ISSN(Online) : 2319-8753 ISSN (Print) : 2347-6710 International Journal of Innovative Research in Science, Engineering and Technology (An ISO 3297: 2007 Certified Organization) Website: www.ijirset.com Vol. 6, I ssue 3, March 2017 Copyright to IJIRSET DOI:10.15680/IJIRSET.2017.0603306 5051 Design Analysis of Air Craft Wing RIB Syed Noman 1 , Mohammed Siddique 2 , Abdullah Zaid Immad 3 , B. Raj Kumar 4 , D. Ravi 5 Asst. Professor, Dept. of Mechanical, Lords Institute of Engineering & Technology, Hyderabad, India 1 Asst. Professor, Dept. of Mechanical, Lords Institute of Engineering & Technology, Hyderabad, India 2 B.Tech, Dept. of Mechanical, Lords Institute of Engineering & Technology, Hyderabad, India 3, 4, 5 ABSTRACT: This work displays the advancement of a parameterized robotized generic model for the basic plan of a aircraft wing. Besides, with a specific end goal to perform finite element analysis on the aircraft wing geometry, the system of finite element (mesh) period is robotized. Aircraft applied outline is characteristically a multi-disciplinary plan prepare which includes an expansive number of orders and skill. In this postulation work, it is examined how top of the line CAD software's can be utilized as a part of the early phases of a aircraft configuration prepare, particularly for the outline of an aircraft wing and its basic substances wing fights (spars) and wing ribs. The generic model that is produced in such manner can computerize the procedure of creation and change of the aircraft wing geometry in light of a progression of parameters which characterize the geometrical qualities of wing boards, wing fights and wing ribs. Two diverse methodologies are utilized for the production of the generic model of a aircraft wing which are "Learning Pattern" and "Power Copy with Visual Basic Scripting" utilizing the PRO-E software. An execution examination of the bland wing model in view of these two methodologies is additionally performed. In the early phases of the aircraft configuration handle, a gauge of the auxiliary normal for the air ship wing is alluring for which a surface static investigation is more reasonable. In such manner, the procedure of finite element work era for the generic wing model is robotized. The finite element work is produced for the wing boards, wingspans and wing ribs. Besides, the finite element work is refreshed in view of any adjustments in geometry and the state of the wing boards and guarantee that all the work components are dependably legitimately associated at the hubs. The robotized FE work produced can be utilized for playing out the auxiliary examination on a aircraft wing. I.INTRODUCTION Aggressive weight targets and shortened development time-scales in the civil aircraft industry naturally calls for an integration of advanced computer aided optimization methods into the overall component design process. Airbus has in a number of recent studies used ANSYS topology, sizing and shape optimization tools in an attempt to achieve lighter and more efficient component designs. Finite element based topology, measuring and shape improvement devices are commonly utilized as a major aspect of a two-stage design process. Firstly, a topology streamlining is performed to acquire a first view on an optimal configuration for the structure – an underlying outline with ideal load paths.Next, the suggested configuration is interpreted to form an engineering design and this design is then optimized using detailed sizing and shape optimization methods with real design requirements. Numerous examples from the automotive industry have demonstrated the ability of such an approach to quickly generate optimum components for stiffness, stress and vibration designs.This paper concentrates the utilization of Altair's finite element based topology, estimating and shape streamlining devices for plan of airplane segments. Aircraft parts are frequently strength outlines and topology enhancement strategies still totally do not have the capacity to manage buckling criteria.The present work therefore uses the traditional compliance based topology optimization method to suggest an optimal design configuration, which is engineered to provide the design with some stability. Finally, a detailed sizing/shape optimization is performed including both stability and stress constraints.