Solution of coupled dynamic thermoelasticity problem for an infinite cylinder and sphere

AbstractAs an exploratory study for structural deformation and thermodynamic response induced by spacecraft reentry aerodynamic force and thermal environment, a finite element algorithm is presented on the basis of the classic Fourier heat conductive law to simulate the dynamic thermoelasticity coupling performance of the material. The Newmark method and Crank-Nicolson scheme are utilized to discretize the dynamic thermoelasticity equation and heat conductive equation in the time domain, respectively, and the unconditionally stable implicit algorithm is constructed. Four types of finite-element computing schemes are devised and discussed to solve the thermodynamic coupling equation, all of which are implemented and compared in the computational examples including the one-dimensional transient heat conduction in considering and not considering the vibration, the transient heat flow for the infinite cylinder, and the dynamic coupling thermoelasticity around re-entry flat plate from hypersonic aerothermodynamic environment. The computational results show that the transient responses of temperature and displacement field generate lag phenomenon in case of considering the deformation effect on temperature field. Propagation, rebounding, attenuation and stabilized phenomena of elastic wave are also observed by the finite-element calculation of thermodynamic coupling problem considering vibration and damping, and the oscillation of the temperature field is simultaneously induced. As a result, the computational method and its application research platform have been founded to solve the transient thermodynamic coupling response problem of the structure in strong aerodynamic heating and force environment. By comparing various coupling calculations, it is demonstrated that the present algorithm could give a correct and reliable description of transient thermodynamic responses of structure, the rationality of the sequentially coupling method in engineering calculation is discussed, and the bending deformation mechanism produced by the thermodynamic coupling response from windward and leeward sides of flying body is revealed, which lays the foundation in developing the numerical method to solve material internal temperature distribution, structural deformation, and thermal damage induced by spacecraft dynamic thermoelasticity coupling response under uncontrolled reentry aerothermodynamic condition.

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General heating distributions on the tumbling infinite cylinder

10.2514/6.1978-42 ◽

1978 ◽

Author(s):

H. CARROLL

Keyword(s):

Infinite Cylinder

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Axisymmetric thermoelasticity problem for two-temperature hollow cylinder

Soviet Applied Mechanics ◽

10.1007/bf00883729 ◽

1978 ◽

Vol 14 (12) ◽

pp. 1271-1275

Author(s):

L. P. Khoroshun ◽

N. S. Soltanov

Keyword(s):

Hollow Cylinder ◽

Thermoelasticity Problem ◽

Two Temperature

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The viscous secondary flow ahead of an infinite cylinder in a uniform parallel shear flow

Journal of Fluid Mechanics ◽

10.1017/s0022112060000098 ◽

1960 ◽

Vol 7 (1) ◽

pp. 145-155 ◽

Cited By ~ 5

Author(s):

Alar Toomre

Keyword(s):

Shear Flow ◽

Lateral Displacement ◽

Reynolds Numbers ◽

Infinite Cylinder ◽

List Type ◽

Displacement Effect ◽

Simple Method ◽

Viscous Shear ◽

Parallel Shear Flow ◽

Viscous Shear Flow

A simple method is presented in this paper for calculating the secondary velocities, andthe lateral displacement of total pressure surfaces (i.e. the ‘displacement effect’) in the plane of symmetry ahead of an infinitely long cylinder situated normal to a steady, incompressible, slightly viscous shear flow; the cylinder is also perpendicular to the vorticity, which is assumed uniform but small. The method is based on lateral gradients of pressure, these being calculated from the primary flow alone. Profiles of the secondary velocities are obtained at several Reynolds numbers ahead of two specific cylindrical shapes: a circular cylinder, and a flat plate normal to the flow. The displacement effect is derived and, rathe surprisingly, is found to be virtually independent of the Reynolds number.

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Spin-up from rest of a compressible fluid in a rapidly rotating cylinder

Journal of Fluid Mechanics ◽

10.1017/s0022112092003471 ◽

1992 ◽

Vol 237 ◽

pp. 413-434 ◽

Cited By ~ 7

Author(s):

Jae Min Hyun ◽

Jun Sang Park

Keyword(s):

Mach Number ◽

Compressible Fluid ◽

Numerical Solutions ◽

Stokes Equations ◽

Axial Direction ◽

Ekman Layer ◽

Infinite Cylinder ◽

Full Time ◽

Viscous Effects ◽

Initial State

Spin-up flows of a compressible gas in a finite, closed cylinder from an initial state of rest are studied, The flow is characterized by small reference Ekman numbers, and the peripheral Mach number is O(1). Comprehensive numerical solutions have been obtained for the full, time-dependent compressible Navier-Stokes equations. The details of the flow, temperature, and density evolution are described. In the early phase of spin-up, owing to the thermoacoustic disturbances caused by the compressible Rayleigh effect, the flows are oscillatory, and this oscillatory behaviour is pronounced at higher Mach numbers. The principal dynamical role of the Ekman layer is dominant over moderate times of orders of the homogeneous spin-up timescales. Owing to the density stratification in the radial direction, the Ekman layer is thicker in the central region of the interior. The interior azimuthal flows are mainly uniform in the axial direction. As the Mach number increases, the rate of spin-up in the interior becomes slower, and the propagating shear front is more diffusive. Explicit comparisons with the results for an infinite cylinder are made to ascertain the contributions of the endwall disks. In contrast to the usual incompressible spin-up from rest, the viscous effects are relatively more important for the case of a compressible fluid.

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