Design Analysis and Stiffness Test of a Large Telescopic Deployable Mechanism Joint

doi:10.3901/JME.2018.07.001

Abstract

Abstract: Stiffness of the locked telescopic deployable mechanism is mainly determined by the joint stiffness of adjacent telescopic tubes. A telescopic joint structure which combines carbon fiber composite and metal materials is designed to ensure the total stiffness of the telescopic deployable mechanism. Considering the influence of joint clearance, telescopic joint stiffness is divided into clearance non-elimination case and clearance elimination case. Theoretical modeling analysis and simulation of the joint bending stiffness is carried out. Experimental device for bending stiffness test is developed and test moments can be loaded quantitatively. According to corresponding test method and procedures, stiffness tests on three telescopic joint specimens with different clearance are performed. This research reveals the change law of joint stiffness in clearance non-elimination case and clearance elimination case, namely joint stiffness decreases with the increase of clearance in the clearance non-elimination case, and is approximately equal to the stiffness of carbon tube with equivalent length in the clearance elimination case. Test results conform the theoretical analysis and simulation and have important significance for the improvement of total stiffness performance of the telescopic deployable mechanism.

Key words: deployable mechanism, stiffness testing, structure, telescopic

CLC Number:

TH136

XIAO Hang, YANG Qiaolong, REN Shouzhi, LI Long, XU Kun, DING Xilun. Design Analysis and Stiffness Test of a Large Telescopic Deployable Mechanism Joint[J]. Journal of Mechanical Engineering, 2018, 54(7): 1-10.

References

[1] 邓宗全. 空间折展机构设计[M]. 哈尔滨:哈尔滨工业大学出版社, 2013. DENG Zongquan. Design of space deployable and foldable mechanisms[M]. Harbin:Harbin Institute of Technology Press, 2013.
[2] 杨毅, 丁希仑. 基于空间多面体向心机构的伸展臂设计研究[J]. 机械工程学报, 2011, 47(5):26-34. YANG Yi, DING Xilun. Design and analysis of mast based on spatial polyhedral linkages mechanism along radial axes[J]. Journal of Mechanical Engineering, 2011, 47(5):26-34.
[3] PUIG L, BARTON A, RANDO N. A review on large deployable structures for astrophysics missions[J]. Acta Astronautica, 2010, 67(1-2):12-26.
[4] 刘荣强,田大可,邓宗全. 空间可展开天线结构的研究现状与展望[J]. 机械设计, 2010, 27(9):1-10. LIU Rongqiang, TIAN Dake, DENG Zongquan. Research actuality and prospect of structure for space depioyable antenna[J]. Journal of Machine Design, 2010, 27(9):1-10.
[5] THOMSON M W. Deployable and retractable telescoping tubular structure development[C]//Proceedings of the Aerospace Design Conference, February 16-19, 1993, Irvine, CA, USA. AIAA, 1993:323-338.
[6] ULLRICH R, MCCAULEY J, TURIN P, et al. The STEREO IMPACT boom[J]. Space Science Reviews, 2008, 136(1):185-201.
[7] SCHMID M, AGUIRRE M. Extendable retractable telescopic mast for deployable structures[C]//Proceedings of the the 20th Aerospace Mechanics Symposium, May 1, 1986, USA. NASA, 1986:13-29.
[8] NOOR A K, VENNERI S L. Flight-vehicle materials, structures, and dynamics——assessment and future directions:Computational structures technology[M]. USA:American Society of Mechanical Engineers, 1995.
[9] TANKERSLEY B C. Maypole (hoop/column) deployable reflector concept development for 30 to 100 meter antenna[C]//Conference on Advanced Technology for Future Space Systems, 1979, Hampton, VA, USA. AIAA, 1979:446-458.
[10] Harris Corporation. AAFE large deployable antenna development program:Executive summary[R]. NASA Langley Research Center, CR-2894, 1977.
[11] Orbital ATK, Inc. Telescoping boom system[EB/OL].[2013-11-30]. http://www.orbitalatk.com/space-systems/space-components/deployables/docs/FS028_15%20Telescoping%20Boom%20Systems.pdf.
[12] OLIVIERI L, BRANZ F, DUZZI M, et al. Tethered electromagnetic capture:A cubesat mission concept[C]//International Astronautical Congress, October, 2015, Jerusalem, Israel. International Astronautical Federation, 2015.
[13] PACINI L, KAUFMAN D, ADAMS M. Next generation space telescope (NGST) pathfinder experiment inflatable sunshield in space (ISIS)[C]//World Aviation Conference, October 19-21, 1999, San Francisco, CA. AIAA, 1999.
[14] ROHWELLER D J. Qualification of the inflatable sunshield in space (ISIS) mast[C]//Proceedings of the 36th Aerospace Mechanisms Symposium, May 14-17, 2002, Glenn Research Center.
[15] MOBREM M, SPIER C. Design and performance of the telescopic tubular mast[C]//Proceedings of the 41st Aerospace Mechanisms Symposium, May 16-18, 2012, Jet Propulsion Laboratory. NASA, 2012:127-140.
[16] 钟博文. 套筒式伸展臂的设计与分析[D]. 哈尔滨:哈尔滨工业大学, 2008. ZHONG Bowen. The design and analysis of telescopic mast[D]. Harbin:Harbin Institute of Technology, 2008.
[17] 林上民. 空间伸展臂的结构设计与分析[D]. 西安:西安电子科技大学, 2012. LIN Shangmin. Structural design and analysis of deployable mast[D]. Xi'an:Xidian University, 2012.
[18] ZHANG J, SONG A, XU X, et al. A rigid and flexible structures combined deployable boom for space exploration[C]//Intelligent Robots and Systems (IROS), 2016 IEEE/RSJ International Conference on. IEEE, 2016:2920-2926.
[19] XU K, LI L, BAI S, et al. Design and analysis of a metarnorphic mechanism cell for multistage orderty deployable/retractable mechanism[J]. Mechanism & Machine Theory, 2017, 111:85-98.
[20] 杜善义. 先进复合材料与航空航天[J]. 复合材料学报, 2007, 24(1):1-12. DU Shanyi. Advanced composite materials and aerospace engineering[J]. Acta Materiae Composite Sinica, 2007, 24(1):1-12.
[21] SOUTIS C. Carbon fiber reinforced plastics in aircraft construction[J]. Materials Science & Engineering A, 2005, 412(1):171-176.