Расчёт теплового состояния камеры сгорания жидкостного ракетного двигателя малой тяги на топливе АТ-НДМГ, работающего на установившемся импульсном режиме

Abstract

Analysis of the thermal state of small thrust rocket engine is a rather difficult problem for theoretical calculation. It's connected with: - needed to use a large numbers of calculated ratios describing the physical processes occurring in the combustion chamber; - using a large amount of information of thermodynamic database for a variety of engine operating conditions, taking into account the irregular distribution of the components ratio in the sections of combustion chamber of small thrust liquid rocket engine; - complexity of the simulation of thermal and gas dynamic nonstationary processes in impulse mode of the engine. The main difficulty in calculating for impulse operating modes is the lack of reliable experimental data on the processes in the chambers volume, especially for the filling and emptying of the combustion chamber. A theoretical study of the thermal state of LRE with thrust 200N, working on fuel NTO-UDMH. The cases of engine operating at steady state with a non-stationary thermal state and the steady impulse modes.