Simulation of the effect of attack angle on ejection and deployment of a parachute
WANG Guangxing1,2, FANG Guanhui1,2, LI Jian1,2, LIU Tao1,2, HE Qingsong1,2, JIA He1,2
1. Beijing Institute of Space Mechanics & Electricity, Beijing 100094, China; 2. Laboratory of Aerospace Entry, Descent and Landing Technology, China Aerospace Science and Technology Corporation, Beijing 100094, China
Abstract：[Objective] Ejection and deployment are the first key actions in the working process of a parachute, thereby resulting in its inflation. Ejection and deployment typically work in the wake of space crafts; therefore, the wake greatly influences the process. The conditions of the free stream may affect the wake flow, such as the attitude, Mach number, and angle of attack. Consequently, the angle of attack of an aircraft is an important consideration in parachute design.[Methods] Ejection and deployment are related to multiple factors, including fluid dynamics, multibody separation, and flexibility deformation. Owing to the advantages of fluid field information and low cost, computation fluid dynamics has become a powerful tool for solving engineering problems regarding fluids. This article focuses on the effect of attack angle on the ejection and deployment of a parachute. Based on the overset grid technology, the three-dimensional unsteady Reynolds averaged Navier-Stokes (URANS) coupled with a six-degrees-of-freedom (6DoF) equation of motion is applied to the research. The simulation consists of two steps:the static flow field simulation and the dynamic separation process based on the static flow field.[Results] The simulation results showed the following:(1) The negative aero force at 0° angle of attack in the recirculation zone hindered the separator department. (2) The wake during the 0° angle of attack was parallel to the axis of capsule; however, 10° and 20° angles of attack demonstrated an obvious deviation from the axis. (3) The separator showed almost no attitude variation for 0° angle of attack, whereas an obvious attitude variation for 10° and 20° angles of attack resulted from the direction of the wake. (4) An obvious interaction occurred between the wake behind the capsule and shock before the separator.[Conclusions] The following conclusions can be drawn from the research:The effects of the angle of attack significantly change the characteristics of the wake. Compared with the 0° condition, the capsule wakes present an asymmetric character in the other two conditions. What's more, the wake shows an obvious deviation from the direction of the initial separated velocity; the asymmetrical wake will affect the trajectory and attitude of the separator; and the effect of the angle of attack will change the relative position between the capsule and the separator and influence the separated time:the time of ejection and deployment will be reduced with an increase in the angle of attack. The method and the conclusions can provide a valuable reference for the validation and design of the recovery system.
王广兴, 房冠辉, 李健, 刘涛, 何青松, 贾贺. 攻角效应对降落伞拉直过程影响的仿真模拟[J]. 清华大学学报（自然科学版）, 2023, 63(3): 311-321.
WANG Guangxing, FANG Guanhui, LI Jian, LIU Tao, HE Qingsong, JIA He. Simulation of the effect of attack angle on ejection and deployment of a parachute. Journal of Tsinghua University(Science and Technology), 2023, 63(3): 311-321.
[1] 荣伟. 航天器进入下降与着陆技术[M]. 北京:北京理工大学出版社, 2018. RONG W. Spacecraft entry, descent and landing technology[M]. Beijing:Beijing Institute of Technology Press, 2018. (in Chinese) [2] 高兴龙. 物伞流固耦合及多体系统动力学研究[D]. 长沙:国防科学技术大学, 2016. GAO X L. Research on multibody dynamics and fluid-structure interaction of parachute-body system[D]. Changsha:National University of Defense Technology, 2016. (in Chinese) [3] MCVEY D F, WOLF D F. Analysis of deployment and inflation of large ribbon parachutes[J]. Journal of Aircraft, 1974, 11(2):96-103. [4] PURVIS J W. Prediction of line sail during lines-first deployment[J]. Journal of Aircraft, 1983, 20(11):940-945. [5] 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) [6] 宋旭民, 范丽, 秦子增. 大型降落伞开伞过程中的抽鞭现象[J]. 航天返回与遥感, 2009, 30(3):16-21. SONG X M, FAN L, QIN Z Z. "Vent Whip" during large parachute deployment[J]. Spacecraft Recovery & Remote Sensing, 2009, 30(3):16-21. (in Chinese) [7] 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) [8] 黄伟. 降落伞最小弹射分离速度的计算方法[J]. 航天返回与遥感, 2018, 39(2):26-33. HUANG W. The Calculation method of minimum ejectionvelocity of the first stage parachute[J]. Spacecraft Recovery &Remote Sensing, 2018, 39(2):26-33. (in Chinese) [9] 王海涛, 程文科. 考虑尾流影响的降落伞弹射拉直过程研究[J]. 航天返回与遥感, 2017, 38(5):3-9. WANG H T, CHENG W K. Research on ejecting and deploying process of parachute considering wake flow effects[J]. Spacecraft Recovery & Remote Sensing, 2017, 38(5):3-9. (in Chinese) [10] 鲁媛媛, 荣伟, 吴世通. 火星探测器降落伞拉直过程中的"绳帆"现象研究[J]. 宇航学报, 2014, 35(11):1238-1244. LU Y Y, RONG W, WU S T. Study on line sail during Mars probe parachute deployment[J]. Journal of Astronautics, 2014, 35(11):1238-1244. (in Chinese) [11] WAY D W, POWELL R W, CHEN A, et al. Mars science laboratory:Entry, descent, and landing system performance[C]//2007 IEEE Aerospace Conference. Big Sky, USA:IEEE, 2007:1-19. [12] 徐琳, 宋万强. 基于动态网格的多体分离计算技术研究[J]. 航空科学技术, 2019, 30(2):7-13. XU L, SONG W Q. Research on numerical simulation technology of multi-body separation based on dynamic grid[J]. Aeronautical Science & Technology, 2019, 30(2):7-13. (in Chinese) [13] 王广兴. 迎风面转捩与背风面大分离共存流动一体化研究[D]. 北京:清华大学, 2019. WANG G X. Studies of complex flows with both transition on the windward side and massive separation on the leeward side[D]. Beijing:Tsinghua University, 2019. (in Chinese) [14] MENTER F R. Two-equation eddy-viscosity turbulence models for engineering applications[J]. AIAA Journal, 1994, 32(8):1598-1605. [15] 钱杏芳, 林瑞雄, 赵亚男. 导弹飞行力学[M]. 北京:北京理工大学出版社, 2020. QIAN X F, LIN R X, ZHAO Y N. Missile flight aerodynamics[M]. Beijing:Beijing Institute of Technology Press, 2020. (in Chinese) [16] HEIM E R. CFD Wing/Pylon/Finned store mutual interference wind tunnel experiment[R]. Tennessee:Arnold Engineering Development Center, 1991. [17] PANAGIOTOPOULOS E E, KYPARISSIS S D. CFD transonic store separation trajectory predictions with comparison to wind tunnel investigations[J]. International Journal of Engineering, 2010, 3(6):538-553. [18] 邹东阳. 基于非结构动网格的激波装配/捕捉统一求解方法[D]. 大连:大连理工大学, 2018. ZOU D Y. Combinations of shock-fitting and shock-capturing methods based on unstructured dynamic grids[D]. Dalian:Dalian University of Technology, 2018. (in Chinese)
2023, Vol. 63 
