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launch simulation</title> <meta name="description" content="Search results for: rocket launch simulation"> <meta name="keywords" content="rocket launch simulation"> <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 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action="https://publications.waset.org/abstracts/search"> <div id="custom-search-input"> <div class="input-group"> <i class="fas fa-search"></i> <input type="text" class="search-query" name="q" placeholder="Author, Title, Abstract, Keywords" value="rocket launch simulation"> <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> 5169</div> </div> </div> </div> <h1 class="mt-3 mb-3 text-center" style="font-size:1.6rem;">Search results for: rocket launch simulation</h1> <div class="card paper-listing mb-3 mt-3"> <h5 class="card-header" style="font-size:.9rem"><span class="badge badge-info">5169</span> Rocket Launch Simulation for a Multi-Mode Failure Prediction Analysis</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Mennatallah%20M.%20Hussein">Mennatallah M. Hussein</a>, <a href="https://publications.waset.org/abstracts/search?q=Olivier%20de%20Weck"> Olivier de Weck</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The advancement of space exploration demands a robust space launch services program capable of reliably propelling payloads into orbit. Despite rigorous testing and quality assurance, launch failures still occur, leading to significant financial losses and jeopardizing mission objectives. Traditional failure prediction methods often lack the sophistication to account for multi-mode failure scenarios, as well as the predictive capability in complex dynamic systems. Traditional approaches also rely on expert judgment, leading to variability in risk prioritization and mitigation strategies. Hence, there is a pressing need for robust approaches that enhance launch vehicle reliability from lift-off until it reaches its parking orbit through comprehensive simulation techniques. In this study, the developed model proposes a multi-mode launch vehicle simulation framework for predicting failure scenarios when incorporating new technologies, such as new propulsion systems or advanced staging separation mechanisms in the launch system. To this end, the model combined a 6-DOF system dynamics with comprehensive data analysis to simulate multiple failure modes impacting launch performance. The simulator utilizes high-fidelity physics-based simulations to capture the complex interactions between different subsystems and environmental conditions. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=launch%20vehicle" title="launch vehicle">launch vehicle</a>, <a href="https://publications.waset.org/abstracts/search?q=failure%20prediction" title=" failure prediction"> failure prediction</a>, <a href="https://publications.waset.org/abstracts/search?q=propulsion%20anomalies" title=" propulsion anomalies"> propulsion anomalies</a>, <a href="https://publications.waset.org/abstracts/search?q=rocket%20launch%20simulation" title=" rocket launch simulation"> rocket launch simulation</a>, <a href="https://publications.waset.org/abstracts/search?q=rocket%20dynamics" title=" rocket dynamics"> rocket dynamics</a> </p> <a href="https://publications.waset.org/abstracts/188466/rocket-launch-simulation-for-a-multi-mode-failure-prediction-analysis" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/188466.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">31</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">5168</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">5167</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">5166</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">5165</span> Effect of Design Parameters on a Two Stage Launch Vehicle Performance</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Assem%20Sallam">Assem Sallam</a>, <a href="https://publications.waset.org/abstracts/search?q=Aly%20Elzahaby"> Aly Elzahaby</a>, <a href="https://publications.waset.org/abstracts/search?q=Ahmed%20Makled"> Ahmed Makled</a>, <a href="https://publications.waset.org/abstracts/search?q=Mohamed%20Khalil"> Mohamed Khalil</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Change in design parameters of launch vehicle affects its overall flight path trajectory. In this paper, several design parameters are introduced to study their effect. Selected parameters are the launch vehicle mass, which is presented in the form of payload mass, the maximum allowable angle of attack the launch vehicle can withstand, the flight path angle that is predefined for the launch vehicle second stage, the required inclination and its effect on the launch azimuth and finally by changing the launch pad coordinate. Selected design parameters are studied for their effect on the variation of altitude, ground range, absolute velocity and the flight path angle. The study gives a general mean of adjusting the design parameters to reach the required launch vehicle performance. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=launch%20vehicle%20azimuth" title="launch vehicle azimuth">launch vehicle azimuth</a>, <a href="https://publications.waset.org/abstracts/search?q=launch%20vehicle%20trajectory" title=" launch vehicle trajectory"> launch vehicle trajectory</a>, <a href="https://publications.waset.org/abstracts/search?q=launch%20vehicle%20payload" title=" launch vehicle payload"> launch vehicle payload</a>, <a href="https://publications.waset.org/abstracts/search?q=launch%20pad%20location" title=" launch pad location"> launch pad location</a> </p> <a href="https://publications.waset.org/abstracts/75171/effect-of-design-parameters-on-a-two-stage-launch-vehicle-performance" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/75171.