1845. Extending Derivative Airplane Capaabilities; Weight and Balance Considreation


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B Williams: 1845. Extending Derivative Airplane Capaabilities; Weight and Balance Considreation. 1988.



Loadability plays a large part in defining the limit of thrust and weight growth of derivative aircraft. As gross weight and fuel requirements associated with increasing the payload and range capability go up, structural capability and aerodynamic control limits reduce the allowable center of gravity (C.G.) range available for loading revenue payload. This narrower C.G. range imposes cargo and baggage loading and/or passenger seating restrictions on airline operation. Through selective modification of the critical structural parts of the airplane and use of the gains in aerodynamic capability from increased body length, loadability restrictions can be reduced or eliminated. This paper addresses the general type of loadability limits encountered in defining the C.G. range for a typical wing-engined aircraft, how they are required to change to meet the needs of a derivative, and how the limits change with modifications to the aircraft.


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