Artículos de revistas: "Solid Rocket Motors"

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Abdelraouf, A. M., O. K. Mahmoud y M. A. Al-Sanabawy. "Thrust termination of solid rocket motor". Journal of Physics: Conference Series 2299, n.º 1 (1 de julio de 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 throat area, and sudden opening of an additional port at the forward section of the motor, which increases the depressurization rate (dp/dt) required for extinguishing. The rate of depressurization varies depending on propellant components, combustion pressure, and exhaust pressure, and may be investigated using experimental approaches. The change in the critical area for a motor can be predicted by using MATLAB code to ensure the complete extinguishing by decreasing the pressure under the deflagrationlimit with high depressurization rate.

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2

Schonberg, W. P. "Energy partitioning in high speed impact of analogue solid rocket motors". Aeronautical Journal 103, n.º 1029 (noviembre de 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 ballistic impact hazards. In this study, a theoretical first-principles-based model is developed to determine the partitioning of the kinetic energy of an impacting projectile among various solid rocket motor failure modes. Failure modes considered in the analyses include case perforation, case delamination, and fragmentation of the propellant simulant material. Energies involved in material fragmentation are calculated using a fragmentation scheme based on a procedure developed in a previous impact study utilising propellant simulant material. The model is found to be capable of predicting a variety of response characteristics for analogue solid rocket motors under high speed projectile impact that are consistent with observed response characteristics. Suggestions are made for improving the model and extending its applicability to a wider class of impact scenarios.

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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 likely 75 μm diameter aluminum oxide. Aluminum oxide particulates are a major exhaust product from solid rocket motors. The size of particulates from most current solid rocket motors is found to range between 0.1 μm to 20 μm. Modeling the orbits of particulates from these rockets predicts that measurements in Earth orbit of interplanetary dust in this size range are also likely to include Earth orbiting particulates from solid rocket motors.

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4

Jadhav, Shruti Dipak, Tapas Kumar Nag, Atri Bandyopadhyay y Raghvendra Pratap Singh. "Experimental and Computational Investigation of Sounding Solid Rocket Motor". 3 1, n.º 3 (1 de diciembre de 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 unit in experimental sounding rockets. Initially, basic designs were evaluated, as various concepts of observations of propellant configuration. The accessibility and ease of use of manufacturing and casting of propellants played a significant role in determining the best propellant based on these findings, the theoretical values for combustion chamber parameters were obtained. Also, materials were chosen accordingly, and a fundamental small-scale experimental design was built and extensively tested. This small-scale motor was created by combining all of the analysis and theoretical data.At experimental testing, we got to know the thrust generated is 763.47N and the motor runs for 4.1 sec, the total mass of the propellant is maxed at 1500g which gives us the max mass flow rate of 0.65Kg/sec this is the output for our solid rocket motor.

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Nagappa, R., M. R. Kurup y A. E. Muthunayagam. "ISRO's solid rocket motors". Acta Astronautica 19, n.º 8 (agosto de 1989): 681–97. http://dx.doi.org/10.1016/0094-5765(89)90136-7.

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6

Serrano, Dario Donrey. "Applications of Optimization Techniques for Solid Rocket Design". Highlights in Science, Engineering and Technology 38 (16 de marzo de 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 optimization are usually designed to be multidisciplinary using complex computerized hyper-heuristic algorithms like Genetic Algorithms, sequential quadratic programming, particle swarm optimization. In conclusion, this paper could be a useful reference for those who would like to acquire a scan of the field of modern SRM optimization, learn the core methodologies for the optimization process and understand the logic of related methods.

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7

Muhammed, Safna K. y 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, n.º 5 (31 de mayo de 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 configuration. To find out the magnitude of thrust oscillation, characterization of test setup and force transfer characteristics from motor case to load cell are required.

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8

Kitinirunkul, Thirapat, Prakob Kitchaiya, Chesda Kiriratnikom, Paisarn Boonyarat y 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 (febrero de 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 as filler in liner insulation can improve the thermal insulators and case-bonded in rocket motor between the solid propellant and the rocket motor tube.

