Maneuver planning strategy for rapid response solar sail satellite concept

Date

2021-01-01

Author

Polat, Halim
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

134
views

0
downloads

Regarding the use of Solar Sail Satellites at low altitudes for the proposed concept, a study is carried out to determine the critical mode switching altitude of the mission orbit and a review is presented for the non-ideal solar force model. Based on the results of the study, further analysis is performed regarding the maneuver planning strategy. The proposed concept needs solar sailing maneuvers for reshaping, resizing and/or reorienting the orbit for both station-keeping and transferring to another orbit. These maneuvers can be categorized as in-plane and out-of-plane maneuvers. In order to devise a strategy for maneuver planning, geometrical limitations of the solar sailing mechanism mainly based on the Sun’s relative position are synthesized with mission orbit parameters. The results showed that five significant parameters are needed to predict the applicability of the maneuvers.

URI

https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=85100372705&origin=inward
https://hdl.handle.net/11511/90887

Conference Name

AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2021

Collections

Department of Mechanical Engineering, Conference / Seminar

Suggestions

OpenMETU
Core

Maneuver Planning Strategy for Rapid Response Solar Sail Satellite Concept Polat, Halis Can; Tekinalp, Ozan (2021-01-11) Regarding the use of Solar Sail Satellites at low altitudes for the proposed concept, a study is carried out to determine the critical mode switching altitude of the mission orbit and a review is presented for the non-ideal solar force model. Based on the results of the study, further analysis is performed regarding the maneuver planning strategy. The proposed concept needs solar sailing maneuvers for reshaping, resizing and/or reorienting the orbit for both station-keeping and transferring to another ...
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...
Probing stellar winds and accretion physics in high mass X ray binaries and ultra luminous X ray sources with LOFT Maoura, Orlandini; et. al. (2015-01-01) This is a White Paper in support of the mission concept of the Large Observatory for X-ray Timing (LOFT), proposed as a medium-sized ESA mission. We discuss the potential of LOFT for the study of high-mass X-ray binaries and ultra-luminous X-ray sources. For a summary, we refer to the paper.
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...
Nonlinear controller designs for a reaction wheel actuated observatory satellite Doruk, Reşat Özgür; Kocaoğlan, Erol; Department of Electrical and Electronics Engineering (2008) In this research, nonlinear attitude controllers are designed for a low earth orbit satellite intended to be used in observatory missions. The attitude is represented by the Modified Rodriguez Parameters (MRP) which is a minimal representation providing a fully invertible kinematics. As a difference from the classical satellite models existent in the literature, the model of this work incorporates the dynamics of the reaction wheel (actuator) including a brushless dc motor which is armature controlled. The ...

Citation Formats

H. Polat and O. Tekinalp, “Maneuver planning strategy for rapid response solar sail satellite concept,” presented at the AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2021, Virtual, Online, 2021, Accessed: 00, 2021. [Online]. Available: https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=85100372705&origin=inward.