@conference {3342, title = {3342. V-22 Weight History - Post Design Weight Analysis}, booktitle = {63rd Annual Conference, Newport, California}, year = {2004}, month = {5/15/04}, pages = {56}, publisher = {Society of Allied Weight Engineers, Inc.}, organization = {Society of Allied Weight Engineers, Inc.}, type = {28. WEIGHT REDUCTION - PROCESSES}, address = {Newport, California}, abstract = {The V-22 is a tiltrotor aircraft. Its engines and proprotor systems are contained within wing tip mounted nacelles that rotate, allowing it to take off and land vertically as a helicopter and, once airborne, fly as a turboprop aircraft. The 38 ft (11.58 m) diameter proprotors are powered by two Rolls-Royce AE1107C engines. The proprotors fold and the wing rotates parallel to the fuselage to allow for compact shipboard stowage and maintenance. With a crew of three, the MV-22 (USMC) aircraft is designed to carry twenty-four combat ready troops on a 200 nm (322 km) radius mission, @ 3,000 ft (914 m), 91.5 degree F. The CV-22 (USAF) utilizes a crew of four, and carries eighteen combat ready Special Operations Forces troops on a 500 nm (805 km) radius mission. The V-22 has the capability to carry 10,000 lbs (4,536 kg) externally from a single hook, 15,000 lbs (6,804 kg) on dual hooks. The internal cargo capacity is 20,000 lbs (9,072 kg), contained within a cabin measuring 290 in (737 cm) in length, 71 in (80 cm) in width and 72 in (183 cm) in height. The aircraft will cruise at 275 kts (509 km/hr), with a dash speed of 300 kts (556 km/hr). This paper discusses the evolution of the V-22 design, the weight history of the V-22 as it has moved through its development phases, and descriptions of the major components comprising the aircraft.}, keywords = {28. Weight Reduction - Processes}, url = {https://www.sawe.org/papers/3342/buy}, author = {Harris, Scott} }