喷水预冷却发动机与导弹一体化设计

Integrated Design for Missile and Jet Pre-Cooling Engine

关键词:  导弹  射流预冷却发动机  一体化设计  约束分析  任务分析 

Key words:  Missile  Jet pre-cooling engine  Integrated design  Constraint analysis  Mission analysis

摘要:

以一种高声速导弹作为应用对象,计算了喷水预冷却发动机的安装特性,建立了导弹/喷水预冷却发动机一体化设计的约束分析和任务分析模型,给出了高超声速导弹的升阻特性的确定方法,结合任务剖面、导弹的重量组成以及发动机模型,取爬升率为100m/s,80m/s和50m/s对导弹的爬升和加速任务段进行约束分析,选择巡航马赫数为4.0,5.0和6.0三种情况进行了导弹任务分析。计算结果表明,建立的导弹/发动机一体化约束分析与任务分析模型合理, 当巡航马赫数小于5.0时,虽然装备喷水预冷却发动机与亚燃冲压发动机的导弹相比爬升率和加速度较低,但是导弹射程却有较大幅度的提高,因而在高声速导弹的应用是可行的。 

Abstract:

Taking a hypersonic missile as the application object, the installation characteristics of jet pre-cooling engine (SteamJet) was calculated.The model of the missile-steamJet engine integrated analysis was established.The determining method about the hypersonic missile lift and drag characteristics was set up. As combining with the mission profile,the missile weight and engine model, the constraint analysis for climbing and acceleration mission period were completed. With climbing rate of 100m/s,80m/s and 50m/s,the hypersonic missiles mission analysis was performed for cruising Mach number 4.0,5.0and 6.0states. Calculation results show that the establishment of missile-engine integrated constrain analysis and mission analysis model is reasonable.Although missile dimbing rate and acceleration for equipment SteamJet engine is lower than the ramjet engine, the missile range is greatly improved,thus the application of SteamJet in hypersonic missile is feasible.