A Schematic Study and Enhancement of Instabilities in Honey Comb Structure of Aircraft Wing

Abstract

When designing an aircraft, it’s all about finding the optimal proportion of the weight of the vehicle and payload. It needs to be strong and stiff enough to withstand the exceptional circumstances in which it has to operate. Durability is an important factor. Also, if a part fails, it doesn’t necessarily result in failure of the whole aircraft. The main sections of an aircraft, the fuselage, tail and wing, determine its external shape.

On aircraft with stressed-skin wing design, honeycomb structured wing panels are often used as skin. A honeycomb structure is built up from a core material resembling a bee hive’s honeycomb which is laminated or sandwiched between thin outer skin sheets. Panels formed like this are lightweight and very strong. They have a variety of uses on the aircraft, such as floor panels, bulkheads, and control surfaces, as well as wing skin panels. These honeycomb structures are used in the locations of construction of wing panels on a jet transport aircraft. Sandwich structures have been used for many years in aerospace structures due to their high stiffness compared to their density. Honeycomb structures are natural or man-made structures that have the geometry of a honeycomb to allow the minimization of the amount of used material to reach minimal weight and minimal material cost. Types of honeycomb structures are depend upon the geometrical shape. There are different types of honeycomb core structures like square, hexagonal, pentagonal, tetrahedral, pyramidal etc. In this project we are comparing the structural analysis for square and hexagonal honeycomb structures and thermal analysis of square and hexagonal honeycomb structures. Structural analysis is the determination of the effects of loads on physical structure. To perform an accurate analysis an engineer must determine such information as structural loads, geometry, support conditions, and materials properties. The results of such an analysis typically include deformation, stresses and displacements. This information is then compared to criteria that indicate the conditions of failure. Thermal analysis calculates the temperature distribution and related thermal quantities in the system or component. Typical thermal quantities of interest are: The temperature distributions:(a) The time to reach steady state,(b) The steady state temperature distribution (using a transient analysis),(c) The temperature distribution after 50 seconds ;The amount of heat lost or gained; Thermal gradients; Thermal fluxes.