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">312</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">5164</span> Minimum-Fuel Optimal Trajectory for Reusable First-Stage Rocket Landing Using Particle Swarm Optimization</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Kevin%20Spencer%20G.%20Anglim">Kevin Spencer G. Anglim</a>, <a href="https://publications.waset.org/abstracts/search?q=Zhenyu%20Zhang"> Zhenyu Zhang</a>, <a href="https://publications.waset.org/abstracts/search?q=Qingbin%20Gao"> Qingbin Gao</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Reusable launch vehicles (RLVs) present a more environmentally-friendly approach to accessing space when compared to traditional launch vehicles that are discarded after each flight. This paper studies the recyclable nature of RLVs by presenting a solution method for determining minimum-fuel optimal trajectories using principles from optimal control theory and particle swarm optimization (PSO). This problem is formulated as a minimum-landing error powered descent problem where it is desired to move the RLV from a fixed set of initial conditions to three different sets of terminal conditions. However, unlike other powered descent studies, this paper considers the highly nonlinear effects caused by atmospheric drag, which are often ignored for studies on the Moon or on Mars. Rather than optimizing the controls directly, the throttle control is assumed to be bang-off-bang with a predetermined thrust direction for each phase of flight. The PSO method is verified in a one-dimensional comparison study, and it is then applied to the two-dimensional cases, the results of which are illustrated. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=minimum-fuel%20optimal%20trajectory" title="minimum-fuel optimal trajectory">minimum-fuel optimal trajectory</a>, <a href="https://publications.waset.org/abstracts/search?q=particle%20swarm%20optimization" title=" particle swarm optimization"> particle swarm optimization</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=SpaceX" title=" SpaceX"> SpaceX</a> </p> <a href="https://publications.waset.org/abstracts/62012/minimum-fuel-optimal-trajectory-for-reusable-first-stage-rocket-landing-using-particle-swarm-optimization" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/62012.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">277</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">5163</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">5162</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">5161</span> Study of Launch Recovery Control Dynamics of Retro Propulsive Reusable Rockets</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Pratyush%20Agnihotri">Pratyush Agnihotri</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The space missions are very costly because the transportation to the space is highly expensive and therefore there is the need to achieve complete re-usability in our launch vehicles to make the missions highly economic by cost cutting of the material recovered. Launcher reusability is the most efficient approach to decreasing admittance to space access economy, however stays an incredible specialized hurdle for the aerospace industry. Major concern of the difficulties lies in guidance and control procedure and calculations, specifically for those of the controlled landing stage, which should empower an exact landing with low fuel edges. Although cutting edge ways for navigation and control are present viz hybrid navigation and robust control. But for powered descent and landing of first stage of launch vehicle the guidance control is need to enable on board optimization. At first the CAD model of the launch vehicle I.e. space x falcon 9 rocket is presented for better understanding of the architecture that needs to be identified for the guidance and control solution for the recovery of the launcher. The focus is on providing the landing phase guidance scheme for recovery and re usability of first stage using retro propulsion. After reviewing various GNC solutions, to achieve accuracy in pre requisite landing online convex and successive optimization are explored as the guidance schemes. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=guidance" title="guidance">guidance</a>, <a href="https://publications.waset.org/abstracts/search?q=navigation" title=" navigation"> navigation</a>, <a href="https://publications.waset.org/abstracts/search?q=control" title=" control"> control</a>, <a href="https://publications.waset.org/abstracts/search?q=retro%20propulsion" title=" retro propulsion"> retro propulsion</a>, <a href="https://publications.waset.org/abstracts/search?q=reusable%20rockets" title=" reusable rockets"> reusable rockets</a> </p> <a href="https://publications.waset.org/abstracts/160498/study-of-launch-recovery-control-dynamics-of-retro-propulsive-reusable-rockets" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/160498.