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9

Viganò, Davide, Adriano Annovazzi y 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 and reproducibility of performances represent a primary goal in this field. This paper presents an analysis of SRM performance uncertainties throughout the implementation of a quasi-1D numerical model of motor internal ballistics based on Shapiro’s equations. The code is coupled with a Monte Carlo algorithm to evaluate statistics and propagation of some peculiar uncertainties from design data to rocker performance parameters. The model has been set for the reproduction of a small-scale rocket motor, discussing a set of parametric investigations on uncertainty propagation across the ballistic model.

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10

Wang, Zhuopu, Wenchao Zhang y Yuanzhe Liu. "A Phenomenological Model for the Unsteady Combustion of Solid Propellants from a Zel’dovich-Novzhilov Approach". Aerospace 10, n.º 9 (29 de agosto de 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 phenomenological ZN parameters are then calculated. Compared with the traditional ZN-QSHOD linear equivalence relation, the new calculated system yields better results for the pressure coupling response, especially in the non-linear regime. The proposed phenomenological modeling provides a new methodology for the model reduction of the complex flame models.

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11

Dominiak, Adam, Michał Rąpała, Roman Domański, Bartosz Bartkowiak y Piotr Darnowski. "Solid-fuel Rocket Engines: Layered Composite Materials Manufacturing and Thermal Diffusivity Measurements". High Temperature Materials and Processes 33, n.º 2 (1 de abril de 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-fuel rocket motors. Use of composite materials to build combustion chamber walls of solid fuel rocket engines, rather than metal, leads to weight reduction and increases amount of fuel that rocket can carry. That improves performances and gives new possibilities for rocket applications. To apply new high performance solid fuels, development of new composite materials was required. Analysis of thermal properties gives the answer, which material should be used for new solid-fuel rockets designed by RS-SSA.

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12

Cobbald, T. J. "Technical Note — The impingement of underexpanded axisymmetric rocket motor exhausts and cold jets on flat plates". Aeronautical Journal 96, n.º 951 (enero de 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 a rocket exhaust jet is deflected in this manner by a solid obstacle, the situation is usually referred to as rocket exhaust impingement.

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13

Grythe, Kai Frode, Finn Knut Hansen y Torbj⊘rn Olsen. "Adhesion in Solid Propellant Rocket Motors". Journal of Adhesion 83, n.º 3 (8 de marzo de 2007): 223–54. http://dx.doi.org/10.1080/00218460701239059.

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14

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

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15

Hart, Grant W., Kent L. Gee y Mylan R. Cook. "Updated frequency-dependent directivity indices for large solid rocket motors". Journal of the Acoustical Society of America 153, n.º 3_supplement (1 de marzo de 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 indices using an estimated dominant source position for each frequency and assumed spherical spreading. This paper revisits that correction effort by using near-field vector intensity measurements from a similar, but smaller diameter and lower thrust, GEM-60 motor to determine the frequency-dependent origin to adjust the apparent angles and distances of the measurements. Additionally, an effort is made to account for RSRM plume impingement downstream that likely resulted in lower high-frequency levels than would have been measured if the plume had been entirely free. This analysis results in updated, frequency-dependent directivity indices for a large solid rocket motor. Their applicability to other rockets will be discussed.

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16

Soe, Hlaing Tun y Hong Jun Xiang. "Star Grain Regression under Spin Induced Acceleration Effect". Applied Mechanics and Materials 110-116 (octubre de 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 under spin induced acceleration effect to study how the spin affects on the internal ballistics of the solid rocket motor. Grain regression is done by two methods - geometrical approach and numerical approach. The burning rates on the propellant surface are different with its radial distance, acceleration vector angle and surface slope when the rocket is spinning. With the different burn rates on the propellant surface, the propellant surface perimeter and port area are computed by using the numerical method, and the results are compared with that of constant burn rate.

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17

Aswin, C., S. Srichand Vishnu, D. Aravind Kumar, S. Deepthi, S. K. Kumaresh, M. Arun y V. R. Sanal Kumar. "Studies on Ignition Delay and Flame Spread in High-Performance Solid Rocket Motors". Applied Mechanics and Materials 232 (noviembre de 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 of the hot gases moving past the burning surface is large. Under these conditions, the convective flux to the surface of the propellant will be enhanced, which in turn enhance the local Reynolds number. This amounts a reduction in heat transfer film thickness and enhanced heat transfer to the propellant with consequent enhancement in the dynamic burn rate resulting the undesirable starting pressure transient. We concluded that, the more accurate description of gas phase to surface heat transfer process will give a better prediction and control of ignition delay and flame spread rate in solid propellant rockets.

