Journal of the Korea Institute of Military Science and Technology (한국군사과학기술학회지)

The Korea Institute of Military Science and Technology (한국군사과학기술학회)
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A Study on the Flight Vibration Specification of High Speed Vehicle using Response Analysis

응답해석을 이용한 고속비행체의 비행진동규격 연구

  • Hwang, Dongkee (The 1st Research and Development Institute, Agency for Defense Development) ;
  • Song, Ohseop (School of Mechanical Engineering, Chungnam National University)
  • 황동기 (국방과학연구소 제1기술연구본부) ;
  • 송오섭 (충남대학교 기계공학부)
  • Received : 2018.07.31
  • Accepted : 2018.11.16
  • Published : 2018.12.05
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Abstract

A well-designed flight vibration specification enables the optimum weight design of the Surface-to-Air or Air-to-Air Missile, improves the maneuverability of the flight vehicle, improves the engagement of target, and increases the price competitiveness of the components and the missile system. Conventional flight vibration specifications are used by using a somewhat higher standard as suggested in MIL-STD-810C, or based on accumulated data from developed similar missile systems. In this study, we confirmed the validity of FEA response analysis by comparing response data obtained by FEA and response data of real product. Also we proposed that each specification that reflects the structural characteristics of the place where the components are mounted is required instead of verifying all the components by a single flight vibration specification.

Keywords

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Fig. 1. General procedure for response PSD in most FEM codes

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Fig. 2. An object of study

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Fig. 3. Configuration for a axial test

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Fig. 4. Excited force and measured acceleration(axial test)

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Fig. 5. Configuration for a bending test

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Fig. 6. Excited force and measured acceleration(bending test)

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Fig. 7. FE beam/shell/solid model

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Fig. 8. The test results

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Fig. 9. Components motion(test results)

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Fig. 10. Bending mode shape(using accelerometers attached on housing)

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Fig. 11. Bending mode shape(using all accelerometers)

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Fig. 12. The FEA results

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Fig. 13. Grms of components(C1, C2, C3)

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Fig. 14. Grms of measured and analyzed results

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Fig. 15. Frame and measured points for components

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Fig. 16. Proposed flight vibration spec. for C1

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Fig. 17. Proposed flight vibration spec. for C2

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Fig. 18. Proposed flight vibration spec. for C3

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Fig. 19. Comparison of proposed flight vibration spec.

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Fig. 20. Grms of proposed flight vibration spec.

Table 1. Properties of study object

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Table 2. Data measured from the axial test

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Table 3. Applied damping ratio

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Table 4. Data obtained from FEA(axial)

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Table 5. Proposed spec. by analyzed data(g2/Hz)

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References

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