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Lighter packaging for electronics for space applications

Lighter packaging for electronics for space applications
Lighter packaging for electronics for space applications
In this paper, the conventional design of an enclosure for electronic equipment for space application is reviewed and an alternative type of construction is proposed. The alternative design is based on the use of carbon fibre reinforced plastic (CFRP) sandwich panels for the construction of the enclosure, and the substitution of the printed circuit board (PCB) antivibration frames (AVFs) with antivibration rods (AVRs). To put this work into context, the requirements applicable to the structural design of this type of unit are briefly reviewed. Standard structural analyses have been performed on the conventional enclosure and then repeated for the proposed configuration, in order to demonstrate its compliance with the fundamental mechanical requirements. The issues concerning the radiation protection offered by the enclosure are discussed, and some solutions to this potential problem are briefly presented. The work demonstrates the possibility of achieving a saving of about 20 per cent on the overall mass of the unit. Finally, the cost of the proposed enclosure is assessed and compared with the conventional design for various missions.
spacecraft structures, electronic equipment vibrations, spacecraft technologies, launch environment
Aglietti, G.S.
e44d0dd4-0f71-4399-93d2-b802365cfb9e
Aglietti, G.S.
e44d0dd4-0f71-4399-93d2-b802365cfb9e

Aglietti, G.S. (2002) Lighter packaging for electronics for space applications. European Conference on Spacecraft Structures, Materials and Mechanical Testing. 11 - 13 Dec 2002. (doi:10.1243/095441002760553676).

Record type: Conference or Workshop Item (Paper)

Abstract

In this paper, the conventional design of an enclosure for electronic equipment for space application is reviewed and an alternative type of construction is proposed. The alternative design is based on the use of carbon fibre reinforced plastic (CFRP) sandwich panels for the construction of the enclosure, and the substitution of the printed circuit board (PCB) antivibration frames (AVFs) with antivibration rods (AVRs). To put this work into context, the requirements applicable to the structural design of this type of unit are briefly reviewed. Standard structural analyses have been performed on the conventional enclosure and then repeated for the proposed configuration, in order to demonstrate its compliance with the fundamental mechanical requirements. The issues concerning the radiation protection offered by the enclosure are discussed, and some solutions to this potential problem are briefly presented. The work demonstrates the possibility of achieving a saving of about 20 per cent on the overall mass of the unit. Finally, the cost of the proposed enclosure is assessed and compared with the conventional design for various missions.

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More information

Published date: 2002
Venue - Dates: European Conference on Spacecraft Structures, Materials and Mechanical Testing, 2002-12-11 - 2002-12-13
Keywords: spacecraft structures, electronic equipment vibrations, spacecraft technologies, launch environment

Identifiers

Local EPrints ID: 22304
URI: http://eprints.soton.ac.uk/id/eprint/22304
PURE UUID: 7d40d887-3746-4e7f-832f-eed710dfa1cd

Catalogue record

Date deposited: 05 Jun 2006
Last modified: 05 Oct 2018 12:04

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