By Michael C. Niu
The cause of this booklet is to supply a basic realizing in skinny sheet building. The emphasis is on functional program with enter from either fabric energy and hands-on event. a large amount of fabric at the sizing of steel airframe is gifted in tables, charts and/or curves which are in response to previous adventure and/or try out effects. step by step approaches are integrated at any time when attainable and examples of numerical calculation are incorporated to explain both the strategy of sizing or using layout info and layout curves to offer engineers a real-world feeling of ways to accomplish the most productive constructions. The cautious number of structural configurations and fabrics that are mixed to supply an fiscal layout whereas additionally contemplating the consequences of static, fatigue, fail-safe specifications, harm tolerance and reparability also are vital matters during this e-book.
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Extra info for Airframe Stress Analysis and Sizing
Wheel Spring-back VMAX Max. Wheel Vertical Load (* Ground load at instant of peak horizontal load) Fig. 0 Aircraft are designed for the loads acting on the gear at the instant of peak drag. These loads are determined by rational analysis, taking into account the time history of the events that occur during landing impact; gear inertia loads are also included. Following spin up, the gear springs back in a forward direction. A peak loading occurs at the point of maximum forward deflection. The aircraft must be designed for the vertical and horizontal loads occurring at this instant.
The most critical location is near the most outboard tank. ’) are: Tank geometry, as shown in Fig. /sec2 (6 (b) View looking down Front spar (upper) (c) View looking forward H’ Fig. 0 (A) SYMMETRICAL MANEUVER (PITCH OR VERTICAL GUST) An aircraft under symmetrical pitch maneuver (n, = 0) is shown in Fig. l(c) and the fuel pressure at point G : Eq. 5 [(nrzCG + n x x B G ) p] Eq. l(b) Example 1: Determine the ultimate fuel pressure at point G of the fuel tank geometry shown in Fig. l(c) induced by a climb maneuver (assume the fuel overflow tube exists): n.
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.