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JETIR Research Journal © 2019 JETIR May 2019, Volume 6, Issue 5 www.jetir.org (ISSN-2349-5162) Design Optimization and Analysis of Rocket Structure for Aerospace Applications 1Chethan S, 2Niranjan Hiremath 1M.Tech Machine Design Student, 2Associate Professor 1,2 School of Mechanical Engineering, REVA University, Rukmini Knowledge Park, Kattigenahalli, Yelahanka, Bengaluru, India Abstract: The aim of this study is to perform techniques such as pressure mapping of the missile structure, Inertia Relief Analysis for Rocket Structure in the effective way with the low cost. And the analysis plays important role in the structural design and safety. Due to the advances with numerical software’s, the simulation helps in estimating the safety of the structures without actual prototype built up and testing. Firstly we design the Rocket parts by the help of modelling tools using solid edge v19, Catia v6 and assembled it later. In order to find pressure distribution on the missile surface and to find the stress and deformation of missile structure by pressure mapping using CFD mesh in Acusolve on to the Rocket Structure, Pressure values in “X, Y and Z” co-ordinate with magnitudes are obtained in CSV file format. And later we study behavior of the missile parts like Nose, Nose cone, Body, Tail and Fins when the surface remains same from nose to tail and the fins with the varying thickness. And we use the Maraging Steel 250 grade as the material and its properties is assigned to the mesh. And the mesh thickness of the outer shell material is increased for different cases along with a speed of Mach number 0.75 and 5. And structural changes are seen when the loads are applied to the mesh. Characteristics individualities of displacement, stress distribution and high stress locations are determined and results are extracted in terms of plots using the tools Hypermesh for Pre-processing, Optistruct, Acuconsole for Solving and Hyper-view, Acu- Field View for Post Processing. IndexTerms - Rocket Structure, Missile, CFD mesh, Pressure mapping of the Missile Structure, Inertia Relief Analysis. I. Introduction Missile, is a guided self-propelled system, as opposed to an unguided self-propelled munition, referred to as a rocket (although these too can also be guided) Missiles have four system components: targeting or missile guidance, flight system, engine, and warhead. Missiles come in types adapted for different purposes: surface-to-surface and air-to-surface missiles (ballistic, cruise, anti- ship, anti-tank, etc.), surface-to-air missiles (and anti-ballistic), air-to-air missiles, and anti-satellite weapons. A Rocket is a vehicle which acquires push by the response of the rocket to the discharge of plane of quick moving liquid fumes from rocket engine. Solid fuel rockets make their fumes by the ignition of strong charge grain. The subsequent gasses are extended through the spout whose capacity is to change over this inward weight into a supersonic fumes speed. Rocket engine fumes are shaped altogether from force conveyed inside of the rocket before use. Rocket motors work by activity and response. Rocket motors push rockets forward by ousting their fumes the other way at fast. Rockets depend on energy, airfoils, helper response motors, gimbaled push, force wheels, diversion of the fumes stream, charge stream, turn, and/or gravity to help control flight. The first rockets were used as propulsion systems for arrows, and may have appeared as early as the 10th century in Song dynasty China. However more solid documentary evidence does not appear until the 13th century. The technology probably spread across Eurasia in the wake of the Mongol invasions of the mid-13th century. Usage of rockets as weapons before modern rocketry is attested in China, Korea, Indian subcontinent, and Europe. One of the first recorded rocket launchers is the "wasp nest" fire arrow launcher produced by the Ming dynasty in 1380. Iron-cased rockets, known as Mysorean rockets, were developed in Kingdom of Mysore by the mid-18th century in India. William Congreve, son of the Comptroller of the Royal Arsenal, Woolwich, London, became a major figure in the field. From 1801, Congreve researched on the original design of Mysore rockets and set on a vigorous development program at the Arsenal's laboratory. At the beginning of the 20th century, there was a burst of scientific investigation into interplanetary travel, largely driven by the inspiration of fiction by writers such as Jules Verne and H. G. Wells as well as philosophical movements like Russian cosmism. Scientists seized on the rocket as a technology that was able to achieve this in real life, a possibility first recognized in 1861 by William Leitch. II. Literature Review Geyergy kuilanoff and Richard m. Drake fluor Daniel [1] This paper presents criteria and procedures for the design of structures and components for wind generated missiles. Methods