Rocket motor nozzles have to withstand their extreme working loads including thermal loads. In this paper, thermal stress analyses on two different MX-450 motor rocket nozzle designs were performed to study their responses to the ignition thermal loads. The first nozzle design is of which had been used in the 2021 static-firing test while the second one is a newly modified nozzle design with an increased graphite thickness in the front part. The conducted simulations included the fluid-structure interaction method with thermal quantities as the transferred data between the solid region and the fluid region. The results show that the latest iteration of the nozzle has a difference in comparison to the first design in terms of the lowest minimum principal stress by 8.7 MPa.
Thermal stress analysis on solid rocket nozzles with fluid-structure interaction simulations
THE 9TH INTERNATIONAL SEMINAR ON AEROSPACE SCIENCE AND TECHNOLOGY – ISAST 2022 ; 2022 ; Bogor, Indonesia
AIP Conference Proceedings ; 2941 , 1
11.12.2023
7 pages
Aufsatz (Konferenz)
Elektronische Ressource
Englisch
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