Research and Demonstration of the Captive Flight Vibration of Certain Equipment

Shi Liuyang; He GuangQiang

doi:doi:10.11648/j.ijepe.20211004.12

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Research and Demonstration of the Captive Flight Vibration of Certain Equipment

Shi Liuyang, He GuangQiang

Published in International Journal of Energy and Power Engineering (Volume 10, Issue 4)

Received: 2 September 2021 Accepted: 24 September 2021 Published: 29 September 2021

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Abstract

The captive flight vibration is the main induced force environment encountered in the use of air-to-air missile, because of its high vibration intensity and long duration, which has a great impact on the structure and performance of the missile. The captive vibration of the missile is mainly caused by the aerodynamic disturbance around the missile. The captive vibration in the whole missile reliability test should adopt the broadband random vibration of 20 ~ 2000 Hz, and the vibration magnitude of the missile head should be 3 ~ 6 dB lower than that of the missile tail, so as to truly simulate the vibration effect caused by aerodynamic disturbance In this paper, according to the test conditions and calculation formula of airborne external captive flight vibration given in GJB150.16-2009, the power spectral density of captive flight vibration of this type of engine is obtained, and the characteristics and parameters of random vibration are analyzed. The formulas for calculating the power spectral density and the root mean square acceleration at the starting points of the ascending and descending sections corresponding to the slope of the random vibration test condition expressed by the octave are given. The practice shows that the laboratory test results using the research results are similar to those of the air hang flight test.

Published in	International Journal of Energy and Power Engineering (Volume 10, Issue 4)
DOI	10.11648/j.ijepe.20211004.12
Page(s)	75-78
Creative Commons	This is an Open Access article, distributed under the terms of the Creative Commons Attribution 4.0 International License (http://creativecommons.org/licenses/by/4.0/), which permits unrestricted use, distribution and reproduction in any medium or format, provided the original work is properly cited.
Copyright	Copyright © The Author(s), 2024. Published by Science Publishing Group

Keywords

Equipment, Power Spectral Density Function, The Captive Flight Vibration

References

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[2]	Daniel Gapinski, Zbigniew Koruba, Izabela Krzysztofik The model of dynamics and control of modified optical scanning seeker in anti-aircraft rocket missile [J] Mechanical Systems and Signal Processing, 2014, 45 (2).
[3]	Cheng-long Pan, Ji-li Rong, Tian-fu Xu et al. Novel approach for active vibration control of a flexible missile [J] Defence Technology, 2020, 16 (4).
[4]	Bin Zhao, Siyong Xu, Jianguo Guo et al. Integrated strapdown missile guidance and control based on neural network disturbance observer [J] Aerospace Science and Technology, 2019, 84.
[5]	Brian Terranova, Andrew Whittaker, Len Schwer Design of concrete walls and slabs for wind-borne missile loadings [J] Engineering Structures, 2019, 194.
[6]	Akemi Nishida, Zuoyi Kang, Minoru Nagai et al. Evaluation of local damage to reinforced concrete panels subjected to oblique impact by soft missile [J] Nuclear Engineering and Design, 2019, 350.
[7]	M. Viji, N. S. Vikramaditya, S. B. Verma et al. Characteristics of base pressure fluctuations of a typical missile configuration with a propulsive jet [J] Aerospace Science and Technology, 2017, 71.
[8]	Zhi-yong Zhang, Qi-zhong Tang, Xiao-hui Sun et al. Trajectory optimization of a deflectable nose missile [J] Defence Technology, 2017, 13 (3).
[9]	Duc-Kien Thai, Seung-Eock Kim Fluid effect of the water-filled missile on impact force [J] International Journal of Impact Engineering, 2016, 90.
[10]	Changfei Zhuo, Feng Feng, Xiaosong Wu Development process of muzzle flows including a gun-launched missile [J] Chinese Journal of Aeronautics, 2015, 28 (2).
[11]	Wood John D. Comparison of the structural reponses of a captive missile with a free-free missile [J] Planetary and Space Science, 1961, 4.
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[13]	Perching birds damage missile sleds [J] Journal of the Franklin Institute, 1959, 268 (5).
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[15]	Haizhong Zhang, Yan-gang Zhao. Damping modification factor based on random vibration theory using a source-based ground-motion model [J].

