A systematic approach to the structural design verification for space payloads, lessons learned from Solar Orbiter EPT-HET instrument

Ravanbakhsh, Ali and García Pérez, Andrés and Sorribes Palmer, Félix and Seimetz, Lars and Alonso, Gustavo and Kulkarni, Shirinivasrao R. and Richards, Michael L. and Martín, César and Wimmer-Schweingruber, F. (2018). A systematic approach to the structural design verification for space payloads, lessons learned from Solar Orbiter EPT-HET instrument. In: "69th International Astronautical Congress", 1-5 oct, Bremen, Alemania. ISBN 9781510881655. pp. 1-6.

Description

Title: A systematic approach to the structural design verification for space payloads, lessons learned from Solar Orbiter EPT-HET instrument
Author/s:
  • Ravanbakhsh, Ali
  • García Pérez, Andrés
  • Sorribes Palmer, Félix
  • Seimetz, Lars
  • Alonso, Gustavo
  • Kulkarni, Shirinivasrao R.
  • Richards, Michael L.
  • Martín, César
  • Wimmer-Schweingruber, F.
Item Type: Presentation at Congress or Conference (Article)
Event Title: 69th International Astronautical Congress
Event Dates: 1-5 oct
Event Location: Bremen, Alemania
Title of Book: 69th International Astronautical Congress (IAC 2018): Involving Everyone
Date: 2018
ISBN: 9781510881655
Subjects:
Freetext Keywords: Structural design; verification methods; FEM analysis; vibration test
Faculty: Instituto de Microgravedad Ignacio Da Riva (UPM)
Department: Aeronaves y Vehículos Espaciales
Creative Commons Licenses: Recognition - No derivative works - Non commercial

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Abstract

The main functions of the space instrument structural subsystem are to enclose, protect and support the other instrument subsystems integrity and to provide a mechanical interface with the spacecraft. Depending on the mission requirements and the mechanical load envelope defined by the spacecraft, the structure should sustain the severe stresses and loads experienced during the launch. The main challenge for a successful structural design is to consider an appropriate verification method during the design phase, which discards or minimizes the potential hardware failures during the qualification tests. This is not always trivial because the design inputs and requirements at the preliminary design phase (phase B) may change when reaching to the stage that the instrument is built and needs to be qualified by test (phase D). In this paper, based on the lessons learned in the scope of the Electron Proton Telescope and High Energy Telescope (EPT-HET) instrument development for ESA?s Solar Orbiter mission, a systematic approach for a successful structural design is presented. The proposed approach not only includes the structural stress and strength analysis but also involves the fatigue life and shock damage verification for sensitive parts such as electronic components.

More information

Item ID: 55160
DC Identifier: http://oa.upm.es/55160/
OAI Identifier: oai:oa.upm.es:55160
Official URL: https://www.iafastro.org/events/iac/iac-2018/
Deposited by: Memoria Investigacion
Deposited on: 19 Feb 2021 07:57
Last Modified: 19 Feb 2021 07:57
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