Bell X-22

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The Bell X-22 was a 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 as well as the X-22 successor, the Bell XV-15. Another demand was that, while flying horizontally, a minimum speed of 525 km/h (283 knots; 326 mph) was to be attained.

Triple 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 to 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.

Contents 1 History 2 Specifications (X-22A) 2.1 Technical Data 3 External links 4 Related content

[edit] History

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.

Maiden flight of the prototype occurred on March 17th, 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 diminished maintenance, the prototype crashed on August 8th, 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 afterwards.

The second X-22 first flew on August 26th 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 cancelled. The required minimum 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. The craft is currently on display in the Niagara Aerospace Museum, New York.

Although the ducted fan propellers were considered usable, they were never utilized again on a US military aircraft.

[edit] Specifications (X-22A)

[edit] Technical Data

Attribute	Data
Year	1966
Manufacturer	Bell Helicopter
Span	11.96 m (rear wings) 7.01 m (front wings)
Length	12.07 m
Height	6.31 m
Propeller Diameter	2.13 m
Empty Weight	4763 kg
Take-Off Weight	8020 kg
Crew	2
Max. Speed	221 knots (410 km/h; 255 mph)
Range	445 mi (712 km)
Service Ceiling	27,800 ft (8,475 m)
Hovering Altitude with Wing In Ground	12,000 ft (3658 m)
Hovering Altitude without Wing In Ground	6,000 ft (1829 m)
Powerplant	4 General Electric-YT58-GE-8D turboshafts 932 kW (1267 hp) each

[edit] External links

• Bell X-22
• [1]

[edit] Related content

Related development:

Comparable aircraft: V-22

Designation sequence: X-19 - X-20 - X-21 - X-22 - X-23 - X-24 - X-25

See also: