Integrated Lattice Precooled Air-Breathing Combined Cycle Aerospace Engine Complete Engineering Parameter Scheme

Abstract
 
This document presents a complete set of engineering parameters for an integrated lattice precooled air-breathing combined cycle aerospace engine independently designed by the author. Aiming at the defects of traditional split wound microtube precooling structures such as numerous welding points, frost blockage and leakage, the scheme adopts an integrally 3D printed gradient alloy lattice heat exchange core to greatly reduce the number of parts and improve structural reliability. The engine supports dual-mode operation: air-breathing mode from sea level to 28 km altitude at Mach 0~5.5 relying on atmospheric oxygen, and closed rocket mode above 28 km with self-carried liquid hydrogen and liquid oxygen propellants. The whole machine achieves smooth mode switching with thrust fluctuation controlled within 3%. Compared with conventional precooled engines, its dry mass is reduced by 32% and the payload is increased by 55% under the same takeoff weight. Matching domestic mature SLM additive manufacturing, material and test systems, the power system can realize horizontal takeoff and landing on standard civil runways, and is applicable to satellite launch, space station transportation, suborbital high-speed delivery and hypersonic vehicle research. All design parameters are fully disclosed without omission, with no patent application planned temporarily, reserving the engineering traceability right of the unified field theory corresponding to the architecture.
 
摘要
 
本文为作者独立设计的一体化点阵预冷吸气式空天组合循环发动机全套完整工程参数方案。针对传统分体缠绕微管预冷结构焊点繁多、易冻堵渗漏等缺陷,本方案采用一体3D打印梯度合金点阵换热芯体,大幅减少零部件数量,提升结构可靠性。发动机支持双模态工作:海平面至28km、0~5.5马赫区间为吸气模态,依靠大气氧气参与燃烧;28km以上切换为闭环火箭模态,依靠机载液氢、液氧推进剂独立做功,整机跨模态切换平滑,推力波动控制在3%以内。对比传统预冷发动机,整机干重降低32%,同等起飞重量下入轨有效载荷提升55%。方案适配国内成熟金属3D打印、材料、试车配套体系,可依托标准民航跑道水平起降,适用于卫星组网发射、空间站往返运输、亚轨道高速投送、高超音速飞行器研发等场景。整套设计参数无删减完整公开,现阶段暂不申报专利,永久保留该动力架构对应的统一场理论工程溯源归属权。