| Research Article |
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Effect of sail fullness on the aerodynamic performance of ringsail parachutes |
| GAO Chang, LI Yanjun, YU Li, NIE Shunchen |
| Key Laboratory of Aircraft Environment Control and Life Support, Ministry of Industry and Information Technology, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China |
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Abstract [Objective] Previous studies on ringsail parachutes based on computational fluid dynamics (CFD) mainly focused on the slotted structures of the canopy or the overall fabric permeability of ringsail parachutes. Ringsail parachutes with different sail structures, including the upward-exhaust ringsail (UER) and downward-exhaust ringsail (DER), are proposed to allow for different exhaust directions. Sail structures usually account for larger areas and are more complex; therefore, they have a more significant influence on the aerodynamics of parachutes. However, systematic research on the sail structures of ringsail parachutes is lacking. Therefore, the effect of sail structural designs on the deceleration performance of ringsail parachutes is unclear.[Method] In this study, the numerical models of the flow field around a parachute with different exhaust sail directions are established according to the aerodynamic shape of a ringsail parachute under steady descent. The influences of the sail exhaust direction and sail structure fullness on aerodynamic performance are explored via CFD. Wake, jet flow, and canopy surface pressure are explored, the deceleration and stability performances of parachutes with different sail exhaust directions are compared, and the action mechanism is analyzed. Sail fullness is varied as the main parameter, and the relationship between sail configurations and ringsail aerodynamics is analyzed.[Results] The results reveal the following:(1) Jet flow existed at crescent slots. In a UER parachute, jet flow converged in the downstream air column, which reduced the drag and generates an additional restoration moment on the parachute. Therefore, the UER featured smaller drag coefficients but better stabilities than the DER. (2) The UER was significantly affected by geometric permeability; therefore, with increasing sail fullness, the drag coefficient of the UER increased. The jet flow direction was determined by sail fullness. Therefore, under the effect of the reverse thrust of the jet flow, the drag coefficient of the DER decreased with increasing sail fullness. (3) Owing to the effect of the main tail vortex downstream of the canopy and the jet flow at the crescent slots of the sail, the UER and DER featured optimal fullness values for stability. (4) Considering the deceleration and stability performances of ringsail parachutes with different sail fullness values, the aerodynamic performance of ringsail parachutes was optimal at a sail fullness value of K=1.10.[Conclusions] Through the CFD-based numerical calculations of the steady descent states of ringsail parachutes, this study explores the effects of different exhaust directions and sail fullness on the aerodynamic performance of ringsail parachutes. Our research can provide a certain reference for the structural designs and performance analyses of ringsail parachutes.
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| Keywords
ringsail parachute
sail structure
sail fullness
numerical simulation
aerodynamic characteristic
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Issue Date: 04 March 2023
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[1] 王利荣. 降落伞理论与应用[M]. 北京:宇航出版社, 1997. WANG L R. The theory and application of parachutes[M]. Beijing:Astronautic Publishing House, 1997. (in Chinese)
[2] 余莉. 气动减速技术[M]. 北京:科学出版社, 2018. YU L. Aerodynamic deceleration technology[M]. Beijing:Science Press, 2018. (in Chinese)
[3] EWING E G. Ringsail parachute design[R]. Ohio:Air Force Flight Dynamics Laboratory, 1972.