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">91</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">5160</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">5159</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">5158</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">5157</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">5156</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">5155</span> Space Debris: An Environmental Hazard</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Anwesha%20Pathak">Anwesha Pathak</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Space law refers to all legal provisions that may regulate or apply to space travel, as well as to space-related activity. Although there is undoubtedly a core corpus of “space law,” rather than designating a conceptually distinct single kind of law, the phrase can be seen as a label applied to a bucket that includes a variety of different laws and regulations. Similar to ‘family law' or ‘environmental law' "space law" refers to a variety of laws that are identified by the subject matter they address rather than by the logical extension of a single legal concept. The word "space law" refers to the Law of Space, which can cover anything from the specifics of an insurance agreement for a specific space launch to the most general guidelines that direct state behaviour in space. Space debris, often referred to as space junk, space pollution, space waste, space trash, or space garbage, is a term used to describe abandoned human-made objects in space, primarily in Earth orbit. These include disused spacecraft, discarded launch vehicle stages, mission-related detritus, and fragmentation material from the destruction of disused rocket bodies and spacecraft, which is particularly prevalent in Earth orbit. Other types of space debris, besides abandoned human-made objects in orbit, include pieces left over from collisions, erosion, and disintegration, or even paint specks, solidified liquids ejected from spacecraft, and unburned components from solid rocket engines. The initial action of launching or using a spacecraft in near-Earth orbit imposes an external cost on others that is typically not taken into account or fully accounted for in the cost by the launcher or payload owner. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=space" title="space">space</a>, <a href="https://publications.waset.org/abstracts/search?q=outer%20space%20treaty" title=" outer space treaty"> outer space treaty</a>, <a href="https://publications.waset.org/abstracts/search?q=geostationary%20orbit" title=" geostationary orbit"> geostationary orbit</a>, <a href="https://publications.waset.org/abstracts/search?q=satellites" title=" satellites"> satellites</a>, <a href="https://publications.waset.org/abstracts/search?q=spacecrafts" title=" spacecrafts"> spacecrafts</a> </p> <a href="https://publications.waset.org/abstracts/165735/space-debris-an-environmental-hazard" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/165735.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">92</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">5154</span> Two-Stage Launch Vehicle Trajectory Modeling for Low Earth Orbit Applications</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Assem%20M.%20F.%20Sallam">Assem M. F. Sallam</a>, <a href="https://publications.waset.org/abstracts/search?q=Ah.%20El-S.%20Makled"> Ah. El-S. Makled</a> </p> <p class="card-text"><strong>Abstract:</strong></p> This paper presents a study on the trajectory of a two stage launch vehicle. The study includes dynamic responses of motion parameters as well as the variation of angles affecting the orientation of the launch vehicle (LV). LV dynamic characteristics including state vector variation with corresponding altitude and velocity for the different LV stages separation, as well as the angle of attack and flight path angles are also discussed. A flight trajectory study for the drop zone of first stage and the jettisoning of fairing are introduced in the mathematical modeling to study their effect. To increase the accuracy of the LV model, atmospheric model is used taking into consideration geographical location and the values of solar flux related to the date and time of launch, accurate atmospheric model leads to enhancement of the calculation of Mach number, which affects the drag force over the LV. The mathematical model is implemented on MATLAB based software (Simulink). The real available experimental data are compared with results obtained from the theoretical computation model. The comparison shows good agreement, which proves the validity of the developed simulation model; the maximum error noticed was generally less than 10%, which is a result that can lead to future works and enhancement to decrease this level of error. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=launch%20vehicle%20modeling" title="launch vehicle modeling">launch vehicle modeling</a>, <a href="https://publications.waset.org/abstracts/search?q=launch%20vehicle%20trajectory" title=" launch vehicle trajectory"> launch vehicle trajectory</a>, <a href="https://publications.waset.org/abstracts/search?q=mathematical%20modeling" title=" mathematical modeling"> mathematical modeling</a>, <a href="https://publications.waset.org/abstracts/search?q=Matlab-%20Simulink" title=" Matlab- Simulink"> Matlab- Simulink</a> </p> <a href="https://publications.waset.org/abstracts/60074/two-stage-launch-vehicle-trajectory-modeling-for-low-earth-orbit-applications" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/60074.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">277</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">5153</span> Time Optimal Control Mode Switching between Detumbling and Pointing in the Early Orbit Phase</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=W.