摘要
为了提高发射能力和性能,几乎所有现役运载火箭都包含两个或更多子级.在发射过程中,通过分离和抛弃已经燃尽推进剂的子级而逐渐减轻运载火箭重量,对于保证运载火箭的安全性并确保成功发射起着至关重要的作用.火箭部件在制造、安装过程中难以避免地存在一定偏差,这些偏差可能致使运载火箭未能按照预定的计划执行分离动作,进而直接影响分离体的姿态稳定性,甚至可能导致任务失败.文章介绍了运载火箭级间分离原理和动力学方程,基于Modelica语言建立了考虑参数偏差的运载火箭一、二子级模型,作用力模型,爆炸螺栓模型,分离间隙模型和初始状态模型,并通过搭积木和连线的方式搭建了运载火箭级间分离系统Modelica模型;通过与Adams模型对比仿真结果,验证了模型的正确性;由于火箭制造偏差、载荷偏差满足一定的概率分布规律,如均匀分布、正态分布和威布尔分布,使用蒙特卡洛打靶法对考虑这些偏差的运载火箭级间分离过程的可靠性进行了仿真计算分析,指出该方法能够识别出级间分离的恶劣工况,可为设计人员提供极限状态下的最小分离间隙,从而优化分离系统的设计裕度.
To enhance the launch capacity and performance,nearly all active launch vehicles incorporate two or more stages.During the launch process,gradual reduction of the launch vehicle mass is achieved by separating and discarding the spent propellant stages,which plays a vital role in ensuring the safety of the launch vehicle and successful launches.During the manufacturing and assembly processes of launch vehicle components,inherent deviations are inevitably encountered.These deviations may lead to a scenario where the launch vehicle is unable to execute separation maneuvers as per the intended plan,consequently directly impacting the stability of the separation body’s attitude and potentially resulting in mission failure.The principles of stage separation of launch vehicles and dynamic governing equations are elucidated.Utilizing the Modelica language,models for the first stage and second stage of carrier rockets are developed to account for parameter deviations.Additionally,force models,explosive bolt models,separation gap models,and initial state models are established.These components are then assembled using a block-diagram and interconnection approach to construct a comprehensive Modelica model for the stage separation system of launch vehicles.The correctness of the model is verified through comparison of simulation results with an Adams model.Due to manufacturing and force deviations following certain probability distributions,such as uniform,normal,and Weibull distributions,a Monte Carlo shooting method is employed to conduct reliability simulation and analysis of the launch vehicle stage separation process that considers these deviations.The simulation results indicate that this approach can identify adverse conditions during stage separation,providing design engineers with the minimum separation gap under extreme scenarios,thus optimizing the design margin for the separation system.
作者
张文丰
蔡小双
王庆涛
仝一帆
刘丁瑞
蒲锦瑞
王珺珑
Zhang Wenfeng;Cai Xiaoshuang;Wang Qingtao;Tong Yifan;Liu Dingrui;Pu Jinrui;Wang Junlong(Shanghai Aerospace Systems Engineering Institute,Shanghai 201109,China;School of Physics,Nanjing University of Science and Technology,Nanjing 210094,China;National Key Laboratory of Complex Multibody System Dynamics,Nanjing University of Science and Technology,Nanjing 210094,China;School of Mechanical Engineering,Tianjin University,Tianjin 300072,China;State Key Laboratory of Mechanics and Control for Aerospace Structures,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)
出处
《动力学与控制学报》
2025年第6期50-64,共15页
Journal of Dynamics and Control
基金
国防基础科研计划资助项目(JCKY2023203A002)。
作者简介
通信作者:王庆涛,E-mail:qtwang@njust.edu.cn。
