DESIGN AND ANALYSIS OF A TELESCOPIC WING

This is a report of a analysis done for checking the feasibility of telescopic wing in a light aircraft wing . The development of morphing wing technologies for flight regime adaptation has received great interest from Researchers and engineers in the past years. This report in one such research where we have designed a morphing wing structure to our aircraft to adaptive mechanisms and structures. Our report deals with developing an aircraft with a morphing wing in a high-performance aircraft that can operate efficiently in multiple flight conditions by changing its external shape. A new approach was taken to the old concept of a variable span wing by developing a very simple overlapping spar system.

The wing is composed of a high speed (low drag & strong) central wing section with completely retractable high lift sections which move in a span wise direction as opposed to the chord wise direction of conventional flaps. It is the same concept of changing lift with conventional chord wise flaps except that the span wise flap increases span & area instead of only the camber. It also increases the aspect ratio instead of decreasing it, which greatly improves efficiency and safety.

 

    This report shows a highly positive image of telescopic wing, which is entirely justified in view of the numerous benefits offered by them. For large deformations of morphing aircraft the orthotropic properties of composite materials may be used. This may, for example, enable the elimination of hinges, which reduces the stress concentration around the pivot points, and consequently reduces the weight penalty introduced with morphing. Morphing technology allows the design of novel control effectors, often as a result of biological inspiration. One such design, involves innovative wing-tip extensions featuring differentially-variable dihedral angles, referred to as active winglets.

In the result discussion we had discussed about the structural analysis of a telescopic wing with aluminium and composite material. The gathered result shows the increase in lift while using composite material in the wing .The conventional wing having the lift of 2.3 and drag of 0.3 the telescopic wing have the lift of 2.5 and the reduced drag of 0.275 and their is drastic change in the deformation of the wing.

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