“Dynali H3 EasyFlyer”的意思、由来-开放百科全书

The Dynali H3 EasyFlyer is a Belgian helicopter designed and produced by the Dynali of the Thines district of Nivelles. The aircraft is supplied complete and ready-to-fly-aircraft or as a kit for amateur construction.^[1]

Design and development

The H3 was designed for the flight training, utility and personal-use roles. It was designed to comply with the European Class 6 microlight helicopter rules, in particular the French Class 6 Microlight Category, at a gross weight of {{convert|450|kg|lb|0|abbr=on}}. It features a single main rotor and tail rotor, a two-seats-in side-by-side configuration enclosed cockpit with a bubble canopy, skid landing gear and a four-cylinder, liquid and air-cooled, four stroke {{convert|100|hp|kW|0|abbr=on}} Rotax 912ULS engine, a Dynali-developed fuel-injected {{convert|110|hp|kW|0|abbr=on}} conversion Rotax 912ULS-1 engine or a {{convert|115|hp|kW|0|abbr=on}} turbocharged Rotax 914 powerplant.^[1]^[2]

The aircraft's gross weight varies from {{convert|450|kg|lb|0|abbr=on}} for the microlight category, with heavier weights available depending on installed power in other national categories, such as light-sport aircraft. With the Rotax 912ULS engine, the gross weight is {{convert|500|kg|lb|0|abbr=on}}, {{convert|550|kg|lb|0|abbr=on}} with the Rotax 912ULS-1 and {{convert|600|kg|lb|0|abbr=on}} with the Rotax 914.^[1]^[2]

The aircraft fuselage frame is made from welded stainless steel tubing. Its two-bladed rotor has a diameter of {{convert|7.14|m|ft|1|abbr=on}} and a chord of {{convert|18.5|cm|in|1|abbr=on}}. With the Rotax 914 engine the aircraft has a typical empty weight of {{convert|290|kg|lb|0|abbr=on}} and a gross weight of {{convert|600|kg|lb|0|abbr=on}}, giving a useful load of {{convert|310|kg|lb|0|abbr=on}}. With full fuel of {{convert|60|l}} the payload for the pilot, passenger and baggage is {{convert|267|kg|lb|0|abbr=on}}.^[1]^[2]

Specifications (H3)

|genhide=
|crew=one
|capacity=one passenger
|length m=
|length ft=
|length in=
|length note=
|width m=
|width ft=
|width in=
|width note=
|height m=
|height ft=
|height in=
|height note=
|airfoil=
|empty weight kg=285
|empty weight lb=
|empty weight note=
|gross weight kg=500
|gross weight lb=
|gross weight note=in the LSA category
|fuel capacity={{convert|60|l}}
|more general=

|perfhide=
|max speed kmh=
|max speed mph=
|max speed kts=
|max speed note=
|cruise speed kmh=130
|cruise speed mph=
|cruise speed kts=
|cruise speed note=
|never exceed speed kmh=155
|never exceed speed mph=
|never exceed speed kts=
|never exceed speed note=
|range km=
|range miles=
|range nmi=
|range note=
|endurance=3 hours
|ceiling m=
|ceiling ft=10000
|ceiling note=
|g limits=
|roll rate=
|glide ratio=
|climb rate ms=
|climb rate ftmin=900
|climb rate note=
|time to altitude=
|disk loading kg/m2=12.5
|disk loading lb/sqft=
|disk loading note=
|fuel consumption kg/km=
|fuel consumption lb/mi=
|power/mass=
|thrust/weight=
|more performance=
|avionics=
}}

Design and development

Specifications (H3)

See also

References

External links