远程飞航导弹燃油质量快速求解方法  

Quickly Calculating Method for Fuel Mass of Long-range Cruise Missile

作　　者：齐少军[1] 廖崇尧[1] 刘忠仕[1] 陈昌伟[1] 

机构地区：[1]第二炮兵装备研究院,北京100085

出　　处：《导弹与航天运载技术》2008年第1期53-55,共3页Missiles and Space Vehicles

摘　　要：基于涡扇/涡喷发动机性能特征参数和导弹运动方程,研制了远程飞航导弹燃油质量计算模型。该模型能够实现对燃油质量的快速计算;利用该模型研究了飞行马赫数、海拔高度对燃油质量的影响,初步分析了导弹射程和质量的关系。Based on the performance characteristics of turbofan/turbojet engine and dynamic equations of cruise missile, the calculating model of missile fuel mass are developed, by which can quickly calculate the fuel mass. This model is used to research the affects of flight mach and height on fuel mass, the relation between missile mass and range is primarily analysed.

关 键 词：远程飞航导弹 燃油质量 快速计算模型 

分 类 号：TJ761.6[兵器科学与技术—武器系统与运用工程]