ORBIT TRANSFER OF AN EARTH ORBITING SOLAR SAIL CUBESAT

Date

2017-02-09

Author

Atas, Omer
Tekinalp, Ozan

Metadata

Show full item record

This work is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

Item Usage Stats

211
views

0
downloads

Propelling a spacecraft by using solar radiation pressure is examined in the context of orbital maneuvers. A locally optimal steering law to progressively change number of selected orbital elements together is addressed. An Earth centered cubesat satellite with solar sail is used as an example. The proper attitude maneuver mechanization is proposed to harvest highest solar radiation force in the desired direction for Earth orbiting satellites. The satellite attitude control is realized using to-go quaternion feedback control. And the effectiveness of the approach to progressively changing the orbital parameters is demonstrated.

URI

https://hdl.handle.net/11511/53547

Conference Name

27th AAS/AIAA Space Flight Mechanics Meeting, San-Antonio, (5 - 09 Şubat 2017)

Collections

Department of Aerospace Engineering, Conference / Seminar

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. ...
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...
SATELLITE ATTITUDE CONTROL USING DISSIMILAR REDUNDANT ACTUATORS Kahraman, Ozgur; Tekinalp, Ozan (2009-02-12) Low Earth orbit satellites are usually equipped with magnetic torquers for momentum dumping and reaction wheels to carry out three axis attitude stabilization and control. These two different types of actuators mixed and used together to carry out slew maneuvers. The problem of allocating the control to these different types of actuators is realized using a recently developed algorithm called blended inverse. The algorithm is compared with the Moore-Penrose pseudo inverse demonstrating its success in realiz...
Trajectory computation of small solid particles released and carried by flowfields of helicopters in forward flight Pekel, Yusuf Okan; Özyörük, Yusuf; Department of Aerospace Engineering (2010) In this thesis, trajectory computations of chaff particles ejected from a medium weight utility helicopter are performed using computational fluid dynamics. Since these chaff particles are ejected from a helicopter and carried by its flow field, it is necessary to compute and include the effects of the helicopter flow field in general and engine hot gases, main and tail rotor wakes in particular. The commercial code FLUENT is used for flow field and trajectory computations. Both main rotor and tail rotor ar...
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...

Citation Formats

O. Atas and O. Tekinalp, “ORBIT TRANSFER OF AN EARTH ORBITING SOLAR SAIL CUBESAT,” San-Antonio, Kuzey Mariana Adaları, 2017, vol. 160, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/53547.