11 Modelling and Static Structural Analysis of Aeroplane Wing by Considering Various Alloy Materials S Sapthagiri 1 , Dr K Jayathirtha Rao 2 1 Associate Professor, Department of Mechanical Engineering Guru Nanak Institutions Technical Campus, Hyderabad, India 2 Director (Retd), Environmental Test Facility, RCI, Hyderabad, India International Journal of Research in Mechanical Engineering Volume 4, Issue 4, July-August, 2016, pp. 11-17 ISSN Online: 2347-5188 Print: 2347-8772, DOA: 01072016 © IASTER 2016, www.iaster.com ABSTRACT Structural stability of materials for aeronautical applications is one of the task for material providers. Even though some materials are available in the present market there is lack of cost considerations with high stability is still on the process. Main focus of this research considering non coating applications by mixing less percentage of Ni and TiB 2 added for aluminium alloy composites. In this project detailed design of Boeing 707 aircraft wing structure made by using CREO PARAMETER 2.0. Then stress analysis of the wing structure is carried out to compute the stresses at wing structure. The static structural analysis are estimated by using the finite element approach with the help of ANSYS-workbench 14 to find out the safety factor of the structure. The response of the wing structure will be evaluated. Keywords: Aircraft Design, CREO Parameter 2.0, FEA, Static Structural Analysis. I. INTRODUCTION Aviation technology is a revolutionary emerging field. Aeronautical engineering stands as the pillar towards space science. In this regard the developing countries are stepping forward to expand their aviation field although materials. Wing structure consists of skin, ribs and spar sections. The spar carries flight loads and the weight of the wings while on the ground. Other structural and forming members such as ribs are attached to the spars, with stressed skin. The wings are the most important lift producing part of the aircraft. The design of wings may vary according to the type of aircraft and its purpose. Experimental testing of wing structure is more expensive and time consuming process. The particular design of a wing depends on many factors, such as the size, weight, speed, rate of climb, and use of the aircraft. The wing must be constructed so that it holds its aerodynamics shape under the extreme stresses of combat manoeuvres or wing loading. Wings develop the major portion of the lift of a heavier-than-air aircraft. Wing structures carry some of the heavier loads found in the aircraft structure. 80% of the lift load will be carried by wing structure in a transport category aircraft. Because of the lift load, wings will bend upward during flight. The particular design of a wing depends on many factors, such as the size, weight, speed, rate of climb, and use of the aircraft. The wing must be constructed so that it holds its aerodynamics shape under the extreme stresses of combat maneuvers or wing loading. The wings of most naval aircraft are of all metal, full cantilever construction. Often, they may be folded for carrier use. A full cantilever wing structure is very strong.