for determining missile-induced loading, calculated structural response, performance requirements, and design considerations are covered. The presented criteria is applicable to Safety-Related concrete buildings as a whole and to all their exposed external components including walls, roofs, and supporting structural systems and elements. DetlefK uhl [2] The acceleration of these gases through the engine exerts force “thrust" on the combustion chamber and nozzle, propelling the vehicle according to Newton's Third Law. This actually happens because the force pressure time’s area on the combustion chamber wall is unbalanced by the nozzle opening, this is not the case in any other direction. The shape of the nozzle also generates force by directing the exhaust gas along the axis of the rocket. JETIRBZ06053 Journal of Emerging Technologies and Innovative Research (JETIR) www.jetir.org 333 © 2019 JETIR May 2019, Volume 6, Issue 5 www.jetir.org (ISSN-2349-5162) L.C. Scalabrin and J.L.F. Azevedo, P.R.F. Teixeira, A.M. Awruch [3] Aerodynamic flow simulations over the first Brazilian satellite launch vehicle, VLS, during its first-stage flight are presented. The three dimensional compressible flow is modeled by the Euler equations and a Taylor-Galerkin finite element method with artificial dissipation is used to obtain the numerical solution. Transonic and supersonic results for zero angle-of-attack are presented and compared to available experimental results. The influence of mesh refinement and artificial dissipation coefficient on the transonic flow results are discussed. The results obtained for the supersonic simulations present good agreement with experimental data. The transonic simulation results capture the correct trends but they also indicate that this flight condition requires more refined meshes. III. Objectives The specific objectives of the current work are as follows i. To implement the techniques such as structural (static and dynamic) analysis to the sub sonic missile in the effective way with the low cost. To design the missile model by the help of modelling tools using solid edge v19, Catia v6. ii. Is to achieve the Maneuvering in all 6 Dof , The missile flight range, Universal for multiple platforms, Fire and forget principle of operation, Shorter flight times leading to lower target dispersion and quicker engagement, Transport launch canister (TLC) for transportation, Storage and launch. iii. To study behaviour of the missile when the thickness of the outer shell material is increased and structural changes when the loads are applied. To analyse by applying the loads on each parts of the rocket model by using AL-2024, AL-7075, Aluminim-copper alloy-AA2014, Titanium alloy(23Ti6Al4rELI alloy), Maraging Steel and the comparison is made by applying same value of loads, boundary conditions and constraints on the model for the materials considered separately and selected the best feasible material for the missile structural. iv. To obtain the results when load is applied on the first stage of the rocket model comparing the displacement and contour results for the materials respectively using the Hypermesh For Pre-processing, Optistruct, Acuconsole For Solving and Hyper-view, Acu-Field View For Post Processing. 3.1 Methodology JETIRBZ06053 Journal of Emerging Technologies and Innovative Research (JETIR) www.jetir.org 334 © 2019 JETIR May 2019, Volume 6, Issue 5 www.jetir.org (ISSN-2349-5162) IV. Design of Missile Components In this design and modelling of the rocket structure is done through Solid Edge and Catia V6 tools. Here in this proposed rocket structure we have five main parts that is nose, nose cone, body, tail and fin. These parts are individually design first with the respective dimensions. After the modelling of each part they are assembled and we get the final design of the rocket structure. 4.1 Design of Nose Part Nose part is the foremost part in a rocket structure where the nozzle is attached. First we design the nose part of the rocket. Fig 1: Design of Nose Part of Rocket Fig 1.1: Diameter of Nose Part of Rocket 4.2 Design of Nose Cone The second part after nose is nose cone design. Nozzles are carried in this nose cone part. The nose cone is of the most pivotal piece of a rocket. The nose cone of a rocket goes about as an approach to punch an opening in the environment. Fig 2: Design of Nose Cone Part of Rocket JETIRBZ06053 Journal of Emerging Technologies and Innovative Research (JETIR) www.jetir.org 335 © 2019 JETIR May 2019, Volume 6, Issue 5 www.jetir.org (ISSN-2349-5162) Fig 2.1: Inner diameter of Nose Cone Part Fig 2.1.1: Outer diameter of Nose Cone 4.3 Design of Main Body The third part is body of a rocket is one of the more credible part. The reason for the body is to house the fuel. It is frequently as an empty chamber in light of the fact that it diminishes the sum surface space that is in contact with the air.
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