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motor</title> <meta name="description" content="Search results for: solid rocket motor"> <meta name="keywords" content="solid rocket motor"> <meta name="viewport" content="width=device-width, initial-scale=1, minimum-scale=1, maximum-scale=1, user-scalable=no"> <meta charset="utf-8"> <link href="https://cdn.waset.org/favicon.ico" type="image/x-icon" rel="shortcut icon"> <link href="https://cdn.waset.org/static/plugins/bootstrap-4.2.1/css/bootstrap.min.css" rel="stylesheet"> <link href="https://cdn.waset.org/static/plugins/fontawesome/css/all.min.css" rel="stylesheet"> <link href="https://cdn.waset.org/static/css/site.css?v=150220211555" rel="stylesheet"> </head> <body> <header> <div class="container"> <nav class="navbar navbar-expand-lg navbar-light"> <a class="navbar-brand" href="https://waset.org"> <img src="https://cdn.waset.org/static/images/wasetc.png" alt="Open Science Research Excellence" title="Open Science Research Excellence" /> </a> <button class="d-block d-lg-none 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action="https://publications.waset.org/abstracts/search"> <div id="custom-search-input"> <div class="input-group"> <i class="fas fa-search"></i> <input type="text" class="search-query" name="q" placeholder="Author, Title, Abstract, Keywords" value="solid rocket motor"> <input type="submit" class="btn_search" value="Search"> </div> </div> </form> </div> </div> <div class="row mt-3"> <div class="col-sm-3"> <div class="card"> <div class="card-body"><strong>Commenced</strong> in January 2007</div> </div> </div> <div class="col-sm-3"> <div class="card"> <div class="card-body"><strong>Frequency:</strong> Monthly</div> </div> </div> <div class="col-sm-3"> <div class="card"> <div class="card-body"><strong>Edition:</strong> International</div> </div> </div> <div class="col-sm-3"> <div class="card"> <div class="card-body"><strong>Paper Count:</strong> 3220</div> </div> </div> </div> <h1 class="mt-3 mb-3 text-center" style="font-size:1.6rem;">Search results for: solid rocket motor</h1> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">3220</span> Design and Development of Hybrid Rocket Motor</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Aniket%20Aaba%20Kadam">Aniket Aaba Kadam</a>, <a href="https://publications.waset.org/abstracts/search?q=Manish%20Mangesh%20Panchal"> Manish Mangesh Panchal</a>, <a href="https://publications.waset.org/abstracts/search?q=Roushan%20Ashit%20Sharma"> Roushan Ashit Sharma</a> </p> <p class="card-text"><strong>Abstract:</strong></p> This project focuses on the design and development of a lab-scale hybrid rocket motor to accurately determine the regression rate of a fuel/oxidizer combination consisting of solid paraffin and gaseous oxygen (GOX). Hybrid motors offer the advantage of on-demand thrust control over both solid and liquid systems in certain applications. The thermodynamic properties of the propellant combination were calculated using NASA CEA at different chamber pressures and corresponding O/F values to determine initial operating conditions with suitable peak temperatures and optimal O/F values. The project also includes the design of the injector orifice and the determination of the final design configurations of the motor casing, pressure control setup, and valve configuration. This research will be valuable in advancing the understanding of paraffin-based propulsion and improving the performance of hybrid rocket motors. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=hybrid%20rocket" title="hybrid rocket">hybrid rocket</a>, <a href="https://publications.waset.org/abstracts/search?q=NASA%20CEA" title=" NASA CEA"> NASA CEA</a>, <a href="https://publications.waset.org/abstracts/search?q=injector" title=" injector"> injector</a>, <a href="https://publications.waset.org/abstracts/search?q=thrust%20control" title=" thrust control"> thrust control</a> </p> <a href="https://publications.waset.org/abstracts/166470/design-and-development-of-hybrid-rocket-motor" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/166470.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">103</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">3219</span> Failure Analysis: Solid Rocket Motor Type “Candy” - Explosion in a Static Test</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Diego%20Romero">Diego Romero</a>, <a href="https://publications.waset.org/abstracts/search?q=Fabio%20Rojas"> Fabio Rojas</a>, <a href="https://publications.waset.org/abstracts/search?q=J.%20Alejandro%20Urrego"> J. Alejandro Urrego</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The sounding rockets are aerospace vehicles that were developed in the mid-20th century, and Colombia has been involved in research that was carried out with the aim of innovating with this technology. The rockets are university research programs with the collaboration of the local government, with a simple strategy, develop and reduce the greatest costs associated with the production of a kind type of technology. In this way, in this document presents the failure analysis of a solid rocket motor, with the real compatibly to reach the thermosphere with a low-cost fuel. This solid rocket motor is the latest development of the Uniandes Aerospace Project (PUA for its Spanish acronym), an undergraduate and postgraduate research group at Universidad de los Andes (Bogotá, Colombia), dedicated to incurring in this type of technology. This motor has been carried out on Candy-type solid fuel, which is a compound of potassium nitrate and sorbitol, and the investigation has allowed the production of solid motors powerful enough to reach space, and which represents a unique technological advance in Latin America and an important development in experimental rocketry.To outline the main points the explosion in a static test is an important to explore and demonstrate the ways to develop technology, methodologies, production and manufacturing, being a solid rocket motor with 30 kN of thrust. In conclusion, this analysis explores different fields such as: design, manufacture, materials, production, first fire and more, with different engineering tools with principal objective find root failure. Following the engineering analysis methodology, was possible to design a new version of motor, with learned lessons new manufacturing specification, therefore, when publishing this project, it is intended to be a reference for future research in this field and benefit the industry. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=candy%20propellant" title="candy propellant">candy propellant</a>, <a href="https://publications.waset.org/abstracts/search?q=candy%20rockets" title=" candy rockets"> candy rockets</a>, <a href="https://publications.waset.org/abstracts/search?q=explosion" title=" explosion"> explosion</a>, <a href="https://publications.waset.org/abstracts/search?q=failure%20analysis" title=" failure analysis"> failure analysis</a>, <a href="https://publications.waset.org/abstracts/search?q=static%20test" title=" static test"> static test</a>, <a href="https://publications.waset.org/abstracts/search?q=solid%20rocket%20motor" title=" solid rocket motor"> solid rocket motor</a> </p> <a href="https://publications.waset.org/abstracts/128742/failure-analysis-solid-rocket-motor-type-candy-explosion-in-a-static-test" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/128742.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">161</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">3218</span> A Finite Element Method Simulation for Rocket Motor Material Selection</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=T.%20Kritsana">T. Kritsana</a>, <a href="https://publications.waset.org/abstracts/search?q=P.%20Sawitri"> P. Sawitri</a>, <a href="https://publications.waset.org/abstracts/search?q=P.%20Teeratas"> P. Teeratas</a> </p> <p class="card-text"><strong>Abstract:</strong></p> This article aims to study the effect of pressure on rocket motor case by Finite Element Method simulation to select optimal material in rocket motor manufacturing process. In this study, cylindrical tubes with outside diameter of 122 mm and thickness of 3 mm are used for simulation. Defined rocket motor case materials are AISI4130, AISI1026, AISI1045, AL2024 and AL7075. Internal pressure used for the simulation is 22 MPa. The result from Finite Element Method shows that at a pressure of 22 MPa rocket motor case produced by AISI4130, AISI1045 and AL7075 can be used. A comparison of the result between AISI4130, AISI1045 and AL7075 shows that AISI4130 has minimum principal stress and confirm the results of Finite Element Method by the used of calculation method found that, the results from Finite Element Method has good reliability. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=rocket%20motor%20case" title="rocket motor case">rocket motor case</a>, <a href="https://publications.waset.org/abstracts/search?q=finite%20element%20method" title=" finite element method"> finite element method</a>, <a href="https://publications.waset.org/abstracts/search?q=principal%20stress" title=" principal stress"> principal stress</a>, <a href="https://publications.waset.org/abstracts/search?q=simulation" title=" simulation"> simulation</a> </p> <a href="https://publications.waset.org/abstracts/12993/a-finite-element-method-simulation-for-rocket-motor-material-selection" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/12993.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">449</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">3217</span> Design and Burnback Analysis of Three Dimensional Modified Star Grain</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Almostafa%20Abdelaziz">Almostafa Abdelaziz</a>, <a href="https://publications.waset.org/abstracts/search?q=Liang%20Guozhu"> Liang Guozhu</a>, <a href="https://publications.waset.org/abstracts/search?q=Anwer%20Elsayed"> Anwer Elsayed</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The determination of grain geometry is an important and critical step in the design of solid propellant rocket motor. In this study, the design process involved parametric geometry modeling in CAD, MATLAB coding of performance prediction and 2D star grain ignition experiment. The 2D star grain burnback achieved by creating new surface via each web increment and calculating geometrical properties at each step. The 2D star grain is further modified to burn as a tapered 3D star grain. Zero dimensional method used to calculate the internal ballistic performance. Experimental and theoretical results were compared in order to validate the performance prediction of the solid rocket motor. The results show that the usage of 3D grain geometry will decrease the pressure inside the combustion chamber and enhance the volumetric loading ratio. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=burnback%20analysis" title="burnback analysis">burnback analysis</a>, <a href="https://publications.waset.org/abstracts/search?q=rocket%20motor" title=" rocket motor"> rocket motor</a>, <a href="https://publications.waset.org/abstracts/search?q=star%20grain" title=" star grain"> star grain</a>, <a href="https://publications.waset.org/abstracts/search?q=three%20dimensional%20grains" title=" three dimensional grains"> three dimensional grains</a> </p> <a href="https://publications.waset.org/abstracts/82081/design-and-burnback-analysis-of-three-dimensional-modified-star-grain" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/82081.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">245</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">3216</span> Artificial Intelligence and Machine Vision-Based Defect Detection Methodology for Solid Rocket Motor Propellant Grains</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Sandip%20Suman">Sandip Suman</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Mechanical defects (cracks, voids, irregularities) in rocket motor propellant are not new and it is induced due to various reasons, which could be an improper manufacturing process, lot-to-lot variation in chemicals or just the natural aging of the products. These defects are normally identified during the examination of radiographic films by quality inspectors. However, a lot of times, these defects are under or over-classified by human inspectors, which leads to unpredictable performance during lot acceptance tests and significant economic loss. The human eye can only visualize larger cracks and defects in the radiographs, and it is almost impossible to visualize every small defect through the human eye. A different artificial intelligence-based machine vision methodology has been proposed in this work to identify and classify the structural defects in the radiographic films of rocket motors with solid propellant. The proposed methodology can extract the features of defects, characterize them, and make intelligent decisions for acceptance or rejection as per the customer requirements. This will automatize the defect detection process during manufacturing with human-like intelligence. It will also significantly reduce production downtime and help to restore processes in the least possible time. The proposed methodology is highly scalable and can easily be transferred to various products and processes. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=artificial%20intelligence" title="artificial intelligence">artificial intelligence</a>, <a href="https://publications.waset.org/abstracts/search?q=machine%20vision" title=" machine vision"> machine vision</a>, <a href="https://publications.waset.org/abstracts/search?q=defect%20detection" title=" defect detection"> defect detection</a>, <a href="https://publications.waset.org/abstracts/search?q=rocket%20motor%20propellant%20grains" title=" rocket motor propellant grains"> rocket motor propellant grains</a> </p> <a href="https://publications.waset.org/abstracts/168782/artificial-intelligence-and-machine-vision-based-defect-detection-methodology-for-solid-rocket-motor-propellant-grains" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/168782.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">98</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">3215</span> Experimental Investigation of Hybrid Rocket Motor: Ignition, Throttling and Re-Ignition Phenomena</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=A.%20El-S.%20Makled">A. El-S. Makled</a>, <a href="https://publications.waset.org/abstracts/search?q=M.%20K.%20Al-Tamimi"> M. K. Al-Tamimi</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Ignition phenomena are of great interest area over the past many years, and it has a direct impact on many propulsion and combustion applications. The direct goal of the paper is to realize and evaluate a functioning ignition method, shut-off, throttling and re-start operations for the hybrid rocket motor. A small-scale hybrid rocket motor (SSHRM) is designed, manufactured, demonstrated at various operating conditions and finally equipped for laboratory firing tests with high level of safety. Various solid fuel grains as Polymethyle-methacrylate (PMMA) and Polyethylene (PE) are selected, and it is decided to use the commercial gaseous oxygen (GO2) for its availability and low cost. Examine different types of ignition methods, pyrotechnic charge, fuse wire, heat wire and finally hot oxidizer method by using the heat exchanger, which are proposed as very safe ignition methods. Finally; recognize phenomena of throttling and re-start operations. Ignition by hot GO2 impingement is proved to be a very attractive ignition method for laboratory SSHRM, for its high safety, reliability and acceptable delay time. Finally; the throttling and re-start operations are demonstrated several times and can be carried out more easily with hot air ignition method. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=hybrid%20rocket%20motor" title="hybrid rocket motor">hybrid rocket motor</a>, <a href="https://publications.waset.org/abstracts/search?q=ignition%20system" title=" ignition system"> ignition system</a>, <a href="https://publications.waset.org/abstracts/search?q=re-start%20phenomena" title=" re-start phenomena"> re-start phenomena</a>, <a href="https://publications.waset.org/abstracts/search?q=throttling" title=" throttling"> throttling</a> </p> <a href="https://publications.waset.org/abstracts/72481/experimental-investigation-of-hybrid-rocket-motor-ignition-throttling-and-re-ignition-phenomena" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/72481.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">301</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">3214</span> Hybrid Rocket Motor Performance Parameters: Theoretical and Experimental Evaluation</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=A.%20El-S.%20Makled">A. El-S. Makled</a>, <a href="https://publications.waset.org/abstracts/search?q=M.%20K.%20Al-Tamimi"> M. K. Al-Tamimi</a> </p> <p class="card-text"><strong>Abstract:</strong></p> A mathematical model to predict the performance parameters (thrusts, chamber pressures, fuel mass flow rates, mixture ratios, and regression rates during firing time) of hybrid rocket motor (HRM) is evaluated. The internal ballistic (IB) hybrid combustion model assumes that the solid fuel surface regression rate is controlled only by heat transfer (convective and radiative) from flame zone to solid fuel burning surface. A laboratory HRM is designed, manufactured, and tested for low thrust profile space missions (10-15 N) and for validating the mathematical model (computer program). The polymer material and gaseous oxidizer which are selected for this experimental work are polymethyle-methacrylate (PMMA) and polyethylene (PE) as solid fuel grain and gaseous oxygen (GO<sub>2</sub>) as oxidizer. The variation of various operational parameters with time is determined systematically and experimentally in firing of up to 20 seconds, and an average combustion efficiency of 95% of theory is achieved, which was the goal of these experiments. The comparison between recording fire data and predicting analytical parameters shows good agreement with the error that does not exceed 4.5% during all firing time. The current mathematical (computer) code can be used as a powerful tool for HRM analytical design parameters. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=hybrid%20combustion" title="hybrid combustion">hybrid combustion</a>, <a href="https://publications.waset.org/abstracts/search?q=internal%20ballistics" title=" internal ballistics"> internal ballistics</a>, <a href="https://publications.waset.org/abstracts/search?q=hybrid%20rocket%20motor" title=" hybrid rocket motor"> hybrid rocket motor</a>, <a href="https://publications.waset.org/abstracts/search?q=performance%20parameters" title=" performance parameters"> performance parameters</a> </p> <a href="https://publications.waset.org/abstracts/60078/hybrid-rocket-motor-performance-parameters-theoretical-and-experimental-evaluation" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/60078.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">311</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">3213</span> Burnback Analysis of Star Grain Using Level-Set Technique</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Ali%20Yasin">Ali Yasin</a>, <a href="https://publications.waset.org/abstracts/search?q=Ali%20Kamran"> Ali Kamran</a>, <a href="https://publications.waset.org/abstracts/search?q=Muhammad%20Safdar"> Muhammad Safdar</a> </p> <p class="card-text"><strong>Abstract:</strong></p> In order to reduce the hefty cost involved in terms of time and project cost, the development and application of advanced numerical tools to address the burn-back analysis problem in solid rocket motor design and development is the need of time. Several advanced numerical schemes have been developed in recent times, but their usage in the design of propellant grain of solid rocket motors is very rare. In this paper, an advanced numerical technique named the Level-Set method has been utilized for the burn-back analysis of star grain to study the effect of geometrical parameters on ballistic performance indicators such as solid loading, neutrality, and sliver percentage. In the level set technique, simple finite difference methods may fail quickly and require more sophisticated non-oscillatory schemes for feasible long-time simulation. For internal ballistic calculations, a simplified equilibrium pressure method is utilized. Preliminary results of the operative conditions, for all the combustion time, of star grain burn-back using level set techniques are compared with published results using CAD technique to test the developed numerical model. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=solid%20rocket%20motor" title="solid rocket motor">solid rocket motor</a>, <a href="https://publications.waset.org/abstracts/search?q=internal%20ballistic" title=" internal ballistic"> internal ballistic</a>, <a href="https://publications.waset.org/abstracts/search?q=level-set%20technique" title=" level-set technique"> level-set technique</a>, <a href="https://publications.waset.org/abstracts/search?q=star%20grain" title=" star grain"> star grain</a> </p> <a href="https://publications.waset.org/abstracts/156519/burnback-analysis-of-star-grain-using-level-set-technique" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/156519.