Airframe Stress Analysis and Sizing by Michael C. Niu PDF

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By Michael C. Niu

ISBN-10: 1613446624

ISBN-13: 9781613446621

ISBN-10: 9627128120

ISBN-13: 9789627128120

The cause of this publication is to supply a basic figuring out in skinny sheet development. 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 previous event and/or attempt effects. step by step methods are incorporated each time attainable and examples of numerical calculation are incorporated to elucidate both the strategy of sizing or using layout facts and layout curves to provide engineers a real-world feeling of ways to accomplish the best buildings. 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 requisites, harm tolerance and reparability also are vital matters during this e-book.

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Michael C. Niu's Airframe Stress Analysis and Sizing PDF

The cause of this e-book is to supply a basic figuring out in skinny sheet building. The emphasis is on useful software with enter from either fabric power 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 in response to prior event and/or attempt effects.

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Sample text

1 Lifting Force vs. 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.

25 times hot day stall. - During the first part of landing impact, the wheel is spun up to aircraft rolling velocity by friction' between the tire and the runway. This friction induces a short time, aft acting load at the axle which causes the gear to deflect aft as shown in Fig. 2. Forward V P* Max. Wheel Spin-up Max. 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.

The derived gusts at the related aircraft speed of Ve (design speed for maximum gust intensity), Vc (design cruise speed), and Vo (design dive speed) must be investigated for flap-up and flap-down conditions. 5 GROUND LOADS This discussion is based on aircraft configurations with conventional arrangements of main and nose landing gears. S. FAR 23 or FAR 25 for further load requirements. (A) LANDING CONDITIONS The load factors (n) required for design for landing conditions are related to the shock absorbing characteristics of the main and nose gears.

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Airframe Stress Analysis and Sizing by Michael C. Niu

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