Design for modularity of Blended Wing Body (BWB) baseline ii-E2 Unmanned Aerial Vehicle (UAV) / Matzaini Katon
This thesis describes the strategy used for designing the structural modular layout for the Blended Wing Body (BWB) Baseline II-E2 Unmanned Aerial Vehicle (UAV) airplane. In order to give UAV more flexibility in terms of availability of flight mission, there was a need for a quick and ease of assemb...
| Main Author: | |
|---|---|
| Format: | Thesis |
| Language: | English |
| Published: |
2014
|
| Subjects: | |
| Online Access: | http://ir.uitm.edu.my/id/eprint/14006/ http://ir.uitm.edu.my/id/eprint/14006/1/TM_MATZAINI%20KATON%20EM%2014_5.pdf |
| Summary: | This thesis describes the strategy used for designing the structural modular layout for the Blended Wing Body (BWB) Baseline II-E2 Unmanned Aerial Vehicle (UAV) airplane. In order to give UAV more flexibility in terms of availability of flight mission, there was a need for a quick and ease of assembly and disassembly’s process
for the airframe. The goal of this research was to design a BWB modular airframe, focusing on the ease of airframe assembly and disassembly. Morphological Method and Pugh Method were used as the concept generation and evaluation tools in designing the BWB airframe. The BWB was divided into 5 main modules; wing-body module, starboard and portside module and, right-side and left-side canards module. CATIA, a Computational Aided Design (CAD) software was used to build the three dimensional (3-D) model of the airframe. MSC Patran/Nastran was used as the finite
element (FE) analysis tool to analyze the BWB airframe static strength. Analysis was done focusing on the stress and deflections results. FE models for the airframe were developed in MSC Patran. CQUAD4, CTRIA3, CBEAM and CBAR elements were
used to represent the individual components of the airframe such as spar and frames. Validation of FE static analysis was done using the static theoretical analysis in the form of stress calculations using simple beam theory. The airframe design was based on the +3.8 g flight load. Sizing of joints between modules was done through the use of empirical analysis. Internal forces induced in the connector between modules were used to size the joints. Approach using the CAD and Computational Aided
Engineering (CAE) platform for designing the modular BWB airplane has been shown in this research. Design of the airframe proposed here had been analytically proven to be safe. |
|---|