Advertisement

Rigid-flexible-thermal analysis of planar composite solar array with clearance joint considering torsional spring, latch mechanism and attitude controller

  • Yuanyuan LiEmail author
  • Cong Wang
  • Wenhu Huang
Original Paper
  • 37 Downloads

Abstract

This paper establishes a thermal-structural coupling model of planar spacecraft system with large flexible composite solar array under nodal coordinate formulation and absolute nodal coordinate formulation framework. Perfect revolute joint is adopted as connection type to give the different influences from fixed constraint used in previous researches, and consequently, torsional spring, latch mechanism, and attitude controller are involved into the spacecraft system. Imperfect revolute joint is further introduced to investigate the coupling effects of thermal load, adjustment motion, and joint clearance on dynamics of the system, including spacecraft attitude, solar panel responses, and wear prediction. Results of six comparison models (with or without clearance joint, considering thermal environment, or adjustment motion, and considering both these two conditions) show that the coupling effect of thermal environment and overall motion brings dramatic and unmanageable shock to the system with clearance joint, that is no longer can be seen as a simple superposition of each single condition effect like the system with ideal joint, although the suspension damper property of clearance joint can weaken thermal-induced vibration or motion induced vibration separately. For a period after attitude adjustment, wear depth of the system subjected to solar radiation is two orders of magnitude lager than that of the system without considering thermal environment. Joint clearance and thermal environment should be considered both; for on-orbit spacecraft system, the coupling effects of them are significant and non-ignorable for relevant mechanism design and performance analysis.

Keywords

Rigid-flexible-thermal coupling Solar array Clearance joint Wear prediction 

Notes

Acknowledgements

This work is supported by the National Natural Science Foundation of China (U1637207). The author Yuanyuan Li acknowledges the support from China Scholarship Council (CSC) and the kind help from Prof. Mathias Legrand.

Compliance with ethical standards

Conflict of interest

The authors declare that they have no conflict of interest.

