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Persistent URL http://purl.org/net/epubs/work/54359020
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Record Id 54359020
Title Ariel Payload Structural Architecture: Design, Analysis and Verification Challenges
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Abstract Ariel (the Atmospheric Remote-sensing Infrared Exoplanet Large-survey), the M4 mission for the ESA cosmic vision program, will conduct a large, unbiased spectroscopic survey. It will explore the nature of exoplanet atmospheres and interiors and, through this, the key factors affecting the formation and evolution of planetary systems.[1] Ariel is planned to be launched on board an Ariane 6.2 in 2029 and the payload is developed by a consortium of more than 50 institutes from 16 ESA countries. The Ariel payload has recently approached the Preliminary Design Review milestone. The baseline architecture splits the payload into two major sections; the cold Payload Module (PLM) and the items of the payload that mount within the Spacecraft Service Module (SVM). The integrated payload consists of an all-aluminium off-axis Cassegrain telescope (primary mirror 1100 mm x 730 mm ellipse) with a re-focussing mechanism accommodated behind the M2 mirror that allows correction for any misalignment generated during the telescope assembly or launch and cool down. The current design foresees that all the cryogenic components of the payload architecture, including reflective optical elements, are manufactured from a common material, aluminium 6061 T651 or T652 (or 6082 T651) alloy. This ensures that the design has a matched CTE, allowing warm alignment of the payload to proceed, with a high degree of confidence that this will be maintained when cooled to operating temperatures. This builds on the significant design heritage within Europe of building all aluminium space instruments for cryogenic operation. The Bipods connect the Telescope Assembly to the Spacecraft Module, at the Payload Interface Plate. The (six) struts consist of carbon fibre tubes (which are stiff and have low thermal conductivity) with titanium alloy flexures at both ends (whose stiffness has been tuned to meet both the launch and thermal contraction requirements). To achieve the required operational temperatures, the Telescope Assembly must also be shielded from the thermal radiation emitted and reflected from the Spacecraft Module. The V-Groove assembly performs this function. Analysis and testing of such a complex payload pose significant technical and programmatic challenges Starting with the definition of responsibilities within the large payload consortium, this paper focuses on the structural analysis and test strategies and methodologies defined at Ariel payload level. Details on the results of the structural analyses, performed on the Finite Element Model of the Ariel Payload Module are provided. The results show overall compliance to the main requirements, including verification of the minimum resonance frequencies and the definition of the notching to be applied during sine vibration testing. Static, dynamic and thermo-elastic load cases have been successfully analysed. Moreover, input levels for the various instruments and subsystems have been generated. Finally, the paper describes the mechanical test approaches and configurations which are to be implemented at the various verification levels and stages.
Organisation STFC , RALSP , RALSP - SETD
Keywords model philosophy , ariel , structural analysis , FEA , vibration testing , payload architecture , exoplanet , thermo-elastic deformation , structural design , FEM
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Language English (EN)
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Paper In Conference Proceedings In 17th European Conference on Spacecraft Structures Materials and Environmental Testing (ECSSMET 2023), Toulouse, France, 28-30 Mar 2023, (2023): 336-347. Ariel Payload Str…SMET2023 - Paper.pdf 2023