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rocket</title> <meta name="description" content="Search results for: rocket"> <meta name="keywords" content="rocket"> <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 navbar-toggler ml-auto" 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class="input-group"> <i class="fas fa-search"></i> <input type="text" class="search-query" name="q" placeholder="Author, Title, Abstract, Keywords" value="rocket"> <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> 94</div> </div> </div> </div> <h1 class="mt-3 mb-3 text-center" style="font-size:1.6rem;">Search results for: rocket</h1> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">94</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">93</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">92</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">91</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">90</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">89</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">88</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">87</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">86</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">85</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">84</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">83</span> High Thrust Upper Stage Solar Hydrogen Rocket Design</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Maged%20Assem%20Soliman%20Mossallam">Maged Assem Soliman Mossallam</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The conversion of solar thruster model to an upper stage hydrogen rocket is considered. Solar thruster categorization limits its capabilities to low and moderate thrust system with high specific impulse. The current study proposes a different concept for such systems by increasing the thrust which enables using as an upper stage rocket and for future launching purposes. A computational model for the thruster is discussed for solar thruster subsystems. The first module depends on ray tracing technique to determine the intercepted solar power by the hydrogen combustion chamber. The cavity receiver is modeled using finite volume technique. The final module imports the heated hydrogen properties to the nozzle using quasi one dimensional simulation. The probability of shock waves formulation inside the nozzle is almost diminished as the outlet pressure in space environment tends to zero. The computational model relates the high thrust hydrogen rocket conversion to the design parameters and operating conditions of the thruster. Three different designs for solar thruster systems are discussed. The first design is a low thrust high specific impulse design that produces about 10 Newton of thrust .The second one output thrust is about 250 Newton and the third design produces about 1000 Newton. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=space%20propulsion" title="space propulsion">space propulsion</a>, <a href="https://publications.waset.org/abstracts/search?q=hydrogen%20rocket" title=" hydrogen rocket"> hydrogen rocket</a>, <a href="https://publications.waset.org/abstracts/search?q=thrust" title=" thrust"> thrust</a>, <a href="https://publications.waset.org/abstracts/search?q=specific%20impulse" title=" specific impulse "> specific impulse </a> </p> <a href="https://publications.waset.org/abstracts/128850/high-thrust-upper-stage-solar-hydrogen-rocket-design" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/128850.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">166</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">82</span> Numerical Analysis of Various V- rib Cross-section to Optimize Thermal Performance of the Rocket Engine</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Hisham%20Elmouazen">Hisham Elmouazen</a>, <a href="https://publications.waset.org/abstracts/search?q=Xiaobing%20Zhang"> Xiaobing Zhang</a> </p> <p class="card-text"><strong>Abstract:</strong></p> In regenerative-cooled rocket engines, understanding the coolant behaviour within cooling channels is essential to enhance engine performance and maintain chamber walls at low temperatures. However, modelling and testing the rocket engine's cooling channels is challenging due to the high temperature of the chamber walls, supercritical flow, and high Reynolds number. Therefore, a numerical analysis of five different V-rib cross-sections to optimize rocket engine cooling channels' performance is developed and validated in this work. Three-dimensional CFD simulations are employed by the Shear Stress Transport (k- ω) turbulent model at Reynolds number 42,500. The study findings illustrate that the V-ribbed channel performance is optimized by 59.5% relative to the plain/flat channel. Additionally, the chamber wall temperature is decreased to 726.4 K, and the right-angle trapezoidal V-rib (Case 4) improves thermal augmentation up to 74.3 % with a slightly high friction factor. