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
Smooth slew maneuvers of flexıble spacecraft
Download
index.pdf
Date
2019
Author
Altınışık, Süleyman
Metadata
Show full item record
Item Usage Stats
202
views
110
downloads
Cite This
In this thesis, the vibration suppression of flexible spacecraft that carries out attitude tracking maneuvers is addressed. Attitude control algorithm that uses quaternion parametrization is employed. The nonlinear tracking controller employs the to-go quaternion and its derivative. Feedback controller designed is based on this recently developed attitude formulation. Piezoelectric sensors and actuators are also included to rapidly suppress structural vibration. The simulation results demonstrate the success of the algorithm in attitude tracking and vibration suppression.
Subject Keywords
Space vehicles.
,
Vibration (Aeronautics).
,
Airplanes
,
Trajectories (Mechanics).
URI
http://etd.lib.metu.edu.tr/upload/12623111/index.pdf
https://hdl.handle.net/11511/28058
Collections
Graduate School of Natural and Applied Sciences, Thesis
Suggestions
OpenMETU
Core
Autonomous spacecraft rendezvous and docking on safe trajectories
Büyükkoçak, Ali Tevfik; Tekinalp, Ozan; Department of Aerospace Engineering (2018)
In this thesis, rendezvous and docking operation of a pair of low earth orbit spacecraft is addressed. Two different sets of equations for the nonlinear orbital relative motion of spacecraft are derived and simulation codes for this motion are developed. First, Hill-Clohessy-Wiltshire (HCW) equations are used in chaser-target spacecraft configuration with Model Predictive Control (MPC) algorithm including some safety considerations such as debris avoidance, direction of approach constraint and slow impact r...
Low reynolds number aerodynamics of flapping airfoils in hover and forward flight
Günaydınoğlu, Erkan; Kurtuluş, Dilek Funda; Department of Aerospace Engineering (2010)
The scope of the thesis is to numerically investigate the aerodynamics of flapping airfoils in hover and forward flight. The flowfields around flapping airfoils are computed by solving the governing equations on moving and/or deforming grids. The effects of Reynolds number, reduced frequency and airfoil geometry on unsteady aerodynamics of flapping airfoils undergoing pure plunge and combined pitch-plunge motions in forward flight are investigated. It is observed that dynamic stall of the airfoil is the mai...
Vibration isolation system for space launch vehicles
Karaman, Burak; Özgen, Gökhan Osman; Department of Mechanical Engineering (2018)
In the frame of this thesis, novel vibration isolation systems for spaces launch vehicles are designed and verified by vibration tests in laboratory environment. Payloads, satellites or spacecraft, are exposed high level of vibration loads during launch. These vibration loads are transmitted from launch vehicle to the payload and may have a detrimental effect on the payload. Vibration isolation systems can be used at the payload-launch vehicle interface in order to reduce vibration environment of a payload....
Numerical and experimantal analysis of flapping motion in hover, application to micro air vehicles
Kurtuluş, Dilek Funda; Alemdaroğlu, Hüseyin Nafiz; Department of Aerospace Engineering (2005)
The aerodynamics phenomena of flapping motion in hover are considered in view of the future Micro Air Vehicle applications. The aim of this work is to characterize the vortex dynamics generated by the wing in motion using direct numerical simulation and experimental analysis then to propose a simplified analytical model for prediction of the forces in order to optimize the parameters of the motion leading to maximum force. A great number of cases are investigated corresponding to different angles of attack,...
Aircraft motion dynamics and lateral trajectory tracking algorithm design for the enhancement of flight safety
Günhan, Cahide Yeliz; Demirbaş, Kerim; Department of Electrical and Electronics Engineering (2018)
This thesis aspires to cover the fundamentals of an aircraft control for Flight Management System (FMS). FMS, trajectory tracking and performance requirements of a flight are the focal points of the thesis. In view of this, the thesis consists of the outlined components to achieve its goal; (i) generating paths - which denotes the creation of reference paths for trajectory by complying with the avionic performance standardizations, (ii) controlling the aircraft – which propagates the control commands by usi...
Citation Formats
IEEE
ACM
APA
CHICAGO
MLA
BibTeX
S. Altınışık, “Smooth slew maneuvers of flexıble spacecraft,” M.S. - Master of Science, Middle East Technical University, 2019.