Download e-book for kindle: Airframe Stress Analysis and Sizing by Michael C. Niu

By Michael C. Niu

ISBN-10: 1613446624

ISBN-13: 9781613446621

ISBN-10: 9627128120

ISBN-13: 9789627128120

The cause of this e-book is to supply a primary realizing 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 metal airframe is gifted in tables, charts and/or curves which are in keeping with previous event and/or try effects. step by step methods are integrated each time attainable and examples of numerical calculation are incorporated to explain both the tactic 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 collection of structural configurations and fabrics that are mixed to supply an fiscal layout whereas additionally contemplating the results of static, fatigue, fail-safe necessities, harm tolerance and reparability also are very important matters during this ebook.

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Extra info for Airframe Stress Analysis and Sizing

Example text

Landing gear shock-absorbing characteristics are determined by analytical means and then verified by drop test of the gear. (C) LOAD ANALYSIS Design loads are determined for the various structural components using computers. 3 WEIGHT AND BALANCE Structural design loads affect the weight of the airframe structure, and the weight of the aircraft influences the magnitude of design loads. This interdependence suggests that a judicious selection of the preliminary design weight is mandatory to the economical design of an airframe.

63 ksi F,. = 52 ksi F,, = 43 ksi Fig. 3 Stress-Strain Curves of Selected Aluminum Alloys (Sheets) (a) Young's modulus (E): Young's modulus is actually the first linear portion of the tangent modulus: E = -f 8 (proportional or elastic range) Eq. 0 (b) Tangent modulus (E,): E'=E f (plastic or inelastic range) Eq. 3 Typical aluminum alloy compressive stress-strain and compressive tangent-modulus curves for 7075-T651 plate and 7075-T651 extrusion are shown i n Figs. 5, respectively. Modulus of rigidity or shear modulus (G): G= c Li (in elastic range) 2 ( 1 +PI Eq.

A) DYNAMIC LOADS It must be shown by analysis that the aircraft can meet the symmetrical and unsymmetrical gust load conditions in flight when various rates of gust load application are considered. These dynamic flight loads must then be compared to the corresponding static gust loads and the increment of dynamic amplification must be considered in the ultimate design loads. Similarly, it must be shown by analysis that the aircraft can withstand the rate of loading applied to the structure by the landing gear during design landing conditions.

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Airframe Stress Analysis and Sizing by Michael C. Niu

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