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18

Abyan, Muhammad Ihsan, Aang Nuryaman, Bagus Hayatul Jihad, Soleh Fajar Junjunan y Asmiati Asmiati. "Design Optimization of Propellant Grain and Nozzle Contour to Improve Performance of Solid Rocket Propulsion". Journal of Engineering and Technological Sciences 54, n.º 5 (15 de septiembre de 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 optimization problem with constraints. The problem studied was limited to the case of the second-stage rocket motor. A genetic algorithm was used to solve the resulting optimization problem of propellant grain configuration cases and a characteristic method for designing the bell nozzle. The results obtained indicated an increase in total impulse by 10% compared to the results before optimization.

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19

Abdelaziz, Almostafa, Liang Guozhu y 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 rocket motor and modified one. Different tests applied to fulfil all the parameters that calculated out from the experiments and by studying the pressure time curve and erosive burning phenomena.

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20

Santos, L. M. C., L. A. R. Almeida, A. M. Fraga y C. A. G. Veras. "EXPERIMENTAL INVESTIGATION OF A PARAFFIN BASED HYBRID ROCKET". Revista de Engenharia Térmica 5, n.º 1 (31 de julio de 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 investigate the ignition of the solid fuels, burning performance and regression rates for different operating conditions. With paraffin-based fuel the hybrid motor had the regression rate enhanced two to three folds compared to the UHMWPE, as reported in the literature. The overall performance of the motor, with paraffin as the fuel, is comparable to other technologies. Paraffin-based hybrid rockets can, then, be a safer and cheaper alternative to satellite launch vehicles for the Brazilian space program.

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21

He, Kai-le y Xiao-chun Xue. "Cook-off Characteristics of Solid Rocket Motor with AP/HTPE Propellant Charge". Journal of Physics: Conference Series 2478, n.º 3 (1 de junio de 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 between ignition temperature and heating rate. But it is obvious that heating rate has a big impact on ignition position. In the slow cook-off numerical calculation, the initial ignition position appears near the propellant head. And the higher the heating rate, the closer the ignition position is to the propellant head. At rapid heating rate of 1.45K/s, the ignition position appears at the edge of the left end face of the propellant. When rapid heating rate is 1.75K/s or 1.95K/s, ignition position appears at the edge of the right end face of the propellant. At this time, the ignition position will change abruptly.

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Man’ko, Tamara Antonovna y 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, n.º 4 (30 de diciembre de 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 imposed to state-of-the-art technology products. The most widespread and sophisticated structures of modern technology – are solid-propellant rocket motors (SPRM) made of polymer composite materials. One of the major tasks associated with their creation is development of the internal thermal protection coating of solid-propellant rocket motor casing. State enterprise Yuzhnoye Design Office named after M.K. Yangel is currently carrying out works on creation of solid-propellant rocket motors. Development of their internal thermal protection coatings using mainly domestically produced materials with specified requirements is a scientific and technological task of high importance which confirms the relevance of dissertational research.The article is devoted to the analysis of components and ingredients for rubber compounds, which provide the properties and basic functions of the thermal protective covering of solid propellant rocket engine. The article shows the main results of the work related to the development of prescribed composition and technology of manufacturing of elastomeric material which used in the manufacture of internal heat-resistant coating of solid-propellant rocket engines made of polymer composite materials.

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Novozhilov, B. V. "NONLINEAR COMBUSTION IN SOLID PROPELLANT ROCKET MOTORS". International Journal of Energetic Materials and Chemical Propulsion 5, n.º 1-6 (2002): 793–802. http://dx.doi.org/10.1615/intjenergeticmaterialschemprop.v5.i1-6.830.

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Vuillot, Francois. "Vortex-shedding phenomena in solid rocket motors". Journal of Propulsion and Power 11, n.º 4 (julio de 1995): 626–39. http://dx.doi.org/10.2514/3.23888.

