Verification by analysis for the ESA 2nd Young Engineers Satellite system

Paper number

IAC-06-C2.P.1.08

Author

Mr. Antonios Vavouliotis, University of Patras, Greece

Coauthor

Mr. Dimitrios Lamprou, University of Patras, Greece

Coauthor

Prof. Vassilis Kostopoulos, University of Patras, Greece

Coauthor

Mr. Erik Van der Heide, Delta-Utec SRC, The Netherlands

Coauthor

Mr. Matteo Appolloni, AOES, The Netherlands

Year

2006

Abstract

This work addresses major part of the structural qualification campaign for the 2nd Young Engineers Satellite (YES2) system. YES2 mission is planned to feature the first European tether deployment where the tether will deorbit accurately a small innovative re-entry capsule. YES2 system is mounted on the Russian spacecraft FOTON-M3 that is scheduled to be launched in September 2007 and consists of 3 main modules: The Foton Located YES2 Deployer (FLOYD) module, the Mechanical and data Acquisition Support (MASS) module and the re-entry capsule (FOTINO) module. 
The objective of the structural verification campaign was to demonstrate that the design met all applicable structural requirements and included proper margins. In this stage of project towards the Critical Design Review the verification campaign envisaged mainly analysis procedures and selected sine and random vibration tests for certain mission-critical subsystems. Due to the low number of modules of YES2 system it was decided to proceed with the creation of one numerical model. MSC.PATRAN/NASTRAN v2005 was used for the FE modelling. All the bolted joints were implemented in the numerical model and special attention was given to the correct simulation of the stiffness that the mechanical interfaces are introducing in the assembly. Finally special attention was given in the modelling of mission-critical parts like motors and PCBs. 
Initially a modal analysis was conducted to verify the frequency requirements and to determine associated modal characteristics. Afterwards a dynamic response analysis was conducted to verify the structural response under random vibration loading for the mission critical parts and to provide vibration levels for the forthcoming dynamic tests. A load analysis was performed to calculate the quasistatic loads resulting from the dynamic behaviour due to the random vibration and linear accelerations launch environment. Those loads were used in a series of static analyses were the displacements and the stresses were extracted and the margins of safety were calculated for all the major parts that consisted primary and secondary structures. Forces on the bolted joints were calculated and used in the fastener analysis where a fail-safe approach was used. Sine and random vibration tests were conducted for the 32 km tether spool core and for the tether deployment control mechanism (barberpole). The results were used for the numerical model validation.     

Abstract document

IAC-06-C2.P.1.08.pdf

Manuscript document

IAC-06-C2.P.1.08.pdf (🔒 authorized access only).

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