%20M.%20Ng">W. M. Ng</a>, <a href="https://publications.waset.org/abstracts/search?q=O.%20B.%20Iskender"> O. B. Iskender</a>, <a href="https://publications.waset.org/abstracts/search?q=L.%20Simonini"> L. Simonini</a>, <a href="https://publications.waset.org/abstracts/search?q=J.%20M.%20Gonzalez"> J. M. Gonzalez</a> </p> <p class="card-text"><strong>Abstract:</strong></p> A multitude of factors, including mechanical imperfections of the deployment system and separation instance of satellites from launchers, oftentimes results in highly uncontrolled initial tumbling motion immediately after deployment. In particular, small satellites which are characteristically launched as a piggyback to a large rocket, are generally allocated a large time window to complete detumbling within the early orbit phase. Because of the saturation risk of the actuators, current algorithms are conservative to avoid draining excessive power in the detumbling phase. This work aims to enable time-optimal switching of control modes during the early phase, reducing the time required to transit from launch to sun-pointing mode for power budget conscious satellites. This assumes the usage of B-dot controller for detumbling and PD controller for pointing. Nonlinear Euler's rotation equations are used to represent the attitude dynamics of satellites and Commercial-off-the-shelf (COTS) reaction wheels and magnetorquers are used to perform the manoeuver. Simulation results will be based on a spacecraft attitude simulator and the use case will be for multiple orbits of launch deployment general to Low Earth Orbit (LEO) satellites. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=attitude%20control" title="attitude control">attitude control</a>, <a href="https://publications.waset.org/abstracts/search?q=detumbling" title=" detumbling"> detumbling</a>, <a href="https://publications.waset.org/abstracts/search?q=small%20satellites" title=" small satellites"> small satellites</a>, <a href="https://publications.waset.org/abstracts/search?q=spacecraft%20autonomy" title=" spacecraft autonomy"> spacecraft autonomy</a>, <a href="https://publications.waset.org/abstracts/search?q=time%20optimal%20control" title=" time optimal control"> time optimal control</a> </p> <a href="https://publications.waset.org/abstracts/108761/time-optimal-control-mode-switching-between-detumbling-and-pointing-in-the-early-orbit-phase" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/108761.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">5152</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">5151</span> Review of Factors Which Affect Throttling by Oxidiser Flow Control in Hybrid Rocket Engine</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Natcha%20Laethongkham">Natcha Laethongkham</a>, <a href="https://publications.waset.org/abstracts/search?q=Gayan%20Ramanayake"> Gayan Ramanayake</a>, <a href="https://publications.waset.org/abstracts/search?q=Philip%20Charlesworth"> Philip Charlesworth</a>, <a href="https://publications.waset.org/abstracts/search?q=Leshan%20Uggalla"> Leshan Uggalla</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The throttling process in hybrid rocket engines (HREs) poses challenges due to inherent instability, impacting the engine’s reliability and robustness. Identifying and advancing existing technology is crucial to meet the demands of complex mission profiles required for next-generation launch vehicles. This paper reviews the current literature, focusing on oxidiser flow control for throttling purposes in HREs. Covered areas include oxidiser choices, commonly used throttle valves, and literature trends. Common oxidisers for throttling are hydrogen peroxide, nitrous oxide, and liquid oxygen. Two frequently chosen valves for throttling are the ball and variation pintle valves. The review identifies two primary research focuses: flow control valve studies and control system design. The current research stage is highlighted, and suggestions for future directions are proposed to advance thrust control systems in HREs. This includes further studies in existing research focuses and exploring new approaches such as system scheme design, numerical modelling, and applications. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=hybrid%20rocket%20engines" title="hybrid rocket engines">hybrid rocket engines</a>, <a href="https://publications.waset.org/abstracts/search?q=oxidiser%20flow%20control" title=" oxidiser flow control"> oxidiser flow control</a>, <a href="https://publications.waset.org/abstracts/search?q=thrust%20control" title=" thrust control"> thrust control</a>, <a href="https://publications.waset.org/abstracts/search?q=throttle%20valve" title=" throttle valve"> throttle valve</a>, <a href="https://publications.waset.org/abstracts/search?q=review" title=" review"> review</a> </p> <a href="https://publications.waset.org/abstracts/191042/review-of-factors-which-affect-throttling-by-oxidiser-flow-control-in-hybrid-rocket-engine" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/191042.