火箭弹中制导凸优化方法  

Convex optimization method for rocket midrange guidance

作　　者：刘译蔓 陈琦[1] LIU Yiman;CHEN Qi(School of Energy and Power Engineering,Nanjing University of Science and Technology,Nanjing 210094,China)

机构地区：[1]南京理工大学能源与动力工程学院,南京210094

出　　处：《兵器装备工程学报》2024年第9期175-181,共7页Journal of Ordnance Equipment Engineering

摘　　要：为提高火箭弹制导过程中的可靠性和环境适应性,提出一种基于凸优化的在线求解规划弹道的方法,使其尽可能的达到其原有的毁伤效能。以制导火箭弹滑翔弹道模型为仿真实例,以控制能量最优轨迹规划模型为研究对象,利用伪谱法离散连续变量,线性凸化非线性动态方程,建立标准凸优化模型,基于凸优化方法求解并进行循环仿真计算得到仿真弹道,并与原理想弹道进行了比对。仿真结果表明,该方法能在偏离预设的初始弹道时,快速求解得到可行的优化弹道,证明了该方法在存在偏差时求解弹道规划问题有一定效果。In order to improve the reliability and environmental adaptability of rocket guidance,an online trajectory planning method based on convex optimization is proposed to achieve the original damage efficiency as much as possible.Taking the glide trajectory model of guided rocket as the simulation example and the trajectory planning model of optimal control energy as the research object,the standard convex optimization model is established by using the pseudo-spectrum method to discrete continuous variables and linearize the nonlinear dynamic equations.The simulation trajectory is obtained by solving the convex optimization method and conducting cyclic simulation calculation,and compared with the original ideal trajectory.The simulation results show that the proposed method can quickly obtain feasible optimal trajectory when deviating from the preset initial trajectory,which proves that the proposed method is effective in solving trajectory planning problems when there is deviation.

关 键 词：制导律 弹道优化 凸优化 在线优化 

分 类 号：TJ303.4[兵器科学与技术—火炮、自动武器与弹药工程]