Development of an external ballistics simulation software

Download
2013
Körpe, Serkan Berkay
A fully automatic external ballistic CFD analysis software is developed in C++ for the purpose of acquiring instant aerodynamic properties, particularly pressure based drag coefficient during the free flight of any intended flat based or boat tailed projectile. To eliminate any dependency on other commercial or third party software, a three-dimensional Computational Fluid Dynamics (CFD) analysis code is developed for the entire analysis process including a three-dimensional geometry modeler and surface mesh generator, an adaptively-refined Cartesian volume mesh generator, an Euler solver and a motion solver. Characteristic equations of a projectile are embedded to the surface modeler to draw the two-dimensional outline of it. Then, the three-dimensional surface is generated by revolving the two-dimensional outline around the centerline. Triangular surface mesh of the projectile is created by using the point cloud over the surface. Surface mesher module of the software creates output mesh file for the usage of Cartesian volume mesh generator. Volume mesh generation process starts by creating the root cell and uniform mesh. Neighboring relativities are set during the cell creation. The intended projectile is fitted into uniform mesh by using the triangular surface mesh file. The inside – outside states of the cell corners are determined by the ray-casting approach. Depending on the states of the corners, the cell types are specified. Then, the cut cells are formed by the marching cubes method. Euler equations are solved for determining the flow field around a projectile. Finite volume method is used for the discretization of the equations. Solution-adaptive mesh refinement is applied to the developed flow solver. Finally, the trajectory of a projectile is calculated by using the developed motion solver.

Suggestions

Parallel, navier-stokes computation of the flowfield of a hovering helicopter rotor
Geçgel, Murat; Özyörük, Yusuf; Department of Aerospace Engineering (2003)
The aim of this study is to extend a parallel Fortran90 code to compute three6dimensional laminar and turbulent flowfields over rotary wing configurations. The code employs finite volume discretization and the compact, four step Runge-Kutta type time integration technique to solve unsteady, thin6layer Navier6Stokes equations. Zero6order Baldwin6Lomax turbulence model is utilized to model the turbulence for the computation of turbulent flowfields. A fine, viscous, H type structured grid is employed in the co...
Multi objective conceptual design optimization of an agricultural aerial robot (AAR)
Özdemir, Segah; Tekinalp, Ozan; Department of Aerospace Engineering (2005)
Multiple Cooling Multi Objective Simulated Annealing algorithm has been combined with a conceptual design code written by the author to carry out a multi objective design optimization of an Agricultural Aerial Robot. Both the single and the multi objective optimization problems are solved. The performance figures of merits for different aircraft configurations are compared. In this thesis the potential of optimization as a powerful design tool to the aerospace problems is demonstrated.
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...
Experimental Investigation of Aerodynamics of Flapping-Wing Micro-Air-Vehicle by Force and Flow-Field Measurements
Deng, Shuanghou; Perçin, Mustafa; van Oudheusden, Bas (2016-02-01)
This study explores the aerodynamic characteristics of a flapping-wing micro aerial vehicle (MAV) in hovering configuration by means of force and flowfield measurements. The effects of flapping frequency and wing geometry on force generation were examined using a miniature six-component force sensor. Additional high-speed imaging allowed identification of the notable different deformation characteristics of the flexible wings under vacuum condition in comparison to their behavior in air, illustrating the re...
COMPARATIVE STRUCTURAL OPTIMIZATION STUDY OF COMPOSITE AND ALUMINUM HORIZONTAL TAIL PLANE OF A HELICOPTER
Arpacıoğlu, Bertan; Kayran, Altan (2019-11-11)
This work presents structural optimization studies of aluminum and composite material horizontal tail plane of a helicopter by using MSC. NASTRAN SOL200 optimization capabilities. Structural design process starts from conceptual design phase, and structural layout design is performed by using CATIA. In the preliminary design phase, study focuses on the minimum weight optimization with multiple design variables and similar constraints for both materials. Aerodynamic load calculation is performed using ANSYS ...
Citation Formats
S. B. Körpe, “Development of an external ballistics simulation software,” M.S. - Master of Science, Middle East Technical University, 2013.