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">25</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">5150</span> Numerical Simulation of Supersonic Gas Jet Flows and Acoustics Fields</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Lei%20Zhang">Lei Zhang</a>, <a href="https://publications.waset.org/abstracts/search?q=Wen-jun%20Ruan"> Wen-jun Ruan</a>, <a href="https://publications.waset.org/abstracts/search?q=Hao%20Wang"> Hao Wang</a>, <a href="https://publications.waset.org/abstracts/search?q=Peng-Xin%20Wang"> Peng-Xin Wang</a> </p> <p class="card-text"><strong>Abstract:</strong></p> The source of the jet noise is generated by rocket exhaust plume during rocket engine testing. A domain decomposition approach is applied to the jet noise prediction in this paper. The aerodynamic noise coupling is based on the splitting into acoustic sources generation and sound propagation in separate physical domains. Large Eddy Simulation (LES) is used to simulate the supersonic jet flow. Based on the simulation results of the flow-fields, the jet noise distribution of the sound pressure level is obtained by applying the Ffowcs Williams-Hawkings (FW-H) acoustics equation and Fourier transform. The calculation results show that the complex structures of expansion waves, compression waves and the turbulent boundary layer could occur due to the strong interaction between the gas jet and the ambient air. In addition, the jet core region, the shock cell and the sound pressure level of the gas jet increase with the nozzle size increasing. Importantly, the numerical simulation results of the far-field sound are in good agreement with the experimental measurements in directivity. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=supersonic%20gas%20jet" title="supersonic gas jet">supersonic gas jet</a>, <a href="https://publications.waset.org/abstracts/search?q=Large%20Eddy%20Simulation%28LES%29" title=" Large Eddy Simulation(LES)"> Large Eddy Simulation(LES)</a>, <a href="https://publications.waset.org/abstracts/search?q=acoustic%20noise" title=" acoustic noise"> acoustic noise</a>, <a href="https://publications.waset.org/abstracts/search?q=Ffowcs%20Williams-Hawkings%28FW-H%29%20equations" title=" Ffowcs Williams-Hawkings(FW-H) equations"> Ffowcs Williams-Hawkings(FW-H) equations</a>, <a href="https://publications.waset.org/abstracts/search?q=nozzle%20size" title=" nozzle size"> nozzle size</a> </p> <a href="https://publications.waset.org/abstracts/44797/numerical-simulation-of-supersonic-gas-jet-flows-and-acoustics-fields" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/44797.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">413</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">5149</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">5148</span> Study of Acoustic Resonance of Model Liquid Rocket Combustion Chamber and Its Suppression</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Vimal%20O.%20Kumar">Vimal O. Kumar</a>, <a href="https://publications.waset.org/abstracts/search?q=C.%20K.%20Muthukumaran"> C. K. Muthukumaran</a>, <a href="https://publications.waset.org/abstracts/search?q=P.%20Rakesh"> P. Rakesh</a> </p> <p class="card-text"><strong>Abstract:</strong></p> Liquid rocket engine (LRE) combustion chamber is subjected to pressure oscillation during the combustion process. The combustion noise (acoustic noise) is a broad band, small amplitude, high frequency component pressure oscillation. They constitute only a minor fraction ( < 1%) of the entire combustion process. However, this high frequency oscillation is huge concern during the design phase of LRE combustion chamber as it would cause catastrophic failure of the chamber. Depends on the chamber geometry, certain frequencies form standing wave pattern, and they resonate with high amplitude and are known as Eigen modes. These Eigen modes could cause failures unless it is suppressed to be within safe limits. These modes are categorized into radial, tangential, and azimuthal modes, and their structure inside the combustion chamber is of interest to the researchers. In the present proposal, experimental as well as numerical simulation will be performed to obtain the frequency-amplitude characteristics of the model combustion chamber for different baffle configuration. The main objective of this study is to find effect of baffle configuration that would provide better suppression of acoustic modes. The experimental study aims at measuring the frequency amplitude characteristics at certain points in the chamber wall. The experimental measurement will be also used for scheme used in numerical simulation. In addition to experiments, numerical simulation would provide detailed structure of the Eigenmodes exhibited and their level of suppression with the aid of different baffle configurations. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=baffle" title="baffle">baffle</a>, <a href="https://publications.waset.org/abstracts/search?q=instability" title=" instability"> instability</a>, <a href="https://publications.waset.org/abstracts/search?q=liquid%20rocket%20engine" title=" liquid rocket engine"> liquid rocket engine</a>, <a href="https://publications.waset.org/abstracts/search?q=pressure%20response%20of%20chamber" title=" pressure response of chamber"> pressure response of chamber</a> </p> <a href="https://publications.waset.org/abstracts/129395/study-of-acoustic-resonance-of-model-liquid-rocket-combustion-chamber-and-its-suppression" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/129395.