Download PDF by A. S. Taylor, D. J. Eckford (Eds.): Aircraft Loading Action Problems (Proceedings of a

By A. S. Taylor, D. J. Eckford (Eds.)

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Extra info for Aircraft Loading Action Problems (Proceedings of a Symposium held at Farnborough on 28th October, 1966)

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This fact adds another difficulty to the problem of finding the worst fin loads since a large symmetric download on the tailplane is associated with a reduced tailplane rolling moment, and the net fin loads depend on both down-load and rolling moment. In order to obtain the msxlmum tailplane rolling moment it is necessary to have the This will occur with aft centre of gravity maximum symmetric up tail load. The inertia relief on the rear and hence full load in the rear fuselage. a maximum in this case and the m-mum fuselage fuselage loads is, therefore, shears due to tailplane torque are associated with reduced direct shear loads It is not easy to select the worst since there is so much inertia relief.

R. appears to be rather vague on this point since it calls for checked symmetric manoeuvres from Ig up to the manoeuvre envelope , load factor at VA. This is less than n,. , it is obvious required here. The Trident is designed for 2&g at VA. what is VC is taken as equal to VMO, the maximum operating speed, and hence is a practical limit. 2 that VC is reduced at 36 altitudes below 6000 ft. on the windscreen of the aircraft. 88. loads operation * . VD is fixed relative to VC so that the margin between them is sufficient to ccver inadvertent speed increases due to gusts, loss of control or varlation of Mach number due to temperature fronts.

The aircraft elements have two degrees of freedom, translation and pitch. The aircraft is then considered as flying through the gust specified by the requirement3 for the speed and altitude under consideration. The The aerodynamic loads induced by the gust is assumed to be of sin2 shape. gust are calculated using the appropriate aerodynamic lag functions (Kiissner functions). The aircraft is given 8 degrees of freedom, rigid body The aerodynamic damping due translation and pitch and 6 modes of vibration.

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Aircraft Loading Action Problems (Proceedings of a Symposium held at Farnborough on 28th October, 1966) by A. S. Taylor, D. J. Eckford (Eds.)


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