Experimental validation of a mathematical model for forced vibrations of an open thin-walled cylindrical shell

2020 ◽  
Author(s):  
A. Yu. Dobryshkin ◽  
M. K. Hlaing ◽  
O. E. Sysoev ◽  
E. O. Sysoev
Keyword(s):  
Mathematical Model ◽  
Cylindrical Shell ◽  
Experimental Validation ◽  
Forced Vibrations ◽  
Thin Walled

Investigation of the Influence of the Location of the Unified Mass on the Formed Vibrations of a Thin Containing Extended Shell

2019 ◽  
Vol 945 ◽  
pp. 885-892 ◽  
Author(s):  
O.E. Sysoev ◽  
A.Y. Dobryshkin ◽  
Nyein Sit Naing ◽  
A.V. Baenkhaev
Keyword(s):  
Experimental Data ◽  
Mathematical Model ◽  
Test Bench ◽  
Cylindrical Shells ◽  
Forced Vibrations ◽  
Cyclic Loads ◽  
Attached Mass ◽  
Mass System ◽  
Thin Walled ◽  
Reduced Scale

The operation of a structure of thin-walled open cylindrical shells with high economic efficiency is associated with the phenomenon of oscillations and resonance from the effects of cyclic loads and systems of attached masses. The oscillation processes of such structures are not sufficiently studied at present. The article describes a test bench for testing open thin-walled cylindrical shells hinged on the edges that carry a system of attached masses, and the results of experiments on the nature of a reduced-scale shell model are presented. The attached mass system represents metal cylinders of different masses arranged in a certain sequence on the shell body. The experimental dependence of the change in the frequency spectrum of the shell oscillations on the number, mass, and location of the system of attached masses is obtained. A mathematical model is developed for the behavior of an open thin-walled cylindrical shell with a system of attached masses, consistent with the experimental data for forced vibrations of the shell.

Strongly Nonlinear Vibrations of a Hyperelastic Thin-walled Cylindrical Shell Based on the Modified Lindstedt–Poincaré Method

2019 ◽  
Vol 19 (12) ◽  
pp. 1950160 ◽  
Author(s):  
Jing Zhang ◽  
Jie Xu ◽  
Xuegang Yuan ◽  
Wenzheng Zhang ◽  
Datian Niu
Keyword(s):  
Cylindrical Shell ◽  
Nonlinear System ◽  
Differential Equations ◽  
Nonlinear Vibrations ◽  
Harmonic Excitation ◽  
System Of Differential Equations ◽  
Response Curves ◽  
Strongly Nonlinear ◽  
Hardening Behavior ◽  
Thin Walled

Some significant behaviors on strongly nonlinear vibrations are examined for a thin-walled cylindrical shell composed of the classical incompressible Mooney–Rivlin material and subjected to a single radial harmonic excitation at the inner surface. First, with the aid of Donnell’s nonlinear shallow-shell theory, Lagrange’s equations and the assumption of small strains, a nonlinear system of differential equations for the large deflection vibration of a thin-walled shell is obtained. Second, based on the condensation method, the nonlinear system of differential equations is reduced to a strongly nonlinear Duffing equation with a large parameter. Finally, by the appropriate parameter transformation and modified Lindstedt–Poincar[Formula: see text] method, the response curves for the amplitude-frequency and phase-frequency relations are presented. Numerical results demonstrate that the geometrically nonlinear characteristic of the shell undergoing large vibrations shows a hardening behavior, while the nonlinearity of the hyperelastic material should weak the hardening behavior to some extent.

scholarly journals Wave-Based Attitude Control of Spacecraft with Fuel Sloshing Dynamics

2016 ◽  
Vol 63 (2) ◽  
pp. 263-275 ◽  
Author(s):  
Joseph William Thompson ◽  
William O’Connor
Keyword(s):  
Mathematical Model ◽  
Attitude Control ◽  
Experimental Validation ◽  
Uniform Structure ◽  
Structural Flexibility ◽  
Control Laws ◽  
Single Plane ◽  
Pendulum Model ◽  
Sloshing Dynamics ◽  
Upper Stage

Abstract Wave-Based Control has been previously applied successfully to simple under-actuated flexible mechanical systems. Spacecraft and rockets with structural flexibility and sloshing are examples of such systems but have added difficulties due to non-uniform structure, external disturbing forces and non-ideal actuators and sensors. The aim of this paper is to extend the application of WBC to spacecraft systems, to compare the performance of WBC to other popular controllers and to carry out experimental validation of the designed control laws. A mathematical model is developed for an upper stage accelerating rocket moving in a single plane. Fuel sloshing is represented by an equivalent mechanical pendulum model. A wave-based controller is designed for the upper stage AVUM of the European launcher Vega. In numerical simulations the controller successfully suppresses the sloshing motion. A major advantage of the strategy is that no measurement of the pendulum states (sloshing motion) is required.

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