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">122</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">5147</span> Hybrid Reusable Launch Vehicle for Space Application A Naval Approach</h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=Rajasekar%20Elangopandian">Rajasekar Elangopandian</a>, <a href="https://publications.waset.org/abstracts/search?q=Anand%20Shanmugam"> Anand Shanmugam </a> </p> <p class="card-text"><strong>Abstract:</strong></p> In order to reduce the cost of launching satellite and payloads to the orbit this project envisages some immense combined technology. This new technology in space odyssey contains literally four concepts. The first mode in this innovation is flight mission characteristics which, says how the mission will induct. The conventional technique of magnetic levitation will help us to produce the initial thrust. The name states reusable launch vehicle shows its viability of reuseness. The flight consists miniature rocket which produces the required thrust and the two JATO (jet assisted takeoff) boosters which gives the initial boost for the vehicle. The vehicle ostensibly looks like an airplane design and will be located on the super conducting rail track. When the high power electric current given to the rail track, the vehicle starts floating as per the principle of magnetic levitation. If the flight reaches the particular takeoff distance the two boosters gets starts and will give the 48KN thrust each. Obviously it`ll follow the vertical path up to the atmosphere end/start to space. As soon as it gets its speed the two boosters will cutoff. Once it reaches the space the inbuilt spacecraft keep the satellite in the desired orbit. When the work finishes, the apogee motors gives the initial kick to the vehicle to come in to the earth’s atmosphere with 22N thrust and automatically comes to the ground by following the free fall, the help of gravitational force. After the flying region it makes the spiral flight mode then gets landing where the super conducting levitated rail track located. It will catch up the vehicle and keep it by changing the poles of magnets and varying the current. Initial cost for making this vehicle might be high but for the frequent usage this will reduce the launch cost exactly half than the now-a-days technology. The incorporation of such a mechanism gives `hybrid` and the reusability gives `reusable launch vehicle` and ultimately Hybrid reusable launch vehicle. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=the%20two%20JATO%20%28jet%20assisted%20takeoff%29%20boosters" title="the two JATO (jet assisted takeoff) boosters">the two JATO (jet assisted takeoff) boosters</a>, <a href="https://publications.waset.org/abstracts/search?q=magnetic%20levitation" title=" magnetic levitation"> magnetic levitation</a>, <a href="https://publications.waset.org/abstracts/search?q=48KN%20thrust%20each" title=" 48KN thrust each"> 48KN thrust each</a>, <a href="https://publications.waset.org/abstracts/search?q=22N%20thrust%20and%20automatically%20comes%20to%20the%20ground" title=" 22N thrust and automatically comes to the ground"> 22N thrust and automatically comes to the ground</a> </p> <a href="https://publications.waset.org/abstracts/33609/hybrid-reusable-launch-vehicle-for-space-application-a-naval-approach" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/33609.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">427</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">5146</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">5145</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">5144</span> An Accurate Prediction of Surface Temperature History in a Supersonic Flight </h5> <div class="card-body"> <p class="card-text"><strong>Authors:</strong> <a href="https://publications.waset.org/abstracts/search?q=A.%20M.%20Tahsini">A. M. Tahsini</a>, <a href="https://publications.waset.org/abstracts/search?q=S.%20A.%20Hosseini"> S. A. Hosseini</a> </p> <p class="card-text"><strong>Abstract:</strong></p> In the present study, the surface temperature history of the adaptor part in a two-stage supersonic launch vehicle is accurately predicted. The full Navier-Stokes equations are used to estimate the aerodynamic heat flux. The one-dimensional heat conduction in solid phase is used to compute the temperature history. The instantaneous surface temperature is used to improve the applied heat flux, to improve the accuracy of the results. <p class="card-text"><strong>Keywords:</strong> <a href="https://publications.waset.org/abstracts/search?q=aerodynamic%20heating" title="aerodynamic heating">aerodynamic heating</a>, <a href="https://publications.waset.org/abstracts/search?q=heat%20conduction" title=" heat conduction"> heat conduction</a>, <a href="https://publications.waset.org/abstracts/search?q=numerical%20simulation" title=" numerical simulation"> numerical simulation</a>, <a href="https://publications.waset.org/abstracts/search?q=supersonic%20flight" title=" supersonic flight"> supersonic flight</a>, <a href="https://publications.waset.org/abstracts/search?q=launch%20vehicle" title=" launch vehicle"> launch vehicle</a> </p> <a href="https://publications.waset.org/abstracts/1462/an-accurate-prediction-of-surface-temperature-history-in-a-supersonic-flight" class="btn btn-primary btn-sm">Procedia</a> <a href="https://publications.waset.org/abstracts/1462.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">452</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">5143</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">5142</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">5141</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">5140</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" 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