Bibliografías temáticas / Solid Rocket Motors

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Literatura académica sobre el tema "Solid Rocket Motors"

Autor: Grafiati

Publicado: 4 de junio de 2021

Última modificación: 6 de septiembre de 2023

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Artículos de revistas sobre el tema "Solid Rocket Motors"

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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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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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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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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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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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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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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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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Tesis sobre el tema "Solid Rocket Motors"

Hovland, Douglas Lyle. "Particle sizing in solid rocket motors". Thesis, Monterey, California. Naval Postgraduate School, 1989. http://hdl.handle.net/10945/26153.

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Particle size distribution measurements were made with a Malvern 2600c forward laser light diffraction system across the exhaust nozzle entrance and exhaust plume of a small two-dimensional rocket motor. The solid propellants tested were GAP propellants containing 2.0% and 4.69% aluminum. Surface agglomeration of the aluminum, indicated by the in-motor results, was found to decrease as the motor chamber pressures were increased. At low pressures, increasing the aluminum loading with fixed total solids decreased the mean particle size at the nozzle entrance. Exhaust plume particle size was practically independent of nozzle inlet particle diameters, supporting the critical Weber number particle breakup theory. Initial validation of the Malvern 2600c measurements was accomplished by favorable comparison to exhaust plume particle distribution results obtained using a particle collection probe. Particle sizing
Solid propellant rocket engines
Light scattering
Theses

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McCrorie, J. David. "Particle behavior in solid propellant rocket motors and plumes". Thesis, Monterey, California. Naval Postgraduate School, 1992. http://hdl.handle.net/10945/24002.

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Puskulcu, Gokay. "Analysis Of 3-d Grain Burnback Of Solid Propellant Rocket Motors And Verification With Rocket Motor Tests". Master's thesis, METU, 2004. http://etd.lib.metu.edu.tr/upload/12605270/index.pdf.

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Solid propellant rocket motors are the most widely used propulsion systems for military applications that require high thrust to weight ratio for relatively short time intervals. Very wide range of magnitude and duration of the thrust can be obtained from solid propellant rocket motors by making some small changes at the design of the rocket motor. The most effective of these design criteria is the geometry of the solid propellant grain. So the most important step in designing the solid propellant rocket motor is determination of the geometry of the solid propellant grain. The performance prediction of the solid rocket motor can be achieved easily if the burnback steps of the rocket motor are known. In this study, grain burnback analysis for some 3-D grain geometries is investigated. The method used is solid modeling of the propellant grain for some predefined intervals of burnback. In this method, the initial grain geometry is modeled parametrically using commercial software. For every burn step, the parameters are adapted. So the new grain geometry for every burnback step is modeled. By analyzing these geometries, burn area change of the grain geometry is obtained. Using this data and internal ballistics parameters, the performance of the solid propellant rocket motor is achieved. To verify the outputs obtained from this study, rocket motor tests are performed. The results obtained from this study shows that, the procedure that was developed, can be successfully used for the preliminary design of a solid propellant rocket motor where a lot of different geometries are examined.

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Matta, Lawrence Mark. "Investigation of the flow turning loss in unstable solid propellant rocket motors". Diss., Georgia Institute of Technology, 1993. http://hdl.handle.net/1853/15938.

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Romano, Federico. "Q1D unsteady ballistic model for solid rocket motors performance prediction". Master's thesis, Alma Mater Studiorum - Università di Bologna, 2021.

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The simulation tool ROBOOST, in use at the Alma Propulsion Lab of the University of Bologna – Forlì Campus, exploits a hybrid ballistic model 0D-1D. The need of a complete Q1D model for the entire combustion time, from motor start-up to burn out arised. The present work is devoted to the development and test of a Q1D unsteady ballistic model for solid rocket motors performance prediction. The newly developed code, called SOL1D, is written in Matlab environment and is capable of predicting the time and space evolution of all the main thermodynamic variables during the solid rocket motor combustion process. The model has been tested and validated on a BARIA motor, thus demonstrating its adherence to experimental data. SOL1D paves the way for future works aimed at simulating performances of actual launchers.

