拉姆导弹总体构型设计分析

Analysis on Preliminary Layout Design of RAM Missile

分析旋转导弹在锥形运动条件下的控制策略,使之既可用于调整弹体姿态,又可用于控制锥形运动幅度,得出拉姆导弹在构型上采用中立稳定及减小横向转动惯量的设计;利用矩形舵面与三角形舵面产生的涡旋所造成的不同气动光学效应对激光引信虚警的影响,分析拉姆导弹采用三角形舵面的合理性;借助于变质量陀螺方程,分析在主动段发动机尾喷口直径的大小对导弹自旋速度变化的影响,得出发动机尾喷口直径应与燃烧室内径相等的结论。

Based on the studying of control strategy on spinning missiles in coning motion,the method which was applied to both the adjusting of the attitude and the controlling of the amplitude of coning motion was gotten,and the principle of aerodynamic neutral stability and the design with decreasing the lateral rolling inertia were found in RAM missile configuration.Compared the effects of aero-optical vortex from rectangular rudder with that from delta rudder,it was known that aero-optical effectiveness on vortex from rectangular rudder results in the laser fuse false-alarm,and the reasonability for RAM missile to adopt the delta rudder was analyzed.With the variable-mass gyroscopic equation,the influence of the engine nozzle diameter on fluctuations of spinning velocity in the powered-flight phase was obtained,and the result that the engine nozzle diameter should be equal to the inside diameter of the chamber was concluded.