**Abstract:**
As an Aerospace Structures Engineer, the main apotheosis of this research was to reinforce a conventional wing box structure – idealization based using various FEA methodologies, along with various FEA packages used for modelling and reinforcing the structure which includes Strand 7, MSC Patran, and for performing the deformation on the mode of linear static analysis, determining post-buckling behaviour of the skin panel with respect to ribs and stringers supporting the skin subjected to pressurised loading, vibration analysis and Global Strength FEA with ‘g’ force on application of a point load on a single structural component. The wing box structure consists of the structural components such as front spar, rear spar, ribs, stringers, and the skin, which when integrated, and on reinforcement form the wing box structure of the wing of an aircraft. Here the wing box structure is taken as a whole to reinforce, and when performing the Structural Analysis the Front Spar is taken into consideration, which is a C- channel beam cross section, assumed to be as a Cantilever beam with a Point load application. The Solver is Linear Static – Structural analysis, to calculate the Bending Moment, Shear Force and deformation of the structural beam component on Strand 7, MSC Patran and Abaqus. Here as the beam element is taken into consideration for analysis, it will have 6 Degrees of freedom, whereas for the Skin, as it’s a plate element, it will have 5 Degrees of Freedom, as they do not account for twisting stiffness normal to the plate surface, and the missing degree of freedom is called as ‘Drilling Degree of Freedom’. Furthermore, the whole structural model is reinforced and a Global FEA analysis is done to check for the total deformation of the reinforced structure. Aircrafts and Rocket structures are capable of high-G manoeuvring, the reason which enables them to take tighter turns than the required target, and for this the structure needs to be strong enough to sustain these loads. When such a turn is entered, the structure is highly loaded by the inertia of the payload and the structural mass, and for this an ‘Inertia Relief’ solver is analysed, which is subjected to high ‘2g’ to ‘6g’ acceleration, which results in deformation of the structure, with a normal pressure force acting. The super structure is reinforced finally with the centre wing box structure and the fuselage along with the wings, after performing all these calculations. Sub-Space Iteration and Negative Eigenvalues including gravity force are taken into consideration.

**Keywords:**
Strand 7, MSC Patran, Abaqus, Global FEA Structural analysis.