PSI - Issue 14

Available online at www.sciencedirect.com Structural Integrity Procedia 00 (2018) 000–000 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2018) 000–000 ScienceDirect

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ScienceDirect

Procedia Structural Integrity 14 (2019) 820–829

2nd International Conference on Structural Integrity and Exhibition 2018 Numerical and experimental comparative study of Aluminum and hybrid mounting interfaces of launch vehicle avionics for weight reduction G Vamsi Krishna a , Tarak Nath De b* , Rajesh Kumar Burman c , B Veera Sekhar d , V Govind Rao e a,b,c,d Advanced Systems Laboratory, Kanchanbagh, Hyderabad – 500058, India e Research Center Imarat, Vigyanakancha, Hyderabad – 500069, India Abstract Weight is a paramount parameter for launch vehicle applications. Avionics are used for command, control and guidance of launch vehicle. Interface brackets are used for mounting of these avionic packages to the launch vehicle chassis. Dynamic loads and vibration responses dominate the design criteria for these interface brackets. The weight sensitivity on range is more prominent for the upper stages of the launch vehicle. To improve the performance of launch vehicle, employment of light weight hybrid (Aluminum honeycomb panel made up of honeycomb core with face sheets at top and bottom) bracket instead of comparatively heavy conventional all metallic aluminum alloy bracket, for a particular case of mounting two of the launch vehicle avionic packages is explored in this study. Comparable vibration responses are obtained along all three axes for the two bracket configurations (aluminium alloy vs hybrid) with packages mounted for the standard random vibration inputs. Sufficient static margin of safety is achieved for high deceleration re-entry flight loads as well. It is concluded that tremendous weight saving on mounting interfaces can be gained without compromising on factor of safety and amplification of vibration responses. 2nd International Conference on Structural Integrity and Exhibition 2018 Numerical a d experimental comparative study of Aluminum and hybrid mounting interfaces of launch vehicle avionics for weight reduction G Vamsi Krishna a , Tarak Nath De b* , Rajesh Kumar Burman c , B Veera Sekhar d , V Govind Rao e a,b,c,d Advanced Systems Laboratory, Kanchanbagh, Hyderabad – 500058, India e Research Center Imarat, Vigyanakancha, Hyderabad – 500069, India Abstract Weight is a param unt para eter for launch vehicle applications. Avionics are used for command, con rol and guidance of launch vehicle. Interface brackets ar used for mounting of thes avionic packag s to the launc v hicle chassis. Dynamic loads and vibration responses d inate the design criteria for these int rface brackets. The weight sensi ivity on range is more prominent for t upper stages f the aunch vehicle. To improve the p rformance of launch vehicle, employment of light weight hybrid (Aluminum honeycomb panel made p of honeycomb core with face sheets a top and bottom) br cket ins ead of comparatively heavy conventional a l metallic aluminum alloy bracket, for a particular case of ounting two of the launch veh le vio ic packages is explored in this study. Compa able vibration responses are obtained a ong all thre axes for the two bracket configurations (aluminium alloy vs hybrid) with ackages mounted f r th standard random vibration inputs. Sufficient static margin of safety is achieved for high deceleration re-entry flight loads as well. It is concluded that tremendous weight saving on mounting interfaces can be gained without compromising on factor of safety and amplification of vibration responses. © 2019 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (https://creativecommons.org/licenses/by-nc-nd/4.0/) Selection and peer-review under responsibility of Peer-review under responsibility of the SICE 2018 organizers. © 2018 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (https://creativecommons.org/licenses/by-nc-nd/4.0/) Selection and peer-review under responsibility of Peer-review under responsibility of the SICE 2018 organizers. © 2018 The Autho s. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (https://creativecommons.org/licenses/by-nc-nd/4.0/) S lection and peer-review under responsibility of Peer-review unde responsibility of the SICE 2018 organizers. Keywords: Honeycomb; random vibration; avionics mounting interface; vibration response; light weight

Keywords: Honeycomb; random vibration; avionics mounting interface; vibration response; light weight

*Corresponding author. Tel.: +91-9848466271 E-mail address: taraknathde@gmail.com *Corresponding author. Tel.: +91-9848466271 E-mail address: taraknathde@gmail.com

2452-3216 © 2018 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (https://creativecommons.org/licenses/by-nc-nd/4.0/) Selection and peer-review under responsibility of Peer-review under responsibility of the SICE 2018 organizers. 2452-3216 © 2018 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (https://creativecommons.org/licenses/by-nc-nd/4.0/) Selection and peer-review under responsibility of Peer-review under responsibility of the SICE 2018 organizers.

2452-3216  2019 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (https://creativecommons.org/licenses/by-nc-nd/4.0/) Selection and peer-review under responsibility of Peer-review under responsibility of the SICE 2018 organizers. 10.1016/j.prostr.2019.07.060