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Development of the MiniSIL™ structural design

Development of the MiniSIL™ structural design
Development of the MiniSIL™ structural design
There is a wide range of launch opportunities currently available for small- and medium-sized satellites, although the launcher constraints and costs are quite variable. In order to reduce the cost of small satellites it is desirable to define a spacecraft bus which is compatible with as wide a range of vehicles as possible. One of the most promising methods of providing this compatibility for mini-satellites in the range 100--500 kg is by using a stack configuration where the mini-satellite is positioned between a launcher primary payload (LPP) and the launch vehicle. This paper describes the design process for the structure of MiniSILTM, a small satellite bus which is being designed and produced by Space Innovations Limited
mini-satellites, structural, design, structure, launch, loads, spacecraft, testing
2041-3025
255-263
Aglietti, G.S.
e44d0dd4-0f71-4399-93d2-b802365cfb9e
Wicks, A.
3f398ec8-b041-4f2b-a1af-cd5cb3caaff4
Barrington-Brown, A.J.
2b2e9c0c-0938-4ebb-a6aa-6161a5af1e75
Aglietti, G.S.
e44d0dd4-0f71-4399-93d2-b802365cfb9e
Wicks, A.
3f398ec8-b041-4f2b-a1af-cd5cb3caaff4
Barrington-Brown, A.J.
2b2e9c0c-0938-4ebb-a6aa-6161a5af1e75

Aglietti, G.S., Wicks, A. and Barrington-Brown, A.J. (1999) Development of the MiniSIL™ structural design. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 213 (4), 255-263.

Record type: Article

Abstract

There is a wide range of launch opportunities currently available for small- and medium-sized satellites, although the launcher constraints and costs are quite variable. In order to reduce the cost of small satellites it is desirable to define a spacecraft bus which is compatible with as wide a range of vehicles as possible. One of the most promising methods of providing this compatibility for mini-satellites in the range 100--500 kg is by using a stack configuration where the mini-satellite is positioned between a launcher primary payload (LPP) and the launch vehicle. This paper describes the design process for the structure of MiniSILTM, a small satellite bus which is being designed and produced by Space Innovations Limited

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More information

Published date: 1999
Keywords: mini-satellites, structural, design, structure, launch, loads, spacecraft, testing

Identifiers

Local EPrints ID: 22202
URI: http://eprints.soton.ac.uk/id/eprint/22202
ISSN: 2041-3025
PURE UUID: c744ae05-cde9-4350-b78c-8f01fe465c03

Catalogue record

Date deposited: 01 Feb 2007
Last modified: 05 Oct 2018 12:04

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Contributors

Author: G.S. Aglietti
Author: A. Wicks
Author: A.J. Barrington-Brown

University divisions

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