This report results from a contract tasking University of Manchester as follows: The Grantee will analytically investigate the use of a passive buckling load alleviation concept for a sensorcraft type wing configuration. The outer wing of the sensor craft design leads to the high aspect ratio, which is very favorable for reduction in fuel consumption and range extension. However, it produces high bending moments stemming from maneuvers or wind gusts. This project will investigate the use of an attachment of the outer wing that will enable passive load alleviation due to the washout deflection of the wingtip. A finite element model will be used to investigate and compare strength behavior as well as the static and dynamic aeroelastic performance. An investigation will be performed to show how the load alleviation features can be installed. A study of the outer wing will be performed to investigate the static aeroelastic behavior, position and attachment stiffness of the device. A divergence and flutter analysis will also be performed, and also a buckling analysis will be made to show that this phenomenon will not occur for limit gust or maneuver loads. An assessment of the overall weight reduction using the alleviation device will be conducted.
Structural Design and Analysis of an Aeroelastic Tailoring and Passive Load Alleviation Concept for a Sensor Craft
2007
34 pages
Report
Keine Angabe
Englisch
Environmental & Occupational Factors , Structural Analyses , Fluid Mechanics , Aeroelasticity , Structural analysis , Stiffness , Deflection , Strength(Mechanics) , United kingdom , Dynamics , Aspect ratio , Flutter , Bending moments , Buckling , Sensor craft , Passive loads , Structural design , Foreign reports , Finite element method , Flutter analysis , Aeroelastic tailoring
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