Hostname: page-component-5b777bbd6c-5mwv9 Total loading time: 0 Render date: 2025-06-18T21:34:32.625Z Has data issue: false hasContentIssue false
  • English
  • Français

Study on the dynamic modelling method of a coilable mast based on hinge equivalent rotational stiffness identification

Published online by Cambridge University Press:  16 June 2025

Y. Liu ,
L. Sun Open the ORCID record for L. Sun [Opens in a new window] ,
H. Huang ,
W. Li  and
X. Zhao
Y. Liu
Affiliation:
School of Astronautics, Beihang University, Beijing, China
L. Sun*
Affiliation:
School of Astronautics, Beihang University, Beijing, China
H. Huang
Affiliation:
School of Astronautics, Beihang University, Beijing, China
W. Li
Affiliation:
School of Astronautics, Beihang University, Beijing, China
X. Zhao
Affiliation:
Institute of Remote Sensing Satellite, China Academy of Space Technology, Beijing, China
*
Corresponding author: L. Sun; Email: sunliang@buaa.edu.cn
Get access Rights & Permissions [Opens in a new window]

Abstract

With numerous applications of coilable masts in high-precision space application scenarios, there are also greater demands on the accuracy of their dynamic modelling and analysis. The modelling of hinges is a critical issue in the dynamic modelling of coilable masts, which significantly affects the accuracy of the dynamic response analysis. For coilable masts, the rotational effect is the most important problem in hinge modelling. However, few studies have focused on this topic. To address this problem, the concept of hinge equivalent rotational stiffness is proposed in this paper to describe the rotational effect of the coilable mast hinges. After that, a new coilable mast dynamic model containing the undetermined hinge equivalent rotational stiffness is introduced, and an identification method for the hinge equivalent rotational stiffness based on the hammer test is proposed. Finally, the dynamic modelling method is validated through an actual coilable mast example, and the analysis and test results show that the accuracy of the dynamic model established by the proposed method in this paper is greater than that of the traditional model.

Keywords

coilable mastdynamic modelhinge equivalent rotational stiffnessparameter identification
Type
Research Article
Information
The Aeronautical Journal , First View , pp. 1 - 20
Check for updates
Copyright
© The Author(s), 2025. Published by Cambridge University Press on behalf of Royal Aeronautical Society

