Design Dive Airspeed m/s íµí± Gravity acceleration íµí±/íµí± 2 íµí± íµí± Design Dive Airspeed m/s íµí°¼ íµí± Moment of Inertia kg/m 2 íµí±¤ Wing loading íµí±/íµí± 2 íµí± Spring constant íµí±/íµí± X Displacement m m Mass kg íµí±¥̇ Velocity m/s M Aeroplane Mass kg íµí±¥̈ Acceleration m/s 2 Load factor.
In order to demonstrate the results obtained with the methods implemented in Microsoft Excel® throughout this work, the shear force, bending moment and torsion are plotted along each of the main components of a Lockheed C-130H Hercules. The user is required to introduce its geometry and operational conditions and the maximum loads acting on the landing gears, wing, horizontal stabilizer, vertical stabilizer and fuselage are then determined.
So as to materialize this purpose, a number of interconnected Microsoft Excel® workbooks that evaluate the structural loads acting on a generic aeroplane have been developed.
The present research aimed to enhance the work developed by the OGMA, Indústria Aeronáutica de Portugal, SA Engineering, Design and Modifications Office by performing an evaluation of the structural loads acting on an aeroplane to estimate the maximum loads acting on the airframe using a thorough analysis that can work both as an alternative and a validation of the most commonly used methods, namely Computational Fluid Dynamics and Finite Element Methods commercial softwares and as a primary mean of showing compliance with the applicable regulations.
From the design viewpoint, the determination of the loads acting on an aircraft is of outmost relevance, because their critical combinations are the designer's limit constraints.
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