References

  1. 1.
    Thornton, E.A., Kim, Y.A.: Thermally induced bending vibrations of a flexible rolled-up solar array. J. Spacecr. Rockets 30(4), 438–448 (1993)CrossRefGoogle Scholar
  2. 2.
    Thornton, E.A., Foster, R.S.: Dynamic response of rapidly heated space structures, Computational Nonlinear Mechanics in Aerospace. Engineering 146, 451–477 (1992)Google Scholar
  3. 3.
    Thornton, E.A., Chini, G.P., Gulick, D.W.: Thermal induced vibrations of a self-shadowed split-blanket solar array. J. Spacecr. Rockets 32, 302–311 (1995)CrossRefGoogle Scholar
  4. 4.
    Foster, C.L., Tinker, M.L., Nurre, G.S., Till, W.A.: The solar array-induced disturbance of the Hubble Space Telescope pointing system. NASA STI/Recon Tech. Rep. N 95, 1–36 (1995)Google Scholar
  5. 5.
    Li, J.L., Yan, S.Z., Cai, R.Y.: Thermal analysis of composite solar array subjected to space heat flux. Aerosp. Sci. Technol. 27, 84–94 (2013)CrossRefGoogle Scholar
  6. 6.
    Li, J.L., Yan, S.Z.: Thermally induced vibration of composite solar array with honeycomb panels in low earth orbit. Appl. Therm. Eng. 71(1), 419–432 (2014)CrossRefGoogle Scholar
  7. 7.
    Shen, Z.X., Tian, Q., Liu, X.N., Hu, G.K.: Thermally induced vibrations of flexible beams using absolute nodal coordinate formulation. Aerosp. Sci. Technol. 29, 386–393 (2013)CrossRefGoogle Scholar
  8. 8.
    Liu, J., Pan, K.: Rigid-flexible-thermal coupling dynamic formulation for satellite and plate multibody system. Aerosp. Sci. Technol. 52, 102–14 (2016)CrossRefGoogle Scholar
  9. 9.
    Liu, L., Cao, D., Huang, H., et al.: Thermal-structural analysis for an attitude maneuvering flexible spacecraft under solar radiation. Int. J. Mech. Sci. 126, 161–170 (2017)CrossRefGoogle Scholar
  10. 10.
    Azadi, E., Fazelzadeh, S.A., Azadi, M.: Thermally induced vibrations of smart solar panel in a low-orbit satellite. Adv. Space Res. 59(6), 1502–1513 (2017)CrossRefGoogle Scholar
  11. 11.
    Bai, J.B., Shenoi, R.A., Xiong, J.J.: Thermal analysis of thin-walled deployable composite boom in simulated space environment. Compos. Struct. 173, 210–218 (2017)CrossRefGoogle Scholar
  12. 12.
    Yaqubi, S., Dardel, M., Daniali, H.M., et al.: Modeling and control of crank-slider mechanism with multiple clearance joints. Multibody Syst. Dyn. 36(2), 143–167 (2016)MathSciNetCrossRefzbMATHGoogle Scholar
  13. 13.
    Flores, P., Ambrósio, J., Claro, J.C.P., et al.: Lubricated revolute joints in rigid multibody systems. Nonlinear Dyn. 56(3), 277–295 (2009)CrossRefzbMATHGoogle Scholar
  14. 14.
    Flores, P., Koshy, C.S., Lankarani, H.M., Ambrósio, J., Claro, J.C.P.: Numerical and experimental investigation on multibody systems with revolute clearance joints. Nonlinear Dyn. 65(4), 383–398 (2011)CrossRefGoogle Scholar
  15. 15.
    Erkaya, S., Doğan, S., Ulus, Ş.: Effects of joint clearance on the dynamics of a partly compliant mechanism: numerical and experimental studies. Mech. Mach. Theory 88, 125–140 (2015)CrossRefGoogle Scholar
  16. 16.
    Koshy, C.S., Flores, P., Lankarani, H.M.: Study of the effect of contact force model on the dynamic response of mechanical systems with dry clearance joints: computational and experimental approaches. Nonlinear Dyn. 73(1–2), 325–338 (2013)CrossRefGoogle Scholar
  17. 17.
    Flores, P., Lankarani, H.M.: Dynamic response of multibody systems with multiple clearance joints. J. Comput. Nonlinear Dyn. 7(3), 031003 (2012)CrossRefGoogle Scholar
  18. 18.
    Erkaya, S., Doğan, S., Şefkatlıoğlu, E.: Analysis of the joint clearance effects on a compliant spatial mechanism. Mech. Mach. Theory 104, 255–273 (2016)CrossRefGoogle Scholar
  19. 19.
    Wang, Z., Tian, Q., Hu, H., et al.: Nonlinear dynamics and chaotic control of a flexible multibody system with uncertain joint clearance. Nonlinear Dyn. 86(3), 1571–1597 (2016)CrossRefGoogle Scholar
  20. 20.
    Zhang, L.X., Bai, Z.F., Zhao, Y., et al.: Dynamic response of solar panel deployment on spacecraft system considering joint clearance. Acta Astronaut. 81(1), 174–185 (2012)CrossRefGoogle Scholar
  21. 21.
    Li, J., Yan, S., Guo, F., et al.: Effects of damping, friction, gravity, and flexibility on the dynamic performance of a deployable mechanism with clearance. Proc. Inst. Mech. Eng. Part C J. Mech. Eng. Sci. 227(8), 1791–1803 (2013)CrossRefGoogle Scholar
  22. 22.
    Li, Y., Wang, Z., Wang, C., et al.: Dynamic responses of space solar arrays considering joint clearance and structural flexibility. Adv. Mech. Eng. 8(7), 1–11 (2016)Google Scholar
  23. 23.
    Li, H.Q., Liu, X.F., Duan, L.C., et al.: Deployment and control of spacecraft solar array considering joint stick-slip friction. Aerosp. Sci. Technol. 42, 342–352 (2015)CrossRefGoogle Scholar
  24. 24.
    Li, H.Q., Duan, L.C., Liu, X.F., et al.: Deployment and control of flexible solar array system considering joint friction. Multibody Syst. Dyn. 39(3), 249–265 (2017)MathSciNetCrossRefGoogle Scholar
  25. 25.
    Li, Y., Wang, Z., Wang, C., et al.: Planar rigid-flexible coupling spacecraft modeling and control considering solar array deployment and joint clearance. Acta Astronaut. 142, 138–151 (2018)CrossRefGoogle Scholar
  26. 26.
    Li, Y., Wang, Z., Wang, C., et al.: Effects of torque spring, CCL and latch mechanism on dynamic response of planar solar arrays with multiple clearance joints. Acta Astronaut. 132, 243–255 (2017)CrossRefGoogle Scholar
  27. 27.
    Johnston, J.D., Thornton, E.A.: Thermally induced dynamics of satellite solar panels. J. Spacecr. Rockets 37(5), 604–613 (2000)CrossRefGoogle Scholar
  28. 28.
    Shabana, A.A.: Definition of the slopes and the finite element absolute nodal coordinate formulation. Multibody Syst. Dyn. 1, 339–348 (1997)CrossRefzbMATHGoogle Scholar
  29. 29.
    Li, T., Wang, Y.: Deployment dynamic analysis of deployable antennas considering thermal effect. Aerosp. Sci. Technol. 13, 210–215 (2009)CrossRefGoogle Scholar
  30. 30.
    Liu, C., Tian, Q., Hu, H.: Dynamics of a large scale rigid-flexible multibody system with composite laminated plates. Multibody Syst. Dyn. 26, 283–305 (2011)CrossRefzbMATHGoogle Scholar
  31. 31.
    Johnston, J.D., Thornton, E.A.: Thermally induced attitude dynamics of a spacecraft with a flexible appendage. J. Guid. Control Dyn. 21(4), 581–587 (1998)CrossRefGoogle Scholar
  32. 32.
    Lankarani, H.M., Nikravesh, P.E.: A contact force model with hysteresis damping for impact analysis of multibody systems. J. Mech. Des. 112(3), 369–376 (1990)CrossRefGoogle Scholar
  33. 33.
    Archard, J.F.: Contact and rubbing of flat surfaces. J. Appl. Phys. 24(8), 981–988 (1953)CrossRefGoogle Scholar
  34. 34.
    Lai, X., He, H., Lai, Q., et al.: Computational prediction and experimental validation of revolute joint clearance wear in the low-velocity planar mechanism. Mech. Syst. Signal Process. 85, 963–976 (2017)CrossRefGoogle Scholar
  35. 35.
    Zhu, A., He, S., Zhao, J., et al.: A nonlinear contact pressure distribution model for wear calculation of planar revolute joint with clearance. Nonlinear Dyn. 88(1), 315–328 (2017)CrossRefGoogle Scholar

Copyright information

© Springer Nature B.V. 2019

Authors and Affiliations

  1. 1.Qian Xuesen Laboratory of Space TechnologyChina Academy of Space TechnologyBeijingPeople’s Republic of China
  2. 2.School of AstronauticsHarbin Institute of TechnologyHarbinPeople’s Republic of China

Personalised recommendations