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

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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Hatfield) SUMMARY loads This paper gives for the structure a review of the methods used to determine of the Hawker Siddeley Trident. 14 Fail-safe cases a CONCLUSIONS Table I Illustrations loads 45 46 51 52 53 54 55 56 56 56 gusts Figures 59 i-46 166 34 1 INTRODUCTION The purpose of this paper is to give a review of the processes in deriving the design loads for a typical modern high-speed namely the Hawker Siddeley Trident. As far as possible, all formulae have been avoided and the paper is intended to give amount of work and the organisation necessary rather than to explain any of the theoretical particularly with flexible to aeroelastic craft like involved .

3) acting It . 15, is plotted, that the three where the timemse values do not all variation reach factor of these a maximum at the 166 50 same instant contrlbuticn stringer. and the determination of the crltical time depends on the which each of these values mekes to the flnal stress in the Three different ent times: solutions to this diffwulty have been tried at dlffer- . to assume that the peak values of all three parameters cCCur simultaneously. This gives severe design loads and, hence, 18 a safe approach but it seems wasteful, to say the least, to carry cut lengthy involved calculations on the response of an aircraft to gusts, and then to SubJeCt the results (1) to this kind of heavy-handed treatment whxh Invalidates the accuracy of all the preceding work.

DRSIGN SPWXDS The determination of the design speeds for the aircraft does not really enter into the scope of this paper. However, the speeds used for the different design cases are so fundamental in relation to the design loads produced that a brief mention of them must be made here. 2 shows curves of the various stressing speeds and their variation with altitude. The requirements define speed at lg where Vs, = stalling = manoeuvring load factor. "1 falls off with increasing Mach number, it follows that Since CL this definitionmazf VA gives a lower value than the speed corresponding to a 2&g stall.

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