一种基于固体火箭发动机的悬浮火箭弹道建模与仿真研究  

Research on Trajectory Modeling and Simulation of Suspended Rocket Based on Solid Rocket Motor

作　　者：高乔 杨军 李晓晖 张兵峰 GAO Qiao;YANG Jun;LI Xiaohui;ZHANG Bingfeng(Xi'an Aerospace Propulsion Technology,Xi'an 710025,China)

机构地区：[1]西安航天动力技术研究所,西安710025

出　　处：《弹箭与制导学报》2022年第2期100-104,共5页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：针对舰船在海面受到反舰导弹攻击的问题,采用悬浮火箭将导弹导引至舰船外安全区域的方法进行规避。对于悬浮火箭的工作过程,提出一种控制方案,首先是利用仿真软件搭建悬浮火箭的六自由度仿真模型,为使悬浮火箭在爬升段、平飞段进行可控飞行,对姿态采用阻尼回路、姿态回路双回路反馈控制,对高度采用“高度+速度”的双回路反馈控制,同时对速度采用“速度+加速度”的双回路反馈控制。仿真结果表明,这种控制方案是可行的,悬浮火箭在悬浮阶段能够保持稳定的姿态,并能够控制高度与速度进行稳定飞行,弹道特性基本满足要求。Aiming at the problem that the ship is attacked by anti-ship missiles on the sea,the suspension rocket is used to guide the missile to the safe area outside the ship.For the working process of suspension rocket,a control scheme is proposed.The first is to use the simulation software to build the six degree of freedom simulation model of the suspension rocket.In order to make the suspension rocket conduct controllable flight in the climbing phase and level flight phase,the dual loop feedback control of damping loop and attitude loop is adopted for the attitude,the dual loop feedback control of“height+speed”is adopted for the altitude,and the dual loop feedback control of“speed+acceleration”is adopted for the speed.The simulation results show that this control scheme is feasible.The suspension rocket can maintain a stable attitude in the suspension stage,and can control the altitude and speed for stable flight.The ballistic characteristics basically meet the requirements.

关 键 词：悬浮火箭 姿态控制 高度控制 定高飞行 弹道模型 弹道特性 

分 类 号：V448.1[航空宇航科学与技术—飞行器设计]