火箭助飞鱼雷基准弹道设计探讨

Design of Base Trajectory for Rocket Assisted Torpedo

为了提高以固体火箭发动机为主发动机的火箭助飞鱼雷空中导引弹道的安全性和落点精度,提出了一种求解不同工况下滑翔弹道设计域的交集,将滑翔弹道与交集边缘的相对距离作为定量分析弹道安全性的参量,确定最安全滑翔弹道的方法,给出了在滑翔段采用动态基准弹道和可变雷箭分离点的制导方案,滑翔段不分射程统一装定一簇滑翔弹道曲线,制导系统在飞行中按程序插值计算导引弹道,视情况向最安全滑翔弹道方向修正;在导引弹道末端,雷箭分离点的高度随航速相关调整,该方法可显著减小雷箭分离点的落点散布。研究结果表明,在交集中求解基准弹道可提高安全性,动态基准弹道可增强对弹道偏差和目标修正的适应能力,有助于克服强风场干扰。

To improve both security and fall point precision of air guidance trajectory of a rocket assisted torpedo with a main engine of solid rocket, an approach to ensure the safest glide trajectory is proposed by solving the intersection set of design field of glide trajectory under different conditions and taking the relative distance between the glide trajectory and intersection set edge as a parameter. A guidance scheme adopting dynamic base trajectory during glide and variable separation point of torpedo and rocket is presented. The guidance system calculates guidance trajectory through programmed interpolation during the torpedo rocketing into the air, and corrects the trajectory towards the safest glide trajectory. The scatter scope of separation points of torpedo and rocket can be narrowed obviously when the height of separation point is adjusted with speed at the end of the trajectory. The re- suhs show that the security can be improved as the base trajectory is solved in the intersection set. Dynamic base trajectory may enhance the tolerance of trajectory error and target correction, which helps to overcome the interference of strong wind field.