摘要
介绍了10kN双向摇摆发动机的主要技术方案和关键技术,对涂层和边区余氧系数等影响因素进行了传热计算及分析,获得了再生冷却身部的气壁温、液壁温和热流密度的轴向分布曲线,指出了发动机身部可靠冷却的边界工况。针对两种推进剂(N2O4/MMH、N2O4/UDMH),设计了喷注压降和流量不同的两种喷注器方案,地面热试车表明,两种喷注器方案燃烧稳定,其燃烧效率相当,可达95%～96%。发动机多次地面试验研究验证了发动机设计方案的可行性。
Main concept and key technologies for a 10kN gimbaled rocket engine were introduced in this paper. Heat transfer calculation and analysis were performed for main influencing factors such as coating and peripheral excess oxidizer coefficient. Axial distribution curves of gas-side wall temperature, liquid-side wall temperature and heat flux were obtained. Boundary condition for engine combustion chamber cooling was established. Two types of injectors with different pressure drops and flow rates for two kinds of propellants combination （N2OJMMH; NiO4/UDMH） were designed. Ground hot tests indicated that the two injectors operated well with high combustion effi- ciency of 95%-96%, which proved the reasonability and feasibility of the engine design concept.
出处
《火箭推进》
CAS
2009年第5期8-12,共5页
Journal of Rocket Propulsion
关键词
液体火箭发动机
再生冷却
摇摆
热试车
liquid rocket engine
regenerative cooling
gimbaled chamber
firing test