[4] 林斌. 我国航天降落伞技术的发展[J]. 航天返回与遥感, 1999, 20(3):1-5. LIN B. Development of space parachute technology in China[J]. Spacecraft Recovery & Remote Sensing, 1999, 20(3):1-5. (in Chinese)
[5] 李健, 唐明章. "神舟八号"飞船主伞的改进设计与试验[J]. 航天返回与遥感, 2011, 32(6):26-32. LI J, TANG M Z. Improvement and tests of the Shenzhou-8 spacecraft main parachute[J]. Spacecraft Recovery & Remote Sensing, 2011, 32(6):26-32. (in Chinese)
[6] 荣伟, 王学, 贾贺, 等. "神舟号"飞船回收着陆系统可靠性分析中的几个问题[J]. 航天返回与遥感, 2011, 32(6):19-25. RONG W, WANG X, JIA H, et al. Some problems for reliability analysis of recovery and landing system of the Shenzhou spacecraft[J]. Spacecraft Recovery & Remote Sensing, 2011, 32(6):19-25. (in Chinese)
[7] 荣伟, 高树义, 李健, 等. 神舟飞船降落伞系统减速策略及其可靠性验证[J]. 中国科学:技术科学, 2014, 44(3):251-260. RONG W, GAO S Y, LI J, et al. The deceleration strategy and reliability validation of the parachute system on the Shenzhou spacecraft[J]. Scientia Sinica Technologica, 2014, 44(3):251-260. (in Chinese)
[8] 贾贺, 荣伟, 江长虹, 等. 探月三期月地高速再入返回器降落伞减速系统设计与实现[J]. 中国科学:技术科学, 2015, 45(2):185-192. JIA H, RONG W, JIANG C H, et al. The design and implementation of the parachute deceleration system on the circumlunar return and reentry spacecraft of 3rd phase of China lunar exploration program[J]. Scientia Sinica Technologica, 2015, 45(2):185-192. (in Chinese)
[9] TAKIZAWA K, MOORMAN C, WRIGHT S, et al. Fluid-structure interaction modeling and performance analysis of the Orion spacecraft parachutes[J]. International Journal for Numerical Methods in Fluids, 2011, 65(1-3):271-285.
[10] TEZDUYAR T E, SATHE S, SCHWAAB M, et al. Fluid-structure interaction modeling of ringsail parachutes[J]. Computational Mechanics, 2008, 43(1):133-142.
[11] TAKIZAWA K, SPIELMAN T, MOORMAN C, et al. Fluid-structure interaction modeling of spacecraft parachutes for simulation-based design[J]. Journal of Applied Mechanics, 2012, 79(1):1-9.
[12] 甘和麟, 荣伟. 环帆伞可变参数对设计偏差的灵敏度分析[J]. 航天返回与遥感, 2014, 35(2):14-24. GAN H L, RONG W. Alternative-parameter sensitivity ofringsail parachute design deviation[J]. Spacecraft Recovery &Remote Sensing, 2004, 35(2):14-24. (in Chinese)
[13] 高树义, 余莉. 环帆伞收口比对开伞性能的影响[J]. 中国空间科学技术, 2014, 34(1):63-70. GAO S Y, YU L. Influence of reefing ratio on inflation performance of ringsail parachute[J]. Chinese Space Science and Technology, 2014, 34(1):63-70. (in Chinese)
[14] COCKRELL D, HUNTLEY I, AYRES R. Aerodynamic and inertial forces on model parachute canopies[C]//Proceedings of the 5th Aerodynamic Deceleration Systems Conference. Albuquerque, USA:AIAA, 1975:1371.
[15] LAFARGE R A, NELSEN J M, GWINN K W. A novelCFD/structural analysis of a cross parachute[C]//Proceedings of the 32nd Aerospace Sciences Meeting and Exhibit. Reno, USA:AIAA, 1994:752.
[16] GNOFFO P A. Computational aerothermodynamics in aeroassist applications[J]. Journal of Spacecraft and Rockets, 2003, 40(3):305-312.
[17] BENNEY R J, STEIN K R, TEZDUYAR T E, et al. Fluid-structure interaction modeling of the US army personnel parachute system[C]//Proceedings of Modeling and Simulation Technologies Conference. Denver, USA:AIAA, 2000:4531.
[18] GREATHOUSE J S, SCHWING A M. Study of geometric porosity on static stability and drag using computational fluid dynamics for rigid parachute shapes[C]//Proceedings of the 23rd AIAA Aerodynamic Decelerator Systems Technology Conference. Daytona Beach, USA:AIAA, 2015:2131.
[19] 贾贺, 姜璐璐, 薛晓鹏, 等. 超声速透气降落伞系统的气动干扰数值模拟研究[J]. 航天返回与遥感, 2019, 40(6):26-34. JIA H, JIANG L L, XUE X P, et al. Numerical simulation of aerodynamic interaction of supersonic porosity parachutes[J]. Spacecraft Recovery & Remote Sensing, 2019, 40(6):26-34. (in Chinese)
[20] 杨雪, 余莉, 李允伟, 等. 环帆伞稳降阶段织物透气性影响数值模拟[J]. 空气动力学学报, 2015, 33(5):714-719. YANG X, YU L, LI Y W, et al. Numerical simulation of the effect of the permeability on the ringsail parachute in terminal descent stage[J]. Acta Aerodynamica Sinica, 2015, 33(5):714-719. (in Chinese) |
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2023,
Vol. 63
