PECULIARITIES OF COOLING COMBUSTION CHAMBER OF ROCKET ENGINE, WHICH UTILIZE HIGH-TEST PEROXIDE AS AN OXIDIZER

Abstract

Interest in storable ecologically friendly propellant has increased recently. One of the reasons for that is convenience in storage, handle and delivery. The most interesting storable propellant for launch vehicles is high-test peroxide with kerosene. A few companies are engaged in development of small launch vehicle on this propellant. Moreover, European Space Agency announced a tender for the development of the engine which runs on the high-test peroxide. Taking these circumstances into account, researches focused on these engines become more relevant. One of the best features of this propellant is a high density and high propellant mixture ratio. Taking into account that for the full burning of kerosene eight times more hydrogen peroxide is needed, traditional cooling with fuel becomes difficult. That is why the other ways to arrange cooling be found. One of the most evident ways of solving this task is to use oxidizer as a coolant. High-test peroxide has a few advantages such as high specific heat capacity, high density and thermal conductivity, but using it as a coolant is connected with difficulties. Material for combustion chamber should be chosen properly because it should be compatible with peroxide and temperature of inner wall must not be higher than temperature of high-test peroxide decomposition. Though, there were engines which were cooled with high-test peroxide (Gamma 2, AR-2), but there are no definite recommendations about designing such a combustion chambers. This article threats peculiarities of cooling combustion chamber of rocket engine, which runs on high-test peroxide and kerosene. Method of cooling combustion chamber with hydrogen peroxide is considered in the article. Design calculations of engine with thrust level 250 kg have been made. Designed engine have been manufactured and fired for a few times. Experimental data have been compared with calculations and recommendations on how to arrange cooling of combustion chamber with hydrogen peroxide have been given. Also, conclusions about the advantages of rocket engines which run on high-test peroxide and kerosene have been made in comparison with ones which utilize liquid oxygen as an oxidizer.

Keywords

• ракетний двигун
• охолодження перекисом водню
• вогневі випробування