By A. S. Taylor, D. J. Eckford (Eds.)
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Additional info for Aircraft Loading Action Problems (Proceedings of a Symposium held at Farnborough on 28th October, 1966)
The landing case loads are the design loads for a large part of the and for the structure in the wing root in the fuselage and centre-section, area of the undercarriage attachments. 9 Take-off oases The loads in the take-off cases have been calculated on the assumption The vertx%J. reaction factor F specified in that the aircraft is rigid. R. B. The take-off oases provide the design loads for carriage and the local attachment to the wmg. 10 Ground manoeuvres These oases are straightforward and do not require any detailed The turning and swinging case designs the undercarriage explanations.
2, there is an infinite number of manceuvre and gust envelopes. 3 and 4. In fact, these envelopes are of very little use in practice today, and appear usually only as a standard item in the aircraft Type Record as a matter of tradition. 5 DESIGN CASES FOR THE AIRCRAFT It sidered is convenxent to categorise under the following headings: the design cases which have to be ccn- 166 37 (I) Airborne (a) cases Manoeuvres (produced by pilot's Symmetric (elevator-induced) Asymmetric Rolling cases (aileron-induced) (i) (ii) Yawing cases (b) 5 (3) , 6 Vertical Lateral Head-on of pilot's actions) gusts gusts gusts.
The modes of higher as stated earlier, so The computer output is usually obtained for 16 to 20 time intervals covering a total time of about a third of a second. This has been found to be long enough, in general, to include the time when the peak structural loads For each time interval the computer outputs the shear, bending moment, occur. torque, lift coefficient and linear and angular accelerations This represents the time history of the aircraft 48 elements. A typical set of output values aircraft penetrates the gust.
Aircraft Loading Action Problems (Proceedings of a Symposium held at Farnborough on 28th October, 1966) by A. S. Taylor, D. J. Eckford (Eds.)