SNECMA Tail Sitters/ Flying jeep
Société Nationale d'Etudes et de Constructions de Moteurs d'Aviation (SNECMA) (France)
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| pre Coléoptère designs |
Tail Sitter |
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| Early SNECMA tailsitter design |
Tail Sitter |
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Three concepts, studied in 1953, there used an auxiliary rocket engine for take-off.
These designs also all used retractable landing gear that ended in small skids.
Both sitting and prone pilot accommodations were considered.
The largest of these (which weighed over 50% more than the C.450) was calculated to fly beyond Mach 2,
with a 285 m/s climb rate at 2 km altitude, and be able to climb from 1 km to 15 km altitude in 35 s.
These projects were not pursued, however, because SNECMA did not have engines in the right thrust class for these aircraft.
Power:
Engine thrust:
Rocket thrust:
Length:
Height:
Empty Weight:
Maximum VTO Weight:
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AP.466 E
Atar 101 M.16
4500 kg
1550 kg
7.46 m
3 m diameter
2650 kg
5000 kg
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AP.466 G
Vulcain 104
7200 kg
2500 kg
9.65 m
3 m diameter
3880 kg
8000 kg
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AP.466 H
AP.25
9000 kg
3100 kg
9.4 m
3.13 m diameter
4650 kg
10,000 kg
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Project was proposed in July 1954 for strike missions.
- Power: Atar 101 G-32 engine with afterburner, but no ramjet (4200 kg thrust)
- Maximum Speed (sl): 0.92 Mach
- Maximum Speed (6 km): 0.96 Mach
- Maximum Altitude: 15 km (49,200 ft)
- Maximum rate of climb (sl): 250 m/s (820 ft/s)
- Range (sl): 300 km (162 nm)
- Range (6 km): 700 km (378 nm)
- Length: 8.9 m (29.2 ft)
- Height: 2.62 m (8.6 ft)
- Empty Weight: 2,060 kg (4542 lb)
- Take-off Weight: 3,760 kg (8989 lb)
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The study was begun in October 1957. It featured a wide, arced inlet over the "bottom" half of the fuselag
circumference and a prone accommodation for the pilot with a "periscope" for seeing forward; very small pop-out
canards were also planned for stability in transition. The concept had a smaller duct and longer fuselage for a reduced
supersonic drag - Mach 3 was expected.
The loss of the C.450 in July 1959 meant the end of SNECMA's Coléoptère studies.
- Engine thrust: 9,250 kg (20,393 lb)
- Maximum Speed (20 km): 3 Mach
- Maximum Range: 900 km (486 nm) in 19:24 min
- Wing span: 3.7 m (12.1 ft)
- Length: 11.02 m (36.2 ft)
- Height: 2.7 m (8.9 ft) diameter
- Empty Weight: 3,955 kg (8,719 lb)
- Take-off Weight: 8,000 kg (17,637 lb)
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Designd in February 1960 as a response to comments by the Chief of Staff about the application of a VTOL aircraft
for attack and reconnaissance for tactical use.
With two pods approximately mid-span on both sides of the cranked delta wing.
- Power: two SNECMA license-built Pratt & Whitney JTF10 (which received the military designation TF30) engines
- Engine thrust: 2 x 4,700 kg (2 x 10,360 lb)
- Maximum Take-off Weight: 7,520 kg (16,579 lb)
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| A.P.521 Pégase |
Tilt Propeller |
SNECMA designed a flying jeep called Pégase (Pegasus) around 1963, similar to the Breguet flying jeeps.
- Power: two 530 shp (395 kW) Turbomeca Astazou turbine engines
- Drive power: 48 hp Panhard engine was used to power the wheels for driving on the ground
- Propellers: four 3 m (9.8 m) diameter propellers
- Width: 7.6 m (24.9 ft) with extended prop.; under 2 m (6.6 ft) with stowed prop.
- Overall Length: 6.1 m (20 ft)
- Capacity: 4 seats
- 3-side-view
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