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Publisher Summary The maximum loads on the components of an aircraft's structure generally occur when the aircraft is undergoing some form of acceleration or deceleration such as in landings, take-offs, and maneuvers within the flight and gust envelopes. Therefore, before a structural component can be designed, the inertia loads corresponding to these accelerations and decelerations must be calculated. This chapter considers the calculation of aircraft loads corresponding to the flight conditions specified by flight envelopes. The next section determines aircraft loads corresponding to a given maneuver load factor. Clearly, it is necessary to relate this load factor to given types of maneuver. Two cases arise: the first involves a steady pull-out from a dive and the second, a correctly banked turn. Although the latter is not a symmetric maneuver in the strict sense of the word, it gives rise to normal accelerations in the plane of symmetry and is, therefore, included. The chapter considers aircraft loads resulting from prescribed maneuvers in the longitudinal plane of symmetry. Other types of in-flight load are caused by air turbulence. The movements of the air in turbulence are generally known as gusts and produce changes in wing incidence, thereby subjecting the aircraft to sudden or gradual increases or decreases in lift from which normal accelerations result. These may be critical for large, high-speed aircraft and may possibly cause higher loads than control initiated maneuvers. |
