Micro-Satellite Structure Fracture Investigation techniques

Gasser Abdelal, Abou Bakr Elhady, Ahmed Hamdy

Research output: Contribution to conferencePaper

1 Citation (Scopus)

Abstract

Mounting accuracy of satellite payload and
ADCS (attitude determination and control subsystem) seats
is one of the requirements to achieve the satellite mission
with satisfactory performance. Deviation of the position of
the mounting seat for Multi-Band-Earth-Imager (MBEI) is
caused by cracks in the plate of the basis unit and bracket
for attachment of MBEI. These cracks were detected during
inspection of the satellite strength mock-up after vibration
testing for air transportation phase. Most probable reason of
the cracking is fatigue damage as strength mock-up
structure was subjected to prolonged vibration loading
during various loading cases. Total vibration duration
during testing is about 56 hours. In order to study the
cracking reasons, finite element modeling of the structural
parts of the basis unit including MBEI bracket and
instrument MBEI is subjected to harmonic response to
simulate vibration loading for the case of air transportation.
Numerical results are compared with the experimental ones,
and mechanical design of the basis-plate unit is modified
Original languageEnglish
Pages1-9
Number of pages9
DOIs
Publication statusPublished - Mar 2009
EventAerospace conference, 2009 IEEE - Big Sky, MT, United States
Duration: 01 Mar 200901 Mar 2009

Conference

ConferenceAerospace conference, 2009 IEEE
CountryUnited States
CityBig Sky, MT
Period01/03/200901/03/2009

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  • Cite this

    Abdelal, G., Elhady, A. B., & Hamdy, A. (2009). Micro-Satellite Structure Fracture Investigation techniques. 1-9. Paper presented at Aerospace conference, 2009 IEEE, Big Sky, MT, United States. https://doi.org/10.1109/AERO.2009.4839626