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1999 | Buch

Thermomechanics of Composites under High Temperatures

verfasst von: Yuriy I. Dimitrienko

Verlag: Springer Netherlands

Buchreihe : Solid Mechanics and Its Applications

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Über dieses Buch

The thermomechanical properties of composites on polymer matrix at high tem­ peratures are essentially different from those at normal temperatures. The main distinctions briefly consist in the following: • at high temperatures there occurs an irreversible variation (degradation) of all mechanical and thermal properties of a material that usually has a complex non-linear character depending on time exposure under high temperature; • there are complicated internal physico-chemical processes in a matrix and fibres under high temperatures called by the general notion of ablation; the internal physico-chemical and mechanical processes run differently in the matrix and fibres, and this leads to the appearance of considerable internal thermal stresses. Generally speaking, a composite under high temperatures can be considered as a multiphase system consisting of solid, gaseous and fluid phases interact.ing mechanically and chemically with each ot.her. There are t.hree levels of temperature: normal, elevated and high. Normal, or room temperatures are 10 - 30°C; elevated temperatures are 30 200°C; hzgh temperatures are those above 200°C. However, the dividing line between elevated and high temperat.ures depends on the material involved; a temperature is called high for a particular composite material if, at this temperature, irreversible internal physico-chemical transformations occur in the matrix and/ or fibres of the material.

