Omega BS-12

Omega BS-12
Role Helicopter
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)

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] It was one of the early twin engine designs to be developed, and had a unique pod-and-boom style design similar to the later Sikorsky S-60

The manufacturer went bankrupt before it entered full production, even though the prototypes were successfully completed with some order after being certified.

The design is noted for pioneering twin-engine utility helicopter design for a variety of commercial uses.[2]

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.[3][4] Omega's first design was a twin-engined flying crane / utility helicopter, intended to be inexpensive to produce and relatively cheap to operate.[3][5]

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.[3][6][7]

Operational history

The first example made its maiden flight on December 29, 1956.[3] The type was certified by the Federal Aviation Administration in April 1961.[3] 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.[8] Although Omega received orders for several BS-12s following certification, shortages of funds stopped production, and Omega entered into bankruptcy in July 1962.[9] 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.[10]

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.[11]
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.[12]
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.[8]
ARDC/Omega RP-400
Planned production version for ARDC. Powered by two 290 hp (220 kW) Lycoming IO-540s.[13]
ARDC/Omega TP-900
Proposed advanced derivate of RP-400, powered by three turboshaft engines.[14]

Specifications (BS-12D1)

Data from Jane's All the World's Aircraft 1961–62[3]

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

References

  1. ^ "Picture News: Whirlybird Flying Crane". Popular Science. June 1958. p. 94.
  2. ^ Publications, Alfred H. Saulniers Spinner. "Trivia: New Bedford makes helicopter history". New Bedford Standard-Times. Retrieved 2024-05-23.
  3. ^ a b c d e f Taylor 1961, p. 300
  4. ^ Gunston 2005, pp. 348, 448
  5. ^ Hawkes Aviation Week May 7, 1956, p. 50
  6. ^ Hawkes Aviation Week May 7, 1956, pp. 50–51
  7. ^ Bass Flying October 1961, pp. 32–33
  8. ^ a b Aviation Week June 12, 1961, pp. 123, 125
  9. ^ Aviation Week November 11, 1963, p. 108
  10. ^ Taylor 1967, p. 193
  11. ^ R.Simpson (1998). Airlife's Helicopter and Rotorcraft.
  12. ^ Aviation Week June 12, 1961, p. 123
  13. ^ Taylor 1967, pp. 193–194
  14. ^ Taylor 1969, pp. 243–244