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=computational%20fluid%20dynamics%20CFD" title="computational fluid dynamics CFD">computational fluid dynamics CFD</a>, <a href="https://publications.waset.org/abstracts/search?q=regenerative-cooled%20system" title=" regenerative-cooled system"> regenerative-cooled system</a>, <a href="https://publications.waset.org/abstracts/search?q=thermal%20performance" title=" thermal performance"> thermal performance</a>, <a href="https://publications.waset.org/abstracts/search?q=V-rib%20cross-sections" title=" V-rib cross-sections"> V-rib cross-sections</a> </p> <a href="https://publications.waset.org/abstracts/163876/numerical-analysis-of-various-v-rib-cross-section-to-optimize-thermal-performance-of-the-rocket-engine" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/163876.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">75</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">81</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">80</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">79</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">78</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">77</span> Experimental Study of Upsetting and Die Forging with Controlled Impact</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=T.%20Penchev">T. Penchev</a>, <a href="https://publications.waset.org/abstracts/search?q=D.%20Karastoyanov"> D. Karastoyanov</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The results from experimental research of deformation by upsetting and die forging of lead specimens wit controlled impact are presented. Laboratory setup for conducting the investigations, which uses cold rocket engine operated with compressed air, is described. The results show that when using controlled impact is achieving greater plastic deformation and consumes less impact energy than at ordinary impact deformation process. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=rocket%20engine" title="rocket engine">rocket engine</a>, <a href="https://publications.waset.org/abstracts/search?q=forging%20hammer" title=" forging hammer"> forging hammer</a>, <a href="https://publications.waset.org/abstracts/search?q=sticking%20impact" title=" sticking impact"> sticking impact</a>, <a href="https://publications.waset.org/abstracts/search?q=plastic%20deformation" title=" plastic deformation"> plastic deformation</a> </p> <a href="https://publications.waset.org/abstracts/3645/experimental-study-of-upsetting-and-die-forging-with-controlled-impact" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/3645.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">371</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">76</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">75</span> Environmental Safety and Occupational Health Risk Assessment for Rocket Static Test </h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Phontip%20Kanlahasuth">Phontip Kanlahasuth </a> </p> <p class="card-text"><strong>Abstract:</strong></p> This paper presents the environmental safety and occupational health risk assessment of rocket static test by assessing risk level from probability and severity and then appropriately applying the risk control measures. Before the environmental safety and occupational health measures are applied, the serious hazards level is 31%, medium level is 24% and low level is 45%. Once risk control measures are practically implemented, the serious hazard level can be diminished, medium level is 38%, low level is 45% and eliminated level is 17%. It is clearly shown that the environmental safety and occupational health measures can significantly reduce the risk level. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=rocket%20static%20test" title="rocket static test">rocket static test</a>, <a href="https://publications.waset.org/abstracts/search?q=hazard" title=" hazard"> hazard</a>, <a href="https://publications.waset.org/abstracts/search?q=risk" title=" risk"> risk</a>, <a href="https://publications.waset.org/abstracts/search?q=risk%20assessment" title=" risk assessment"> risk assessment</a>, <a href="https://publications.waset.org/abstracts/search?q=risk%20analysis" title=" risk analysis"> risk analysis</a>, <a href="https://publications.waset.org/abstracts/search?q=environment" title=" environment"> environment</a>, <a href="https://publications.waset.org/abstracts/search?q=safety" title=" safety"> safety</a>, <a href="https://publications.waset.org/abstracts/search?q=occupational%20health" title=" occupational health"> occupational health</a>, <a href="https://publications.waset.org/abstracts/search?q=acceptable%20risk" title=" acceptable risk"> acceptable risk</a>, <a href="https://publications.waset.org/abstracts/search?q=probability" title=" probability"> probability</a>, <a href="https://publications.waset.org/abstracts/search?q=severity" title=" severity"> severity</a>, <a href="https://publications.waset.org/abstracts/search?q=risk%20level" title=" risk level"> risk level</a> </p> <a href="https://publications.waset.org/abstracts/4165/environmental-safety-and-occupational-health-risk-assessment-for-rocket-static-test" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/4165.