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Satelitte multifunctional power structure: feasibility and mass savings

Satelitte multifunctional power structure: feasibility and mass savings
Satelitte multifunctional power structure: feasibility and mass savings
A multi-functional structure saves mass from a spacecraft by incorporating other functional subsystems into the structure. By using the structural properties of a non-structural element, inert structure may be eliminated, and the requirement to allot internal volume to the subsystem in question is removed.

The current paper describes a multi-functional structure based on the secondary power system. By using commercially available plastic lithium-ion cells to form the core of a sandwich panel, inert mass is eliminated from both the structure and from the battery enclosure. The feasibility of the proposed multi-functional structure is demonstrated though vibration testing on a single cell, and the successful manufacture of a test panel.

The work goes on to quantify the potential mass savings that may be achieved by using a multi-functional structure of this type. By varying a set of spacecraft attributes, the study identifies that small spacecraft with high power requirements have the potential to gain the most benefit from using a multi-functional structure of this type.
multi-functional structures, spacecraft structures, spacecraft power systems
2041-3025
41-51
Roberts, S.C.
7bd2b67d-960b-4040-81ed-8ac07ba9f113
Aglietti, G.S.
e44d0dd4-0f71-4399-93d2-b802365cfb9e
Roberts, S.C.
7bd2b67d-960b-4040-81ed-8ac07ba9f113
Aglietti, G.S.
e44d0dd4-0f71-4399-93d2-b802365cfb9e

Roberts, S.C. and Aglietti, G.S. (2008) Satelitte multifunctional power structure: feasibility and mass savings. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 222 (1), 41-51. (doi:10.1243/09544100JAERO255).

Record type: Article

Abstract

A multi-functional structure saves mass from a spacecraft by incorporating other functional subsystems into the structure. By using the structural properties of a non-structural element, inert structure may be eliminated, and the requirement to allot internal volume to the subsystem in question is removed.

The current paper describes a multi-functional structure based on the secondary power system. By using commercially available plastic lithium-ion cells to form the core of a sandwich panel, inert mass is eliminated from both the structure and from the battery enclosure. The feasibility of the proposed multi-functional structure is demonstrated though vibration testing on a single cell, and the successful manufacture of a test panel.

The work goes on to quantify the potential mass savings that may be achieved by using a multi-functional structure of this type. By varying a set of spacecraft attributes, the study identifies that small spacecraft with high power requirements have the potential to gain the most benefit from using a multi-functional structure of this type.

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More information

Published date: February 2008
Keywords: multi-functional structures, spacecraft structures, spacecraft power systems

Identifiers

Local EPrints ID: 150441
URI: http://eprints.soton.ac.uk/id/eprint/150441
ISSN: 2041-3025
PURE UUID: e25dfca2-7e0d-4089-a1ee-6760c7347eeb

Catalogue record

Date deposited: 05 May 2010 10:58
Last modified: 14 Mar 2024 01:17

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Contributors

Author: S.C. Roberts
Author: G.S. Aglietti

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