Eventos Anais de eventos
COBEM 2021
26th International Congress of Mechanical Engineering
DEVELOPMENT OF ROCKET MOTOR TRANSIENT THERMAL ANALYSIS SOFTWARE
Submission Author:
Andres Gilberto Machado da Silva Benoit , RS , Brazil
Co-Authors:
Andres Gilberto Machado da Silva Benoit, João Vítor Bernardi Rohr, João Felipe De Araujo Martos
Presenter: Andres Gilberto Machado da Silva Benoit
doi://10.26678/ABCM.COBEM2021.COB2021-0109
Abstract
Thermal analysis in the rocketry field has a wide impact on overall success of the mission. Nowadays, university rocket teams do not have means to early examine the motor thermal conditions and its behavior. Thus, studying and developing a thermal simulator which is not time expensive and with positive user experience can be broadly used from rocketry teams around the world helping them to build safer and more reliable projects. In order to fulfill that, it was created a graphical user interface (GUI) in which is presented the inputs and outputs for two analysis scenarios, first one considers one dimension discretization and occurs on the combustion chamber wall, the second has a bi-dimensional approach and it is applied directly on the motor bulkhead. The inputs needed to run the software are the chamber dimensions, initial temperature in the chamber, flame temperature of the propellant, burn time, time and radial number of sections. The model considers a combustion chamber that maintains a constant flame temperature during all burn time, a thermal insulation material that is in direct contact with the hot gases in the chamber and bounded to the metal casing. For the calculation of the convection heat it is used the Newton's Law of Cooling where the convective heat coefficient is calculated by the equation for flow inside long cylinders. On chamber-insulator interface it is applied the energy balance equation and inside both insulator and metal casing the transient Fourier Law. Notwithstanding, the solution method used was finite difference solved by explicit and implicit methods. After burn time is achieved the heat from the combustion chamber is not considered, the chamber-insulator interface is assumed to be isolated, and only convection to the exterior air is taken in consideration for the remaining total time. Therefore, the explicit method exhibited a stable solution with similar behavior to that of the implicit solution, as expected from theory research. Also, a comparison with other thermal analysis software was conducted and results revealed that the software built in this work has better accordance with real results.
Keywords
rocket motor, transient thermal analysis, Thermal Analysis
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