MISSION ANALYSIS OF A NEW SOLAR SAIL SATELLITE CONCEPT AT LOW EARTH ORBIT

MISSION ANALYSIS OF A NEW SOLAR SAIL SATELLITE CONCEPT AT LOW EARTH ORBIT Polat, Hakkı; Tekinalp, Ozan (2021-01-01) © 2021, Univelt Inc. All rights reserved.Exploiting the propellant free maneuver capability of solar sail satellites for high resolution Earth observation mission is addressed with an elliptical low Earth orbit. The employed orbit has a low perigee altitude for observation and a high apogee altitude for orbit maneuvers. For the purpose of mission analysis of this new concept, a reference satellite configuration is designed with an aim to determine the technological readiness level based on the characteristi...
Mission Analysis of a New Solar Sail Satellite Concept at Low Earth Orbit POLAT, HALİS CAN; Tekinalp, Ozan (2021-01-01)
Trajectory optimization of advanced launch system Karsli, G; Tekinalp, Ozan (2005-06-11) Trajectory optimization of an advanced launch vehicle is addressed. The optimal control problem is converted into a parameter optimization problem. Then, simulated annealing based single and multiobjective optimization algorithms are used. The single objective optimization problem is formulated to minimize the total flight time, while the multiobjective formulation tries to maximize payload mass and orbit insertion velocity. The problem is also solved using our novel multiple cooling multiobjective simulate...
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.
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

H. C. POLAT and O. Tekinalp, “MISSION ANALYSIS OF A NEW SOLAR SAIL SATELLITE CONCEPT AT LOW EARTH ORBIT,” presented at the American Astronautical Society, 2020 Astrodynamics Specialist Conference, Lake Tahoe, Virtual, Amerika Birleşik Devletleri, 2020, Accessed: 00, 2022. [Online]. Available: https://www.xcdsystem.com/aas/abstract/abstract.cfm?CFID=52603838CFTOKEN=554da6ba9849220e-7E7E656C-D4D5-F0DA-FF9D01E236848D6D.