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Operation of such helicopters requires calculating CG along two axes: one calculation for longitudinal CG (fore-to-aft balance) and another calculation for lateral CG (left-to-right balance). The weight, arm, and moment values of the fixed items on the aircraft (i.e. engines, wings, electronic components) do not change and are provided by the ...
The aircraft gross weight (also known as the all-up weight and abbreviated AUW) is the total aircraft weight at any moment during the flight or ground operation. [ 1 ] [ 2 ] [ 3 ] An aircraft's gross weight will decrease during a flight due to fuel and oil consumption.
The "Operating empty weight" (OEW) is the sum of the empty weight and the crew plus their baggage. Standard items include all structural modification or configuration orders that may have altered the MEW, including all fluids necessary for operation such as engine oil , engine coolant , water , hydraulic fluid and unusable fuel .
Takeoff weight components. The maximum takeoff weight (MTOW) or maximum gross takeoff weight (MGTOW) or maximum takeoff mass (MTOM) of an aircraft, also known as the maximum structural takeoff weight or maximum structural takeoff mass, [1] is the maximum weight at which the pilot is allowed to attempt to take off, due to structural or other limits.
Takeoff weight is the weight of an aircraft as it takes off partway along a runway. Few flight planning systems calculate the actual takeoff weight; instead, the fuel used for taking off is counted as part of the fuel used for climbing up to the normal cruise height. Landing weight is the weight of an aircraft as it lands at the destination ...
|empty weight= – the unloaded, unfuelled, unoccupied weight of the aircraft. In most cases, this will be the Basic Aircraft Empty Weight. For lighter-than-air or hybrid aircraft, this will be the structural weight of the aircraft. |gross weight= – the fully-loaded weight of the aircraft. In most cases, this will be the Maximum Take Off Weight.
The weight of the aircraft is the common factor that links all aspects of aircraft design such as aerodynamics, structure, and propulsion, all together. An aircraft's weight is derived from various factors such as empty weight, payload, useful load, etc. The various weights are used to then calculate the center of mass of the entire aircraft. [37]
The load factor, and in particular its sign, depends not only on the forces acting on the aircraft, but also on the orientation of its vertical axis. During straight and level flight, the load factor is +1 if the aircraft is flown "the right way up", [2]: 90 whereas it becomes −1 if the aircraft is flown "upside-down" (inverted). In both ...