|Bell X-22 on the tarmac|
|Manufacturer||Bell Aircraft Corporation|
|First flight||17 March 1966|
|Status||1 preserved in museum|
The Bell X-22 was a United States V/STOL X-plane with four tilting ducted fans. Take-off was to selectively occur either with the propellers tilted vertically upwards, or on a short runway with the nacelles tilted forward at approximately 45°. Additionally, the X-22 was to provide more insight into the tactical application of vertical take-off troop transporters such as the preceding Hiller X-18 and the X-22 successor, the Bell XV-15. Another program requirement was a true airspeed in level flight of at least 525 km/h (326 mph; 283 knots).
Design and developmentEdit
In 1962, the US Navy announced their request for two prototype aircraft with V/STOL capability, powered by four ducted fan nacelles. Bell Helicopter already had intensive experience with VTOL aircraft and was able to utilize an already developed test mockup. In 1964 the prototype, internally referred to by Bell as Model D2127, was ordered by the Navy and received the X-22 designation.
Three-blade propellers were mounted on four wings and, synchronized through a wave-interconnection system, were connected to four gas turbines which themselves were mounted in pairs on the rear wings. Maneuvering was achieved by tilting the propeller blades in combination with control surfaces (elevators & ailerons), which were located in the thrust stream of the propellers.
The maiden flight of the prototype occurred on 17 March 1966. In contrast to other tilt-rotor craft (such as the Bell XV-3), transitions between hovering and horizontal flight succeeded nearly immediately. However, interest increased more towards VTOL and V/STOL properties, not the specific design of the prototype.
Due to failure of a prop control, described by the test pilot, Stanley Kakol, as the only non redundant component in the power chain, the prototype crashed on 8 August 1966 and technicians stripped it for components in order to make the second prototype flight capable. The fuselage was still used as a simulator for some time afterward.
The second X-22 first flew on 26 August 1967. Early that year, it was equipped with a variable flight control and stabilizer system from Cornell Aeronautical Laboratory, which improved flight performance. Although the X-22 was considered to be the best aircraft of its type at the time, the program was canceled. The required maximum speed of 525 km/h was never reached. The second prototype was moved to Cornell Aeronautical Laboratory for further testing; the last flight occurred in 1988. Although the ducted fan propellers were considered usable, they were not used again on a US military aircraft until the F-35B.
- Crew: 2+6 Passengers
- Length: 39 ft 7 in (12.07 m)
- Wingspan: 39 ft 3 in (11.96 m)
- Wingspan (front wing): 22.916 ft (6.98 m)
- Height: 20 ft 8 in (6.31 m)
- Empty weight: 10,478 lb (4,753 kg)
- Max takeoff weight: 17,644 lb (8,003 kg)
- Powerplant: 4 × General Electric-YT58-GE-8D turboshaft engines, 1,267 hp (945 kW) each
- Propellers: 3-bladed propellers mounted in wing-tip swivelling ducts, 7 ft 0 in (2.13 m) diameter
- Maximum speed: 221 kn (254 mph; 409 km/h)
- Service ceiling: 27,800 ft (8,500 m)
- Hover ceiling in ground effect : 12,000 ft (3,658 m)
- Hover ceiling out of ground effect : 6,000 ft (1,829 m)
- Apostolo, Giorgio. The Illustrated Encyclopedia of Helicopters. New York: Bonanza Books, 1984. ISBN 0-517-439352.
- "Bell-X22A: Analysis of a VTOL research vehicle." Flight International, 23 March 1967, p. 445.
- Markman, Steve and Bill Holder. Straight Up: A History of Vertical Flight. Atglen, Pennsylvania: Schiffer Publishing, 2000. ISBN 0-7643-1204-9.
- Rogers, Mike. VTOL: Military Research Aircraft. New York: Orion Books, 1989. ISBN 0-517-57684-8.
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