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Yakin, Bülent. "Combustor and nozzle effects on particulate behavior in solid rocket motors /". Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1993. http://handle.dtic.mil/100.2/ADA277304.

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Yakin, Bulent. "Combustor and nozzle effects on particulate behavior in solid rocket motors". Thesis, Monterey, California. Naval Postgraduate School, 1993. http://hdl.handle.net/10945/39764.

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Approved for public release; distribution is unlimited.
An investigation was conducted using a subscale solid rocket motor to measure the effect of nozzle residence time on the behavior of Al203 particles to assess the applicability of subscale motor data to full-scale motors and to measure the effects of nozzle entrance particle size distribution on the slag accumulated with submerged nozzles. Although particles as large as 140 micrometers were present at the nozzle entrance, most of the particulate mass was contained in much smaller particles. This observation is in good agreement with the small mass that accumulated above the submerged nozzle. It was found that both particle breakup and collision coalescence occurred across the exhaust nozzle, with a significant increase in the mass fraction of small (<2 micrometers) particles. Increasing the nozzle residence time enhanced particle breakup but did not affect the maximum plume particle size. Thus, full-scale motors are expected to have a higher percentage of mass in particles less than 2 micrometers than subscale motors but with similar diameters of the largest particles.

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Mini, Stefano <1991&gt. "Analysis of the main phenomena affecting solid rocket motors internal ballistics". Doctoral thesis, Alma Mater Studiorum - Università di Bologna, 2021. http://amsdottorato.unibo.it/9878/1/PhD_Thesis.pdf.

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In solid rocket motors, the absence of combustion controllability and the large amount of financial resources involved in full-scale firing tests, increase the importance of numerical simulations in order to asses stringent mission thrust requirements and evaluate the influence of thrust chamber phenomena affecting the grain combustion. Among those phenomena, grain local defects (propellant casting inclusions and debondings), combustion heat accumulation involving pressure peaks (Friedman Curl effect), and case-insulating thermal protection material ablation affect thrust prediction in terms of not negligible deviations with respect to the nominal expected trace. Most of the recent models have proposed a simplified treatment to the problem using empirical corrective functions, with the disadvantages of not fully understanding the physical dynamics and thus of not obtaining predictive results for different configurations of solid rocket motors in a boundary conditions-varied scenario. This work is aimed to introduce different mathematical approaches to model, analyze, and predict the abovementioned phenomena, presenting a detailed physical interpretation based on existing SRMs configurations. Internal ballistics predictions are obtained with an in-house simulation software, where the adoption of a dynamic three-dimensional triangular mesh together with advanced computer graphics methods, allows the previous target to be reached. Numerical procedures are explained in detail. Simulation results are carried out and discussed based on experimental data.

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Hasanoglu, Mehmet Sinan. "Storage Reliability Analysis Of Solid Rocket Propellants". Master's thesis, METU, 2008. http://etd.lib.metu.edu.tr/upload/2/12609897/index.pdf.

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Solid propellant rocket motor is the primary propulsion technology used for short and medium range missiles. It is also commonly used as boost motor in many di_erent applications. Its wide spread usage gives rise to diversity of environments in which it is handled and stored. Ability to predict the storage life of solid propellants plays an important role in the design and selection of correct protective environments. In this study a methodology for the prediction of solid propellant storage life using cumulative damage concepts is introduced. Finite element mesh of the solid propellant grain is created with the developed parametric grain geometry generator. Finite element analyses are carried out to obtain the temperature and stress response of the propellant to the environmental thermal loads. Daily thermal cycles are assumed to be sinusoidal cycles represented by their means and amplitudes. With the cumulative damage analyses, daily damage accumulated in the critical locations of the solid propellant grain are investigated. Meta-models relating the daily damage amount with the daily temperature cycles are constructed in order to compute probability of failure. The results obtained in this study imply that it is possible to make numerical predictions for the storage life of solid propellants even in the early design phases. The methodology presented in this study provides a basis for storage life predictions.

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Vernacchia, Matthew T. "Development of low-thrust solid rocket motors for small, fast aircraft propulsion". Thesis, Massachusetts Institute of Technology, 2020. https://hdl.handle.net/1721.1/127069.

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Thesis: Ph. D., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, May, 2020
Cataloged from the official PDF of thesis.
Includes bibliographical references (pages 281-289).
Small, uncrewed aerial vehicles (UAVs) are expanding the capabilities of aircraft systems. However, a gap exists in the size and capability of aircraft: no small aircraft are capable of sustained fast flight. A small, fast aircraft requires a propulsion system which is both miniature and high-power, requirements which current UAV propulsion technologies do not meet. Solid propellant rocket motors could be used, but must be re-engineered to operate at much lower thrust and for much longer burn times than conventional small solid rocket motors. This imposes unique demands on the motor and propellant. This work investigates technological challenges of small, low-thrust solid rocket motors: slow-burn solid propellants, motors which have low thrust relative to their size (and thus have low chamber pressure), thermal protection for the motor case, and small nozzles which can withstand long burn times.
Slow-burn propellants were developed using ammonium perchlorate oxidizer and the burn rate suppressant oxamide. By varying the amount of oxamide (from 0-20%), burn rates from 4mms⁻¹ to 1mms⁻¹ (at 1MPa) were achieved. Using these propellants, a low-thrust motor successfully operated at a (thrust / burn area) ratio 10 times less than that of typical solid rocket motors. This motor can provide 5-10N of thrust for 1-3 minutes. An ablative thermal protection liner was tested in these firings. Despite the long burn time, only a few millimeters of ablative are needed. A new ceramic-insulated nozzle was demonstrated on this motor. The nozzle has a small throat diameter (only a few millimeters) and can operate in thermal steady-state. Models were developed for the propellant burn rate, motor design, heat transfer within the motor and nozzle, and for thermal stresses in the nozzle insulation.
This work shows that small, low-thrust solid motors are feasible, by demonstrating these key technologies in a prototype motor. Further, the experimental results and models will enable engineers to design and predict the performance of solid rocket motors for small, fast aircraft. By providing insight into the physics of these motors, this thesis may help to enable a new option for aircraft propulsion.
by Matthew T. Vernacchia.
Ph. D.
Ph.D. Massachusetts Institute of Technology, Department of Aeronautics and Astronautics

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Libros sobre el tema "Solid Rocket Motors"

North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Design methods in solid rocket motors. Neuilly sur Seine, France: AGARD, 1988.

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North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Design Methods in Solid Rocket Motors. S.l: s.n, 1987.

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Hovland, Douglas Lyle. Particle sizing in solid rocket motors. Monterey, California: Naval Postgraduate School, 1989.

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North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Propulsion and Energetics Panel. y North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Consultant and Exchange Programme., eds. Design methods in solid rocket motors. Neuilly sur Seine, France: North Atlantic Treaty Organization, Advisory Group for Aerospace Research and Development, 1987.

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Langhenry, M. T. Acceleration effects in solid propellant rocket motors. New York: AIAA, 1986.

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Xie, Kan, Xinmin Chen, Junwei Li y Yu Liu. Fluidic Nozzle Throats in Solid Rocket Motors. Singapore: Springer Singapore, 2019. http://dx.doi.org/10.1007/978-981-13-6439-6.

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L, Derr Ronald y North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development., eds. Hazard studies for solid propellant rocket motors. Neuilly-sur-Seine, France: AGARD, 1990.

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North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Hazard studies for solid propellant rocket motors. Neuilly-sur-Seine: AGARD, 1990.

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McCrorie, J. David. Particle behavior in solid propellant rocket motors and plumes. Monterey, Calif: Naval Postgraduate School, 1992.

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Greatrix, David R. A study of combustion and flow behaviour in solid-propellant rocket motors. [Downsview, Ont.]: [Institute for Aerospace Studies], 1987.

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Capítulos de libros sobre el tema "Solid Rocket Motors"

Greatrix, David R. "Solid-Propellant Rocket Motors". En Powered Flight, 323–79. London: Springer London, 2012. http://dx.doi.org/10.1007/978-1-4471-2485-6_10.

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Xie, Kan, Xinmin Chen, Junwei Li y Yu Liu. "Erosion Characteristics of Fluidic Throat in Solid-Rocket Motors". En Fluidic Nozzle Throats in Solid Rocket Motors, 183–95. Singapore: Springer Singapore, 2019. http://dx.doi.org/10.1007/978-981-13-6439-6_8.

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Xie, Kan, Xinmin Chen, Junwei Li y Yu Liu. "Thrust Modulation Process of Fluidic Throat for Solid Rocket Motors". En Fluidic Nozzle Throats in Solid Rocket Motors, 171–82. Singapore: Springer Singapore, 2019. http://dx.doi.org/10.1007/978-981-13-6439-6_7.

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Xie, Kan, Xinmin Chen, Junwei Li y Yu Liu. "Introduction". En Fluidic Nozzle Throats in Solid Rocket Motors, 1–19. Singapore: Springer Singapore, 2019. http://dx.doi.org/10.1007/978-981-13-6439-6_1.

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Xie, Kan, Xinmin Chen, Junwei Li y Yu Liu. "System Application Modes and Key Technologies". En Fluidic Nozzle Throats in Solid Rocket Motors, 207–37. Singapore: Springer Singapore, 2019. http://dx.doi.org/10.1007/978-981-13-6439-6_10.

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Xie, Kan, Xinmin Chen, Junwei Li y Yu Liu. "Steady Characteristics of a Gas–Gas Aerodynamic Throat". En Fluidic Nozzle Throats in Solid Rocket Motors, 21–51. Singapore: Springer Singapore, 2019. http://dx.doi.org/10.1007/978-981-13-6439-6_2.

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Xie, Kan, Xinmin Chen, Junwei Li y Yu Liu. "The Characteristic Function and Nozzle Efficiency". En Fluidic Nozzle Throats in Solid Rocket Motors, 53–67. Singapore: Springer Singapore, 2019. http://dx.doi.org/10.1007/978-981-13-6439-6_3.

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Xie, Kan, Xinmin Chen, Junwei Li y Yu Liu. "The Fluidic Throat in Gas–Particle Two-Phase Flow Conditions". En Fluidic Nozzle Throats in Solid Rocket Motors, 69–93. Singapore: Springer Singapore, 2019. http://dx.doi.org/10.1007/978-981-13-6439-6_4.

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Xie, Kan, Xinmin Chen, Junwei Li y Yu Liu. "Secondary Flow TVC for Fluidic-Throat Nozzles". En Fluidic Nozzle Throats in Solid Rocket Motors, 95–133. Singapore: Springer Singapore, 2019. http://dx.doi.org/10.1007/978-981-13-6439-6_5.

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Xie, Kan, Xinmin Chen, Junwei Li y Yu Liu. "Gas–Liquid Fluidic Throat". En Fluidic Nozzle Throats in Solid Rocket Motors, 135–69. Singapore: Springer Singapore, 2019. http://dx.doi.org/10.1007/978-981-13-6439-6_6.

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Actas de conferencias sobre el tema "Solid Rocket Motors"

DELANNOY, GUY. "Computation of performance for different solid rocket motors - Conventional motors, nozzleless rocket motors, rocket ramjets". En 24th Joint Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1988. http://dx.doi.org/10.2514/6.1988-3046.

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MACBETH, A. "Refurbishment of the Space Shuttle redesigned solid rocket motors - The first reusable solid rocket motors". En 25th Joint Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1989. http://dx.doi.org/10.2514/6.1989-2403.

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Courta, A. "Vortex shedding in solid rocket motors". En 33rd Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1995. http://dx.doi.org/10.2514/6.1995-727.

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Parsons, I., P. Alavilli, A. Namazifard, A. Acharya, X. Jiao y R. Fiedler. "Coupled simulations of solid rocket motors". En 36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2000. http://dx.doi.org/10.2514/6.2000-3456.

