Evaluation indexes of the conceptual design scheme for combat aircraft are analyzed , the weight coefficients of every evaluation index are determined with the analytic hierarchy process , and a conceptual design scheme evaluation method for combat aircraft based on the grey relation projection method is proposed 摘要给出了作战飞机总体设计方案的评价指标，采用层次分析法赋给每个指标不同的权重，并提出了一种基于灰色关联投影法的作战飞机总体设计方案评价方法。
The mathematical methods of theoretical analysis to determine some unknown or omitted parameters in combat efficiency theory of military aircraft based on the present models of combat efficiency of airforce equipment and the actual data of military operation are introduced in order to develop or improve the theory with practical work and some new concepts , such as combat efficiency and actual efficiency among airforce mission . for example , the combat efficiency usually comes from academic research and could be also called appraisal efficiency or static efficiency . after modified with actual data of military operation of past records which also could be seen like actual combat efficiency , confrontation efficiency and dynamic efficiency . through calculation and analysis it must be noted that the numerical value of actual combat efficiency is larger or much larger than the value of combat efficiency 通过应用现有的作战飞机空战效能的数学分析模型，在已有的历史空战实例资料数据的基础上，进一步确定或者探讨有关战效分析的数学模型中的待定因子或者假想忽略不计的参数，进而对作战飞机空战时的效能评估的研究模型作一些验证和完善性质的分析，从而提出有关战斗机空战时作战效能评估的新思路或新概念.比如，通常所理解的作战效能，也称为评估效能或静态效能，经过加权以后，形成实战效能或对抗效能，也可称为动态效能.经过计算分析，认为对抗效能的数量级别，要比评估效能的数量级别大，甚至很大
To meet the needs for wider surge margin of the turbofan engine , a new model was developed to predict the characteristics of the fan / high pressure compressor and turbine in this thesis . several ways , including , variable inlet guide vanes of the fan , variable guide vanes of the high pressure compressor , the variable inlet area ratio of the mixer and the nozzle areas , were presented to enlarge the surge margin of the turbofan engine . meanwhile , a method of combined variable geometries for optimizing controls of inlet guide vanes of the fan , guide vanes and the first two stators of high pressure compressor , area ratio of mixer and noz zle areas was established 为了满足下一代作战飞机对推进系统的性能和稳定性要求，本文建立了压缩系统特性和涡轮特性的新模型，并分别采用改变涡扇发动机风扇进口导流叶片、压气机导流叶片和前两级静叶片、混合室进口处内、外涵面积比和尾喷管面积，研究了其对发动机性能和稳定性的影响，进而得出了涡扇发动机变几何扩稳的方法，为发动机变几何扩稳研究打下理论基础。
In the first part , human - machine interface design of ucav ( unmanned combat air vehicle ) is studied . the design criterion of display , controller and working environment for human in ucav system is presented . in the second part , based on the analysis of human error cause , human generic error model is presented 论文的第一部分研究无人作战飞机系统的人机界面设计，论文给出了无人作战飞机系统的功能框图，根据无人机的任务剖面，综合功效学的研究成果，给出了无人机系统的显示装置、控制装置、工作环境和操作人员的组织情况等的设计准则。
