Abstract
Heat Transfer Modeling of Bipropellant Thrusters for using in Multidisciplinary Design Optimization Algorithm
Highlights
Liquid thrusters are widely used in space applications especially for orbital maneuvers and launch vehicles
Because of high combustion temperatures and high heat flux rates from the hot gases to the chamber wall, thruster cooling is a major design consideration
In this paper, engineering model for heat transfer will be introduced which can be applied in multidisciplinary design optimization (MDO) algorithms
Summary
Liquid thrusters are widely used in space applications especially for orbital maneuvers and launch vehicles. Because of high combustion temperatures (up to 3700K) and high heat flux rates (peak may go beyond 160 MW/m2) from the hot gases to the chamber wall, thruster cooling is a major design consideration. The first one is steady state method, which the heat transfer rate through combustion wall and temperature on the wall are constant, in other words, there is a thermal equilibrium. Regenerative, transpiration, radiative, ablative and film cooling are generally used to control heat fluxes of combustion chamber and to provide suitable structure temperatures [3], [4].
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