TY - JOUR AU - Aksonov, O.S. AU - Zolotko, O.E. AU - Stolyarchuk, V.V. PY - 2023/02/23 Y2 - 2024/03/29 TI - AN INTEGRATED APPROACH TO SOLVING THE PROBLEM OF RELIABLE COOLING OF THE DETONATION ENGINE CHAMBER JF - Journal of Rocket-Space Technology JA - Rocket-Sp. Tech. VL - 30 IS - 4 SE - Engines and power plants DO - 10.15421/452204 UR - http://rocketspace.dp.ua/index.php/rst/article/view/137 SP - 23-29 AB - One of the most promising areas of development of rocket and space engine building is the development of detonation engines. However, to create such engines need to solve a number of complex technical problems. One of them is the problem of cooling the chamber, which receives high heat loads. For reliable operation of the detonation engine chamber, it is necessary to ensure the allowable temperature of the chamber wall and to prevent spontaneous combustion of the prepared fuel mixture capable of detonation. Since the detonation engine operates in non-stationary mode with a sharp change in the parameters of the chamber, one of the main tasks to create a reliable cooling system is to determine the level of heat load on the structure. One of the tools for solving this problem is the method of numerical experiment using mathematical simulation technologies. A computational experiment was performed to determine the value of the specific heat flux to the wall of the detonation engine chamber. The results of the experiment agree well with the known data of other authors. The peak value of the specific heat flux at the detonation wave front is determined. The obtained results indicate that the chamber of the detonation engine is subjected to a much higher thermal load than the chamber of the liquid rocket engine. The analysis of the possibility of using traditional ways and methods of cooling for the detonation engine chamber showed their lack of efficiency. Therefore, it is necessary to develop new promising methods and ways to cool the chamber of the pulse detonation engine. The difficult task of finding an effective system of external cooling of the rocket detonation engine chamber requires a integrated approach. ER -