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Kourta, A. "Vortex shedding in segmented solid rocket motors". Journal of Propulsion and Power 12, n.º 2 (marzo de 1996): 371–76. http://dx.doi.org/10.2514/3.24038.

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Vargas, Magda B. y R. Jeremy Kenny. "Acoustic measurements for small solid rocket motors." Journal of the Acoustical Society of America 127, n.º 3 (marzo de 2010): 1743. http://dx.doi.org/10.1121/1.3383517.

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Guo, Xufei, Yanwei Yang y Xingcheng Han. "Classification and Inspection of Debonding Defects in Solid Rocket Motor Shells Using Machine Learning Algorithms". Journal of Nanoelectronics and Optoelectronics 16, n.º 7 (1 de julio de 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 characteristic signals of the defect data. Moreover, k-nearest neighbor model, Random Forest model and support vector machine model were applied to the classification. The results showed that the accuracies of the three models were 84.67%, 90.66% and 95.33%, respectively. Positive results indicate that WPT with machine learning model exhibited excellent classification performance. Therefore, WPT combined with machine learning can achieve a precise classification of debonding defects and has the potential to assist or even automate the debonding inspection process of solid rocket motors.

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Islam, Saad y Md Shafiqul Islam. "Numerical Analysis for Determination of Hydrodynamic Characteristics of a Gimbaled Thrust Vectoring Nozzle". Journal of Bangladesh Academy of Sciences 41, n.º 1 (23 de agosto de 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 and subsonic sections were studied in terms of the hydrodynamic aspects such as static pressure and Mach number distribution. It is observed that the tradeoff of implementing thrust vectoring mechanism amounts to an additional pressure loss of 10.06% in the rocket motor. Such analyses are specific to certain types of Short Range Ballistic Missiles (SRBM) having solid state propellant (primary stage) in radial boost, end burning pulsed configuration with exacting demands on maneuverability and control implied upon payload and mission criterion.Journal of Bangladesh Academy of Sciences, Vol. 41, No. 1, 69-84, 2017

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zong-tao, Guo, Song qi-xuan, He zhen-chuan y Luo xi-bin. "Rapid Optimization Method of Solid Rocket Motor Propellant Under Multiple Load Condition". Journal of Physics: Conference Series 2478, n.º 3 (1 de junio de 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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Albarado, Kevin, Roy Hartfield, Wade Hurston y 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 gradient based pattern searching. A preliminary method for designing tapered internal geometry as well as tapered outer mold-line geometry is presented. A total of four optimization cases were performed. The first two case studies examines designing motors to match a given regressive-progressive-regressive burn profile. The third case study studies designing a neutrally burning right circular perforated grain (utilizing inner and external geometry tapering). The final case study studies designing a linearly regressive burning profile for right circular perforated (tapered) grains.

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31

Vinod, G., Manashkumar Bhadra, K. S. Narayanan y V. Thaddeus Basker. "Margin of Safety Estimation of Tongue and Groove Joint of Rocket Motors with Discontinuous End Ring". Applied Mechanics and Materials 877 (febrero de 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 the metal seal between the tongue and the groove. Metal end rings welded to the shell motor cases and shear pins for the final assembly provides the sealing. The load sharing among the pins depends on the presence of the slit in a ring, whole & pin dimensional clearances, internal pressure and friction between the metal end rings. Structural analysis of a discontinuous metallic segment ring and shear pins iscarried out in this study. Structural analysis is based on detailed solid model for the segment joint. The load augmentation in the shear pin near the discontinuity is worked out based on a load augmentation factor derived out of FE analysis. The study further extended to a deviation in a nearby hole / pin combination at the vicinity of the discontinuity and is presented in this paper.

