Structural Engineering and Mechanics

  • 제47권2호
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  • Pages.149-166
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  • 2013
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  • 1225-4568(pISSN)
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  • 1598-6217(eISSN)
테크노프레스 (Techno-Press)
권호 표지
DOI QR코드

DOI QR Code

Reduction of the actuator oscillations in the flying vehicle under a follower force

  • Kavianipour, O. (Department of Mechanical Engineering, Damavand Branch, Islamic Azad University) ;
  • Khoshnood, A.M. (Department of Aerospace and Mechanical Engineering, K.N.T. University of Technology) ;
  • Sadati, S.H. (Department of Aerospace and Mechanical Engineering, K.N.T. University of Technology)
  • 투고 : 2012.06.21
  • 심사 : 2013.07.03
  • 발행 : 2013.07.25
⟨ 이전 논문 다음 논문 ⟩

초록

Flexible behaviors in new aerospace structures can lead to a degradation of their control and guidance system and undesired performance. The objectives of the current work are to analyze the vibration resulting from the propulsion force on a Single Stage to Orbit (SSTO) launch vehicle (LV). This is modeled as a follower force on a free-free Euler-Bernoulli beam consisting of two concentrated masses at the two free ends. Once the effects on the oscillation of the actuators are studied, a solution to reduce these oscillations will also be developed. To pursue this goal, the stability of the beam model is studied using Ritz method. It is determined that the transverse and rotary inertia of the concentrated masses cause a change in the critical follower force. A new dynamic model and an adaptive control system for an SSTO LV have been developed that allow the aerospace structure to run on its maximum bearable propulsion force with the optimum effects on the oscillation of its actuators. Simulation results show that such a control model provides an effective way to reduce the undesirable oscillations of the actuators.

키워드

참고문헌

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