[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.
[1] 陈怡, 闫大庆. 国外新一代载人飞船研制概况[J]. 中国航天, 2015(10):18-23. CHEN Y, YAN D Q. Overview of new generation of manned spacecraft[J]. Aerospace China, 2015(10):18-23. (in Chinese)
[2] 庞之浩. 美国研制中的几种载人天地往返系统[J]. 国际航空, 2014(7):70-71. PANG Z H. U.S. manned spacecraft developing in progress[J]. International Aviation, 2014(7):70-71. (in Chinese)
[3] 雷江利, 荣伟, 贾贺, 等. 国外新一代载人飞船减速着陆技术研究[J]. 航天器工程, 2017, 26(1):100-109. LEI J L, RONG W, JIA H, et al. Research on descent and landing technology for new generation manned spacecraft[J]. Spacecraft Engineering, 2017, 26(1):100-109. (in Chinese)
[4] ROMERO L M. CPAS parachute testing, model development, & verification[C]//International PlanetaryProbe Workshop 10. San Jose, USA:International Planetary, 2013:20130014013.
[5] VARELA J G, RAY E S. Skipped stage modeling and testing of the CPAS main parachutes[C]//22nd AIAA Aerodynamic Decelerator Systems Technology Conference. Daytona Beach, USA:AAIA, 2013:20130011109.
[6] MCKINNEY J, FERGUSON P, WEBER M L, et al. Initial testing of the CST-100 aerodynamic deceleration system[C]//Proceedings of AIAA Aerodynamic Decelerator Systems (ADS) Conference. Daytona Beach, USA:AIAA, 2013:1263.
[7] MCCANN J R, DEPAUW T C, MCKINNEY J, et a1. Boeing CST-100 landing and recovery system design and development an integrated approach to landing[C]//Proceedings of AIAA Space 2013 Conference and Exposition. San Diego, USA:AIAA, 2013:5306.
[8] MCKINNEY J, FERGUSON P, WEBER M L, et al. Boeing CST-100 landing and recovery system design and development testing[C]//Proceedings of AIAA Aerodynamic Decelerator Systems (ADS) Conference. Daytona Beach, USA:AIAA, 2013:1261.
[9] 陈杰. 美国"龙"飞船国际空间站对接试验简析[J]. 中国航天, 2012(8):24-29. CHEN J. The docking test analysis of dragon and the international space station[J]. Aerospace China, 2012(8):24-29. (in Chinese)
[10] 张蕊. 国外新型可重复使用飞船特点分析和未来发展[J]. 国际太空, 2010(12):31-38. ZHANG R. Foreign new reusable spacecraft characteristics analysis and future development[J]. Space International, 2010(12):31-38. (in Chinese)
[11] 杨雷, 张柏楠, 郭斌, 等. 新一代多用途载人飞船概念研究[J]. 航空学报, 2015, 36(3):703-713. YANG L, ZHANG B N, GUO B, et al. Concept definition of new-generation multi-purpose manned spacecraft[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(3):703-713. (in Chinese)
[12] 包进进, 雷江利, 贾贺. 伞包拉出过程仿真及载荷影响分析[J]. 航天返回与遥感, 2017, 38(3):31-42. BAO J J, LEI J L, JIA H. Simulation of pulling main parachute pack and influencing factors analysis on loads[J]. Spacecraft Recovery & Remote Sensing, 2017, 38(3):31-42. (in Chinese)
[13] 林斌. 降落伞伞包载荷分析计算[J]. 航天返回与遥感, 2005, 26(1):14-17. LIN B. Load analysis for parachut bag[J]. Spacecraft Recovery & Remote Sensing, 2005, 26(1):14-17. (in Chinese)
[14] 鲁媛媛, 荣伟, 吴世通. 火星环境下降落伞拉直过程的动力学建模[J]. 航天返回与遥感, 2014, 35(1):29-36. LU Y Y, RONG W, WU S T. Dynamic modeling of parachute deployment in mars environment[J]. Spacecraft Recovery & Remote Sensing, 2014, 35(1):29-36. (in Chinese)
[15] 宋旭民, 程文科, 彭勇, 等. 飞船回收过程动力学建模与仿真[J]. 弹道学报, 2005, 17(2):55-59. SONG X M, CHENG W K, PENG Y, et al. Dynamic modelization and simulation of spaceship recovery scenario[J]. Journal of Ballistics, 2005, 17(2):55-59. (in Chinese)
[16] 夏刚, 郭鹏, 秦子增. 探月返回器伞舱盖拉伞包动力学模型[J]. 航天返回与遥感, 2013, 34(4):25-33. XIA G, GUO P, QIN Z Z. Dynamic model of parachute pack pulling process by parachute container cover[J]. Spacecraft Recovery & Remote Sensing, 2013, 34(4):25-33. (in Chinese)
[17] 张青斌, 程文科, 彭勇, 等. 降落伞拉直过程的多刚体模型[J]. 中国空间科学技术, 2003, 23(2):45-50. ZHANG Q B, CHENG W K, PENG Y, et al. A multi-rigid-body model of parachute deployment[J]. Chinese Space Science and Technology, 2003, 23(2):45-50. (in Chinese)
[18] 宋旭民, 秦子增, 程文科, 等. 具有倒"Y"型吊挂的降落伞系统动力学建模[J]. 国防科技大学学报, 2005, 27(5):103-106. SONG X M, QIN Z Z, CHENG W K, et al. The dynamic model of a parachute system with the inverted ‘Y’ suspension[J]. Journal of National University of Defense Technology, 2005, 27(5):103-106. (in Chinese)
[19] 黄伟. 降落伞附加质量的计算方法[J]. 航天返回与遥感, 2016, 37(2):42-50. HUANG W. Calculation methods of added mass of parachute[J]. Spacecraft Recovery & Remote Sensing, 2016, 37(2):42-50. (in Chinese)
[20] 熊菁, 秦小波, 程文科. 降落伞系统附加质量的研究[J]. 中国空间科学技术, 2002, 22(4):32-38, 56. XIONG J, QIN X B, CHENG W K. The added mass research in parachute system[J]. Chinese Space Science and Technology, 2002, 22(4):32-38, 56. (in Chinese)
[21] FRAIRE U, DEARMAN J, MORRIS A. Proposed framework for determining added mass of orion drogue parachutes[C]//21st AIAA Aerodynamic Decelerator Systems Technology Conference and Seminar. Dublin, Ireland:AAIA, 2011:20110011303.
