基于Monte-Carlo法的微型航天器在轨发射姿态预测方法研究  

Attitude prediction method for micro satellite on-orbit launch based on Monte-Carlo method

作　　者：陶晓宇 杨海波 谈曾巧 张翔[1] 唐超 Tao Xiaoyu;Yang Haibo;Tan Zengqiao;Zhang Xiang;Tang Chao(School of Mechanical Engineering,Nanjing University of Science and Technology,Nanjing 210094,China;Beijing Institute of Aerospace Systems Engineering,Beijing 100094,China)

机构地区：[1]南京理工大学机械工程学院,江苏南京210094 [2]北京宇航系统工程研究所,北京100094

出　　处：《南京理工大学学报》2024年第6期686-691,共6页Journal of Nanjing University of Science and Technology

摘　　要：基于固体推力器在轨发射的微型航天器在空间在轨服务领域应用越来越广泛,微型航天器分离时的姿态是决定任务成功的关键。为了预测微型航天器在轨发射分离时的姿态范围,采用多刚体动力学理论和赫兹接触模型,建立了微型航天器-搭载卫星平台系统发射动力学仿真模型。针对固体推力器的生产、装配过程中产生的推力偏心,提出基于Monte-Carlo仿真的微型航天器在轨分离姿态预测方法。仿真结果表明,微型航天器分离角速度服从正态分布规律,经地面模拟发射试验验证,该发射动力学仿真模型和姿态预测方法准确可行,可为微型航天器在轨快速发射系统设计和发射着靶精度的研究提供参考。Micro satellites based on solid thrusters launched on-orbit are becoming increasingly widely used in the field of space on-orbit services,and the attitude of the micro satellite during separation is the key to determining the success of the mission.In order to predict the attitude range of a micro satellite during on-orbit launch separation,a multi rigid body dynamics theory and a Hertz contact model are used to establish a launch dynamics simulation model for the micro satellite-satellite platform system.A Monte-Carlo based method for predicting the separation attitude of the micro satellite on-orbit is proposed to address the thrust eccentricity generated during the production and assembly process of solid thrusters.The simulation results show that the separation angular velocity of the micro satellite followed a normal distribution law.Through ground simulation launch experiments,the launch dynamics simulation model and attitude prediction method are accurate and feasible,which could provide reference for the design of micro satellite on-orbit rapid launch systems and the study of launch target accuracy.

关 键 词：微型航天器 在轨发射动力学 姿态预测 蒙特卡洛法 

分 类 号：V412.42[航空宇航科学与技术—航空宇航推进理论与工程]