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32

Wang, Zhejun, Hongfu Qiang, Biao Geng y Tingjing Geng. "Numerical simulation of fragment impacting solid rocket motors". AIP Advances 12, n.º 5 (1 de mayo de 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 forms of fragments and impact conditions were determined. It is found that the numerical simulation results under typical conditions are in good agreement with the data calculated with the developed theoretical critical criterion for shock initiation of SRM. However, the shock initiation mechanism becomes more complex when the case thickness of SRM increases to more than 5 mm; thus, the applicability of the developed theoretical critical criterion reduces. Moreover, it is found that all the case thickness, fragment shape, material properties of the fragment, and impact attitude can significantly affect the shock critical initiation velocity of SRM, even the initiation position and time. First, the critical velocity increases linearly with the increase in case thickness, and the increment rate is faster beyond the thickness of 6 mm. Second, the shock critical initiation velocity induced by fragments with different shapes is as follows: spherical fragment > cubic fragment > cylindrical fragment, while the initiation capacity of different fragment materials is ranked as follows: tungsten alloy > 45 steel > 2024 aluminum. Third, the effects of impact attitude on the shock critical initiation velocity, position and time are complex, and these effects are also influenced by fragment shape. When the impact angle is less than 60°, there is a higher shock critical initiation velocity of SRM under inclined impact than that under positive impact. In addition, the critical velocity induced by cubic fragment is the highest under the combination of vertex impact and positive impact. The variation of the critical velocity under this condition is approximately consistent with that by impacting with cylindrical fragment. Furthermore, when the impact angle is greater than 60°, the shock critical initiation velocity of SRM is less obviously influenced by impact attitude and fragment shape. Meanwhile, the critical velocity decreases sharply under this condition, which indicates that it is easier for SRM to detonate.

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33

Gallier, Stany y Franck Godfroy. "Aluminum Combustion Driven Instabilities in Solid Rocket Motors". Journal of Propulsion and Power 25, n.º 2 (marzo de 2009): 509–21. http://dx.doi.org/10.2514/1.37664.

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34

Haloulakos, V. E. "Slag mass accumulation in spinning solid rocket motors". Journal of Propulsion and Power 7, n.º 1 (enero de 1991): 14–21. http://dx.doi.org/10.2514/3.23288.

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35

Heister, S. D. y E. M. Landsbaum. "Analysis of ballistic anomalies in solid rocket motors". Journal of Propulsion and Power 7, n.º 6 (noviembre de 1991): 887–93. http://dx.doi.org/10.2514/3.23406.

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36

Heister, S. D. y R. J. Davis. "Predicting burning time variations in solid rocket motors". Journal of Propulsion and Power 8, n.º 3 (mayo de 1992): 564–69. http://dx.doi.org/10.2514/3.23515.

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37

Tinaztepe, H. Tugrul, I. Sinan Akmandor y Ahmet S. Ucer. "Unsteady internal ballistic calculations of solid rocket motors". Journal of Propulsion and Power 8, n.º 5 (septiembre de 1992): 1125–28. http://dx.doi.org/10.2514/3.23602.

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38

Akpan, Unyime O., Timothy E. Dunbar y Franklin C. Wong. "Probabilistic Risk Assessment of Solid-Propellant Rocket Motors". Journal of Spacecraft and Rockets 40, n.º 3 (mayo de 2003): 426–32. http://dx.doi.org/10.2514/2.3963.

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39

Harper, Stuart A., Kent L. Gee, Jarom H. Giraud y Michael B. Muhlestein. "Statistical analysis of noise from solid rocket motors". Journal of the Acoustical Society of America 130, n.º 4 (octubre de 2011): 2512. http://dx.doi.org/10.1121/1.3655009.

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40

Knauber, R. N. "Thrust misalignments of fixed-nozzle solid rocket motors". Journal of Spacecraft and Rockets 33, n.º 6 (noviembre de 1996): 794–99. http://dx.doi.org/10.2514/3.26840.

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41

Tahsini, A. M. y M. Farshchi. "Thrust Termination Dynamics of Solid Propellant Rocket Motors". Journal of Propulsion and Power 23, n.º 5 (septiembre de 2007): 1142. http://dx.doi.org/10.2514/1.26576.

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42

Dupays, Joël. "Two-phase unsteady flow in solid rocket motors". Aerospace Science and Technology 6, n.º 6 (octubre de 2002): 413–22. http://dx.doi.org/10.1016/s1270-9638(02)01182-3.

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43

Fabignon, Yves, Jöel Dupays, Gérard Avalon, Francois Vuillot, Nicolas Lupoglazoff, Grégoire Casalis y Michel Prévost. "Instabilities and pressure oscillations in solid rocket motors". Aerospace Science and Technology 7, n.º 3 (abril de 2003): 191–200. http://dx.doi.org/10.1016/s1270-9638(02)01194-x.

