avia.wikisort.org - Helicopter

The Omega BS-12 was a utility helicopter with high ground clearance designed to carry loads behind the cabin at, or near, the center of gravity.[1]

Omega BS-12
Role	Helicopter Type of aircraft
National origin	United States of America
Manufacturer	Omega Aircraft Corp, Allied Aero Industries, ADRC
Designer	Bernard W Sznycer
First flight	December 29, 1956
Introduction	1958
Number built	at least 4
Developed from	Sznycer SG-VI-E (a.k.a. Sznycer-Gottlieb SG-VI)

Design & development

Bernard Sznycer, designer of the Sznycer SG-VI, the first helicopter certified in Canada, set up the Omega Aircraft Corporation, based at New Bedford, Massachusetts in December 1953, with himself as President and Chief Designer of the company.[2][3] Omega's first design was a twin-engined flying crane / utility helicopter, intended to be inexpensive to produce and relatively cheap to operate.[2][4]

The helicopter was of conventional layout, with a single four-bladed lift rotor and a two bladed anti-torque rotor. Its fuselage was of pod-and-boom layout, with a small enclosed crew cabin forward connected to an uncovered steel tube tail boom. Cargo, either a slung load or in a pre-loaded pod, could be carried between the crew cabin and the undercarriage mainwheels, while it was planned to also provide a pod to carry passengers. It was powered by twin piston engines mounted horizontally on either side of the main gearbox.[2][5][6]

Operational history

The first example made its maiden flight on December 29, 1956.[2] The type was certified by the Federal Aviation Administration in April 1961.[2] Omega planned to build an initial batch of 25 BS-12-D-1s, which were priced at $77,500, with production gradually building up from one per month.[7] Although Omega received orders for several BS-12s following certification, shortages of funds stopped production, and Omega entered into bankruptcy in July 1962.[8] Omega was purchased by the Aeronautical Research and Development Corporation of Boston, Massachusetts, with the intention of putting the BS-12 into production as the ADRC/Omega RD-400.[9]

Variants

BS-12

Initial prototype powered by 2x 210 hp (156.60 kW) Franklin 6AS-335 engines, one built (c/n 156).

BS-12B

Revised BS-12, one built (c/n 1001).

BS-12D-1

Five-seat passenger cabin, powered by 2x 260 hp (193.88 kW) Lycoming O-540-F1B5 engines, two built (c/n 1002 & 1003).

BS-12D-3

The second BS-12D-1 powered by 2x supercharged Franklin 6AS-335 engines.[10]

BS-12F

Projected turboshaft powered version, 2x Allison T63 or Boeing 502-W turbines.

BS-12J

Projected improved hot-high and single-engined performance, powered by 2x 290 hp (216.25 kW) Lycoming IO-540 engines.[11]

BS-14 Falcon

Projected emergency services version, with longer cabin, powered by 2x 260 hp (193.88 kW) Lycoming O-540 or 290 hp (216.25 kW) Lycoming IO-540 engines.

BS-17A Airliner

Projected enlarged passenger cabin version to have been powered by 3x Allison or Boeing turboshaft engines driving a 5-bladed main rotor.[7]

ARDC/Omega RP-400

Planned production version for ARDC. Powered by two 290 hp (220 kW) Lycoming IO-540s.[12]

ARDC/Omega TP-900

Proposed advanced derivate of RP-400, powered by three turboshaft engines.[13]

Specifications (BS-12D1)

Data from Jane's All the World's Aircraft 1961–62[2]

General characteristics

• Crew: 1
• Capacity: four passengers
• Length: 36 ft 0 in (10.97 m)
• Height: 13 ft 0 in (3.96 m)
• Empty weight: 3,450 lb (1,565 kg)
• Gross weight: 4,880 lb (2,214 kg)
• Powerplant: 2 × Lycoming O-540-F1B5 air-cooled six-cylinder horizontally-opposed, 235 hp (175 kW) each
• Main rotor diameter: 39 ft 0 in (11.89 m)
• Main rotor area: 1,194.6 sq ft (110.98 m²)

Performance

• Maximum speed: 95 mph (153 km/h, 83 kn) at sea level
• Cruise speed: 85 mph (137 km/h, 74 kn) (at 75% power)
• Service ceiling: 9,500 ft (2,900 m)
• Rate of climb: 1,200 ft/min (6.1 m/s)

See also

Aircraft of comparable role, configuration, and era

• Sikorsky S-64 Skycrane

References

---