Show/Hide Menu
Hide/Show Apps
Logout
Türkçe
Türkçe
Search
Search
Login
Login
OpenMETU
OpenMETU
About
About
Open Science Policy
Open Science Policy
Open Access Guideline
Open Access Guideline
Postgraduate Thesis Guideline
Postgraduate Thesis Guideline
Communities & Collections
Communities & Collections
Help
Help
Frequently Asked Questions
Frequently Asked Questions
Guides
Guides
Thesis submission
Thesis submission
MS without thesis term project submission
MS without thesis term project submission
Publication submission with DOI
Publication submission with DOI
Publication submission
Publication submission
Supporting Information
Supporting Information
General Information
General Information
Copyright, Embargo and License
Copyright, Embargo and License
Contact us
Contact us
Varying mass missile dynamics, guidance & control
Download
index.pdf
Date
2007
Author
Günbatar, Yakup
Metadata
Show full item record
Item Usage Stats
242
views
827
downloads
Cite This
The focus of this study is to be able to control the air-to-surface missile throughout the entire flight, with emphasis on the propulsion phase to increase the impact range of the missile. A major difficulty in controlling the missile during the propulsion phase is the important change in mass of the missile. This results in sliding the center of gravity (cg) point and changing inertias. Moreover, aerodynamic coefficients and stability derivatives are not assumed to be constant at predetermined ranges; conversely, they depend on Mach number, angle of attack, and side slip angle. Consequently, as the change of missile mass, cg point, inertia terms, and stability and aerodynamic coefficients come together apart from flight operation stages, a great number of points need to be taken into account when designing the controller. This makes controlling the missile all the more complicated. In this thesis, first the equations of motion are derived, in which, mass of the missile is not assumed constant. Thus, not only the variation of mass but also the variation of inertias is incorporated in the equations of motion. From the derived equations of motion, a nonlinear inverse dynamics controller that can achieve desired guidance for a conceptually developed air-to-surface missile has been designed, tested and verified for a modeled missile with six degrees of freedom. For brevity of the study, conceptual design and aerodynamic calculations are not given in detail. Nevertheless, improvements for conceptual design are suggested. As a result, it is shown that the controller works efficiently: the missile is able to hit the target with less than 12 m circular error of probability (CEP). Finally, studies and improvements are proposed.
Subject Keywords
Air Transportation
URI
http://etd.lib.metu.edu.tr/upload/2/12608977/index.pdf
https://hdl.handle.net/11511/16983
Collections
Graduate School of Natural and Applied Sciences, Thesis
Suggestions
OpenMETU
Core
Hovering Control of a Tilt-Wing UAV
Çakır, Hasan; Kurtuluş, Dilek Funda (2019-09-20)
In this study, the design and analysis of hovering controller of an UAV which is capable of doing vertical take-off and landing using the fixed six rotors placed on the tilt-wing and tilt-tail will be explained. The aircraft will have four rotors on the wing and two rotors on the tail. The main wing and horizontal tail will be capable of 90° tilting. Whole flight is separated into three flight modes, which are VTOL, Transition and Forward Flight, to have a robust control on aircraft. Only hover control of t...
Reinforcement learning control for helicopter landing in autorotation
Kopsa, Kadircan; Kutay, Ali Türker (2018-01-01)
This study presents an application of an actor-critic reinforcement learning method to the nonlinear problem of helicopter guidance during autorotation in order to achieve safe landing following engine power loss. A point mass model of an OH-58A helicopter in autorotation was built to simulate autorotation dynamics. The point-mass model includes equations of motion In vertical plane. The states of the point-mass model are the horizontal and vertical velocities, the horizontal and vertical positions, the rot...
Increasing air defense capability by optimizing burst distance
Türkuzan, Mehmet; Kocaoğlan, Erol; Department of Electrical and Electronics Engineering (2010)
In this thesis, burst distance is optimized to increase air defense capability for systems utilizing airburst munitions. A simulator program is created to use during the study by taking advantage of the MATLAB environment. While creating the simulator program, a munition path model is derived by using fourth order Runge-Kutta method. Then, simulations are conducted at different burst distances and related information are recorded. By using least square optimization method and gathered data, optimum burst di...
High angle attack maneuvering and stabilization control of aircraft
Ateşoğlu, Özgür; Özgören, Mustafa Kemal; Department of Mechanical Engineering (2007)
In this study, the implementation of modern control techniques, that can be used both for the stable recovery of the aircraft from the undesired high angle of attack flight state (stall) and the agile maneuvering of the aircraft in various air combat or defense missions, are performed. In order to accomplish this task, the thrust vectoring control (TVC) actuation is blended with the conventional aerodynamic controls. The controller design is based on the nonlinear dynamic inversion (NDI) control methodologi...
Structured H-Infinity controller design and analysis for highly maneuverable jet aircraft
Özkan, Salih Volkan; Tekinalp, Ozan; Department of Aerospace Engineering (2022-2-10)
Robust control technique is utilized to develop flight control laws for highly maneuverable aircraft. A structured H-Infinity controller is used to optimize the gains of the proposed control algorithm. For this purpose systune algorithm available in Matlab is employed to successfully obtain the controller gains satisfying selected design requirements. Designed control laws are evaluated according to these requirements and validation of the methodology is presented.
Citation Formats
IEEE
ACM
APA
CHICAGO
MLA
BibTeX
Y. Günbatar, “Varying mass missile dynamics, guidance & control,” M.S. - Master of Science, Middle East Technical University, 2007.