By Michael C. Niu
The cause of this publication is to supply a primary realizing in skinny sheet building. The emphasis is on functional software with enter from either fabric power and hands-on event. a large amount of fabric at the sizing of metal airframe is gifted in tables, charts and/or curves which are in response to earlier event and/or try effects. step by step systems are incorporated every time 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 the way to accomplish the most productive buildings. The cautious number of structural configurations and fabrics that are mixed to provide an monetary layout whereas additionally contemplating the consequences of static, fatigue, fail-safe requisites, harm tolerance and reparability also are very important concerns during this booklet.
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Additional info for Airframe Stress Analysis and Sizing
1 ‘n’ values range between 8 and 35 and: Higher values are good for column strength and buckling Lower values are good in redundant structures which have better redistribution of loads 62 Material Properties (A) MODULUS Up to the elastic limit the slope of the f (stress) vs. E (strain) curve is constant and above the elastic limit E is replaced by E, (tangent modulus) which varies with stress level. This explains why the material stress-strain curve is divided into two main sections, namely: Elastic limit (proportional range) Inelastic limit (plastic range) A group of stress-strain curves for several aluminum alloys (including the 2000 alloy series and the 7000 alloy series) are plotted in Fig.
77 psi at the flight altitude of 45,000 ft. 7 psi) in flight, based on Fig. 2, its flight altitude should be reduced to 23,000 ft. 9 WING FUEL PRESSURE LOADS Fuel pressure loads in the fuel tank can induce pressure which is normal to the tank wall structure ( e g , upper and lower covers, inb’d and outb’d ribs, and front and rear spars). 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.
The 7075-T6 alloy is almost twice as strong as 2024-T3, and therefore the weight can be reduced correspondingly in suitable applications. (a) 58 Material Properties Stress corrosion cracking is a defect which usually occurs after some years of service. It often, however, has its origins during the manufacturing process, when temperature differences caused by the unequal rates of cooling in various parts of a component give rise to stresses because the cooler parts contract more than the hotter areas.
Airframe Stress Analysis and Sizing by Michael C. Niu