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
Attitude control of an earth orbiting solar sail satellite to progressively change the selected orbital element
Download
index.pdf
Date
2014
Author
Ataş, Ömer
Metadata
Show full item record
Item Usage Stats
268
views
124
downloads
Cite This
Solar sailing is currently under investigation for space propulsion. Radiation pressure from the Sun is utilized to propel the spacecraft. This thesis examines locally optimal steering law to progressively change the selected orbital elements, without considering others, of an Earth centered Keplerian orbit of a cube satellite with solar sail. The proper attitude maneuver mechanization is proposed to harvest highest solar radiation force in the desired direction for such Earth orbiting satellites. The satellite attitude control is realized by developing quaternion feedback controller. The changes of the orbital elements are observed.
Subject Keywords
Solar sails.
,
Orbital mechanics.
,
Artificial satellites
,
Artificial satellites
,
Artificial satellites
URI
http://etd.lib.metu.edu.tr/upload/12616987/index.pdf
https://hdl.handle.net/11511/23418
Collections
Graduate School of Natural and Applied Sciences, Thesis
Suggestions
OpenMETU
Core
ATTITUDE CONTROL OF AN EARTH ORBITING SOLAR SAIL SATELLITE TO PROGRESSIVELY CHANGE THE SELECTED ORBITAL ELEMENT
Atas, Omer; Tekinalp, Ozan (2015-01-15)
Solar sailing where the radiation pressure from Sun is utilized to propel the spacecraft is examined in the context of orbital maneuvers. In this vein a locally optimal steering law to progressively change the selected orbital elements, without considering others, of an Earth centered Keplerian orbit of a cubesat satellite with solar sail is addressed. The proper attitude maneuver mechanization is proposed to harvest highest solar radiation force in the desired direction for such Earth orbiting satellites. ...
Attitude Control of Satellites with De-Orbiting Solar Sails
Tekinalp, Ozan (2013-06-14)
Utilization of solar sails for the de-orbiting of satellites is investigated. The satellite orbit is assumed to be equatorial. Proper attitude maneuver is prescribed to utilize highest solar drag from the sun. The maneuver is realized using a quaternion feedback algorithm. The success of the attitude control during the continuous and abrupt maneuvers is shown through simulations. The reduction in semi major axis due to solar drag is also demonstrated.
A Control moment gyroscope based on rotational vibrations, dynamic model and experimentation
Arberkli, Ferhat; Azgın, Kıvanç; Department of Mechanical Engineering (2018)
Satellite attitude determination and control system is one of the main subsystems of a spacecraft. Within this domain, there are several types of actuators; such as reaction wheels, control moment gyroscopes (CMG), propulsion systems and magnetic torque rods. All of them are common and currently being used on modern satellites and space stations depending on the application. Conventional reaction wheel and CMG operation are based on the continuous rotation of their rotor mass to exchange angular momentum be...
Numerical Validation of a Pyroshock Test System and Application to Qualification Tests
Yalçınkaya, Tuncay; Gursoy, Bahadir (2022-08-01)
Spacecraft are exposed to severe mechanical loads, i.e., shock loads, during their journey to orbit. Such loads usually develop due to a separation event through the activation of pyrotechnic devices. They might be transmitted throughout the entire structure and strongly influence the service performance of electronic components. Therefore, it is crucial to study whether the instruments can resist such a harsh environment. However, due to the vulnerability and high cost of the equipment, experimental setups...
Orbit Control of an Earth Orbiting Solar Sail Satellite
Polat, Halis Can; Tekinalp, Ozan (2022-09-01)
A concept for the utilization of solar sail satellite's propellant-free thrust capability at Low earth orbit (LEO) is proposed and its orbit control strategy is analyzed. Thrust vector control of the sail's normal direction is used to harvest the solar radiation pressure for generating the necessary acceleration to change the orbital elements. The required control vector direction is determined with two approaches. The first approach is realized by approximating the Gaussian Variational Equations at the emp...
Citation Formats
IEEE
ACM
APA
CHICAGO
MLA
BibTeX
Ö. Ataş, “Attitude control of an earth orbiting solar sail satellite to progressively change the selected orbital element,” M.S. - Master of Science, Middle East Technical University, 2014.
