Omega BS-12
| Omega BS-12 | |
|---|---|
| Role | Helicopter |
| National origin | Canada |
| Manufacturer | Omega Aircraft Corp, Allied Aero Industries, ADRC |
| Designer | Bernard W Sznycer |
| First flight | 29 October 1956 |
| Introduction | 1958 |
| Number built | at least 4 |
| Unit cost |
$7500 in 1958[1] |
| Developed from | Sznycer SG-VI-E (aka 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.[2]
Design & development
After qualified success with his Sznycer SG-VI-D and SG-VI-E single-engined helicopters, Bernard Sznycer expanded his concepts to produce a flying crane / utility helicopter, intended to be inexpensive to produce and relatively cheap to operate. Sznycer designed the BS-12 as a cargo or flying crane helicopter with optional passenger accommodation and licensed development and production to the Omega Aircraft Corp.[3] Powered by twin piston engines mounted horizontally on either side of the main gearbox the BS-12 was designed to be safe in an emergency for single-engined flight even at high gross weights. Accommodation in the flying crane version was for four, (later 5 in the BS-12D), including flight crew, which could be augmented by an underslung passenger cabin.
Operational history
The first example was tested in 1956. By 1960 the program was canceled.
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-FlB5 engines, two built (c/n 1002 & 1003).
- BS-12D-3
- The second BS-12D-1 powered by 2x supercharged Franklin 6AS-335 engines.[4]
- 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.
- 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
Specifications (BS-12)
Data from Popular Science
General characteristics
- Capacity: four
- Length: 11.2 m (36 ft 9 in)
- Height: 3.96 m (13 ft 0 in)
- Empty weight: 1,417 kg (3,125 lb)
- Gross weight: 1,905 kg (4,200 lb)
- Powerplant: 2 × Franklin 6AS-335 Piston, 160 kW (210 hp) each
- Main rotor diameter: 11.89 m (39 ft 0 in)
Performance
- Maximum speed: 138 km/h (86 mph; 75 kn)
- Cruise speed: 137 km/h; 74 kn (85 mph)
- Range: 250 km (155 mi; 135 nmi)
- Service ceiling: 3,450 m (11,319 ft)
- Rate of climb: 6.1 m/s (1,200 ft/min)
See also
- Aircraft of comparable role, configuration and era
References
Flight vol 47. 1958. Missing or empty |title= (help)