一种一箭多星航天发射任务初轨预报方法研究  

Research on Initial Orbit Prediction Method of A Multi-satellite Space Launch Mission Using A Single Rocket

作　　者：何锋 朱明明[1] 高杰 HE Feng;ZHU Mingming;GAO Jie(Jiuquan Satellite Launch Centre,Jiuquan 732750,China)

机构地区：[1]中国酒泉卫星发射中心,酒泉732750

出　　处：《宇航学报》2025年第1期150-156,共7页Journal of Astronautics

摘　　要：发射场测控系统在一箭多星航天发射任务初轨预报时,可用火箭末级入轨段测量数据较短,且缺乏星箭分离后卫星的有效测量数据。面对发射结果快速评定的需求,基于简化的动力学统计定轨模型,设计了一种并行的一箭多星航天发射任务初轨预报方法。通过引入常量脉冲加速度修正星箭分离冲量的摄动,使用鲁棒加权最小二乘方法(rlowess)提高算法对异常值的鲁棒性和收敛速度。实验结果表明,该方法具有秒级的实时性,在最佳初轨预报的测量区间长度下有米级的预报精度,能有效地满足一箭多星航天发射结果快速评定对初轨预报的实时性和精度需求。The telemetry tracking and control system in launch area are always confronted with the situation in which the available rocket measurement data during the final stage orbiting section is short,and effective satellite measurement data after satellite-rocket separation is absent for initial orbit prediction when launching multi satellites by a single rocket.Based on a simplified dynamic statistical orbit determination model,a parallelized initial orbit prediction method is designed for one-rocket,multi-satellite space launching missions.A constant impulse acceleration is introduced to correct the state perturbation caused by the separation momentum,and a robust locally weighted regression(rlowess)method is used to improve the algorithm’s robustness and convergence against outliers.The experimental results show that the method has a real-time performance in second scale,a meter-scale orbit precision under the optimal measurement range,and satisfies the real-time and precision requirements of the fast assessment of launch results for one-rocket,multi-satellite space launching missions.

关 键 词：一箭多星 航天发射 初轨预报 鲁棒加权最小二乘法 发射结果快速评定 

分 类 号：V557.1[航空宇航科学与技术—人机与环境工程]