By Denis Howe
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Extra resources for Aircraft Loading and Structural Layout (Aerospace Series (PEP))
The limit load is the actual maximum load of a particular case anticipated to occur in the prescribed operating conditions. A catastrophic failure due to the application of the limit load must be in the extremely remote category. That is. the limit load can be regarded as one which can be anticipated to be reached once. but not exceeded in, say. 10 million (10') flying hours. It is in fact the maximum load for a particular manoeuvre or environmental condition and represents the most severe isolated intensity of load appropriate to the particular case.
B) High-lift device characteristics, especially the associated pitching moments which have a major impact on the loads needed to trim the aircraft. (c) The overall wing-body pitching moment in the zero-lift condition and the corresponding position of the aerodynamic centre. 1. As indicated above these values depend upon the deflection of the high-lift devices but are also affected by small, detail, aspects of the configuration such as the geometry of the wing-hody junction. 1, it is usually inevitable that the initial evaluation of the aerodynamic characteristics is based on the assumption that the airframe is rigid.
The possible implication of such a target is illustrated in Fig. I . I The numerical values shown are inevitably speculative and to a major extent depend upon the impact of technological development on the individual items of risk. For example, developments in automatic controls could well reduce the probability of crew error. Clearly air traffic control and the aircraft itself are the dominant contributors, but it must be stated that the allocation of equal risks to the airframe components is arbitray.