• Title/Summary/Keyword: 종단 질량

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Modal Analysis for the Rotating Cantilever Beam with a Tip Mass Considering the Geometric Nonlinearity (기하학적 비선형성을 고려한 종단 질량을 갖는 회전하는 외팔보의 모달 분석)

  • Kim, Hyoungrae;Chung, Jintai
    • Transactions of the Korean Society for Noise and Vibration Engineering
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    • v.26 no.3
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    • pp.281-289
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    • 2016
  • In this paper, a new dynamic model for modal analysis of a rotating cantilever beam with a tip-mass is developed. The nonlinear strain such as von Karman type and the corresponding linearized stress are used to consider the geometric nonlinearity, and Euler-Bernoulli beam theory is applied in the present model. The nonlinear equations of motion and the associated boundary conditions which include the inertia of the tip-mass are derived through Hamilton's principle. In order to investigate modal characteristics of the present model, the linearized equations of motion in the neighborhood of the equilibrium position are obtained by using perturbation technique to the nonlinear equations. Since the effect of the tip-mass is considered to the boundary condition of the flexible beam, weak forms are used to discretize the linearized equations. Compared with equations related to stiffening effect due to centrifugal force of the present and the previous model, the present model predicts the dynamic characteristic more precisely than the another model. As a result, the difference of natural frequencies loci between two models become larger as the rotating speed increases. In addition, we observed that the mode veering phenomenon occurs at the certain rotating speed.

Design and Hot Fire Tests of the Pyrostarter for Liquid Rocket Engines (액체로켓엔진용 파이로시동기의 설계 및 연소시험연구)

  • Kang, Sang Hun;Jang, Jesun
    • Journal of the Korean Society of Propulsion Engineers
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    • v.18 no.3
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    • pp.48-55
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    • 2014
  • In present study, design and hot fire tests of the pryostarter are conducted. To prevent the turbopump RPM overshoot, regressive mass flow rate profile is applied. Sudden decrease of the mass flow rate at the end of the propellant burning is realized as well. Firing test results show good agreements with the design requirements. Through the study with ignition substance variations, combustion products and ignition performances are improved.