Substituting the values from equations [1], [5], and [6] for terms highlighted by brackets, and rearranging terms:

The first term consists of three elements of aircraft design that remain constant for a particular aircraft configuration.

The second term [% availability x % efficiency x hours/aircraft/day] is determined from assumptions of future availability, efficiency, and flight time/ aircraft/day. This term can vary from a high of 12 (100% availability x 100% efficiency x 12 hours/aircraft/day) under ideal conditions, with excess flight crews, to a low of 1 (50% availability x 50% efficiency x 4 hours/aircraft/day) under poor conditions, as might prevail at the end of prolonged surge activity.

The third term represents the diminishing effect of distance on productivity when both mission load and sortie rates are reduced with distance. A plot of this term is shown in the upper left-hand corner of Figure D.3.


Payload Versus Mission Distance

There are five major aircraft configurations to be considered:

  • V-22 short takeoff, internal load (V-22 STO);
  • V-22 vertical takeoff, internal load (V-22 int);
  • V-22 vertical takeoff, external load (V-22 ext);
  • CH-53E vertical takeoff, internal load (CH-53E int); and
  • CH-53E vertical takeoff, external load (CH-53E ext).

A plot of useful payload vs. mission distance is shown in Figure D.4. The information regarding V-22 STO, V-22 int, and CH-53E int is derived from briefing charts provided by the Naval Surface Warfare Center, West Bethesda,

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