Advances in aircraft and spacecraft science

  • 제5권2호
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  • Pages.205-223
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  • 2018
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  • 2287-528X(pISSN)
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  • 2287-5271(eISSN)
테크노프레스 (Techno-Press)
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Modelling and simulation of a closed-loop electrodynamic shaker and test structure model for spacecraft vibration testing

  • 투고 : 2016.11.28
  • 심사 : 2017.10.12
  • 발행 : 2018.03.25
⟨ 이전 논문 다음 논문 ⟩

초록

During launch a spacecraft is subjected to a variety of dynamical loads transmitted through the launcher to spacecraft interface or air-born transmission excitations in the acoustic pressure field inside the fairing. As a result, spacecraft are tested on ground to ensure and demonstrate the global integrity of the structure against these loads, to screen the flight hardware for quality of workmanship and to validate mathematical models. This paper addresses the numerical modelling and simulation of the low frequency sine and random vibration tests performed on electrodynamic shaker facilities to comprise the mechanical-borne transmission loads through the launcher to spacecraft interface. Consequently, the paper reviews techniques and methodologies to derive a reliable and representative coupled virtual vibration testing simulation environment based on experimental data. These technologies are explored with the main objectives to ensure a stable, reliable and accurate control while testing. As a result, the use of the derived simulation models in combination with the added value of improved control and signal processing algorithms can lead to a safer and smoother vibration test control of the entire environmental test campaign.

키워드

참고문헌

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피인용 문헌

  1. Development of a steepest-descent control solution for Multi-Input Multi-Output swept sine testing in a virtual shaker environment vol.1264, pp.None, 2018, https://doi.org/10.1088/1742-6596/1264/1/012002