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Design, Analysis and Fabrication of a CEFIR Instrument for an ATV-5 Shallow Reentry
2015 (English)Independent thesis Advanced level (degree of Master (Two Years)), 20 credits / 30 HE creditsStudent thesis
Abstract [en]

National Aeronautics and Space Administration (NASA) and European Space Agency (ESA) planned to conduct a shallow re-entry observation campaign for Automated Transfer Vehicle – 5 (ATV-5). Main objective of the mission is to study the re-entry explosion from DC-8 Airborne Laboratory (Aircraft). This thesis was performed at Astos Solutions GmbH and aimed at developing a CEFIR (Coronagraph for Explosion and Fragmentation Identification of Re-entering Debris) instrument for better characterization of the explosion, particularly to provide precise information on fragmentation. The future perspective of the mission is to improve the modelling tools for the future re-entry vehicle. The conventional CEFIR instrument comprises three units: a) Gimbal unit tracks the fragments and explosion events; b) Telescope unit with Coronagraph arrangements observes the explosion events from the gimbal; c) Attachment Module unit would integrate the instrument in DC-8 aircraft window. However, the CEFIR Instrument has its own limitations owing to the weight of the telescope which limits the accuracy of the tracking system. In order to overcome the limitations, I came up with an alternate of using a mirror unit. This would allow us to retain telescope in static position and adjustable mirror would reflect the images which can be captured via telescopic lens. Such a module will enable us to track events with better accuracy. Finally, the attachment module was designed according to the DFRC regulations for the gimbal, mirror unit and telescope unit provided by Astos Solutions. The mechanical analysis namely a) static structural analysis and b) static vibrational analysis of attachment module was done using the ANSYS 14.5. The data obtained from the above analysis revealed that the proposed design would comply all the essential parameters required to withstand the forces from gimbal and telescope unit.Furthermore, I also took an attempt to develop a preliminary user interface which would allow us to test the motion of the gimbal. At last, the designed CEFIR instrument was successfully integrated into the aircraft. We firmly believe that the design would allow the scientific committee to obtain new insights of explosion event.

Place, publisher, year, edition, pages
2015. , 124 p.
Keyword [en]
Technology, CEFIR, Gimbal, Telescope, Instrument Attachment Module, Deformation, Stress, Strain, Natural Frequency, User Interface, Coronagraph.
Keyword [sv]
URN: urn:nbn:se:ltu:diva-50857Local ID: 813f1871-86dc-4039-99e9-17a40c0bec26OAI: diva2:1024220
External cooperation
Subject / course
Student thesis, at least 30 credits
Educational program
Space Engineering, master's level
Validerat; 20150914 (global_studentproject_submitter)Available from: 2016-10-04 Created: 2016-10-04Bibliographically approved

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Sudalayandi, Saravanan

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