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">587</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">74</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">73</span> Computational Fluid Dynamics Model of Various Types of Rocket Engine Nozzles</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Konrad%20Pietrykowski">Konrad Pietrykowski</a>, <a href="https://publications.waset.org/abstracts/search?q=Michal%20Bialy"> Michal Bialy</a>, <a href="https://publications.waset.org/abstracts/search?q=Pawel%20Karpinski"> Pawel Karpinski</a>, <a href="https://publications.waset.org/abstracts/search?q=Radoslaw%20Maczka"> Radoslaw Maczka</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The nozzle is an element of the rocket engine in which the conversion of the potential energy of gases generated during combustion into the kinetic energy of the gas stream takes place. The design parameters of the nozzle have a decisive influence on the ballistic characteristics of the engine. Designing a nozzle assembly is, therefore, one of the most responsible stages in developing a rocket engine design. The paper presents the results of the simulation of three types of rocket propulsion nozzles. Calculations were made using CFD (Computational Fluid Dynamics) in ANSYS Fluent software. The next types of nozzles differ in shape. The analysis was made of a conical nozzle, a bell type nozzle with a conical supersonic part and a bell type nozzle. Calculation results are presented in the form of pressure, velocity and kinetic energy distributions of turbulence in the longitudinal section. The courses of these values along the nozzles are also presented. The results show that the cone nozzle generates strong turbulence in the critical section. Which negatively affect the flow of the working medium. In the case of a bell nozzle, the transformation of the wall caused the elimination of flow disturbances in the critical section. This reduces the probability of waves forming before or after the trailing edge. The most sophisticated construction is the bell type nozzle. It allows you to maximize performance without adding extra weight. The bell type nozzle can be used as a starter and auxiliary engine nozzle due to its advantages. The project/research was financed in the framework of the project Lublin University of Technology-Regional Excellence Initiative, funded by the Polish Ministry of Science and Higher Education (contract no. 030/RID/2018/19). <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=computational%20fluid%20dynamics" title="computational fluid dynamics">computational fluid dynamics</a>, <a href="https://publications.waset.org/abstracts/search?q=nozzle" title=" nozzle"> nozzle</a>, <a href="https://publications.waset.org/abstracts/search?q=rocket%20engine" title=" rocket engine"> rocket engine</a>, <a href="https://publications.waset.org/abstracts/search?q=supersonic%20flow" title=" supersonic flow"> supersonic flow</a> </p> <a href="https://publications.waset.org/abstracts/106607/computational-fluid-dynamics-model-of-various-types-of-rocket-engine-nozzles" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/106607.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">158</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">72</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">71</span> Some Changes in Biochemical Parameters of Body and Hepato-Biliary System under the Influence of Hydrazine Derivatives</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=G.%20Y.%20Saspugayeva">G. Y. Saspugayeva</a>, <a href="https://publications.waset.org/abstracts/search?q=R.%20R.%20Beysenova"> R. R. Beysenova</a>, <a href="https://publications.waset.org/abstracts/search?q=M.%20R.%20Khanturin"> M. R. Khanturin</a>, <a href="https://publications.waset.org/abstracts/search?q=E.%20T.%20Abseitov"> E. T. Abseitov</a>, <a href="https://publications.waset.org/abstracts/search?q=K.%20B.%20Massenov"> K. B. Massenov </a> </p> <p class="card-text"><strong>Abstract:</strong></p> This research is devoted to the problems of rocket fuel and impact of its derivatives on environment and living things. Hydrazine derivatives are used in different spheres, in aero-space activity, medical practice, laboratory-diagnosis practice and etc. For Kazakhstan, which has the cosmodrome "Baikonur", the problem of environmental pollution by rocket fuel and its components is important issue. An unsymmetrical dimethylhydrazine is mostly used as rocket fuel for launch vehicles which has high toxicity to humans and animals referred to the World Health Organization. The question about influence of hydrazine derivatives on human organism and ways of detoxication is very actual and requires special approaches in solving these problems. In connection with this situation, we set the goal: study the negative influence of hydrazine derivatives-hydrazine sulphur, nitrosodimethylamine (NDMA), phenylhydrazine, isonicotinic acid hydrazide (IAH) on some biochemical parameters of blood, hepatobiliary system and correction of functional damages of organism with “Salsocollin” drugs. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=isonicotinic%20acid%20hydrazide%20%28IAH%29" title="isonicotinic acid hydrazide (IAH)">isonicotinic acid hydrazide (IAH)</a>, <a href="https://publications.waset.org/abstracts/search?q=N-nitrosodimethylamine%20%28NDMA%29" title=" N-nitrosodimethylamine (NDMA)"> N-nitrosodimethylamine (NDMA)</a>, <a href="https://publications.waset.org/abstracts/search?q=AlAT-alanine%20aminotransferase" title=" AlAT-alanine aminotransferase"> AlAT-alanine aminotransferase</a>, <a href="https://publications.waset.org/abstracts/search?q=AsAT-aspartate%20aminotransaminase" title=" AsAT-aspartate aminotransaminase "> AsAT-aspartate aminotransaminase </a> </p> <a href="https://publications.waset.org/abstracts/16379/some-changes-in-biochemical-parameters-of-body-and-hepato-biliary-system-under-the-influence-of-hydrazine-derivatives" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/16379.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">355</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">70</span> Heat Treatment of Additively Manufactured Hybrid Rocket Fuel Grains</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Jim%20J.%20Catina">Jim J. Catina</a>, <a href="https://publications.waset.org/abstracts/search?q=Jackee%20M.%20Gwynn"> Jackee M. Gwynn</a>, <a href="https://publications.waset.org/abstracts/search?q=Jin%20S.%20Kang"> Jin S. Kang</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Additive manufacturing (AM) for hybrid rocket engines is becoming increasingly attractive due to its ability to create complex grain configurations with improved regression rates when compared to cast grains. However, the presence of microvoids in parts produced through the additive manufacturing method of Fused Deposition Modeling (FDM) results in a lower fuel density and is believed to cause a decrease in regression rate compared to ideal performance. In this experiment, FDM was used to create hybrid rocket fuel grains with a star configuration composed of acrylonitrile butadiene styrene (ABS). Testing was completed to determine the effect of heat treatment as a post-processing method to improve the combustion performance of hybrid rocket fuel grains manufactured by FDM. For control, three ABS star configuration grains were printed using FDM and hot fired using gaseous oxygen (GOX) as the oxidizer. Parameters such as thrust and mass flow rate were measured. Three identical grains were then heat treated to varying degrees and hot fired under the same conditions as the control grains. This paper will quantitatively describe the amount of improvement in engine performance as a result of heat treatment of the AM hybrid fuel grain. Engine performance is measured in this paper by specific impulse, which is determined from the thrust measurements collected in testing. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=acrylonitrile%20butadiene%20styrene" title="acrylonitrile butadiene styrene">acrylonitrile butadiene styrene</a>, <a href="https://publications.waset.org/abstracts/search?q=additive%20manufacturing" title=" additive manufacturing"> additive manufacturing</a>, <a href="https://publications.waset.org/abstracts/search?q=fused%20deposition%20modeling" title=" fused deposition modeling"> fused deposition modeling</a>, <a href="https://publications.waset.org/abstracts/search?q=heat%20treatment" title=" heat treatment"> heat treatment</a> </p> <a href="https://publications.waset.org/abstracts/157623/heat-treatment-of-additively-manufactured-hybrid-rocket-fuel-grains" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/157623.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">117</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">69</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">68</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">67</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">66</span> Experimental Study of Iron Metal Powder Compacting by Controlled Impact</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Todor%20N.%20Penchev">Todor N. Penchev</a>, <a href="https://publications.waset.org/abstracts/search?q=Dimitar%20N.%20Karastoianov"> Dimitar N. Karastoianov</a>, <a href="https://publications.waset.org/abstracts/search?q=Stanislav%20D.%20Gyoshev"> Stanislav D. Gyoshev</a> </p> <p class="card-text"><strong>Abstract:</strong></p> For compacting of iron powder are used hydraulic presses and high velocity hammers. In this paper are presented initial research on application of an innovative powder compacting method, which uses a hammer working with controlled impact. The results show that by this method achieves the reduction of rebounds and improve efficiency of impact, compared with a high-speed compacting. Depending on the power of the engine (industrial rocket engine), this effect may be amplified to such an extent as to obtain a impact without rebound (sticking impact) and in long-time action of the impact force. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=powder%20metallurgy" title="powder metallurgy">powder metallurgy</a>, <a href="https://publications.waset.org/abstracts/search?q=impact" title=" impact"> impact</a>, <a href="https://publications.waset.org/abstracts/search?q=iron%20powder%20compacting" title=" iron powder compacting"> iron powder compacting</a>, <a href="https://publications.waset.org/abstracts/search?q=rocket%20engine" title=" rocket engine"> rocket engine</a> </p> <a href="https://publications.waset.org/abstracts/33204/experimental-study-of-iron-metal-powder-compacting-by-controlled-impact" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/33204.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">521</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">65</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 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