Development of a structural design methodology for filament winding composite rocket motor case

Download

index.pdf

Date

2019

Author

Erturan, Yakup

Metadata

Show full item record

This work is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

Item Usage Stats

411
views

482
downloads

Filament winding pressure vessels have a unique place in many areas such as space and ground applications for decades. Filament winding pressure vessels are used in products where weight is very critical. In such applications, composite winding pressure vessels have significant advantages over metal pressure vessels due to their high specific strength. In this study, it is aimed to design and analyze composite rocket motor cases produced by the filament winding method. Within the scope of the study, the dome profile, filament winding angle and strength of the filament winding composite case are calculated. Two methods are used in the design of dome of the filament winding pressure bearing containers. One of them gives a geodesic dome profile while the other is designed with a non-geodesic dome. Since geodesic winding dome design method limits the design parameters and boundary conditions, non-geodesic winding method, which provides wider design space, is used in this study. The fibers must remain stable on the winding mandrel during production and the slip tendency should also be taken into account in the design of the dome profile. Therefore, it is necessary to emphasize the importance of finding a suitable winding pattern by considering both the production and design criteria. 2-D analyses are performed in ABAQUS program in order to understand the design method better and to see how the case behaves when subjected to an internal pressure loading.

Subject Keywords

Rocket engines., Keywords: Composite Rocket Motor Casing, Fiber Reinforced Pressure Vessel, Filament Winding, Non-geodesic Dome Profile.

URI

http://etd.lib.metu.edu.tr/upload/12623844/index.pdf
https://hdl.handle.net/11511/44400

Collections

Graduate School of Natural and Applied Sciences, Thesis

Suggestions

OpenMETU
Core

DEVELOPMENT OF BOLTED FLANGE DESIGN TOOL BASED ON FINITE ELEMENT ANALYSIS AND ARTIFICIAL NEURAL NETWORK Yildirim, Alper; Kayran, Altan; Gulasik, Hasan; Çöker, Demirkan; Gürses, Ercan (2015-11-19) In bolted flange connections, commonly utilized in aircraft engine designs, structural integrity and minimization of the weight are achieved by the optimum combination of the design parameters utilizing the outcome of Many structural analyses. Bolt size, the number of bolts, bolt locations, casing thickness, flange thickness, bolt preload, and axial external force are some of the critical design parameters in bolted flange connections. Theoretical analysis and finite element analysis (FEA) are two main appr...
Use of artificial neural network in rotorcraft cooling system Akin, Altug; Kahveci, Harika Senem (2019-07-01) In this study, an Artificial Neural Network (ANN) is used to determine the surface temperatures of the avionics equipment located in an avionics bay of a rotorcraft. The bay is cooled via a system of a fan that supplies ambient air to the interior of the bay and an exhaust. A Feedforward Multi-Layer ANN is used with the input parameters of the fan and exhaust locations and the air mass flow rate of the fan. For training of the network, the results obtained by a large number of Computational Fluid Dynamics (...
DEVELOPMENT OF ARTIFICIAL NEURAL NETWORK BASED DESIGN TOOL FOR AIRCRAFT ENGINE BOLTED FLANGE CONNECTION SUBJECT TO COMBINED AXIAL AND MOMENT LOAD Sanli, T. Volkan; Gürses, Ercan; Çöker, Demirkan; Kayran, Altan (2017-11-09) Bolted flange connections are one of the most commonly used joint types in aircraft structures. Typically, bolted flange connections are used in aircraft engines. The main duty of a bolted flange connection in an aircraft engine is to serve as the load transfer interface from one part of the engine to the other part of the engine. In aircraft structures, weight is a very critical parameter which has to be minimized while having the required margin of safety for the structural integrity. Therefore, optimum d...
Development of an iterative method for liquid-propellant combustion chamber instability analysis Cengiz, Kenan; Özyörük, Yusuf; Department of Aerospace Engineering (2010) Controlling unsteady combustion induced gas flow fluctuations and the resultant motor vibrations is a very significant step in rocket motor design. It occurs when the unsteady heat release due to combustion happens to feed the acoustic oscillations of the closed duct forming a feed-back system. The resultant vibrations concerned may even lead to total failure of the rocket system unless analysed and tested thoroughly. This thesis aims developing a linear numerical analysis method for the growth rate of inst...
Use of split-disk tests for the process parameters of filament wound epoxy composite tubes Kaynak, Cevdet; PARNAS, LEVENT; ŞENEL, FİKRET (2005-08-01) The aim of this study was to investigate processing parameters of continuous fiber reinforced epoxy composite tubes produced by the filament winding technique. For this purpose, split-disk tests (according to ASTM D-2290 standard) were performed for the specimens produced with two different epoxy resin systems, five different fiber materials and five different winding angles. By determining the hoop tensile strength and modulus of these specimens, the effects of three filament-winding processing parameters;...

Citation Formats

Y. Erturan, “Development of a structural design methodology for filament winding composite rocket motor case,” Thesis (M.S.) -- Graduate School of Natural and Applied Sciences. Aerospace Engineering., Middle East Technical University, 2019.