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Nevertheless, in spite of the important effect of the distortion on the aerodynamic derivatives and the loads calculated by using them. thcrc is no easy alternative to the assumption of a rigid airframe for the initiation of the loading analysis. Subsequent correction for the effects of distortion is essential. 5. I Specification of design conditions Operating and design flight envelopes The structural integrity of the aircraft must be established at all points on, and within, its operating envelope with adequate allowance for possible excursions outside this envelope.

It should be pointed out that the requirements contain much more than conditions to ensure structural strength and stiffness. Their scope ranges over performance, handling, general operating requirements and procedures, and the design of systems and installations. The latter have major relevance to the achievement of airworthiness targets. 2 Cause of loads The loads experienced by a vehicle fall into two broad categories, see Fig. 2. One group consists of the loads resulting directly from the action of the pilot, or when appropriate, of the autopilot.

It is particularly applicable in three circumstances: (a) When the structure is very special both in concept and application such that there is inadequate past experience to be able to specify realistic factors. (b) When there is high variability or randomness in the loading, material properties, construction techniques, and the like. (c) When the design is a complex system having many components as, for example. in a flight control system. The first two of these circumstances are encountered in nautical structures where each one may be different from every other and the wind and wave loadings are random.

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