基于迭代制导的运载火箭入轨级弹道设计及仿真  

Design and Simulation of Launch Vehicles in Orbit Stage Based on Iterative Guidance

作　　者：高家智 陈小前[1] Gao Jia-zhi;Chen Xiao-qian(College of Aerospace Science and Engineering,National University of Defense Technology,Changsha,410073;Taiyuan Satellite Launch Center,Taiyuan,030027)

机构地区：[1]国防科技大学空天科学学院,长沙410073 [2]太原卫星发射中心,太原030027

出　　处：《导弹与航天运载技术》2021年第4期36-40,共5页Missiles and Space Vehicles

摘　　要：为了实现运载火箭快速高精度入轨,基于迭代制导设计了入轨级制导方案。纵向通道采用基于飞马火箭的线性正切迭代制导律,采用牛顿迭代法快速求解俯仰姿态角;利用纵平面预测得到的纵向关机点状态和关机时间以及侧向通道关机点状态公式,对轨道倾角进行预测控制。数值仿真表明,提出的方法在稳定性、快速性、制导精度等方面均具有相对优良的品质。In order to achieve rapid and high-precision orbit entry of the launch vehicle,the stage guidance scheme is designed based on iterative guidance law.The longitudinal channel adopts linear tangent iterative guidance law used by the Pegasus rocket,and the Newton iterative method is adopted to solve the pitch angle rapidly.By using the predicted longitudinal shutdown point state and shutdown time and the lateral channel shutdown point state formula,the orbit inclination is predicted and controlled.The numerical simulation shows that the method proposed has relatively good quality in stability,rapidity,guidance accuracy and so on.

关 键 词：运载火箭 迭代制导 最优控制 弹道仿真 

分 类 号：V448.133[航空宇航科学与技术—飞行器设计]