PROCEDURES FOR INCLUDING TEMPERATURE EFFECTS IN STRUCTURAL ANALYSES OF ELASTIC WINGS. PART I. AN EQUIVALENT PLATE METHOD OF STRUCTURAL ANALYSIS FOR ELEVATED TEMPERATURE STRUCTURES
Some of the structural problems of a heated wing are discussed with specific emphasis on the necessary additions or changes needed in the standard non-thermal methods of analysis to include non-uniform temperature distribution in the structure. With the plate-like hypothesis as a starting point the differential equations of static deflection, including finite deflection terms, have been derived. This development yields two coupled nonlinear partial differential equations in which the vertical deflection and the neutral surface stress function are the dependent variables. The development allows, the load distribution to be stated either explicitly or in terms of the deformed shape, the Young's modulus and the coefficient of thermal expansion to be functions of the local temperature, and the temperature distribution to be an arbitrary function of the space variables. The specific structural problems which can be derived as specializations of the general deflection equations are stress analysis, deflection analysis, wing divergence and aileron effectiveness. A proposed solution by the assumed mode method is outlined. The equations governing the dynamic properties of the wing are derived by including the inertial force in the pressure term of the vertical equilibrium equation. These equations are further simplified by assuming small vibrations about a static deformed shape. This reduces the type and the number of the differential equations to one linear equation which has the vibratory deflection as the dependent variable. A proecdure for solving for the natural vibratory mode shapes and frequencies by the assumed mode method is considered. The aerodynamic loads are described using piston theory aerodynamics. This two-dimensional aerodynamic theory allows the pressure at any point on the wing to be described in terms of the angle of attack, thickness, and motion at that point. (auth)
- Research Organization:
- Massachusetts Inst. of Tech., Cambridge. Aero-Elastic and Structures Research Lab.
- DOE Contract Number:
- AF33(616)-3517
- NSA Number:
- NSA-13-008996
- OSTI ID:
- 4292429
- Report Number(s):
- WADC-TR-57-754(Pt.I); AD-14223
- Resource Relation:
- Other Information: Project No. 6-(8-1367). Orig. Receipt Date: 31-DEC-59
- Country of Publication:
- United States
- Language:
- English
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