Multidisciplinary optimization and performance analysis tool for ballistic missiles

Date

2019-01-01

Author

Adsız, Mısra Ayşe
Kutay, Ali Türker

Metadata

Show full item record

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

Item Usage Stats

110
views

0
downloads

© 2019 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.During rocket/missile system design process, system design must be made in accordance with military standards, which have very strict rules. Product delivery dates usually are very rigid. Despite this, during conceptual design, requirements are often updated within the design process that requires the design to be updated frequently. It is essential to perform these steps as efficiently and quickly as possible. The products which are inexpensive and have best performance parameters are preferred, and so the companies with these products can survive. For this purpose, the conceptual design, which is the first step of the system design process, needs to be optimized. In this study, it is aimed to develop a system design tool that simplifies the conceptual design process, creates design alternatives quickly, tests them, performs performance analysis, and selects the optimum among these alternatives. By using this tool, it is possible for the designer to obtain the information needed for the preliminary process quickly and efficiently.

URI

https://hdl.handle.net/11511/56173

DOI

https://doi.org/10.2514/6.2019-1972

Collections

Department of Aerospace Engineering, Conference / Seminar

Suggestions

OpenMETU
Core

Fully transient conjugate analysis of silica-phenolic charing ablation coupled with interior ballistics Alanyalıoğlu, Çetin Ozan; Özyörük, Yusuf (2019-01-01) © 2019, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.Due to its excellent insulation capability, usage of silica-phenolic charring ablator as nozzle liner is a common practice in solid rocket motor industry. During the design of a solid rocket motor employing silica-phenolic as nozzle liner, it is desired to conduct an accurate analysis yielding in-depth thermal response and recession characteristics. As the interior ballistics and nozzle recession rate mutually interact...
Multi-element high-lift design using the Navier-Stokes equations Eyi, Sinan; Lee, K.D.; Rogers, S.E.; Kwak, D. (1996-01-01) © by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.A method of optimizing the geometry and position of high-lift system elements is presented. The design optimization method maximizes lift without increasing the drag of multi-element airfoils at take-off and landing configurations. It uses an incompressible Navier-Stokes flow solver, a chimera overlaid grid system, and a constrained numerical optimizer. A finite-difference method is used to obtain aerodynamic sensitivity d...
Computational fluid dynamics and proper orthogonal decomposition based control of flow over supersonic cavities Gelisli, Kubra Asena; Aradag, Selin; Tascioglu, Yigit; Özer, Mehmet Bülent (2019-01-01) © 2019, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.A Computational Fluid Dynamics (CFD) study is conducted to investigate the unsteady, turbulent supersonic cavity flow characteristics and to control the severe effects of the flow field. Simulations of Mach 1.5 supersonic cavity flow with a length to depth ratio of 5.07 are performed using commercial ANSYS Fluent solver. Unsteady density-based Reynolds Averaged Navier-Stokes equations are modeled with standard k-ω turb...
Static aeroelastic analysis of supersonic nozzles and performance response Duzel, U.; Eyi, Sinan (2014-01-01) © 2014 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.The effects of static aeroelasticity on the performance of supersonic nozzles are analyzed. A flow analysis was conducted to investigate five different configurations of two dimensional convergingdiverging nozzles. Computational results are validated with experimental data. Two of the configurations, which have the same throat area, throat radius, and convergence angle and total nozzle length are selected as the basel...
A multi-point optimization for transonic airfoil design Hager, J.O.; Eyi, Sinan; Lee, K.D. (1992-01-01) © 1992 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.A two-point, aerodynamic design method is presented which improves the aerodynamic performance of transonic airfoils over a range of the flight envelope. It couples an Euler flow solver and a numerical optimization tool. The major limitation of single-point design is the poor off-design performance. Two-point design is used to extend the optimized performance range over more of the desired flight envelope. The method ...

Citation Formats

M. A. Adsız and A. T. Kutay, “Multidisciplinary optimization and performance analysis tool for ballistic missiles,” 2019, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/56173.