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">123</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">3212</span> A Spatial Perspective on the Metallized Combustion Aspect of Rockets</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Chitresh%20Prasad">Chitresh Prasad</a>, <a href="https://publications.waset.org/abstracts/search?q=Arvind%20Ramesh"> Arvind Ramesh</a>, <a href="https://publications.waset.org/abstracts/search?q=Aditya%20Virkar"> Aditya Virkar</a>, <a href="https://publications.waset.org/abstracts/search?q=Karan%20Dholkaria"> Karan Dholkaria</a>, <a href="https://publications.waset.org/abstracts/search?q=Vinayak%20Malhotra"> Vinayak Malhotra</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Solid Propellant Rocket is a rocket that utilises a combination of a solid Oxidizer and a solid Fuel. Success in Solid Rocket Motor design and development depends significantly on knowledge of burning rate behaviour of the selected solid propellant under all motor operating conditions and design limit conditions. Most Solid Motor Rockets consist of the Main Engine, along with multiple Boosters that provide an additional thrust to the space-bound vehicle. Though widely used, they have been eclipsed by Liquid Propellant Rockets, because of their better performance characteristics. The addition of a catalyst such as Iron Oxide, on the other hand, can drastically enhance the performance of a Solid Rocket. This scientific investigation tries to emulate the working of a Solid Rocket using Sparklers and Energized Candles, with a central Energized Candle acting as the Main Engine and surrounding Sparklers acting as the Booster. The Energized Candle is made of Paraffin Wax, with Magnesium filings embedded in it’s wick. The Sparkler is made up of 45% Barium Nitrate, 35% Iron, 9% Aluminium, 10% Dextrin and the remaining composition consists of Boric Acid. The Magnesium in the Energized Candle, and the combination of Iron and Aluminium in the Sparkler, act as catalysts and enhance the burn rates of both materials. This combustion of Metallized Propellants has an influence over the regression rate of the subject candle. The experimental parameters explored here are Separation Distance, Systematically varying Configuration and Layout Symmetry. The major performance parameter under observation is the Regression Rate of the Energized Candle. The rate of regression is significantly affected by the orientation and configuration of the sparklers, which usually act as heat sources for the energized candle. The Overall Efficiency of any engine is factorised by the thermal and propulsive efficiencies. Numerous efforts have been made to improve one or the other. This investigation focuses on the Orientation of Rocket Motor Design to maximize their Overall Efficiency. The primary objective is to analyse the Flame Spread Rate variations of the energized candle, which resembles the solid rocket propellant used in the first stage of rocket operation thereby affecting the Specific Impulse values in a Rocket, which in turn have a deciding impact on their Time of Flight. Another objective of this research venture is to determine the effectiveness of the key controlling parameters explored. This investigation also emulates the exhaust gas interactions of the Solid Rocket through concurrent ignition of the Energized Candle and Sparklers, and their behaviour is analysed. Modern space programmes intend to explore the universe outside our solar system. To accomplish these goals, it is necessary to design a launch vehicle which is capable of providing incessant propulsion along with better efficiency for vast durations. The main motivation of this study is to enhance Rocket performance and their Overall Efficiency through better designing and optimization techniques, which will play a crucial role in this human conquest for knowledge. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=design%20modifications" title="design modifications">design modifications</a>, <a href="https://publications.waset.org/abstracts/search?q=improving%20overall%20efficiency" title=" improving overall efficiency"> improving overall efficiency</a>, <a href="https://publications.waset.org/abstracts/search?q=metallized%20combustion" title=" metallized combustion"> metallized combustion</a>, <a href="https://publications.waset.org/abstracts/search?q=regression%20rate%20variations" title=" regression rate variations"> regression rate variations</a> </p> <a href="https://publications.waset.org/abstracts/95905/a-spatial-perspective-on-the-metallized-combustion-aspect-of-rockets" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/95905.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">178</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">3211</span> Design, Modeling, Fabrication, and Testing of a Scaled down Hybrid Rocket Engine </h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Pawthawala%20Nancy%20Manish">Pawthawala Nancy Manish</a>, <a href="https://publications.waset.org/abstracts/search?q=Syed%20Alay%20Hashim"> Syed Alay Hashim</a> </p> <p class="card-text"><strong>Abstract:</strong></p> A hybrid rocket is a rocket engine which uses propellants in two different states of matter- one is in solid and the other either gas or liquid. A hybrid rocket exhibit advantages over both liquid rockets and solid rockets especially in terms of simplicity, stop-start-restart capabilities, safety and cost. This paper deals the design and development of a hybrid rocket having paraffin wax as solid fuel and liquid oxygen as oxidizer. Due to variation of pressure in combustion chamber there is significantly change in mass flow rate, burning rate and uneven regression along the length of the grain. This project describes the working model of a hybrid propellant rocket motor. We have designed a hybrid rocket thrust chamber based on the predetermined combustion chamber pressure and the properties of hybrid propellant. This project is all ready in working condition with normal oxygen injector. Now we have planned to modify the injector design to improve the combustion property. We will use spray type injector for injecting the oxidizer. This idea will increase the performance followed by the regression rate of the solid fuel. By employing mass conservation law, oxygen mass flux, oxidizer/fuel ratio and regression rate the thrust coefficient can be obtained for our current design. CATIA V5 R20 is our design software for the complete setup. This project is fully based on experimental evaluation and the collection of combustion and flow parameters. The thrust chamber is made of stainless steel and the duration of test is around 15-20 seconds (Maximum). These experiments indicates that paraffin based fuel provides the opportunity to satisfy a broad range of mission requirements for the next generation of the hybrid rocket system. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=burning%20rate" title="burning rate">burning rate</a>, <a href="https://publications.waset.org/abstracts/search?q=liquid%20oxygen" title=" liquid oxygen"> liquid oxygen</a>, <a href="https://publications.waset.org/abstracts/search?q=mass%20flow%20rate" title=" mass flow rate"> mass flow rate</a>, <a href="https://publications.waset.org/abstracts/search?q=paraffin%20wax%20and%20%20sugar" title=" paraffin wax and sugar"> paraffin wax and sugar</a> </p> <a href="https://publications.waset.org/abstracts/45401/design-modeling-fabrication-and-testing-of-a-scaled-down-hybrid-rocket-engine" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/45401.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">335</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">3210</span> Aging Evaluation of Ammonium Perchlorate/Hydroxyl Terminated Polybutadiene-Based Solid Rocket Engine by Reactive Molecular Dynamics Simulation and Thermal Analysis</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=R.%20F.%20B.%20Gon%C3%A7alves">R. F. B. Gonçalves</a>, <a href="https://publications.waset.org/abstracts/search?q=E.%20N.%20Iwama"> E. N. Iwama</a>, <a href="https://publications.waset.org/abstracts/search?q=J.%20A.%20F.%20F.%20Rocco"> J. A. F. F. Rocco</a>, <a href="https://publications.waset.org/abstracts/search?q=K.%20Iha"> K. Iha</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Propellants based on Hydroxyl Terminated Polybutadiene/Ammonium Perchlorate (HTPB/AP) are the most commonly used in most of the rocket engines used by the Brazilian Armed Forces. This work aimed at the possibility of extending its useful life (currently in 10 years) by performing kinetic-chemical analyzes of its energetic material via Differential Scanning Calorimetry (DSC) and also performing computer simulation of aging process using the software Large-scale Atomic/Molecular Massively Parallel Simulator (LAMMPS). Thermal analysis via DSC was performed in triplicates and in three heating ratios (5 ºC, 10 ºC, and 15 ºC) of rocket motor with 11 years shelf-life, using the Arrhenius equation to obtain its activation energy, using Ozawa and Kissinger kinetic methods, allowing comparison with manufacturing period data (standard motor). In addition, the kinetic parameters of internal pressure of the combustion chamber in 08 rocket engines with 11 years of shelf-life were also acquired, for comparison purposes with the engine start-up data. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=shelf-life" title="shelf-life">shelf-life</a>, <a href="https://publications.waset.org/abstracts/search?q=thermal%20analysis" title=" thermal analysis"> thermal analysis</a>, <a href="https://publications.waset.org/abstracts/search?q=Ozawa%20method" title=" Ozawa method"> Ozawa method</a>, <a href="https://publications.waset.org/abstracts/search?q=Kissinger%20method" title=" Kissinger method"> Kissinger method</a>, <a href="https://publications.waset.org/abstracts/search?q=LAMMPS%20software" title=" LAMMPS software"> LAMMPS software</a>, <a href="https://publications.waset.org/abstracts/search?q=thrust" title=" thrust"> thrust</a> </p> <a href="https://publications.waset.org/abstracts/99235/aging-evaluation-of-ammonium-perchloratehydroxyl-terminated-polybutadiene-based-solid-rocket-engine-by-reactive-molecular-dynamics-simulation-and-thermal-analysis" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/99235.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">127</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">3209</span> Studies on Pre-ignition Chamber Dynamics of Solid Rockets with Different Port Geometries</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=S.