GEN H-4
| H-4 | |
|---|---|
| Role | Helicopter |
| National origin | Japan |
| Manufacturer | GEN Corporation |
| Status | Production suspended (2012) |
| Number built | Prototypes only |
| Unit cost |
US$ 59,500 (2011) |
The GEN H-4 is a Japanese helicopter under development by GEN Corporation of Nagano. The aircraft is intended to be supplied as a kit for amateur construction.[1]
Design and development
The H-4 was designed to comply with the US FAR 103 Ultralight Vehicles rules, including the category's maximum empty weight of 115 kg (254 lb). The aircraft has a standard empty weight of 70 kg (154 lb). It features two contra-rotating main rotors, a single-seat open cockpit without a windshield, four-wheeled landing gear and four twin-cylinder, air-cooled, two-stroke, 10 hp (7 kW) GEN 125-F engines to provide operational redundancy since the aircraft cannot autorotate in the event of a power failure.[1]
The aircraft fuselage is a simple open frame with a seat mounted on it. Its two coaxial, contra-rotating two-bladed rotors have diameters of 4 m (13.1 ft). The main rotors are both of fixed pitch design, with no articulation in any axis. Steering is accomplished by pivoting the rotor head on a gimbal using a control handle, in a similar manner to a weight shift hang glider. Climb and descent is controlled by increasing and decreasing the throttle. The aircraft lacks a tail rotor as the coaxial, contra-rotating main rotors produce zero net torque. Yawing motion is produced and controlled by electronic gyroscopically-controlled differential electric braking of the main rotors. With its empty weight of 70 kg (154 lb) and a gross weight of 220 kg (485 lb) the H-4 has a useful load of 150 kg (331 lb). With full fuel of 19 litres (4.2 imp gal; 5.0 US gal) the payload is 136 kg (300 lb).[1]
The company indicated that it had suspended production plans by 2012 due to lack of dealers outside Japan and put the cost of a single H-4 at JPY 7,500,000.00 (about US$80,887.59 in 2013). The company stated that it could build the aircraft economically only in lots of ten and at a discounted rate only in lots of one hundred. To facilitate future production the company indicated that it was "looking for sponsors, investors and partners".[2]
Variants
- H-4
- Initial model powered by four twin-cylinder, air-cooled, two-stroke, 10 hp (7 kW) GEN 125-F engines[1][2]
- H-4E
- Electrically-powered model under development[2]
- H-4R
- Remote-control model under development[2]
Accidents
On 29 June 2000, the prototype H-4, registered JX0076, was on a test flight at the company plant in Matsumoto-City, Nagano. The pilot was hovering, when the H-4 was hit by a wind gust and contacted the building, 40 m (131 ft) to northwest and then impacted the ground. The pilot was injured and the airframe damaged.[3][4]
Specifications (H-4)
Data from Bayerl[1]
General characteristics
- Crew: one
- Empty weight: 70 kg (154 lb)
- Gross weight: 220 kg (485 lb)
- Fuel capacity: 19 litres (4.2 imp gal; 5.0 US gal)
- Powerplant: 4 × GEN 125-F two cylinder, air-cooled, two stroke engines, 7.5 kW (10 hp) each
- Main rotor diameter: × 4 m (13 ft 1 in)
Performance
- Maximum speed: 200 km/h (124 mph; 108 kn)
- Cruise speed: 100 km/h (62 mph; 54 kn)
- Rate of climb: 4 m/s (790 ft/min)
References
- 1 2 3 4 5 Bayerl, Robby; Martin Berkemeier; et al: World Directory of Leisure Aviation 2011-12, page 191. WDLA UK, Lancaster UK, 2011. ISSN 1368-485X
- 1 2 3 4 GEN Corporation (2013). "GEN H-4". Retrieved 3 February 2013.
- ↑ Aviation Accident Report (Japanese)
- ↑ List of aviation accidents/incidents occurred in Japan 2000 (Japanese)