Research Papers

Study on the Natural Vibration Characteristics of Flexible Missile With Thrust by Using Riccati Transfer Matrix Method

[+] Author and Article Information
Gangli Chen

Institute of Launch Dynamics,
Nanjing University of Science and Technology,
Nanjing 210094, China
e-mail: chengangli1988@163.com

Xiaoting Rui

Institute of Launch Dynamics,
Nanjing University of Science and Technology,
Nanjing 210094, China
e-mail: ruixt@163.net

Fufeng Yang

Institute of Launch Dynamics,
Nanjing University of Science and Technology,
Nanjing 210094, China
e-mail: fufengyang@aliyun.com

Jianshu Zhang

Institute of Launch Dynamics,
Nanjing University of Science and Technology,
Nanjing 210094, China
e-mail: zhangdracpa@sina.com

1Corresponding author.

Contributed by the Applied Mechanics Division of ASME for publication in the JOURNAL OF APPLIED MECHANICS. Manuscript received September 28, 2015; final manuscript received November 18, 2015; published online December 10, 2015. Editor: Yonggang Huang.

J. Appl. Mech 83(3), 031006 (Dec 10, 2015) (8 pages) Paper No: JAM-15-1518; doi: 10.1115/1.4032049 History: Received September 28, 2015; Revised November 18, 2015

Due to the mass consumption and engine thrust of a flexible missile during the powered phase flight, its natural vibration characteristics may be changed significantly. The calculation of natural frequencies and mode shapes plays an important role in the structural design of the missile. Aiming at calculating the natural vibration characteristics of the missile rapidly and accurately, a nonuniform beam subjected to an engine thrust is used to model the free vibration of the missile and Riccati transfer matrix method (RTMM) is adopted in this paper. Numerical results show that the natural frequencies of a typical single stage flexible missile are increased unceasingly in its powered phase, and its mode shapes are changed a lot. When the presented methodology is used to study the natural vibration characteristics of flexible missiles, not only the mass, stiffness, and axial compressive force distributions are described realistically but also numerical stability, high computation speed, and accuracy are achieved.

Copyright © 2016 by ASME
Topics: Thrust , Vibration , Missiles
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Fig. 1

Dynamics model of a typical flexible missile with thrust

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Fig. 8

The values of characteristic determinant of RTMM

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Fig. 2

Schematic diagram of the value of the characteristic determinant with respect to frequency

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Fig. 10

Effect of thrust magnitude on the fundamental natural frequency

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Fig. 11

The first four-order natural frequencies of the missile in its powered phase

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Fig. 12

The first four-order mode shapes of the missile at the initial and final times of its powered phase (a) first mode, (b) second mode, (c) third mode, and (d) fourth mode

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Fig. 3

Mass per unit length

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Fig. 4

Bending stiffness distribution

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Fig. 5

Compressive stiffness distribution

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Fig. 6

Axial compressive force distribution

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Fig. 7

Comparison of computation time

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Fig. 9

The values of characteristic determinant of TMM



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