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44

Iyer, A. S., V. K. Chakravarthy, S. Saha y D. Chakraborty. "Damping of modal perturbations in solid rocket motors". Aeronautical Journal 120, n.º 1231 (27 de junio de 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 cross-sectional area at the nozzle entry plane is found to increase damping rates of all the modes. The flow-turning loss for a mode increases if the more mass addition due to combustion is added at pressure nodes. For the fundamental mode, this loss is, therefore, maximum if burning area is maximum at the centre. The insights from this study in addition to recommendations made by Blomshield(1)based on combustion considerations would be very helpful in realizing rocket motors free from combustion instability.

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45

Lovine, Richard L., Joseph D. Baum y Jay N. Levine. "Ejecta pulsing of subscale solid propellant rocket motors". AIAA Journal 23, n.º 3 (marzo de 1985): 416–23. http://dx.doi.org/10.2514/3.8929.

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46

Stella, F. y F. Paglia. "Pressure oscillations in solid rocket motors: Numerical study". Aerospace Science and Technology 15, n.º 1 (enero de 2011): 53–59. http://dx.doi.org/10.1016/j.ast.2010.06.008.

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47

Hamaide, S., M. Quidot y J. Brunet. "Tactical Solid Rocket Motors Response to Bullet Impact". Propellants, Explosives, Pyrotechnics 17, n.º 3 (junio de 1992): 120–25. http://dx.doi.org/10.1002/prep.19920170306.

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48

Kovalev, Oleg B. "Motor and Plume Particle Size Prediction in Solid-Propellant Rocket Motors". Journal of Propulsion and Power 18, n.º 6 (noviembre de 2002): 1199–210. http://dx.doi.org/10.2514/2.6079.

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49

Tian, Weiping y Chunguang Wang. "Constitutive Model and Deformation Characteristics of a Throat Insert Made of the C/C Composite". International Journal of Aerospace Engineering 2021 (30 de septiembre de 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 features of the axial braided C/C composite throat insert are investigated during the working process of motors, and the strain of the throat insert during the working process is obtained by FEM. The strain and temperature in the outer surface of the throat insert are measured in the ground test of motors and are compared with the numerical results by FEM to verify the accuracy of the model. The results show that the result calculated based on the modified Jones-Nelson model by FEM is in a good agreement with the test result. It shows that the modified Jones-Nelson model can better describe the constitutive relation of C/C composite materials, and it can be promoted to the engineering application of the throat insert of solid rocket motors.

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50

Toscano, Angelica Maria, Marco Rocco Lato, Donato Fontanarosa y Maria Grazia De Giorgi. "Optical Diagnostics for Solid Rocket Plumes Characterization: A Review". Energies 15, n.º 4 (17 de febrero de 2022): 1470. http://dx.doi.org/10.3390/en15041470.

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In recent decades, solid fuel combustion propulsion of spacecraft has become one of the most popular choices for rocket propulsion systems. The reasons for this success are a wide range of applications, lower production costs, simplicity, and safety. The rocket’s plumes leave the nozzle at high temperatures; hence, the knowledge of produced infrared (IR) emissions is a crucial aspect during the design and tests of the rocket motors. Furthermore, rocket plume composition is given by N2, H2, H2O, CO and CO2, while solid rocket motors (SRM) additionally inject some solid particles, given by metal fuel additives in the propellant grain, i.e., aluminum oxide (Al2O3) particles. The main issue is the detection of the particles remaining in the atmosphere due to the exhaust gas of the solid rocket propulsion system that could have effects on ozone depletion. The experimental characterization of SRM plumes in the presence of alumina particles can be conducted using different optical techniques. The present study aims to review the most promising ones with a description of the optics system and their potential applications for SRM plume measurements. The most common measurement techniques are infrared spectroscopy imaging, IR imaging. UV–VIS measurements, shadowgraph, and Schlieren optical methods. The choice of these techniques among many others is due to the ability to study the plume without influencing the physical conditions existing in and around the study object. This paper presents technical results concerning the study of rocket engines plumes with the above-mentioned methods and reveals the feasibility of the measurement techniques applied.

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