%20Vivek">S. Vivek</a>, <a href="https://publications.waset.org/abstracts/search?q=Sharad%20Sharan"> Sharad Sharan</a>, <a href="https://publications.waset.org/abstracts/search?q=R.%20Arvind"> R. Arvind</a>, <a href="https://publications.waset.org/abstracts/search?q=D.%20V.%20Praveen"> D. V. Praveen</a>, <a href="https://publications.waset.org/abstracts/search?q=J.%20Vigneshwar"> J. Vigneshwar</a>, <a href="https://publications.waset.org/abstracts/search?q=S.%20Ajith"> S. Ajith</a>, <a href="https://publications.waset.org/abstracts/search?q=V.%20R.%20Sanal%20Kumar"> V. R. Sanal Kumar</a> </p> <p class="card-text"><strong>Abstract:</strong></p> In this paper numerical studies have been carried out to examine the starting transient flow features of high-performance solid propellant rocket motors with different port geometries but with same propellant loading density. Numerical computations have been carried out using a 3D SST k-ω turbulence model. This code solves standard k-omega turbulence equations with shear flow corrections using a coupled second order implicit unsteady formulation. In the numerical study, a fully implicit finite volume scheme of the compressible, Reynolds-Averaged, Navier-Stokes equations are employed. We have observed from the numerical results that in solid rocket motors with highly loaded propellants having divergent port geometry the hot igniter gases can create pre-ignition thrust oscillations due to flow unsteadiness and recirculation. Under these conditions the convective flux to the surface of the propellant will be enhanced, which will create reattachment point far downstream of the transition region and it will create a situation for secondary ignition and formation of multiple-flame fronts. As a result the effective time required for the complete burning surface area to be ignited comes down drastically giving rise to a high pressurization rate (dp/dt) in the second phase of starting transient. This in effect could lead to starting thrust oscillations and eventually a hard start of the solid rocket motor. We have also observed that the igniter temperature fluctuations will be diminished rapidly and will reach the steady state value faster in the case of solid propellant rocket motors with convergent port than the divergent port irrespective of the igniter total pressure. We have concluded that the thrust oscillations and unexpected thrust spike often observed in solid rockets with non-uniform ports are presumably contributed due to the joint effects of the geometry dependent driving forces, transient burning and the chamber gas dynamics forces. We also concluded that the prudent selection of the port geometry, without altering the propellant loading density, for damping the total temperature fluctuations within the motor is a meaningful objective for the suppression and control of instability and/or pressure/thrust oscillations often observed in solid propellant rocket motors with non-uniform port geometry. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=ignition%20transient" title="ignition transient">ignition transient</a>, <a href="https://publications.waset.org/abstracts/search?q=solid%20rockets" title=" solid rockets"> solid rockets</a>, <a href="https://publications.waset.org/abstracts/search?q=starting%20transient" title=" starting transient"> starting transient</a>, <a href="https://publications.waset.org/abstracts/search?q=thrust%20transient" title=" thrust transient"> thrust transient</a> </p> <a href="https://publications.waset.org/abstracts/35068/studies-on-pre-ignition-chamber-dynamics-of-solid-rockets-with-different-port-geometries" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/35068.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">449</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">3208</span> Static Test Pad for Solid Rocket Motors</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Svanik%20Garg">Svanik Garg</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Static Test Pads are stationary mechanisms that hold a solid rocket motor, measuring the different parameters of its operation including thrust and temperature to better calibrate it for launch. This paper outlines a specific STP designed to test high powered rocket motors with a thrust upwards of 4000N and limited to 6500N. The design includes a specific portable mechanism with cost an integral part of the design process to make it accessible to small scale rocket developers with limited resources. Using curved surfaces and an ergonomic design, the STP has a delicately engineered façade/case with a focus on stability and axial calibration of thrust. This paper describes the design, operation and working of the STP and its widescale uses given the growing market of aviation enthusiasts. Simulations on the CAD model in Fusion 360 provided promising results with a safety factor of 2 established and stress limited along with the load coefficient A PCB was also designed as part of the test pad design process to help obtain results, with visual output and various virtual terminals to collect data of different parameters. The circuitry was simulated using ‘proteus’ and a special virtual interface with auditory commands was also created for accessibility and wide-scale implementation. Along with this description of the design, the paper also emphasizes the design principle behind the STP including a description of its vertical orientation to maximize thrust accuracy along with a stable base to prevent micromovements. Given the rise of students and professionals alike building high powered rockets, the STP described in this paper is an appropriate option, with limited cost, portability, accuracy, and versatility. There are two types of STP’s vertical or horizontal, the one discussed in this paper is vertical to utilize the axial component of thrust. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=static%20test%20pad" title="static test pad">static test pad</a>, <a href="https://publications.waset.org/abstracts/search?q=rocket%20motor" title=" rocket motor"> rocket motor</a>, <a href="https://publications.waset.org/abstracts/search?q=thrust" title=" thrust"> thrust</a>, <a href="https://publications.waset.org/abstracts/search?q=load" title=" load"> load</a>, <a href="https://publications.waset.org/abstracts/search?q=circuit" title=" circuit"> circuit</a>, <a href="https://publications.waset.org/abstracts/search?q=avionics" title=" avionics"> avionics</a>, <a href="https://publications.waset.org/abstracts/search?q=drag" title=" drag"> drag</a> </p> <a href="https://publications.waset.org/abstracts/148080/static-test-pad-for-solid-rocket-motors" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/148080.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">380</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">3207</span> Design and Analysis of Active Rocket Control Systems</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Piotr%20Jerzy%20Rugor">Piotr Jerzy Rugor</a>, <a href="https://publications.waset.org/abstracts/search?q=Julia%20Wajoras"> Julia Wajoras</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The presented work regards a single-stage aerodynamically controlled solid propulsion rocket. Steering a rocket to fly along a predetermined trajectory can be beneficial for minimizing aerodynamic losses and achieved by implementing an active control system on board. In this particular case, a canard configuration has been chosen, although other methods of control have been considered and preemptively analyzed, including non-aerodynamic ones. The objective of this work is to create a system capable of guiding the rocket, focusing on roll stabilization. The paper describes initial analysis of the problem, covers the main challenges of missile guidance and presents data acquired during the experimental study. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=active%20canard%20control%20system" title="active canard control system">active canard control system</a>, <a href="https://publications.waset.org/abstracts/search?q=rocket%20design" title=" rocket design"> rocket design</a>, <a href="https://publications.waset.org/abstracts/search?q=numerical%20simulations" title=" numerical simulations"> numerical simulations</a>, <a href="https://publications.waset.org/abstracts/search?q=flight%20optimization" title=" flight optimization"> flight optimization</a> </p> <a href="https://publications.waset.org/abstracts/78444/design-and-analysis-of-active-rocket-control-systems" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/78444.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">195</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">3206</span> Artificial Neural Network Based Parameter Prediction of Miniaturized Solid Rocket Motor</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Hao%20Yan">Hao Yan</a>, <a href="https://publications.waset.org/abstracts/search?q=Xiaobing%20Zhang"> Xiaobing Zhang</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The working mechanism of miniaturized solid rocket motors (SRMs) is not yet fully understood. It is imperative to explore its unique features. However, there are many disadvantages to using common multi-objective evolutionary algorithms (MOEAs) in predicting the parameters of the miniaturized SRM during its conceptual design phase. Initially, the design variables and objectives are constrained in a lumped parameter model (LPM) of this SRM, which leads to local optima in MOEAs. In addition, MOEAs require a large number of calculations due to their population strategy. Although the calculation time for simulating an LPM just once is usually less than that of a CFD simulation, the number of function evaluations (NFEs) is usually large in MOEAs, which makes the total time cost unacceptably long. Moreover, the accuracy of the LPM is relatively low compared to that of a CFD model due to its assumptions. CFD simulations or experiments are required for comparison and verification of the optimal results obtained by MOEAs with an LPM. The conceptual design phase based on MOEAs is a lengthy process, and its results are not precise enough due to the above shortcomings. An artificial neural network (ANN) based parameter prediction is proposed as a way to reduce time costs and improve prediction accuracy. In this method, an ANN is used to build a surrogate model that is trained with a 3D numerical simulation. In design, the original LPM is replaced by a surrogate model. Each case uses the same MOEAs, in which the calculation time of the two models is compared, and their optimization results are compared with 3D simulation results. Using the surrogate model for the parameter prediction process of the miniaturized SRMs results in a significant increase in computational efficiency and an improvement in prediction accuracy. Thus, the ANN-based surrogate model does provide faster and more accurate parameter prediction for an initial design scheme. Moreover, even when the MOEAs converge to local optima, the time cost of the ANN-based surrogate model is much lower than that of the simplified physical model LPM. This means that designers can save a lot of time during code debugging and parameter tuning in a complex design process. Designers can reduce repeated calculation costs and obtain accurate optimal solutions by combining an ANN-based surrogate model with MOEAs. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=artificial%20neural%20network" title="artificial neural network">artificial neural network</a>, <a href="https://publications.waset.org/abstracts/search?q=solid%20rocket%20motor" title=" solid rocket motor"> solid rocket motor</a>, <a href="https://publications.waset.org/abstracts/search?q=multi-objective%20evolutionary%20algorithm" title=" multi-objective evolutionary algorithm"> multi-objective evolutionary algorithm</a>, <a href="https://publications.waset.org/abstracts/search?q=surrogate%20model" title=" surrogate model"> surrogate model</a> </p> <a href="https://publications.waset.org/abstracts/159614/artificial-neural-network-based-parameter-prediction-of-miniaturized-solid-rocket-motor" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/159614.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">90</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">3205</span> An Experimental Study on the Coupled Heat Source and Heat Sink Effects on Solid Rockets</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Vinayak%20Malhotra">Vinayak Malhotra</a>, <a href="https://publications.waset.org/abstracts/search?q=Samanyu%20Raina"> Samanyu Raina</a>, <a href="https://publications.waset.org/abstracts/search?q=Ajinkya%20Vajurkar"> Ajinkya Vajurkar</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Enhancing the rocket efficiency by controlling the external factors in solid rockets motors has been an active area of research for most of the terrestrial and extra-terrestrial system operations. Appreciable work has been done, but the complexity of the problem has prevented thorough understanding due to heterogenous heat and mass transfer. On record, severe issues have surfaced amounting to irreplaceable loss of mankind, instruments, facilities, and huge amount of money being invested every year. The coupled effect of an external heat source and external heat sink is an aspect yet to be articulated in combustion. Better understanding of this coupled phenomenon will induce higher safety standards, efficient missions, reduced hazard risks, with better designing, validation, and testing. The experiment will help in understanding the coupled effect of an external heat sink and heat source on the burning process, contributing in better combustion and fire safety, which are very important for efficient and safer rocket flights and space missions. Safety is the most prevalent issue in rockets, which assisted by poor combustion efficiency, emphasizes research efforts to evolve superior rockets. This signifies real, engineering, scientific, practical, systems and applications. One potential application is Solid Rocket Motors (S.R.M). The study may help in: (i) Understanding the effect on efficiency of core engines due to the primary boosters if considered as source, (ii) Choosing suitable heat sink materials for space missions so as to vary the efficiency of the solid rocket depending on the mission, (iii) Giving an idea about how the preheating of the successive stage due to previous stage acting as a source may affect the mission. The present work governs the temperature (resultant) and thus the heat transfer which is expected to be non-linear because of heterogeneous heat and mass transfer. The study will deepen the understanding of controlled inter-energy conversions and the coupled effect of external source/sink(s) surrounding the burning fuel eventually leading to better combustion thus, better propulsion. The work is motivated by the need to have enhanced fire safety and better rocket efficiency. The specific objective of the work is to understand the coupled effect of external heat source and sink on propellant burning and to investigate the role of key controlling parameters. Results as of now indicate that there exists a singularity in the coupled effect. The dominance of the external heat sink and heat source decides the relative rocket flight in Solid Rocket Motors (S.R.M). <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=coupled%20effect" title="coupled effect">coupled effect</a>, <a href="https://publications.waset.org/abstracts/search?q=heat%20transfer" title=" heat transfer"> heat transfer</a>, <a href="https://publications.waset.org/abstracts/search?q=sink" title=" sink"> sink</a>, <a href="https://publications.waset.org/abstracts/search?q=solid%20rocket%20motors" title=" solid rocket motors"> solid rocket motors</a>, <a href="https://publications.waset.org/abstracts/search?q=source" title=" source"> source</a> </p> <a href="https://publications.waset.org/abstracts/95362/an-experimental-study-on-the-coupled-heat-source-and-heat-sink-effects-on-solid-rockets" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/95362.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">223</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">3204</span> A Single Stage Rocket Using Solid Fuels in Conventional Propulsion Systems</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=John%20R%20Evans">John R Evans</a>, <a href="https://publications.waset.org/abstracts/search?q=Sook-Ying%20%20Ho"> Sook-Ying Ho</a>, <a href="https://publications.waset.org/abstracts/search?q=Rey%20Chin"> Rey Chin</a> </p> <p class="card-text"><strong>Abstract:</strong></p> This paper describes the research investigations orientated to the starting and propelling of a solid fuel rocket engine which operates as combined cycle propulsion system using three thrust pulses. The vehicle has been designed to minimise the cost of launching small number of Nano/Cube satellites into low earth orbits (LEO). A technology described in this paper is a ground-based launch propulsion system which starts the rocket vertical motion immediately causing air flow to enter the ramjet’s intake. Current technology has a ramjet operation predicted to be able to start high subsonic speed of 280 m/s using a liquid fuel ramjet (LFRJ). The combined cycle engine configuration is in many ways fundamentally different from the LFRJ. A much lower subsonic start speed is highly desirable since the use of a mortar to obtain the latter speed for rocket means a shorter launcher length can be utilized. This paper examines the means and has some performance calculations, including Computational Fluid Dynamics analysis of air-intake at suitable operational conditions, 3-DOF point mass trajectory analysis of multi-pulse propulsion system (where pulse ignition time and thrust magnitude can be controlled), etc. of getting a combined cycle rocket engine use in a single stage vehicle. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=combine%20cycle%20propulsion%20system" title="combine cycle propulsion system">combine cycle propulsion system</a>, <a href="https://publications.waset.org/abstracts/search?q=low%20earth%20orbit%20launch%20vehicle" title=" low earth orbit launch vehicle"> low earth orbit launch vehicle</a>, <a href="https://publications.waset.org/abstracts/search?q=computational%20fluid%20dynamics%20analysis" title=" computational fluid dynamics analysis"> computational fluid dynamics analysis</a>, <a href="https://publications.waset.org/abstracts/search?q=3dof%20trajectory%20analysis" title=" 3dof trajectory analysis "> 3dof trajectory analysis </a> </p> <a href="https://publications.waset.org/abstracts/136487/a-single-stage-rocket-using-solid-fuels-in-conventional-propulsion-systems" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/136487.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">191</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">3203</span> Optimization of Heat Source Assisted Combustion on Solid Rocket Motors</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Minal%20Jain">Minal Jain</a>, <a href="https://publications.waset.org/abstracts/search?q=Vinayak%20Malhotra"> Vinayak Malhotra</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Solid Propellant ignition consists of rapid and complex events comprising of heat generation and transfer of heat with spreading of flames over the entire burning surface area. Proper combustion and thus propulsion depends heavily on the modes of heat transfer characteristics and cavity volume. Fire safety is an integral component of a successful rocket flight failing to which may lead to overall failure of the rocket. This leads to enormous forfeiture in resources viz., money, time, and labor involved. When the propellant is ignited, thrust is generated and the casing gets heated up. This heat adds on to the propellant heat and the casing, if not at proper orientation starts burning as well, leading to the whole rocket being completely destroyed. This has necessitated active research efforts emphasizing a comprehensive study on the inter-energy relations involved for effective utilization of the solid rocket motors for better space missions. Present work is focused on one of the major influential aspects of this detrimental burning which is the presence of an external heat source, in addition to a potential heat source which is already ignited. The study is motivated by the need to ensure better combustion and fire safety presented experimentally as a simplified small-scale mode of a rocket carrying a solid propellant inside a cavity. The experimental setup comprises of a paraffin wax candle as the pilot fuel and incense stick as the external heat source. The candle is fixed and the incense stick position and location is varied to investigate the find the influence of the pilot heat source. Different configurations of the external heat source presence with separation distance are tested upon. Regression rates of the pilot thin solid fuel are noted to fundamentally understand the non-linear heat and mass transfer which is the governing phenomenon. An attempt is made to understand the phenomenon fundamentally and the mechanism governing it. Results till now indicate non-linear heat transfer assisted with the occurrence of flaming transition at selected critical distances. With an increase in separation distance, the effect is noted to drop in a non-monotonic trend. The parametric study results are likely to provide useful physical insight about the governing physics and utilization in proper testing, validation, material selection, and designing of solid rocket motors with enhanced safety. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=combustion" title="combustion">combustion</a>, <a href="https://publications.waset.org/abstracts/search?q=propellant" title=" propellant"> propellant</a>, <a href="https://publications.waset.org/abstracts/search?q=regression" title=" regression"> regression</a>, <a href="https://publications.waset.org/abstracts/search?q=safety" title=" safety"> safety</a> </p> <a href="https://publications.waset.org/abstracts/94979/optimization-of-heat-source-assisted-combustion-on-solid-rocket-motors" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/94979.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">161</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">3202</span> Embedded Digital Image System </h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Dawei%20Li">Dawei Li</a>, <a href="https://publications.waset.org/abstracts/search?q=Cheng%20Liu"> Cheng Liu</a>, <a href="https://publications.waset.org/abstracts/search?q=Yiteng%20Liu"> Yiteng Liu</a> </p> <p class="card-text"><strong>Abstract:</strong></p> This paper introduces an embedded digital image system for Chinese space environment vertical exploration sounding rocket. In order to record the flight status of the sounding rocket as well as the payloads, an onboard embedded image processing system based on ADV212, a JPEG2000 compression chip, is designed in this paper. Since the sounding rocket is not designed to be recovered, all image data should be transmitted to the ground station before the re-entry while the downlink band used for the image transmission is only about 600 kbps. Under the same condition of compression ratio compared with other algorithm, JPEG2000 standard algorithm can achieve better image quality. So JPEG2000 image compression is applied under this condition with a limited downlink data band. This embedded image system supports lossless to 200:1 real time compression, with two cameras to monitor nose ejection and motor separation, and two cameras to monitor boom deployment. The encoder, ADV7182, receives PAL signal from the camera, then output the ITU-R BT.656 signal to ADV212. ADV7182 switches between four input video channels as the program sequence. Two SRAMs are used for Ping-pong operation and one 512 Mb SDRAM for buffering high frame-rate images. The whole image system has the characteristics of low power dissipation, low cost, small size and high reliability, which is rather suitable for this sounding rocket application. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=ADV212" title="ADV212">ADV212</a>, <a href="https://publications.waset.org/abstracts/search?q=image%20system" title=" image system"> image system</a>, <a href="https://publications.waset.org/abstracts/search?q=JPEG2000" title=" JPEG2000"> JPEG2000</a>, <a href="https://publications.waset.org/abstracts/search?q=sounding%20rocket" title=" sounding rocket"> sounding rocket</a> </p> <a href="https://publications.waset.org/abstracts/37615/embedded-digital-image-system" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/37615.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">421</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">3201</span> Machine Learning Algorithms for Rocket Propulsion</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=R%C3%B4mulo%20Eust%C3%A1quio%20Martins%20de%20Souza">Rômulo Eustáquio Martins de Souza</a>, <a href="https://publications.waset.org/abstracts/search?q=Paulo%20Alexandre%20Rodrigues%20de%20Vasconcelos%20Figueiredo"> Paulo Alexandre Rodrigues de Vasconcelos Figueiredo</a> </p> <p class="card-text"><strong>Abstract:</strong></p> In recent years, there has been a surge in interest in applying artificial intelligence techniques, particularly machine learning algorithms. Machine learning is a data-analysis technique that automates the creation of analytical models, making it especially useful for designing complex situations. As a result, this technology aids in reducing human intervention while producing accurate results. This methodology is also extensively used in aerospace engineering since this is a field that encompasses several high-complexity operations, such as rocket propulsion. Rocket propulsion is a high-risk operation in which engine failure could result in the loss of life. As a result, it is critical to use computational methods capable of precisely representing the spacecraft's analytical model to guarantee its security and operation. Thus, this paper describes the use of machine learning algorithms for rocket propulsion to aid the realization that this technique is an efficient way to deal with challenging and restrictive aerospace engineering activities. The paper focuses on three machine-learning-aided rocket propulsion applications: set-point control of an expander-bleed rocket engine, supersonic retro-propulsion of a small-scale rocket, and leak detection and isolation on rocket engine data. This paper describes the data-driven methods used for each implementation in depth and presents the obtained results. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=data%20analysis" title="data analysis">data analysis</a>, <a href="https://publications.waset.org/abstracts/search?q=modeling" title=" modeling"> modeling</a>, <a href="https://publications.waset.org/abstracts/search?q=machine%20learning" title=" machine learning"> machine learning</a>, <a href="https://publications.waset.org/abstracts/search?q=aerospace" title=" aerospace"> aerospace</a>, <a href="https://publications.waset.org/abstracts/search?q=rocket%20propulsion" title=" rocket propulsion"> rocket propulsion</a> </p> <a href="https://publications.waset.org/abstracts/168232/machine-learning-algorithms-for-rocket-propulsion" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/168232.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">115</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">3200</span> Winged Test Rocket with Fully Autonomous Guidance and Control for Realizing Reusable Suborbital Vehicle</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Koichi%20Yonemoto">Koichi Yonemoto</a>, <a href="https://publications.waset.org/abstracts/search?q=Hiroshi%20Yamasaki"> Hiroshi Yamasaki</a>, <a href="https://publications.waset.org/abstracts/search?q=Masatomo%20Ichige"> Masatomo Ichige</a>, <a href="https://publications.waset.org/abstracts/search?q=Yusuke%20Ura"> Yusuke Ura</a>, <a href="https://publications.waset.org/abstracts/search?q=Guna%20S.%20Gossamsetti"> Guna S. Gossamsetti</a>, <a href="https://publications.waset.org/abstracts/search?q=Takumi%20Ohki"> Takumi Ohki</a>, <a href="https://publications.waset.org/abstracts/search?q=Kento%20Shirakata"> Kento Shirakata</a>, <a href="https://publications.waset.org/abstracts/search?q=Ahsan%20R.%20Choudhuri"> Ahsan R. Choudhuri</a>, <a href="https://publications.waset.org/abstracts/search?q=Shinji%20Ishimoto"> Shinji Ishimoto</a>, <a href="https://publications.waset.org/abstracts/search?q=Takashi%20Mugitani"> Takashi Mugitani</a>, <a href="https://publications.waset.org/abstracts/search?q=Hiroya%20Asakawa"> Hiroya Asakawa</a>, <a href="https://publications.waset.org/abstracts/search?q=Hideaki%20Nanri"> Hideaki Nanri</a> </p> <p class="card-text"><strong>Abstract:</strong></p> This paper presents the strategic development plan of winged rockets WIRES (WInged REusable Sounding rocket) aiming at unmanned suborbital winged rocket for demonstrating future fully reusable space transportation technologies, such as aerodynamics, Navigation, Guidance and Control (NGC), composite structure, propulsion system, and cryogenic tanks etc., by universities in collaboration with government and industries, as well as the past and current flight test results. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=autonomous%20guidance%20and%20control" title="autonomous guidance and control">autonomous guidance and control</a>, <a href="https://publications.waset.org/abstracts/search?q=reusable%20rocket" title=" reusable rocket"> reusable rocket</a>, <a href="https://publications.waset.org/abstracts/search?q=space%20transportation%20system" title=" space transportation system"> space transportation system</a>, <a href="https://publications.waset.org/abstracts/search?q=suborbital%20vehicle" title=" suborbital vehicle"> suborbital vehicle</a>, <a href="https://publications.waset.org/abstracts/search?q=winged%20rocket" title=" winged rocket"> winged rocket</a> </p> <a href="https://publications.waset.org/abstracts/40850/winged-test-rocket-with-fully-autonomous-guidance-and-control-for-realizing-reusable-suborbital-vehicle" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/40850.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">365</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">3199</span> Simulation and Design of an Aerospace Mission Powered by “Candy” Type Fuel Engines</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=N.%20Hern%C3%A1ndez%20Huertas">N. Hernández Huertas</a>, <a href="https://publications.waset.org/abstracts/search?q=F.%20Rojas%20Mora"> F. Rojas Mora</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Sounding rockets are aerospace vehicles that were developed in the mid-20th century, and since then numerous investigations have been executed with the aim of innovate in this type of technology. However, the costs associated to the production of this type of technology are usually quite high, and therefore the challenge that exists today is to be able to reduce them. In this way, the main objective of this document is to present the design process of a Colombian aerospace mission capable to reach the thermosphere using low-cost “Candy” type solid fuel engines. This mission is the latest development of the Uniandes Aerospace Project (PUA for its Spanish acronym), which is an undergraduate and postgraduate research group at Universidad de los Andes (Bogotá, Colombia), dedicated to incurring in this type of technology. In this way, the investigations that have been carried out on Candy-type solid fuel, which is a compound of potassium nitrate and sorbitol, have allowed the production of engines powerful enough to reach space, and which represents a unique technological advance in Latin America and an important development in experimental rocketry. In this way, following the engineering iterative design methodology was possible to design a 2-stage sounding rocket with 1 solid fuel engine in each one, which was then simulated in RockSim V9.0 software and reached an apogee of approximately 150 km above sea level. Similarly, a speed equal to 5 Mach was obtained, which after performing a finite element analysis, it was shown that the rocket is strong enough to be able to withstand such speeds. Under these premises, it was demonstrated that it is possible to build a high-power aerospace mission at low cost, using Candy-type solid fuel engines. For this reason, the feasibility of carrying out similar missions clearly depends on the ability to replicate the engines in the best way, since as mentioned above, the design of the rocket is adequate to reach supersonic speeds and reach space. Consequently, with a team of at least 3 members, the mission can be obtained in less than 3 months. Therefore, when publishing this project, it is intended to be a reference for future research in this field and benefit the industry. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=aerospace%20missions" title="aerospace missions">aerospace missions</a>, <a href="https://publications.waset.org/abstracts/search?q=Candy%20type%20solid%20propellant%20engines" title=" Candy type solid propellant engines"> Candy type solid propellant engines</a>, <a href="https://publications.waset.org/abstracts/search?q=design%20of%20solid%20rockets" title=" design of solid rockets"> design of solid rockets</a>, <a href="https://publications.waset.org/abstracts/search?q=experimental%20rocketry" title=" experimental rocketry"> experimental rocketry</a>, <a href="https://publications.waset.org/abstracts/search?q=low%20costs%20missions" title=" low costs missions"> low costs missions</a> </p> <a href="https://publications.waset.org/abstracts/126878/simulation-and-design-of-an-aerospace-mission-powered-by-candy-type-fuel-engines" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/126878.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">111</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">3198</span> Wall Heat Flux Mapping in Liquid Rocket Combustion Chamber with Different Jet Impingement Angles</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=O.%20S.%20Pradeep">O. S. Pradeep</a>, <a href="https://publications.waset.org/abstracts/search?q=S.%20Vigneshwaran"> S. Vigneshwaran</a>, <a href="https://publications.waset.org/abstracts/search?q=K.%20Praveen%20Kumar"> K. Praveen Kumar</a>, <a href="https://publications.waset.org/abstracts/search?q=K.%20Jeyendran"> K. Jeyendran</a>, <a href="https://publications.waset.org/abstracts/search?q=V.%20R.%20Sanal%20Kumar"> V. R. Sanal Kumar</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The influence of injector attitude on wall heat flux plays an important role in predicting the start-up transient and also determining the combustion chamber wall durability of liquid rockets. In this paper comprehensive numerical studies have been carried out on an idealized liquid rocket combustion chamber to examine the transient wall heat flux during its start-up transient at different injector attitude. Numerical simulations have been carried out with the help of a validated 2d axisymmetric, double precision, pressure-based, transient, species transport, SST k-omega model with laminar finite rate model for governing turbulent-chemistry interaction for four cases with different jet intersection angles, viz., 0<sup>o</sup>, 30<sup>o</sup>, 45<sup>o</sup>, and 60<sup>o</sup>. We concluded that the jets intersection angle is having a bearing on the time and location of the maximum wall-heat flux zone of the liquid rocket combustion chamber during the start-up transient. We also concluded that the wall heat flux mapping in liquid rocket combustion chamber during the start-up transient is a meaningful objective for the chamber wall material selection and the lucrative design optimization of the combustion chamber for improving the payload capability of the rocket.   <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=combustion%20chamber" title="combustion chamber">combustion chamber</a>, <a href="https://publications.waset.org/abstracts/search?q=injector" title=" injector"> injector</a>, <a href="https://publications.waset.org/abstracts/search?q=liquid%20rocket" title=" liquid rocket"> liquid rocket</a>, <a href="https://publications.waset.org/abstracts/search?q=rocket%20engine%20wall%20heat%20flux" title=" rocket engine wall heat flux"> rocket engine wall heat flux</a> </p> <a href="https://publications.waset.org/abstracts/62084/wall-heat-flux-mapping-in-liquid-rocket-combustion-chamber-with-different-jet-impingement-angles" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/62084.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">487</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">3197</span> Design and Implementation Guidance System of Guided Rocket RKX-200 Using Optimal Guidance Law</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Amalia%20Sholihati">Amalia Sholihati</a>, <a href="https://publications.waset.org/abstracts/search?q=Bambang%20Riyanto%20Trilaksono"> Bambang Riyanto Trilaksono</a> </p> <p class="card-text"><strong>Abstract:</strong></p> As an island nation, is a necessity for the Republic of Indonesia to have a capable military defense on land, sea or air that the development of military weapons such as rockets for air defense becomes very important. RKX rocket-200 is one of the guided missiles which are developed by consortium Indonesia and coordinated by LAPAN that serve to intercept the target. RKX-200 is designed to have the speed of Mach 0.5-0.9. RKX rocket-200 belongs to the category two-stage rocket that control is carried out on the second stage when the rocket has separated from the booster. The requirement for better performance to intercept missiles with higher maneuverability continues to push optimal guidance law development, which is derived from non-linear equations. This research focused on the design and implementation of a guidance system based OGL on the rocket RKX-200 while considering the limitation of rockets such as aerodynamic rocket and actuator. Guided missile control system has three main parts, namely, guidance system, navigation system and autopilot systems. As for other parts such as navigation systems and other supporting simulated on MATLAB based on the results of previous studies. In addition to using the MATLAB simulation also conducted testing with hardware-based ARM TWR-K60D100M conjunction with a navigation system and nonlinear models in MATLAB using Hardware-in-the-Loop Simulation (HILS). <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=RKX-200" title="RKX-200">RKX-200</a>, <a href="https://publications.waset.org/abstracts/search?q=guidance%20system" title=" guidance system"> guidance system</a>, <a href="https://publications.waset.org/abstracts/search?q=optimal%20guidance%20law" title=" optimal guidance law"> optimal guidance law</a>, <a href="https://publications.waset.org/abstracts/search?q=Hils" title=" Hils"> Hils</a> </p> <a href="https://publications.waset.org/abstracts/57098/design-and-implementation-guidance-system-of-guided-rocket-rkx-200-using-optimal-guidance-law" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/57098.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">254</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">3196</span> Substructure Method for Thermal-Stress Analysis of Liquid-Propellant Rocket Engine Combustion Chamber</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Olga%20V.%20Korotkaya">Olga V. Korotkaya</a> </p> <p class="card-text"><strong>Abstract:</strong></p> This article is devoted to an important problem of calculation of deflected mode of the combustion chamber and the nozzle end of a new liquid-propellant rocket cruise engine. A special attention is given to the methodology of calculation. Three operating modes are considered. The analysis has been conducted in ANSYS software. The methods of conducted research are mathematical modelling, substructure method, cyclic symmetry, and finite element method. The calculation has been carried out to order of S. P. Korolev Rocket and Space Corporation «Energia». The main results are practical. Proposed methodology and created models would be able to use for a wide range of strength problems. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=combustion%20chamber" title="combustion chamber">combustion chamber</a>, <a href="https://publications.waset.org/abstracts/search?q=cyclic%20symmetry" title=" cyclic symmetry"> cyclic symmetry</a>, <a href="https://publications.waset.org/abstracts/search?q=finite%20element%20method" title=" finite element method"> finite element method</a>, <a href="https://publications.waset.org/abstracts/search?q=liquid-propellant%20rocket%20engine" title=" liquid-propellant rocket engine"> liquid-propellant rocket engine</a>, <a href="https://publications.waset.org/abstracts/search?q=nozzle%20end" title=" nozzle end"> nozzle end</a>, <a href="https://publications.waset.org/abstracts/search?q=substructure" title=" substructure"> substructure</a> </p> <a href="https://publications.waset.org/abstracts/3281/substructure-method-for-thermal-stress-analysis-of-liquid-propellant-rocket-engine-combustion-chamber" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/3281.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">506</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">3195</span> Study of Transformer and Motor Winding under Pulsed Power Application</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Arijit%20Basuray">Arijit Basuray</a>, <a href="https://publications.waset.org/abstracts/search?q=Saibal%20Chatterjee"> Saibal Chatterjee</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Pulsed Power in the form of Recurrent Surge Generator (RSG) can be used for testing various parameters of Motor or Transformer windings including inter-turn, interlayer insulation. Windings with solid insulation in motor and transformer have many interfaces and undesirable defects, and these defects can be exposed under this nondestructive testing methodology. Due to rapid development in power electronics variable frequency drives (VFD), Dry Type or cast resin Transformer used with PWM Sine wave inverters for solar power, solid insulation system used nowadays are shifting more and more to a high-frequency application. Authors have used the recurrent surge generator for testing winding integrity as well as Partial Discharge(PD) at fast rising voltage enabling PD measurement at closer situation under which the insulation system is supposed to work. Authors have discussed test results on a different system with recurrent surge voltages of different rise time. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=fast%20rising%20voltage" title="fast rising voltage">fast rising voltage</a>, <a href="https://publications.waset.org/abstracts/search?q=partial%20discharge" title=" partial discharge"> partial discharge</a>, <a href="https://publications.waset.org/abstracts/search?q=pulsed%20power" title=" pulsed power"> pulsed power</a>, <a href="https://publications.waset.org/abstracts/search?q=recurrent%20surge%20generator" title=" recurrent surge generator"> recurrent surge generator</a>, <a href="https://publications.waset.org/abstracts/search?q=solid%20insulation" title=" solid insulation"> solid insulation</a> </p> <a href="https://publications.waset.org/abstracts/66468/study-of-transformer-and-motor-winding-under-pulsed-power-application" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/66468.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">273</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">3194</span> An Investigation of How Salad Rocket May Provide Its Own Defence Against Spoilage Bacteria</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Huda%20Aldossari">Huda Aldossari</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Members of the Brassicaceae family, such as rocket species, have high concentrations of glucosinolates (GLSs). GSLs and isothiocyanates (ITCs), the product of GLSs hydrolysis, are the most influential compounds that affect flavour in rocket species. Aside from their contribution to the flavour, GSLs and ITCs are of particular interest due to their potential ability to inhibit the growth of human pathogenic bacteria such as E. coli O157. Quantitative and qualitative analysis of glucosinolate compounds in rocket extracts was obtained by Liquid Chromatography-Mass Spectrometry (LC–MS).Each individual component of non-volatile GLSs and ITCs was isolated by High-Performance Liquid Chromatography (HPLC) fractionation. The identity and purity of each fraction were confirmed using Ultra High-Performance Liquid Chromatography (UPLC). The separation of glucosinolates in the complex rocket extractions was performed by optimizing a HPLC fractionation method through changing the mobile phase composition, solvent gradient, and the flow rate. As a result, six glucosinolates compounds (Glucosativin, 4-Methoxyglucobrassicin, Glucotropaeolin GTP, Glucoiberin GIB, Diglucothiobenin, and Sinigrin) have been isolated, identified and quantified in the complex samples. This step aims to evaluate the antibacterial activity of glucosinolates and their enzymatic hydrolysis against bacterial growth of E.coli k12. Therefore, fractions from this study will be used to determine the most active compounds by investigating the efficacy of each component of GLSs and ITCs at inhibiting bacterial growth. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=rocket" title="rocket">rocket</a>, <a href="https://publications.waset.org/abstracts/search?q=glucosinolates" title=" glucosinolates"> glucosinolates</a>, <a href="https://publications.waset.org/abstracts/search?q=E.coli%20k12." title=" E.coli k12."> E.coli k12.</a>, <a href="https://publications.waset.org/abstracts/search?q=HPLC%20fractionatio" title=" HPLC fractionatio"> HPLC fractionatio</a> </p> <a href="https://publications.waset.org/abstracts/158926/an-investigation-of-how-salad-rocket-may-provide-its-own-defence-against-spoilage-bacteria" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/158926.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">96</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">3193</span> Induction Motor Analysis Using LabVIEW</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=E.%20Ramprasath">E. Ramprasath</a>, <a href="https://publications.waset.org/abstracts/search?q=P.%20Manojkumar"> P. Manojkumar</a>, <a href="https://publications.waset.org/abstracts/search?q=P.%20Veena"> P. Veena</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Proposed paper dealt with the modelling and analysis of induction motor based on the mathematical expression using the graphical programming environment of Laboratory Virtual Instrument Engineering Workbench (LabVIEW). Induction motor modelling with the mathematical expression enables the motor to be simulated with the various required parameters. Owing to the invention of variable speed drives study about the induction motor characteristics became complex.In this simulation motor internal parameter such as stator resistance and reactance, rotor resistance and reactance, phase voltage, frequency and losses will be given as input. By varying the speed of motor corresponding parameters can be obtained they are input power, output power, efficiency, torque induced, slip and current. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=induction%20motor" title="induction motor">induction motor</a>, <a href="https://publications.waset.org/abstracts/search?q=LabVIEW%20software" title=" LabVIEW software"> LabVIEW software</a>, <a href="https://publications.waset.org/abstracts/search?q=modelling%20and%20analysi" title=" modelling and analysi"> modelling and analysi</a>, <a href="https://publications.waset.org/abstracts/search?q=electrical%20and%20mechanical%20characteristics%20of%20motor" title=" electrical and mechanical characteristics of motor"> electrical and mechanical characteristics of motor</a> </p> <a href="https://publications.waset.org/abstracts/31481/induction-motor-analysis-using-labview" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/31481.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">555</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">3192</span> Rollet vs Rocket: A New in-Space Propulsion Concept</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Arthur%20Baraov">Arthur Baraov</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Nearly all rocket and spacecraft propulsion concepts in existence today can be linked one way or the other to one of the two ancient warfare devices: the gun and the sling. Chemical, thermoelectric, ion, nuclear thermal and electromagnetic rocket engines – all fall into the first group which, for obvious reasons, can be categorized as “hot” space propulsion concepts. Space elevator, orbital tower, rolling satellite, orbital skyhook, tether propulsion and gravitational assist – are examples of the second category which lends itself for the title “cold” space propulsion concepts. The “hot” space propulsion concepts skyrocketed – literally and figuratively – from the naïve ideas of Jules Verne to the manned missions to the Moon. On the other hand, with the notable exception of gravitational assist, hardly any of the “cold” space propulsion concepts made any progress in terms of practical application. Why is that? This article aims to show that the right answer to this question has the potential comparable by its implications and practical consequences to that of transition from Jules Verne’s stillborn and impractical conceptions of space flight to cogent and highly fertile ideas of Konstantin Tsiolkovsky and Yuri Kondratyuk. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=propulsion" title="propulsion">propulsion</a>, <a href="https://publications.waset.org/abstracts/search?q=rocket" title=" rocket"> rocket</a>, <a href="https://publications.waset.org/abstracts/search?q=rollet" title=" rollet"> rollet</a>, <a href="https://publications.waset.org/abstracts/search?q=spacecraft" title=" spacecraft"> spacecraft</a> </p> <a href="https://publications.waset.org/abstracts/29858/rollet-vs-rocket-a-new-in-space-propulsion-concept" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/29858.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">538</span> </span> </div> </div> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">3191</span> Fault Diagnosis in Induction Motor</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Kirti%20Gosavi">Kirti Gosavi</a>, <a href="https://publications.waset.org/abstracts/search?q=Anita%20Bhole"> Anita Bhole</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The paper demonstrates simulation and steady-state performance of three phase squirrel cage induction motor and detection of rotor broken bar fault using MATLAB. This simulation model is successfully used in the fault detection of rotor broken bar for the induction machines. A dynamic model using PWM inverter and mathematical modelling of the motor is developed. The dynamic simulation of the small power induction motor is one of the key steps in the validation of the design process of the motor drive system and it is needed for eliminating advertent design errors and the resulting error in the prototype construction and testing. The simulation model will be helpful in detecting the faults in three phase induction motor using Motor current signature analysis. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=squirrel%20cage%20induction%20motor" title="squirrel cage induction motor">squirrel cage induction motor</a>, <a href="https://publications.waset.org/abstracts/search?q=pulse%20width%20modulation%20%28PWM%29" title=" pulse width modulation (PWM)"> pulse width modulation (PWM)</a>, <a href="https://publications.waset.org/abstracts/search?q=fault%20diagnosis" title=" fault diagnosis"> fault diagnosis</a>, <a href="https://publications.waset.org/abstracts/search?q=induction%20motor" title=" induction motor"> induction motor</a> </p> <a href="https://publications.waset.org/abstracts/22499/fault-diagnosis-in-induction-motor" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/22499.pdf" target="_blank" class="btn btn-primary btn-sm">PDF</a> <span class="bg-info text-light px-1 py-1 float-right rounded"> Downloads <span class="badge badge-light">633</span> </span> </div> </div> <ul class="pagination"> <li class="page-item disabled"><span class="page-link">&lsaquo;</span></li> <li class="page-item active"><span class="page-link">1</span></li> <li class="page-item"><a class="page-link" href="https://publications.waset.org/abstracts/search?q=solid%20rocket%20motor&page=2">2</a></li> <li class="page-item"><a class="page-link" href="https://publications.waset.org/abstracts/search?q=solid%20rocket%20motor&page=3">3</a></li> <li class="page-item"><a class="page-link" href="https://publications.waset.org/abstracts/search?q=solid%20rocket%20motor&page=4">4</a></li> <li class="page-item"><a class="page-link" href="https://publications.waset.org/abstracts/search?q=solid%20rocket%20motor&page=5">5</a></li> <li class="page-item"><a class="page-link" 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