Mass minimization approach for the optimal preliminary design of CMC inner liners in rocket thrust chambers-Reference-Cited by-同舟云学术

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Mass minimization approach for the optimal preliminary design of CMC inner liners in rocket thrust chambers

Published:2024-08 Issue: Volume:16 Page:100281
ISSN:2666-3597
Container-title:Forces in Mechanics
language:en
Short-container-title:Forces in Mechanics

Author:

Berardi Valentino Paolo,Meola Nicola,Ferraiuolo Michele^ORCID

Publisher

Elsevier BV

Reference27 articles.

1. Thermal performance of MMH/NTO rocket thrust chamber based on pintle injector by using liquid film cooling;Zhang;Appl. Therm. Eng.,2023

2. Review on film cooling of liquid rocket engines;Shine;Propuls. Power Res.,2018

3. Investigations on an all-oxide ceramic composites based on Al2O3 fibres and alumina–zirconia matrix for application in liquid rocket engines;Bach;Aerospace,2022

4. RANS based numerical simulation of a GCH4/GO2 rocket engine combustion chamber with film cooling and improvement of wall heat flux prediction;Liu;Appl. Therm. Eng.,2023

5. Analysis of a transpiration cooled LOX/CH4 rocket thrust chamber;Munk;Int. J. Heat Mass Transf.,2022

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