Inhaltsverzeichnis

Frontmatter
Chapter 1. High-Temperature Environment and Composite Materials
Abstract
The aim of the present work is to model the behaviour of composite materials under high temperatures.
Yuriy I. Dimitrienko
Chapter 2. General Equations of Multiphase Continuum Mechanics for Ablative Composites
Abstract
Models of multiphase media mechanics have been considered in many works [56, 60, 68, 83, 107 etc.]. In the present chapter general relationships of multiphase media mechanics are developed for ablative composites. These are the key points: derivation of expressions for a phase transformation rate with the help of thermodynamical equations at a phase interface; and determination of the way in which constitutive relations depend on the characteristics of the natural configurations of phases. In the first four paragraphs the general case of finite deformations of phases is considered using, in the main, the Euler (space) description given in works [22, 51, 56, 74, 80, 107 etc.]; and in the last paragraph the case of infinitesimal deformations of phases is analyzed.
Yuriy I. Dimitrienko
Chapter 3. Mathematical Model of Ablative Composites
Abstract
The present chapter describes an averaging method for internal thermal and mechanical processes in ablative composites. The method is based on the assumption of a regularity in the internal structure of the ablative composite, and the concept of asymptotic expansion for partial differential equations with rapidly oscillating coefficients. This theory was formulated by N.S.Bakhvalov [8] and developed by B.E.Pobedria [91, 92], D.Lions [73] and others for composites without, phase transformations, and by E.Sanchez-Palencia [104] for porous media without phase transformations. For heterogeneous media with phase transformations the averaging method has been developed in works [39, 41].
Yuriy I. Dimitrienko
Chapter 4. Behaviour of Matrices at High Temperatures
Abstract
The aim of the present chapter is to investigate the behaviour of unreinforced isotropic ablative matrices at high temperatures. We will consider the following questions:
  • solving the local problems over a periodicity cell;
  • calculating the effective characteristics of ablative isotropic materials with the help of these solutions;
  • determining the relationship between microcharacteristics of phases (in the main, microstresses) and macrocharacteristics;
  • formulating a failure criterion for ablative isotropic materials;
  • investigating the phenomena caused by volumetric ablation inside matrices.
Yuriy I. Dimitrienko
Chapter 5. Reinforcing Fibres under High Temperatures
Abstract
The following types of fillers are most widely used for reinforcing ablative matrices:
  • continuous fibres (in the form of threads, bands, fabrics etc.);
  • short fibres;
  • dispersed particles (in the form of hollow microspheres or continuous balls etc.).
Yuriy I. Dimitrienko
Chapter 6. Unidirectional Composites under High Temperatures
Abstract
Unidirectional composites (UCs) are bundles of monofibres assembled as a thread and surrounded by a matrix. Properties of unidirectional composites differ considerably from features of a fibre bundle not impregnated by a matrix. The reason for this is the presence of fibre defects. As mentioned in Chapter 5, monofibres have a spread in strength properties due to the presence of microcracks in them. When the whole thread is loaded, its fibres break one at a time beginning with the weakest ones. In a non-impregnated bundle a destroyed fibre makes rio contribution to the total strength of the thread; in a UC, due to tangential stresses in its matrix, the destroyed fibre does contribute; only some section L neff of monofibre around the break does not contribute to the strength.
Yuriy I. Dimitrienko
Chapter 7. Textile Ablative Composite Materials
Abstract
Let us consider textile composite materials which are most widely used in structures working under high temperatures.
Yuriy I. Dimitrienko
Chapter 8. Composites Reinforced by Dispersed Particles
Abstract
We consider a composite material consisting of two phases in the initial state: polymer binder (b-phase) and filler in the form of dispersed particles (a-phase).
Yuriy I. Dimitrienko
Chapter 9. Phenomena in Composite Materials Caused by Gradient Heating
Abstract
In earlier chapters we assumed that the temperature θ of a composite was uniformly distributed over the whole domain V occupied by the material (or by a specimen, a structure element). This assumption was necessary in order to establish a dependence of effective properties of composites on temperature θ(x, t) at a given material point x. The expressions for thermomechanical characteristics of composites derived above are applicable for the case of gradient heating, i.e. when temperature θ(x, t) changes in passing from one spatial point x to another within the domain V occupied by a composite structure at a fixed time t. Therefore all the aforementioned phenomena of changing (degradation) properties of composites under high temperatures will also take place under gradient heating. However under gradient heating there appear new specific phenomena in the behaviour of composites, which will be investigated below. As an example, the behaviour of composites is considered for textile materials, for which orthotropy axes are directed so that fabric layers are orthogonal to the Ox 1 axis.
Yuriy I. Dimitrienko
Chapter 10. Linear Ablation of Composites
Abstract
For composites under gradient heating up to very high temperatures 1500 – 2000 °C, linear (surface) ablation must be considered in addition to volumetric ablation. The definitions and classification of linear ablation processes were given in paragraph 1.2. The purpose of the present chapter is to establish relationships for the calculation of the linear rate D for different types of surface ablation: combustion, sublimation, melting and thermomechanical erosion of composites.
Yuriy I. Dimitrienko
Chapter 11. Thermal Stresses in Composite Structures under High Temperatures
Abstract
Many stress-strain problems for elements of structures made of ablative composites are axisymmetric. We will use the statements of problems ‘A’ and ‘B’ formulated in paragraph 3.6.
Yuriy I. Dimitrienko
Chapter 12. Mechanics of Composite Thin-Walled Shells under High Temperatures
Abstract
Composite thin-walled shell structures are widely used now in design of high-speed air-space vehicles (ASVs) moving in dense layers of the atmosphere, for example, re-entry vehicles descending from the Earth’s orbit. The typical aerospace composite structure is a three-layer shell (Figure 12.1): the external layer is a thermal-protective composite material based on thermostable resins (phenol, silicon-organic); the middle layer is a low-density thermoinsulative material, and the internal layer is a high strength composite material with epoxy, polyimide etc. resin base. These structures are much more effective than metallic ones. The behaviour of thin-walled composite structures under mechanical actions and normal temperatures (20–150 °C) has been well investigated (for example [3, 120, 121]). The behaviour of thin-walled composite structures under high temperatures, when there is ablation of composite materials, has specific features.
Yuriy I. Dimitrienko
Backmatter
Metadaten
Titel
Thermomechanics of Composites under High Temperatures
verfasst von
Yuriy I. Dimitrienko
Copyright-Jahr
1999
Verlag
Springer Netherlands
Electronic ISBN
978-94-015-9183-6
Print ISBN
978-90-481-5122-6
DOI
https://doi.org/10.1007/978-94-015-9183-6