某飞行器指挥仪姿态解算与装订模型设计与验证  

Altitude Sovling and Output Model for Fire Control Director of Vehicle

作　　者：丁军辉 DING Jun-hui(Unit 91851 of PLA,Huludao 125000,China)

机构地区：[1]解放军91851部队

出　　处：《指挥控制与仿真》2018年第2期136-140,共5页Command Control & Simulation

摘　　要：针对某飞行器发射前初始姿态测量装订需求,构建一种动基座条件下的姿态解算与装订模型。以船艇平台罗经、发射架安装方式、目标指向为模型输入,推导飞行器实时姿态角模型;以固定地理坐标点为目标,构建飞行器几何射击模型,推算前置航向角;根据飞行器发射姿态和平飞姿态,结合机械陀螺安装方式,推算陀螺测量角输出模型,给出与控制结构匹配的指挥仪模型输出。经不同发射工况下理论弹道仿真验证,本模型输出极性、幅度正确有效。This paper construct a model of altitude solving and output for measuring initial altitude of vehicle in battery in moving base.The realtime altitude model of vehicle is described with some constrainst include the ship platform compass,the assembly of launching set and the target azimuth.The geometric firing model aimed at fixed geographic coordinates point is presented and the lead-angle is calculated.The mechanical gyroacope measuring model is discussed based on the firing altitude,constant-height flight altitude of vehicle and the assembly in vehicle body of mechanical gyroacope,the output of fire control director mode is presented adapted to control structure of vehicle.Finally,the digit Trajectory computation in several conditions showed that the output ploarity and amplitude of this model is correct and validity.

关 键 词：指挥仪 动基座 模型 设计 验证 

分 类 号：TJ392[兵器科学与技术—火炮、自动武器与弹药工程] E91[军事]