid rocket motors." Journal of Propulsion and Power 12, no. 2 (1996): 371–76. http://dx.doi.org/10.2514/3.24038.

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37

Vargas, Magda B., and R. Jeremy Kenny. "Acoustic measurements for small solid rocket motors." Journal of the Acoustical Society of America 127, no. 3 (2010): 1743. http://dx.doi.org/10.1121/1.3383517.

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38

Islam, Saad, and Md Shafiqul Islam. "Numerical Analysis for Determination of Hydrodynamic Characteristics of a Gimbaled Thrust Vectoring Nozzle." Journal of Bangladesh Academy of Sciences 41, no. 1 (2017): 69–84. http://dx.doi.org/10.3329/jbas.v41i1.33505.

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Gimbaled thrust vectoring nozzles are employed in Solid Rocket Motors (SRM) to account for the aspects of maneuverability of the flight vehicle. The flow field of such a solid pulsed rocket motor is explored numerically (from dome-closeout onward) by solving Reynolds-averaged Navier-Stokes equations with Menters Shear Stress Transport (SST) k - ? turbulence model using a Computational Fluid Dynamics (CFD) tool. Parametric studies are carried out to find out the thermochemical and hydrodynamic characteristics of the hot gas in the rocket motor nozzle. The performances of different supersonic a

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zong-tao, Guo, Song qi-xuan, He zhen-chuan, and Luo xi-bin. "Rapid Optimization Method of Solid Rocket Motor Propellant Under Multiple Load Condition." Journal of Physics: Conference Series 2478, no. 3 (2023): 032031. http://dx.doi.org/10.1088/1742-6596/2478/3/032031.

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Abstract In order to design a solid rocket motor with a high mass ratio, it is necessary to find out the parameters of the grain shape to meet the structural strength under volume loading fraction condition. A rapid optimization method for a complex grain of solid rocket motors based on parametric modeling and GA-BP is proposed. Based on this, the neural network prediction results are optimized as a function of fitness in GA, and the optimization results show that the maximum Von Mises strain is reduced by 9.8% while the constraints are satisfied.

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Vinod, G., Manashkumar Bhadra, K. S. Narayanan, and V. Thaddeus Basker. "Margin of Safety Estimation of Tongue and Groove Joint of Rocket Motors with Discontinuous End Ring." Applied Mechanics and Materials 877 (February 2018): 354–59. http://dx.doi.org/10.4028/www.scientific.net/amm.877.354.

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Rocket motors are used worldwide in both upper and booster stages.Solid rockets can provide high thrust for relatively low cost. Considering the large size of solid motors, these motors are to be designed as segmented motor cases. Segmented motor cases have to be joined by segment joint. Segment joint with tongue and groove configuration provides performance reliability in effective sealing of joints. A tongue-and-groove arrangement employs a pressure-energized metal seal which expands radially when the cylinders are internally pressurized. The radial expansion enhances the sealing effect of t

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41

Albarado, Kevin, Roy Hartfield, Wade Hurston, and Rhonald Jenkins. "Solid Rocket Motor Design Using Hybrid Optimization." International Journal of Aerospace Engineering 2012 (2012): 1–9. http://dx.doi.org/10.1155/2012/987402.

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A particle swarm/pattern search hybrid optimizer was used to drive a solid rocket motor modeling code to an optimal solution. The solid motor code models tapered motor geometries using analytical burn back methods by slicing the grain into thin sections along the axial direction. Grains with circular perforated stars, wagon wheels, and dog bones can be considered and multiple tapered sections can be constructed. The hybrid approach to optimization is capable of exploring large areas of the solution space through particle swarming, but is also able to climb “hills” of optimality through gradien

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42

Iyer, A. S., V. K. Chakravarthy, S. Saha, and D. Chakraborty. "Damping of modal perturbations in solid rocket motors." Aeronautical Journal 120, no. 1231 (2016): 1425–45. http://dx.doi.org/10.1017/aer.2016.65.

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ABSTRACTQuasi-one-dimensional (quasi-1D) tools developed for capturing flow and acoustic dynamics in non-segmented solid rocket motors are evaluated using multi-dimensional computational fluid dynamic simulations and used to characterise damping of modal perturbations. For motors with high length-to-diameter ratios (of the order of 10), remarkably accurate estimates of frequencies and damping rates of lower modes can be obtained using the the quasi-1D approximation. Various grain configurations are considered to study the effect of internal geometry on damping rates. Analysis shows that lower

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43

Tian, Weiping, and Chunguang Wang. "Constitutive Model and Deformation Characteristics of a Throat Insert Made of the C/C Composite." International Journal of Aerospace Engineering 2021 (September 30, 2021): 1–12. http://dx.doi.org/10.1155/2021/9510768.

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Axial braided C/C composite materials are widely applied in the throat insert of solid rocket motors. It is the key for the development and design of solid rocket motors to characterize accurately the macromechanical properties of the materials. The Jones-Nelson model is employed to characterize the constitutive relation of the axial braided C/C composite material in this paper. The Jones-Nelson model is expanded and modified to characterize the C/C composite under complex load conditions. The typical external load tests were carried out to verify the accuracy. On this basis, the deformation f

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44

Wang, Zhejun, Hongfu Qiang, Biao Geng, and Tingjing Geng. "Numerical simulation of fragment impacting solid rocket motors." AIP Advances 12, no. 5 (2022): 055204. http://dx.doi.org/10.1063/5.0088412.

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For the initiation characteristics of solid rocket motors (SRMs) filled with high-energy solid propellant under fragment impact, the related theoretical critical criterion for shock initiation was established based on the critical energy criterion and equivalent analysis method. Afterward, numerical simulation of fragment impacting SRM was carried out by using the ANSYS/LS-DYNA software and the nonlinear finite element method. Based on the calculated pressure and reactivity in the high-energy solid propellant grain, the shock critical initiation velocity of SRM and its variation with different

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45

Gallier, Stany, and Franck Godfroy. "Aluminum Combustion Driven Instabilities in Solid Rocket Motors." Journal of Propulsion and Power 25, no. 2 (2009): 509–21. http://dx.doi.org/10.2514/1.37664.

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46

Haloulakos, V. E. "Slag mass accumulation in spinning solid rocket motors." Journal of Propulsion and Power 7, no. 1 (1991): 14–21. http://dx.doi.org/10.2514/3.23288.

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Heister, S. D., and E. M. Landsbaum. "Analysis of ballistic anomalies in solid rocket motors." Journal of Propulsion and Power 7, no. 6 (1991): 887–93. http://dx.doi.org/10.2514/3.23406.

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48

Heister, S. D., and R. J. Davis. "Predicting burning time variations in solid rocket motors." Journal of Propulsion and Power 8, no. 3 (1992): 564–69. http://dx.doi.org/10.2514/3.23515.

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Tinaztepe, H. Tugrul, I. Sinan Akmandor, and Ahmet S. Ucer. "Unsteady internal ballistic calculations of solid rocket motors." Journal of Propulsion and Power 8, no. 5 (1992): 1125–28. http://dx.doi.org/10.2514/3.23602.

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50

Akpan, Unyime O., Timothy E. Dunbar, and Franklin C. Wong. "Probabilistic Risk Assessment of Solid-Propellant Rocket Motors." Journal of Spacecraft and Rockets 40, no. 3 (2003): 426–32. http://dx.doi.org/10.2514/2.3963.

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