Theoretical and Experimental Heat Transfer in Solid Propellant Rocket Engine

• Published in: Journal of aerospace technology and management Vol. 11; no. 1; p. 3819
• Main Authors: Vicentin, Izabel Cecilia Ferreira de Souza, Marchi, Carlos Henrique, Foltran, Antonio Carlos, Moro, Diego, Silva, Nicholas Dicati Pereira da, Campos, Marcos Carvalho, Araki, Luciano Kiyoshi, Diógenes, Alysson Nunes
• Format: Journal Article
• Language: English
• Published: Departamento de Ciência e Tecnologia Aeroespacial 01.01.2019; Instituto de Aeronáutica e Espaço (IAE)
• Subjects: Combustion chambers; ENGINEERING, AEROSPACE; Heat conduction; Heat flux; Ill-posed problems; Heat conduction; Ill-posed problems; Combustion chambers; Heat flux
• ISSN: 2175-9146; 1984-9648; 2175-9146
• DOI: 10.5028/jatm.v11.1066

Accurate determination of heat flux is an important task not only in the designing aspect, but also in the performance analysis of rocket engines. In this purpose, this work deals with the heat flux determination in a combustion chamber through the inverse method. In this approach, the transient heat flux is determined from the experimental temperature data measured at the outer sidewall of the rocket engine. In this work the physical phenomenon was modeled by the transient one-dimensional heat equation in cylindrical coordinates and the material properties of the chamber were considered constant. Furthermore, the model is solved using the inverse heat conduction problem with least squares modified by the addition of Tikhonov regularization term of zero-order. Moreover, the sensitivity coefficients were obtained by Duhamel’s theorem. Through the regularization parameter, it was able to generate acceptable results even when using data with considerable experimental errors.