研究了小样本理论中的偏最小二乘法在航空发动机研制费估算中的适用性,系统收集了国内10余种军用涡喷/涡扇发动机的技术性能和研制费数据,选取涡轮进口温度、军用耗油率、发动机军用推力、发动机加力推力、发动机推重比、发动机净重、总增压比、空气流量、翻修寿命、原型机数量、完成时间等技术参数,将小样本理论中的偏最小二乘法应用于军用航空发动机研制费估算模型的研究,形成了基于主要性能指标的军用航空发动机研制费参数估算模型,并建立了军用航空发动机研制继承系数的概念.计算结果表明,该模型较国内其他已有模型的精度有所提高,达到了10%,可以应用于我国航空发动机研制费的快速估算. The applicability of partial least squares in the estimation of aeroengine research and development costs is studied. The system collects the technical performance and development cost data of more than 10 kinds of military turbojet / turbofan engines in China, selects the turbine inlet temperature, military Fuel consumption, engine thrust, engine thrust, engine thrust-weight ratio, engine net weight, total pressure ratio, air flow, overhaul life, prototype number, completion time and other technical parameters, The second part is the research on the estimating model of military aeroengine research cost and the parameter estimation model of military aeroengine research and development based on the main performance index is established.The concept of inheritance coefficient of military aeroengine is established.The calculation results show that the model is more efficient than the domestic The precision of other existing models has been improved to 10%, which can be applied to the rapid estimation of the cost of aero-engine development in China.