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Trajectory Design of a Spacecraft Formation for Space-Based Solar Power Using Sequential Convex Programming

Goel, Ashish and Chung, Soon-Jo and Pellegrino, Sergio (2017) Trajectory Design of a Spacecraft Formation for Space-Based Solar Power Using Sequential Convex Programming. In: Proceedings 9th International Workshop on Satellite Constellations and Formation Flying. , Art. No. 17-43. http://resolver.caltech.edu/CaltechAUTHORS:20170630-094657577

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Abstract

The concept of collecting solar power in space and transmitting it to the Earth using microwaves has been studied by numerous researchers in the past. The Space Solar Power Initiative (SSPI) at Caltech is a collaborative project to bring about the scientific and technological innovations necessary for enabling a space-based solar power system. The proposed system comprises an array of ultra-light, membrane-like deployable modules with high efficiency photovoltaic (PV) concentrators and microwave transmission antennas embedded in the structure. Each module is 60m x 60m in size and in the final configuration, hundreds of these modules span a 3km x 3km array in a geosynchronous orbit. As this formation goes around the Earth, the orientation and position of each module has to be changed so as to optimize the angle made by the photovoltaic surface with respect to the sun and by the antenna surface with respect to the receiving station on Earth. In order to achieve high antenna array efficiency, the modules have to remain in a tight formation with an edge-to-edge distance on the order of a few meters. In addition, the modules also have to avoid collisions and maintain a planar configuration to avoid the possibility of both PV and RF shadowing. In this paper, we present the trajectory design that achieves the dual goal of minimizing the propellant usage and maximizing the power delivered to the ground station, while meeting the various orbital constraints. The optimal control problem is solved using sequential convex programming for a 4 x 4 formation and the results obtained show that it is possible to maintain the formation for 11 years in a geo-synchronous orbit with relatively small amounts of propellant. This serves as a critical achievement in the path towards realizing the objective of space-based solar power.


Item Type:Book Section
Related URLs:
URLURL TypeDescription
http://ccar.colorado.edu/iwscff2017/OrganizationConference Website
ORCID:
AuthorORCID
Chung, Soon-Jo0000-0002-6657-3907
Pellegrino, Sergio0000-0001-9373-3278
Additional Information:The authors thank Northrop Grumman Corporation for supporting this project. We also thank all other members of the SSPI team at Caltech for their valuable inputs.
Funders:
Funding AgencyGrant Number
Northrop Grumman CorporationUNSPECIFIED
Other Numbering System:
Other Numbering System NameOther Numbering System ID
IWSCFF17-43
Record Number:CaltechAUTHORS:20170630-094657577
Persistent URL:http://resolver.caltech.edu/CaltechAUTHORS:20170630-094657577
Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:78719
Collection:CaltechAUTHORS
Deposited By: Tony Diaz
Deposited On:30 Jun 2017 16:59
Last Modified:30 Jun 2017 16:59

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