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ACTA AERONAUTICAET ASTRONAUTICA SINICA ›› 2015, Vol. 36 ›› Issue (3): 848-856.doi: 10.7527/S1000-6893.2014.0080

• Solid Mechanics and Vehicle Conceptual Design • Previous Articles     Next Articles

Acceleration response prediction for lunar lander using time-domain substructure methods

DONG Weili, LIU Li, ZHOU Sida   

  1. Key Laboratory of Dynamics and Control of Flight Vehicle, Ministry of Education, School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China
  • Received:2014-03-24 Revised:2014-04-25 Online:2015-03-15 Published:2015-03-31
  • Supported by:

    Beijing Institute of Technology Foundation for Basic Research (20120142009)

Abstract:

The remarkable increase in the complexity and size of spacecraft has inflicted unprecedented difficulties and challenges on system level dynamics simulation. At present, dynamic substructure method is mainly adopted to improve the solution efficiency and protect the proprietary technologies in model sharing among different project groups. The acceleration shock response spectrum is commonly used to describe the impact dynamic environment during the soft landing phase. It is acknowledged that the effects of high order modes on acceleration responses are more significant than those on displacement responses, so under the condition of small damping, the acceleration prediction accuracy is far lower than the prediction accuracy of displacement obtained by classical substructure methods based on modal with identical cut-off frequency. To solve this problem, a recently proposed novel method called impulse based substructuring (IBS) method is applied and its reduced-order form of iterative solution format used to predict acceleration is presented. Based on the buffer load measured from the soft landing numerical experiment, the acceleration response of the lunar lander is respectively calculated through the Craig-Bampton (CB) method and the IBS method. A numerical example shows that the IBS method has higher accuracy and efficiency than CB method, and it is suitable for rapid prediction for acceleration of the lunar lander with high accuracy.

Key words: lunar lander, component modal synthesis method, dynamic substructure method, time domain, impulse response

CLC Number: