10吨级电循环液氧甲烷火箭发动机研发报告

摘要 为推动电循环技术与新一代清洁推进剂的工程化融合应用,依托国内航天材料、制造、试验全链条成熟工艺体系,开展10吨级电循环液氧甲烷火箭发动机自主研发。本研究以工艺自主适配、性能精准优化、技术自主创新为核心原则,采用纯电驱动泵循环+液氧甲烷全量燃烧架构,通过动力循环、核心部件、热管理三大模块定向优化,实现海平面推力10±0.3吨、海平面比冲≥330s、推重比≥130:1的核心性能指标;所有设计均锚定国内现有工业能力,100%适配20-50吨级中小型试车台,无需新增设备与产线。研究完成了从方案设计、部件制造到40s连续点火试验的全流程研发,形成具备自主知识产权的核心技术方案,填补国内电循环液氧甲烷小推力发动机的技术空白,为航天动力基础研究、小型运载火箭动力验证提供高性价比试验载体,同时为电循环技术与液氧甲烷推进剂的融合应用提供全新工程化思路。本研究核心性能指标达国内同级别发动机顶尖水平,且研发周期可控、落地效率高,具备良好的产业化与参数迭代扩展能力。 Abstract To promote the engineering integration application of electric cycle technology and a new generation of clean propellants, the independent research and development of a 10-ton electric cycle liquid oxygen methane rocket engine was carried out based on the domestic mature industrial system of aerospace materials, manufacturing and testing. Adhering to the core principles of independent process adaptation, precise performance optimization and independent technological innovation, this research adopted the pure electric drive pump cycle + liquid oxygen methane full combustion architecture. Through directional optimization of three core modules including power cycle, key components and thermal management, the core performance indicators of sea-level thrust 10±0.3 tons, sea-level specific impulse ≥330s and thrust-to-weight ratio ≥130:1 were achieved. All designs were anchored to the existing domestic industrial capabilities, 100% compatible with 20-50 ton medium and small test beds without adding new equipment and production lines. The whole research process from scheme design, component manufacturing to 40s continuous ignition test was completed, and a core technical scheme with independent intellectual property rights was formed, which filled the technical gap of domestic small-thrust electric cycle liquid oxygen methane rocket engine. It provides a cost-effective test carrier for aerospace power basic research and small launch vehicle power verification, and also a new engineering idea for the integration application of electric cycle technology and liquid oxygen methane propellant. The core performance indicators of this research reach the top level of domestic engines of the same level, with controllable R & D cycle, high landing efficiency, and good industrialization and parameter iteration expansion capabilities.