摘要
中国新一代载人飞船试验船的气动减速系统由2具减速伞和3具主伞组成,减速伞在实现第1阶段减速后分离并将主伞包从飞船中拉出。主伞包出舱作为降落伞系统的一个重要工作环节,一直是回收着陆系统的关键技术和设计难点之一,由于这一瞬时高动态过程涉及吊带、伞包和舱盖等多体接触和受力耦合作用,因此采用基于简化动力学模型的理论计算方法难以准确描述该过程。该文提出了一种基于有限元模型的气动-动力学耦合分析方法,建立了主伞包出舱动力学模型,运用气动力载荷动态匹配控制方法实现了降落伞由气动载荷向动力学模型的精确传递,通过对初始速度、防热层拉力和舱盖质量等影响主伞包出舱的因素进行全面分析对比,获得了主伞包出舱过程的载荷、速度和过载等动力学特性,直观且逼真地描述了主伞包出舱的动态过程。该方法有效指导了新一代载人飞船试验船回收系统方案的设计,为后续的正式飞行任务提供了理论支持。
[Objective] China’s new-generation manned spacecraft test ship uses two deceleration parachutes and three main parachutes for pneumatic deceleration recovery. The main parachute bag is separated and pulled out after the deceleration parachute has completed its work. The main parachute bag is then pulled out from the parachute cabin as a key and important link in parachute deceleration in the design of the recovery landing system. The pullout process of the main parachute bag involves multibody coupling, such as slings, parachute bags, and hatch covers. Thus, the process is relatively complicated and theoretical calculations are generally used. Accurately describing the process, which could lead to countless errors in the actual process, is difficult. [Methods] This paper propose a finite element analysis method to establish a dynamic analysis model for the main parachute out of the cabin to solve the aforementioned problem and accurately understand the changes produced in this process. In addition, the actual parachute and rope system calculation model is established to quantify the relative motion and load of each component accurately in the pullout process of the main parachute, and the load distribution of different connecting parts is obtained, providing support for the system design and evaluation. The parachute aerodynamic deceleration model is simplified on the basis of the aerodynamic load dynamic matching control method, which affects the initial speed of the main parachute out of the cabin. Influencing factors, such as the tensile force of the heat shield and the quality of the hatch cover, are comprehensively analyzed and compared. The response characteristics of the load, speed, and overload of the main parachute bag out of the cabin are obtained, and the entire process of the main parachute bag out of the cabin is intuitively described. [Results] The method for the main parachute out of the cabin demonstrated the following results: 1) The main parachute pullout process based on finite element analysis technology could accurately describe the coupling relationship between parachute components and simplify the aerodynamic calculation of parachutes. The dynamic iterative aerodynamic load subroutine could reduce the calculation amount and provide an efficient analysis means for the dynamic analysis of the reentry capsule. 2) With the increase in the initial speed in the pullout process of the main parachute, the time required for the complete pullout of the main parachute was short, the load on each sling increased, and the overload of the entire cabin also showd a rising trend. Therefore, the initial drawing boundary conditions should be strictly controlled. 3) The mass of the main umbrella covered considerably affected the peak force of the total towing load curve of the umbrella and would increase with the mass. Thus, the weight of the main umbrella cover should be strictly controlled in the scheme design to reduce the load of the umbrella towing. [Conclusions] This method effectively guides the design of the recovery system for a new generation of manned spacecraft test ships and provides theoretical support for subsequent formal flight missions.
作者
王永滨
张亚婧
黄雪姣
殷莎
陈点豪
王奇
雷江利
贾贺
陈金宝
WANG Yongbin;ZHANG Yajing;HUANG Xuejiao;YIN Sha;CHEN Dianhao;WANG Qi;LEI Jiangli;JIA Hel;CHEN Jinbao(College of Astronautics,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;Beijing Instituteof Space Mechanics&Electricity,Beijing 100094,China;Laboratory of Aerospace Entry,Descent and Landing Technology,China Aerospace Science and Technology Corporation,Beijing 100094,China;School of Transportation Science and Engineering,Beihang University,Beijing 100191,China)
出处
《清华大学学报（自然科学版）》
EI
CAS
CSCD
北大核心
2023年第3期376-385,共10页
Journal of Tsinghua University(Science and Technology)
基金
国家重大科技专项
国家自然科学基金资助项目(51505028)。
关键词
新飞船
返回舱
主伞包
出舱
过载
冲击
new spacecraft
return cabin
main parachute bag
exit cabin
overload
impact
作者简介
王永滨(1984-),男,研究员;通信作者:陈金宝,教授,E-mail:chenjbao@nuaa.edu.cn。
