External configuration design and aerodynamic optimization of modular guided munitions

Download

index.pdf

Date

2019

Author

Gün, Mert

Metadata

Show full item record

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

Item Usage Stats

426
views

212
downloads

Guided munitions, also known as gliding missiles, are not stand alone systems; rather, they are converted from a dummy body with the help of guidance kits. Guided munitions are used in great number during military operations, unlike air-to-air or cruise missiles. Guided munitions can be classified in two main sub-categories. First group provides guidance and stability with use of strakes. These type of missiles used for relatively short ranges. Second group has wings instead of strakes and effective in larger ranges. Missiles in first subcategory may be converted to second group by changing their strakes with wings. For such a modification, both versions of that missile should be optimized together during the conceptual design phase. The main focus of this study is to obtain a conceptual design tool, by employing Genetic Algorithm with aerodynamic analysis, that optimizes a guided munition geometry which can be used as both versions, with strakes or wings, in terms of aerodynamics related objectives.

Subject Keywords

Aerodynamics., Keywords: Aerodynamic Optimization, Missile Outer Geometry, Genetic Algorithm, Guided Munitions, Modular Design.

URI

http://etd.lib.metu.edu.tr/upload/12624531/index.pdf
https://hdl.handle.net/11511/44560

Collections

Graduate School of Natural and Applied Sciences, Thesis

Suggestions

OpenMETU
Core

Missile guidance with impact angle constraint Çilek, Barkan; Kutay, Ali Türker; Department of Aerospace Engineering (2014) Missile flight control systems are the brains of missiles. One key element of a missile FCS is the guidance module. It basically generates the necessary command inputs to the autopilot.Guidance algorithm selection depends on the purpose of the corresponding missile type. In this thesis, missile guidance design problem with impact angle constraint is studied which is the main concern of anti-tank and anti-ship missiles. Different algorithms existing in the literature have been investigated using various anal...
Proxy-Based Sliding Mode Stabilization of a Two-Axis Gimbaled Platform Hasturk, Ozgur; Erkmen, Aydan Müşerref; Erkmen, İsmet (2011-10-21) Nowadays, high portion of tactical missiles use gimbaled seekers. For accurate target tracking, the platform where the gimbal is mounted must be stabilized with respect to the motion of the missile body. Line of sight stabilization is critical for fast and precise tracking and alignment. Although conventional PID framework solves many stabilization problems, it is reported that many PID feedback loops are poorly tuned. In this paper, a recently introduced approach, proxy-based sliding mode control to a line...
Missile autopilot design by projective control theory Doruk, Reşat Özgür; Kocaoğlan, Erol; Department of Electrical and Electronics Engineering (2003) In this thesis, autopilots are developed for missiles with moderate dynamics and stationary targets. The aim is to use the designs in real applications. Since the real missile model is nonlinear, a linearization process is required to get use of systematic linear controller design techniques. In the scope of this thesis, the linear quadratic full state feedback approach is applied for developing missile autopilots. However, the limitations of measurement systems on the missiles restrict the availability of ...
Dynamic modeling and control of a hybrid fin actuation system for an air-to-air missile Çelik, Tayfun; Ciğeroğlu, Ender; Yazıcıoğlu, Yiğit; Department of Mechanical Engineering (2014) Air-to-air missiles require high maneuverability. In order to obtain high maneuverability, hybrid fin actuation systems are used. In this study, a hybrid fin actuation system which is composed of aerodynamic control surfaces and thrust vector control is designed. Both aerodynamic and thrust vector control types are explained and the most suitable pair is determined for air-to-air missile. Then, the designed system is physically constructed and system identification procedure is performed. After that three d...
Sliding mode guidance of an air-to-air missile Ulu, Muharrem; Leblebicioğlu, Mehmet Kemal; Department of Electrical and Electronics Engineering (2013) Pursuit of a highly maneuverable aircraft by an air-to-air missile requires a solution to a challenging guidance and control problem. Precision is the most important need for these missiles. Appropriate guidance commands that are generated by the guidance method and an autopilot that can fulfil the agility needs of such a missile are the keys of minimizing the distance between the missile and the target and a successful interception. In this thesis, autopilot and guidance method design of an air-to-air miss...

Citation Formats

M. Gün, “External configuration design and aerodynamic optimization of modular guided munitions,” Thesis (M.S.) -- Graduate School of Natural and Applied Sciences. Aerospace Engineering., Middle East Technical University, 2019.