By Michael C. Niu
The purpose of this e-book is to supply a basic realizing in skinny sheet building. The emphasis is on sensible software with enter from either fabric energy and hands-on adventure. a large amount of fabric at the sizing of steel airframe is gifted in tables, charts and/or curves which are according to prior adventure and/or try out effects. step by step approaches are incorporated at any time when attainable and examples of numerical calculation are incorporated to elucidate both the strategy of sizing or using layout facts and layout curves to offer engineers a real-world feeling of the way to accomplish the most productive constructions. The cautious choice of structural configurations and fabrics that are mixed to provide an fiscal layout whereas additionally contemplating the consequences of static, fatigue, fail-safe specifications, harm tolerance and reparability also are very important matters during this e-book.
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Additional resources for Airframe Stress Analysis and Sizing
Gross Weight of the Aircraft Another apparent example of the effect of the aircraft gross weight on design loads is the vertical load imposed on the landing gear when it contacts the ground at a given sinking speed. The gross weight to be used for structural design is determined from the mission requirements of the aircraft. Mission requirements and/or design criteria spell out maximum and minimum amounts of fuel and payload to be considered at various stages of aircraft operation. Typical aircraft major design weights are: (a) Take-off gross weight - Maximum gross weight to perform the specified mission.
Fig. 0 and moving aft when the brakes are applied as shown in Fig. 2 load for nominal max. static brake torque (limited to OSSV) Fig. 10 Reverse Braking TOWING: Towing requirements consist of many (approximately twelve) separate conditions which provide for main or nose gear towing fittings and fittings at other locations. The tow loads are obtained by multiplying the take-off weight by varying factors. As shown i n Fig. 15W (take-off gross weight) occurs at the nose gear towing fitting. The requirements call for a reaction equal to the vertical gear load to be applied at the axle of the wheel to which the tow load is applied.
These loads are resisted by aircraft transitional and rotation inertia. VM - One-half the max. vertical ground reaction obtained at each main gear in the level landing conditions * Nose gear ground reactions equal to zero. 5 Lateral Drifi Landing REBOUND LANDING: Since an aircraft may rebound into the air after a hard landing, the gear and its supporting structure must be checked out for this condition. With the landing gear fully extended and not in contact with the ground, a load factor of 20 must be applied to the unsprung weights of the gear.