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Guery, J., F. Godfroy, S. Ballereau, S. Gallier, P. Della Pieta, O. Orlandi, Eric Robert y Nathalie Cesco. "Thrust Oscillations in Solid Rocket Motors". En 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2008. http://dx.doi.org/10.2514/6.2008-4979.

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GAUNT, D. "Understanding costs of solid rocket motors". En 22nd Joint Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1986. http://dx.doi.org/10.2514/6.1986-1638.

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Goyal, Vinay, Jacob Rome y Patrick Schubel. "Structural Analysis of Solid Rocket Motors". En 49th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference
16th AIAA/ASME/AHS Adaptive Structures Conference
10t. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2008. http://dx.doi.org/10.2514/6.2008-2110.

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Gallier, Stany, Emmanuel Radenac y Franck Godfroy. "Thermoacoustic Instabilities in Solid Rocket Motors". En 45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2009. http://dx.doi.org/10.2514/6.2009-5252.

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HILBING, J. y S. HEISTER. "Radial slot flows in solid rocket motors". En 29th Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1993. http://dx.doi.org/10.2514/6.1993-2309.

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Zgheib, Nadim y Joseph Majdalani. "Axial Waves in Simulated Solid Rocket Motors". En 46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2010. http://dx.doi.org/10.2514/6.2010-6993.

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Informes sobre el tema "Solid Rocket Motors"

Lhota, J. R., G. C. Panos, E. C. Johnson y M. C. Gregory. Ultrasonic Backscatter Technique for Corrosion Detection in Solid Rocket Motors. Fort Belvoir, VA: Defense Technical Information Center, octubre de 1994. http://dx.doi.org/10.21236/ada307597.

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NAVAL WEAPONS CENTER CHINA LAKE CA. Measured Temperatures of Solid Rocket Motors Dump Stored in the Tropics and Desert. Part 4. Tropics. Fort Belvoir, VA: Defense Technical Information Center, julio de 1989. http://dx.doi.org/10.21236/ada213425.

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Ko, Malcolm, Run-Lie Shia, Debra Weisenstein, Jose Rodriguez y Nien-Dak Sze. Global Stratospheric Impact of Solid Rocket Motor Launchers. Fort Belvoir, VA: Defense Technical Information Center, septiembre de 1999. http://dx.doi.org/10.21236/ada413823.

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Chelner, Herbert. Embedded Sensor Technology for Solid Rocket Motor Health Monitoring. Fort Belvoir, VA: Defense Technical Information Center, julio de 2002. http://dx.doi.org/10.21236/ada405070.

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Chelner, Herbert. Embedded Sensor Technology for Solid Rocket Motor Health Monitoring. Fort Belvoir, VA: Defense Technical Information Center, febrero de 2003. http://dx.doi.org/10.21236/ada412607.

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Reaugh, J., E. Lee y J. Maienschein. The Production of Airblast From Solid Rocket Motor Fallbacks. Office of Scientific and Technical Information (OSTI), septiembre de 2012. http://dx.doi.org/10.2172/1053686.

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Aguilo Valentin, Miguel Alejandro, Steven W. Bova y David R. Noble. Solid Rocket Motor Design using a Low-Dimensional Fluid Model. Office of Scientific and Technical Information (OSTI), febrero de 2019. http://dx.doi.org/10.2172/1496883.

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Hyde, R. S. A Solid Rocket Motor Manufacturer's View of Sensors and Aging Surveillance. Fort Belvoir, VA: Defense Technical Information Center, junio de 2002. http://dx.doi.org/10.21236/ada406078.

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Koo, J. H., O. A. Ezekoye, M. C. Bruns y J. C. Lee. Experimental and Numerical Characterization of Polymer Nanocomposites for Solid Rocket Motor Internal Insulation. Fort Belvoir, VA: Defense Technical Information Center, septiembre de 2009. http://dx.doi.org/10.21236/ada564427.

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Koo, J. H. y O. D. Ezekoye. Experimental and Numerical Characterization of Polymer Nanocomposites for Solid Rocket Motor Internal Insulation. Fort Belvoir, VA: Defense Technical Information Center, septiembre de 2006. http://dx.doi.org/10.21236/ada589776.

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