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

Article purchase

Temporarily unavailable

References

Fernandez, J.M., Lappas, V.J. and Daton-Lovett, A.J. Completely stripped solar sail concept using bi-stable reeled composite booms, Acta Astronaut., 2011, 69, (1–2), pp 78–85.10.1016/j.actaastro.2011.02.015CrossRefGoogle Scholar
Michael, A.B. A deployable mast for solar sails in the range of 100–1000m, Adv. Space Res., 2011, 48, pp 1747–1753.Google Scholar
Meguro, A., Shintate, K., Usui, M., et al. In-orbit deployment characteristics of large deployable antenna reflector onboard Engineering Test Satellite VIII, Acta Astronaut., 2009, 65, (9–10), pp 1306–1316.10.1016/j.actaastro.2009.03.052CrossRefGoogle Scholar
Wang, J., Li, D.X. and Jiang, J.P. Finite element modeling and modal analysis of coilable mast, Appl. Mech. Mater., 2012, 226–228, pp 299–302.Google Scholar
Johnson, L., Alexander, L., Fabisinski, L., et al. Multiple NEO rendezvous using solar sail propulsion, in Proceedings, Global Space Exploration Conference 2012, International Astronautical Federation (IAF), pp 1–9, 2012.Google Scholar
Eiden, M., Brunner, O. and Stavrinidis, C. Deployment analysis of the Olympus Astromast and comparison with test measurements, J. Spacecr. Rockets, 1987, 24, (1), pp 63–68.10.2514/3.25873CrossRefGoogle Scholar
Kitamura, T., Okazaki, K., Natori, M., et al. Development of a “hingeless mast” and its applications, Acta Astronaut., 1988, 17, (3), pp 341–346.10.1016/0094-5765(88)90043-4CrossRefGoogle Scholar
McEachen, M. Validation of SAILMAST technology and modeling by ground testing of a full-scale flight article, in 48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition, American Institute of Aeronautics and Astronautics (AIAA), Report No.: AIAA-2010-1491, pp 1–14, 2010.Google Scholar
Trautt, T. and McEachen, M. Confirmation of non-dimensionalized (scalable) closed-form analytics for modeling slender truss behavior under combined loading, in 48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition, American Institute of Aeronautics and Astronautics (AIAA), Report No.: AIAA-2010-1492, pp 1–19, 2010.10.2514/6.2010-1492CrossRefGoogle Scholar
Murphy, D.M., Murphey, T.W. and Gierow, P.A. Scalable solar-sail subsystem design concept, J. Spacecr. Rockets, 2003, 40, (4), pp 539–547.10.2514/2.3975CrossRefGoogle Scholar
Murphy, D., McEachen, M., Macy, B., et al. Demonstration of a 20-m solar sail system, in 46th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference, American Institute of Aeronautics and Astronautics (AIAA), Report No.: AIAA-2005-2126, pp 1–17, 2005.Google Scholar
Huang, H., Zhao, X., Sun, L., et al. System design and on-orbit test of Student Small Satellite (SSS-1), Chin. J. Aeronaut., 2022, 43, (10), pp 269–279.Google Scholar
Ishimura, K., Minesugi, K., Kawano, T., et al. On orbit structural performance of Hitomi (ASTRO-H), in AIAA Scitech 2019 Forum, American Institute of Aeronautics and Astronautics (AIAA), Report No.: AIAA-2019-0202, pp 1–9, 2019.10.2514/6.2019-0202CrossRefGoogle Scholar
Ishimura, K., Ishida, M., Kawano, T., et al. Induced vibration of high-precision extensible optical bench during extension on orbit. Trans. Jpn. Soc. Aeronaut. Space. Aerosp. Technol. Jpn., 2018, 16, (2), pp 181–187.Google Scholar
Kawano, T., Ishimura, K., Iizuka, R., et al. Validation of on-orbit thermal deformation and finite element model prediction in X-ray astronomical satellite Hitomi, Trans. Jpn. Soc. Aeronaut. Space Sci. Aerosp. Technol. Jpn., 2018, 16, (3), pp 242–247.Google Scholar
Deininger, W.D., Kalinowski, W., Allen, Z., et al. Imaging X-Ray polarimeter explorer mission spacecraft implementation concept, in AIAA SPACE and Astronautics Forum and Exposition, American Institute of Aeronautics and Astronautics (AIAA), Report No.: AIAA-2017-5314, pp 1–10, 2017.10.2514/6.2017-5314CrossRefGoogle Scholar
Weisskopf, M.C., Ramsey, B., O’Dell, S.L., et al. The imaging x-ray polarimetry explorer (IXPE). Results Phys., 2016, 6, pp 1179–1180.10.1016/j.rinp.2016.10.021CrossRefGoogle Scholar
Ma, H., Huang, H., Han, J., et al. Study on the criterion to determine the bottom deployment modes of a coilable mast, Acta Astronaut., 2017, 141, pp 89–97.10.1016/j.actaastro.2017.09.035CrossRefGoogle Scholar
Liu, Y., Sun, L., Huang, H., et al. Nonlinear characteristics of torsional stiffness of a coilable mast with triangular section, Chin. J. Aeronaut., 2024, 37, (10), pp 313–324.10.1016/j.cja.2024.06.025CrossRefGoogle Scholar
Liu, T., Han, H., Ji, B., et al. Experimental investigation and numerical simulation on nonlinear buckling mode of coil-able mast, J. Nanjing Univ. Aeronaut. Astronaut., 2015, 47, (6), pp 897–903.Google Scholar
Jin, Y., Liu, T., Lyu, R., et al. Theoretical analysis and experimental investigation on buckling of FASTMast deployable structures, International Journal of Structural Stability and Dynamics, 2014, 15, (5), p 1450075.10.1142/S0219455414500758CrossRefGoogle Scholar
Xue, Y. and Liu, Z. Analysis of equilibrium with friction of an elastic rod constrained by a cylindrical surface, Chin. Q. Mech., 2016, 37, (1), pp 139–148.Google Scholar
Han, J., Wang, X. and Ma, H. Mechanical principle of the deploying mode for coilable mast, J. Beijing Univ. Aeronaut. Astronaut., 2013, 39, (9), pp 1168–1173.Google Scholar
Han, J., Huang, H. and Ma, H. Vibration model of coilable mast considering slack diagonals, J. Beijing Univ. Aeronaut. Astronaut., 2014, 40, (7), pp 970–977.Google Scholar
Fan, P., Chen, W., Zhang, Y., et al. FEM analysis on the nonlinear vibration properties of a coilable mast, J. Vibrat. Shock, 2018, 37, (10), pp 80–86.Google Scholar
Zhang, J., Guo, H., Liu, R., et al. Nonlinear dynamic modeling and analysis for space deployable structure with clearance joints, J Xi’an Jiaotong Univ., 2013, 47, (11), pp 113–119+126.Google Scholar
Li, T., Guo, J. and Cao, Y. Dynamic characteristics analysis of deployable space structures considering joint clearance. Acta Astronaut., 2011, 68, (7–8), pp 974–983.10.1016/j.actaastro.2010.08.039CrossRefGoogle Scholar
Dubowsky, S. and Freudenstein, F. Dynamic analysis of mechanical systems with clearances, part 1: formation of dynamic model, J. Eng. Ind., 1971, 93, (1), pp 305–309.10.1115/1.3427895CrossRefGoogle Scholar
Dubowsky, S. and Freudenstein, F. Dynamic analysis of mechanical systems with clearances, part 2: dynamic response, J. Eng. Ind., 1971, 93, (1), pp 310–316.10.1115/1.3427896CrossRefGoogle Scholar
Bauchau, O.A. and Rodriguez, J. Modeling of joints with clearance in flexible multibody systems, Int. J. Solids Struct., 2002, 39, (1), pp 41–63.10.1016/S0020-7683(01)00186-XCrossRefGoogle Scholar
Zhang, J. Modeling and analysis of nonlinear dynamics for joint and deployable structure, Doct. Dissertation Harbin Inst. Technol., Harbin Institute of Technology, pp 1–151, 2014.Google Scholar
Zhou, S. and Zhou, X. Development and technical difficulties of deployable space masts, Chin. Space Sci. Technol., 2014, 34, (6), pp 38–50.Google Scholar
James, V.H., Robert, E.S. and John, V. Shape control of tensegrity structures, in AIAA SPACE 2015 Conference and Exposition, American Institute of Aeronautics and Astronautics (AIAA), Report No.: AIAA-2015-4502, pp 1–21, 2015.Google Scholar
Tibert, A.G. and Pellegrino, S. Deployable tensegrity reflectors for small satellites, J. Spacecr. Rockets, 2002, 39, (5), pp 701–709.10.2514/2.3867CrossRefGoogle Scholar