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Shock Response Prediction of a Low Altitude Earth Observation Satellite During Launch Vehicle Separation

  • Lee, Dae-Oen (Department of Aerospace Engineering Korea Advanced Institute of Science and Technology) ;
  • Han, Jae-Hung (Department of Aerospace Engineering Korea Advanced Institute of Science and Technology) ;
  • Jang, Hae-Won (Department of Mechanical Engineering Korea Advanced Institute of Science and Technology) ;
  • Woo, Sung-Hyun (Korea Aerospace Research Institute) ;
  • Kim, Kyung-Won (Korea Aerospace Research Institute)
  • Published : 2010.03.01

Abstract

Several pyrotechnic devices are employed over the course of satellite's missions, generally for the separation of structural subsystems and deployment of appendages. Firing of pyrotechnic devices results in impulsive loads characterized by high peak acceleration and high frequency content which can cause failures of various flight hardware elements and small components. Thus, accurate prediction of acceleration level in various components of spacecraft due to pyrotechnic devices is important. In this paper, two methods for pyroshock prediction, an empirical model and statistical energy analysis in conjunction with virtual mode synthesis, are applied to predict shock response of a low altitude earth observation satellite during launch vehicle separation. The predicted results are then evaluated through comparison with the shock test results.

References

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  3. Pyroshock Acceleration Field Reconstruction in Temporal and Spectral Domains Based on Laser Shock Scanning and Iterative Decomposition and Synthesis Considering Stop Band Effects vol.2017, 2017, https://doi.org/10.1155/2017/8351791
  4. A correlation study of satellite finite element model for coupled load analysis using transmissibility with modified correlation measures vol.33, pp.1, 2014, https://doi.org/10.1016/j.ast.2014.01.002
  5. Pyroshock Prediction of Ridge-Cut Explosive Bolts Using Hydrocodes vol.2016, 2016, https://doi.org/10.1155/2016/1218767
  6. Vibratory loads and response prediction for a high-speed flight vehicle during launch events vol.17, pp.4, 2016, https://doi.org/10.5139/IJASS.2016.17.4.551