2.2.1 X-50 Dragonfly Canard Rotor/Wing (CRW)
User Service: DARPA Manufacturer: Boeing Inventory: 2 Delivered/2 Planned
Background: The CRW concept combines the VTOL capability of a helicopter with the high-subsonic cruise speed (as high as 400 kt) of a fixed-wing aircraft. CRW intends to achieve this by stopping and locking the rotor and using it as a wing to achieve high speed forward flight; the canard and tail provide additional lifting and control surfaces. For both rotary and fixed-wing flight modes, the CRW is powered by a conventional turbofan engine. The X-50 is a technology demonstrator designed to assess and validate the CRW concept. Hover tests were conducted in December 2003 and March 2004, but a hard landing resulted in significant damage to the first air vehicle. The second X-50 is now being readied to continue the flight testing, planned for summer 2005. http://www.darpa.mil/tto/programs/crw.html.
Characteristics:
X-50 X-50
Length 17.7 ft Rotorspan 12 ft
Gross Weight 1,485 lb Payload Capacity none
Fuel Capacity 160 gal Fuel Type Jet-A, JP-8
Engine Make Williams F115 Power 700 lbf
Performance:
Endurance 1/2 hr Max/Loiter Speeds 220/0 kt
Ceiling 20,000 ft Radius 30 nm
Takeoff Means Hover Landing Means Hover
SECTION 2 - CURRENT UA PROGRAMS
Page 15
2.2.2 A-160 Hummingbird
User Service: DARPA/Army/Navy Manufacturer: Boeing/Frontier Inventory: 4 Delivered/10 Planned
Background: The A160 Hummingbird is designed to demonstrate the capability for marked improvements in performance (range, endurance, and controllability), as compared to conventional helicopters, through the use of a rigid rotor with variable RPM, lightweight rotor and fuselage structures, a high efficiency internal combustion engine, large fuel fraction, and an advanced semi-autonomous flight control/flight management system. The patented Optimum Speed Rotor (OSR) system allows the rotor to operate over a wide band of RPM and enables the A160 rotor blades to operate at the best lift/drag ratio over the full spectrum of flight conditions. First flight occurred in January 2002. In flight testing, using a 4-cylinder racing car engine, the A160 has achieved 135 kt speed, 7.3 hour endurance on an 18% fuel load, 7,000 ft altitude, and wide variation in rotor RPM. Autonomous flight achieved for take-off, waypoint flight, landing, and lost-link return to base. Current plans are to test with a 6-cylinder engine, then migrate to a turboshaft engine, and ultimately to a diesel engine, to achieve high endurance (24+ hours) and high altitude (30,000 feet). The DARPA contract ends in 2007. http://www.darpa.mil/tto/programs/a160.html.
Characteristics:
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本文链接地址：无人机系统路线图 Unmanned Aircraft Systems Roadmap(26)
