组合循环发动机飞机/发动机性能一体化分析

Aircraft/engine performance integrated analysis on combined cycle engine

采用飞机/发动机一体化分析方法,开展了两种典型组合循环发动机方案(方案一为涡轮/亚燃冲压/双模态超燃冲压组合发动机,方案二为涡轮/引射冲压/双模态超燃冲压组合发动机)总体性能对比研究。基于给定的马赫数为6.5巡航的高超声速飞行器的飞行任务需求,进行了约束分析与任务分析,优选出满足约束条件下的飞行器起飞推质比和机翼载荷,得到了相应的飞行器起飞总质量和海平面起飞推力,并进行了两种方案的对比研究。结果表明:在完成相同的飞行任务下,方案一的起飞总质量与方案二相当,前者比后者减小了2.6%;方案一的起飞推力比方案二高出10.3%;基于涡轮发动机水平,方案一和方案二分别需要采用两台海平面起飞推力为129kN和119kN量级的涡轮发动机。此外,飞行器起飞总质量随巡航距离增加而显著增加,巡航距离为4 000km时,两种方案的起飞总质量将达到85t左右。

Two cases of combined cycle engines（case 1：turbine engine/ramjet/dual mode scramjet,case 2：turbine engine/ejector ramjet/dual mode scramjet）were comparatively studied by using aircraft/engine performance integrated analysis method.Constraint analysis and mission analysis were conducted based on a given mission of the hypersonic vehicle capable of Mach number of 6.5cruise.The optimal thrust loading and wing loading satisfying the constraint were obtained,and the corresponding takeoff gross mass and sea-level takeoff thrust were further obtained.Results indicated that under the condition of completing the mission of hypersonic vehicle,case 1had a comparable takeoff mass with case 2.The takeoff mass of case 1was 2.6%lower than case 2,and the takeoff thrust of case 1was10.3% higher than case 2.Considering the state-of-the-art of turbine engines,two 129 kNthrust turbine engines and two 119kN-thrust turbine engines were used for case1 and case 2,respectively.In addition,the takeoff mass increased shapely with the cruise distance.The takeoff masses will be about 85 tfor both cases when the cruise distance is 4 000 km.