Orbit Control of an Earth Orbiting Solar Sail Satellite

Polat, Halis Can
Tekinalp, Ozan
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 employed orbit properties and deriving the optimal force direction in the orbital frame as a function of true anomaly. The second approach is accomplished by implementing a Lyapunov-based nonlinear feedback controller that continuously gives solar thrust in the orbital frame. The simulation results for the orbit control methods are given and discussed to show the solar sail satellite's capability for altering the orbital elements at LEO are stated. It is demonstrated that both approaches give satisfactory results.


Attitude and Orbit Control of a Solar Sail Spacecraft for Responsive Operational Concept
Polat, Halis Can; Tekinalp, Ozan; Department of Aerospace Engineering (2021-6-15)
Utilization of the propellant-free thrust capability of Solar Sail Spacecraft (SSS) is addressed. For this purpose, an elliptical orbit with a very low perigee altitude and an apogee altitude high enough to have solar sail acceleration is proposed for Earth observation mission. In the mission part, regional observation tasks are carried out that take place in very Low Earth Orbit region. The orbit maintenance and control are handled in the high altitude regions. The baseline SSS design is accomplished and p...
Solar Sail Application with a Proposed Low Earth Orbit Mission Concept
Polat, Halis Can; Tekinalp, Ozan (2019-01-01)
Solar Sail applications utilizing the advantages of propellant-free and theoretically infinite specific impulse are widely investigated, especially for interplanetary/interstellar and near-Earth asteroid missions and non-Keplerian orbit designs. However, applications regarding to the Low Earth Orbit (LEO), specifically below 700 km, are rarely studied as aerodynamic drag is dominant. This study is aimed to harvest the LEO mission advantages by proposing an elliptical orbit design and control via continuous ...
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.
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. ...
GPS-based real-time orbit determination of artificial satellites using kalman, particle, unscented kalman and H-infinity filters
Erdoğan, Eren; Karslıoğlu, Mahmut Onur; Department of Geodetic and Geographical Information Technologies (2011)
Nowadays, Global Positioning System (GPS) which provide global coverage, continuous tracking capability and high accuracy has been preferred as the primary tracking system for onboard real-time precision orbit determination of Low Earth Orbiters (LEO). In this work, real-time orbit determination algorithms are established on the basis of extended Kalman, unscented Kalman, regularized particle, extended Kalman particle and extended H-infinity filters. Particularly, particle filters which have not been applie...
Citation Formats
H. C. Polat and O. Tekinalp, “Orbit Control of an Earth Orbiting Solar Sail Satellite,” INTERNATIONAL JOURNAL OF AERONAUTICAL AND SPACE SCIENCES, pp. 0–0, 2022, Accessed: 00, 2022. [Online]. Available: https://hdl.handle.net/11511/98877.