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APA Style

Shi Liuyang, He GuangQiang. (2021). Research and Demonstration of the Captive Flight Vibration of Certain Equipment. International Journal of Energy and Power Engineering, 10(4), 75-78. https://doi.org/10.11648/j.ijepe.20211004.12

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ACS Style

Shi Liuyang; He GuangQiang. Research and Demonstration of the Captive Flight Vibration of Certain Equipment. Int. J. Energy Power Eng. 2021, 10(4), 75-78. doi: 10.11648/j.ijepe.20211004.12

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AMA Style

Shi Liuyang, He GuangQiang. Research and Demonstration of the Captive Flight Vibration of Certain Equipment. Int J Energy Power Eng. 2021;10(4):75-78. doi: 10.11648/j.ijepe.20211004.12

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@article{10.11648/j.ijepe.20211004.12,
  author = {Shi Liuyang and He GuangQiang},
  title = {Research and Demonstration of the Captive Flight Vibration of Certain Equipment},
  journal = {International Journal of Energy and Power Engineering},
  volume = {10},
  number = {4},
  pages = {75-78},
  doi = {10.11648/j.ijepe.20211004.12},
  url = {https://doi.org/10.11648/j.ijepe.20211004.12},
  eprint = {https://article.sciencepublishinggroup.com/pdf/10.11648.j.ijepe.20211004.12},
  abstract = {The captive flight vibration is the main induced force environment encountered in the use of air-to-air missile, because of its high vibration intensity and long duration, which has a great impact on the structure and performance of the missile. The captive vibration of the missile is mainly caused by the aerodynamic disturbance around the missile. The captive vibration in the whole missile reliability test should adopt the broadband random vibration of 20 ~ 2000 Hz, and the vibration magnitude of the missile head should be 3 ~ 6 dB lower than that of the missile tail, so as to truly simulate the vibration effect caused by aerodynamic disturbance In this paper, according to the test conditions and calculation formula of airborne external captive flight vibration given in GJB150.16-2009, the power spectral density of captive flight vibration of this type of engine is obtained, and the characteristics and parameters of random vibration are analyzed. The formulas for calculating the power spectral density and the root mean square acceleration at the starting points of the ascending and descending sections corresponding to the slope of the random vibration test condition expressed by the octave are given. The practice shows that the laboratory test results using the research results are similar to those of the air hang flight test.},
 year = {2021}
}

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TY  - JOUR
T1  - Research and Demonstration of the Captive Flight Vibration of Certain Equipment
AU  - Shi Liuyang
AU  - He GuangQiang
Y1  - 2021/09/29
PY  - 2021
N1  - https://doi.org/10.11648/j.ijepe.20211004.12
DO  - 10.11648/j.ijepe.20211004.12
T2  - International Journal of Energy and Power Engineering
JF  - International Journal of Energy and Power Engineering
JO  - International Journal of Energy and Power Engineering
SP  - 75
EP  - 78
PB  - Science Publishing Group
SN  - 2326-960X
UR  - https://doi.org/10.11648/j.ijepe.20211004.12
AB  - The captive flight vibration is the main induced force environment encountered in the use of air-to-air missile, because of its high vibration intensity and long duration, which has a great impact on the structure and performance of the missile. The captive vibration of the missile is mainly caused by the aerodynamic disturbance around the missile. The captive vibration in the whole missile reliability test should adopt the broadband random vibration of 20 ~ 2000 Hz, and the vibration magnitude of the missile head should be 3 ~ 6 dB lower than that of the missile tail, so as to truly simulate the vibration effect caused by aerodynamic disturbance In this paper, according to the test conditions and calculation formula of airborne external captive flight vibration given in GJB150.16-2009, the power spectral density of captive flight vibration of this type of engine is obtained, and the characteristics and parameters of random vibration are analyzed. The formulas for calculating the power spectral density and the root mean square acceleration at the starting points of the ascending and descending sections corresponding to the slope of the random vibration test condition expressed by the octave are given. The practice shows that the laboratory test results using the research results are similar to those of the air hang flight test.
VL  - 10
IS  - 4
ER  -

