Author
Chonghui Shao
Bio: Chonghui Shao is an academic researcher from Harbin Institute of Technology. The author has contributed to research in topics: Flutter & Aeroelasticity. The author has an hindex of 4, co-authored 9 publications receiving 71 citations.
Topics: Flutter, Aeroelasticity, Nonlinear system, SMA*, Hamilton's principle
Papers
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TL;DR: In this paper, a coupled thermal-structural analysis for an attitude maneuvering spacecraft under solar radiation is conducted and the interaction between the thermally induced vibration and attitude maneuver is studied.
35 citations
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TL;DR: In this article, a general approach for the vibration and aeroelastic stability of the functionally graded cylindrical shell with arbitrary boundary conditions is firstly presented, where the Sanders' shell theory, a steady-state heat transfer equation and the piston theory are employed to establish the motion equation.
21 citations
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TL;DR: In this paper, a solution of computing the aero-thermal-elastic problem of FG-CNT reinforced composite panel is proposed, in which the aerodynamic heating and transient heat conduction are accounted for.
19 citations
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TL;DR: In this article, the flutter and thermal buckling behavior of laminated composite panels embedded with shape memory alloy (SMA) wires are investigated using the classical plate theory and nonlinear von-Karman strain-displacement relation to investigate the aeroelastic behavior of smart laminated panels.
Abstract: The flutter and thermal buckling behavior of laminated composite panels embedded with shape memory alloy (SMA) wires are studied in this research. The classical plate theory and nonlinear von-Karman strain-displacement relation are employed to investigate the aeroelastic behavior of the smart laminated panel. The thermodynamic behaviors of SMA wires are simulated based on one-dimensional Brinson SMA model. The aerodynamic pressure on the panel is described by the nonlinear piston theory. Nonlinear governing partial differential equations of motion are derived for the panel via the Hamilton principle. The effects of ply angle of the composite panel, SMA layer location and orientation, SMA wires temperature, volume fraction and prestrain on the buckling, flutter boundary, and amplitude of limit cycle oscillation of the panel are analyzed in detail.
18 citations
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TL;DR: In this paper, an alternative simulation approach is proposed to simplify the calculations for the ONERA model, in which the circulatory part of the OnERA model is solved analytically by using Duhamel integral method, and the corresponding aerodynamic loads can be directly expressed in the modal space of the wing motion through only introducing two additional variables.
Abstract: The ONERA aerodynamic model is a nonlinear aerodynamic model which includes the effects of dynamic stall. With the strip theory, the ONERA model is usually used in the aeroelastic analysis of slender wings. To the classical approach for the ONERA model, the circulatory and nonlinear parts are all described by using aerodynamic elements and the simulation cost may be very high. In this paper, an alternative simulation approach is proposed to simplify the calculations for the ONERA model, in which the circulatory part of the ONERA model is solved analytically by using Duhamel integral method. In this way, the corresponding aerodynamic loads can be directly expressed in the modal space of the wing motion through only introducing two additional variables. For a slender wing model, the new simulation approach is used to analyze its nonlinear aeroelastic responses. In the simulation, the number of the state variables for the system using the proposed approach is reduced modestly comparing with that using the classical approach. In addition, for a slender wing with a pylon-store system which includes a free-play gap, both the proposed approach and the classical approach with the same number of aerodynamic elements are used to analyze the nonlinear dynamic behaviors of the system. Simulation results are given to show that the pylon-store system with a free-play gap can lead the occurrence of sub-critical Hopf bifurcation for a slender wing. Additionally, some nonlinear dynamic phenomena about the wing-pylon-store system are observed by using the new approach. But these phenomena cannot be predicted by employing the classical approach with the same number of aerodynamic elements used in the new approach. The peak of the post-critical responses obtained from the classical approach are larger than those obtained from the new approach in most range of free-stream velocity. The nonlinear flutter velocity predicted by using the classical approach is lower than that predicted by using the new approach.
5 citations
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TL;DR: In this article, an analytical model for fiber reinforced polymer composite cylindrical shells (FRPCCSs) accounting for material and geometric nonlinearities and thermal effect is proposed, which is capable of predicting natural frequencies, damping ratios, and resonant responses under different excitation amplitudes and temperatures.
71 citations
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TL;DR: In this article, a unified solution is developed to analyze the vibration and flutter behaviors of supersonic porous functionally graded material (FGM) plates with general boundary conditions, in which the classical and non-classical boundary conditions can be dealt with.
57 citations
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TL;DR: In this article, small amounts of carbon nanotubes (CNTs) were added to the face sheets of sandwich structures to improve their thermo-mechanical responses.
Abstract: Adding small amounts of carbon nanotubes (CNTs) into the face sheets of sandwich structures can significantly improve their thermo-mechanical responses. However, the formation of CNT clusters, espe...
44 citations
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TL;DR: In this paper, a unified solution is proposed to evaluate the aero-thermo-elastic flutter of supersonic plates with general boundary conditions, in which the classical and non-classical boundary conditions can be dealt with.
44 citations
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TL;DR: In this paper, the influence of CNTs, porosity, mechanical and thermal loading on the vibration and dynamic response of the sandwich functionally graded carbon nanotube-reinforced composite was studied.
Abstract: This paper focuses on the influence of CNTs, porosity, mechanical and thermal loading on the vibration and dynamic response of the sandwich functionally graded carbon nanotube-reinforced composite ...
37 citations