Copy | Download

Author Information

Shi Liuyang

No. 5715 Factory of People's Liberation Army, Luoyang, China
He GuangQiang

No. 5715 Factory of People's Liberation Army, Luoyang, China

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Plain Text BibTeX RIS

APA Style

Shi Liuyang, He GuangQiang. (2021). Research and Demonstration of the Captive Flight Vibration of Certain Equipment. International Journal of Energy and Power Engineering, 10(4), 75-78. https://doi.org/10.11648/j.ijepe.20211004.12

Copy | Download

ACS Style

Shi Liuyang; He GuangQiang. Research and Demonstration of the Captive Flight Vibration of Certain Equipment. Int. J. Energy Power Eng. 2021, 10(4), 75-78. doi: 10.11648/j.ijepe.20211004.12

Copy | Download

AMA Style

Shi Liuyang, He GuangQiang. Research and Demonstration of the Captive Flight Vibration of Certain Equipment. Int J Energy Power Eng. 2021;10(4):75-78. doi: 10.11648/j.ijepe.20211004.12

Copy | Download

@article{10.11648/j.ijepe.20211004.12,
  author = {Shi Liuyang and He GuangQiang},
  title = {Research and Demonstration of the Captive Flight Vibration of Certain Equipment},
  journal = {International Journal of Energy and Power Engineering},
  volume = {10},
  number = {4},
  pages = {75-78},
  doi = {10.11648/j.ijepe.20211004.12},
  url = {https://doi.org/10.11648/j.ijepe.20211004.12},
  eprint = {https://article.sciencepublishinggroup.com/pdf/10.11648.j.ijepe.20211004.12},
  abstract = {The captive flight vibration is the main induced force environment encountered in the use of air-to-air missile, because of its high vibration intensity and long duration, which has a great impact on the structure and performance of the missile. The captive vibration of the missile is mainly caused by the aerodynamic disturbance around the missile. The captive vibration in the whole missile reliability test should adopt the broadband random vibration of 20 ~ 2000 Hz, and the vibration magnitude of the missile head should be 3 ~ 6 dB lower than that of the missile tail, so as to truly simulate the vibration effect caused by aerodynamic disturbance In this paper, according to the test conditions and calculation formula of airborne external captive flight vibration given in GJB150.16-2009, the power spectral density of captive flight vibration of this type of engine is obtained, and the characteristics and parameters of random vibration are analyzed. The formulas for calculating the power spectral density and the root mean square acceleration at the starting points of the ascending and descending sections corresponding to the slope of the random vibration test condition expressed by the octave are given. The practice shows that the laboratory test results using the research results are similar to those of the air hang flight test.},
 year = {2021}
}

Copy | Download

TY  - JOUR
T1  - Research and Demonstration of the Captive Flight Vibration of Certain Equipment
AU  - Shi Liuyang
AU  - He GuangQiang
Y1  - 2021/09/29
PY  - 2021
N1  - https://doi.org/10.11648/j.ijepe.20211004.12
DO  - 10.11648/j.ijepe.20211004.12
T2  - International Journal of Energy and Power Engineering
JF  - International Journal of Energy and Power Engineering
JO  - International Journal of Energy and Power Engineering
SP  - 75
EP  - 78
PB  - Science Publishing Group
SN  - 2326-960X
UR  - https://doi.org/10.11648/j.ijepe.20211004.12
AB  - The captive flight vibration is the main induced force environment encountered in the use of air-to-air missile, because of its high vibration intensity and long duration, which has a great impact on the structure and performance of the missile. The captive vibration of the missile is mainly caused by the aerodynamic disturbance around the missile. The captive vibration in the whole missile reliability test should adopt the broadband random vibration of 20 ~ 2000 Hz, and the vibration magnitude of the missile head should be 3 ~ 6 dB lower than that of the missile tail, so as to truly simulate the vibration effect caused by aerodynamic disturbance In this paper, according to the test conditions and calculation formula of airborne external captive flight vibration given in GJB150.16-2009, the power spectral density of captive flight vibration of this type of engine is obtained, and the characteristics and parameters of random vibration are analyzed. The formulas for calculating the power spectral density and the root mean square acceleration at the starting points of the ascending and descending sections corresponding to the slope of the random vibration test condition expressed by the octave are given. The practice shows that the laboratory test results using the research results are similar to those of the air hang flight test.
VL  - 10
IS  - 4
ER  -

Copy | Download