A single-seat strap-on helicopter. Complete helicopter fitted with one five-USG fuel tank and flown in the ultralight category. Gen H-4 should take 30-40 hours to assemble. Kit: $36,000 in 2009.
Engine: 4 x GEN 125-F
Cruise 60 mph
Empty Weight 155 lbs
Gross Weight 420 lbs
Height 8′
Landing gear foot
Fuel capacity 5 USG
2009: Masumi Yanagisawa Engineering System Co.
5652-83 Sasaga Matsumoto-shi
Nagano-ken, Japan
Built the Gen H4 helicopter.
The sole Master Aircraft Greyhound of 1929 was registered N819H c/n B-1. The owner reported to CAA that the plane was “very unsatisfactory and never used again” and the registration expired on 1 September 1935.
Engine: Velie M-5
Wingspan: 32 ft 0 in
Length: 21 ft 0 in
315 Passaic St
Rochelle Park NJ.
USA
Circa 1929 built one aircraft
In 1988, the purely human powered Daedalus, a light-weight aircraft built by a team at the Massachusetts Institute of Technology, flew 71.5 miles from the Greek island of Crete to Santorini. The 69 lb craft, peadeled by a Greek Olympic cyclist, got caught in turbulence as it approached the beach at Santorini. It crashed in the sea a few yards from shore.
The Masquito Aircraft company was established in Belgium to produce the Masquito M80 ultralight helicopter and design started in November 1994.
Construction of the prototype began in December 1995, with the first flight (G-MASZ) in May 1996. 25 hours of test flying was completed by April 1997. P
The prototype was reconfigured as the M80 with a Jabiru engine and began ground trials in late 1997. The M80 was displayed unflown at the PFA International Air Rally at Cranfield in July 1999. By late 2002, over 120 hours of running time had been accumulated, including 20 within a limited hovering and slow flight envelope.
A CAA go-ahead for ground running of the fourth prototype (also marked G-MASZ) was given in mid-2001. This completed on 26 April 2002, confirming engine integrity.
The UK CAA requires Masquito aircraft to obtain a Design Organisation Approval before starting the flight-test programme for BCAR-VLII; this procedure started in 2003.
Conforms to FAR Pt 27 crashworthiness requirements. Two-blade, teetering main rotor and two-blade tail rotor; main rotor carbon composites blades with 9deg linear twist. Hiller servo rotor for increased stability in hover. Main rotor speed 690 rpm; 2kg lead weight in each tip to increase inertia and decrease rotor speed decay in event of engine failure. Tail rotor 3,200 rpm. Ventral fin offset 2degs. Composites “virtual hinge” main rotor head with elastomeric collective pitch thrust bearings. Prototype had Rotax gearbox for primary reduction and powerdrive toothed aramid fibre belts tor secondary reduction; production version employs toothed drivebelt, centrifugal clutch and flywheel as primary transmission, with flexible driveshaft for tail rotor.
Controls are conventional and manual, with Hiller servo rotor for cyclic pitch control. Primary structure of Ti3A12, 5V alloy; tailboom of 8.9cm carbon fibre tube. Main rotor blades have unidirectional composites spar with PVC foam trailing-edge core and bidirectional composites skin. Two fixed skids of 6061 alloy mounted on unidirectional carbon fibre supports.
Production aircraft to have an 89.5kW Masquito M2.6L four-cylinder, four-stroke air-cooled engine derated to 59.7kW at sea level, equipped with dual electronic ignition, electronic multipoint fuel injection, pressure and temperature compensation and dual variable timing ignition with max rpm limiter. Fuel capacity 67 litres of which 60 litres usable.
Production deliveries were due to begin in early 2004.
M58
Engine: 47.7kW Rotax 582
M58
Engine: Jabiru, 80 hp
Rotor span: 4.60 m
MAUW: 390 kg
Empty weight: 170 kg
Fuel capacity: 52 lt
Max speed: 180 kph
Cruise speed: 150 kph
Minimum speed: 0 kph
Climb rate: 9.6 m/s
Seats: 2
Fuel consumption: 12 lt/hr
Kit price (1998): £30,000
M80
Engine: Masquito M2.6L, 89.5kW
Main rotor diameter: 5.52m
Tail rotor diameter: 1.00m
Overall length, rotors turning: 6.22m
Fuselage length: 4.85m
Height overall: 2.25m
Max. take-off weight: 450kg
Empty weight, equipped: 230kg
Never-exceed speed: 180km/h
Max cruising speed: 148km/h
Max rate of climb at sea level: 335m/min
Hovering ceiling IGE: 2,000m
Range with max internal fuel: 600km
Endurance: 4h
Engine: Jabiru, 80 hp
Rotor span: 4.60 m
MAUW: 390 kg
Empty weight: 170 kg
Fuel capacity: 52 lt
Max speed: 180 kph
Cruise speed: 150 kph
Minimum speed: 0 kph
Climb rate: 9.6 m/s
Seats: 2
Fuel consumption: 12 lt/hr
Kit price (1998): £30,000
The Masquito Aircraft company was established in Belgium to produce the Masquito M80 ultralight helicopter. Developed and first flew in May 1996 the M58 two-seat ultralight helicopter. Improved M80 version with more powerful 80 hp Jabiru 2200 piston engine followed, intended for sale in assembled and certificated form, and as a kit of parts.
1998:
Reigersbaan 31
B-1760 Roosdaal
Belgium
Joe J Mason built the 4/5-scale replica of an Airco DH‑2, registered N32DH cn JM‑3, beginning in 1971, and first flying on 1 March 1975.
The single-place DH-2 was powered by a 90hp LeBlond 5F engine.
Woodland Hills CA.
USA
Built a DH 2 replica circa 1971.
Christavia was designed by Ron Mason around the classic lightplane lines of yesteryear, but with updated performance. It was specifically designed with missionary flying in mind. Mason describes it as a con-ventional, high-wing, strut-braced monoplane easily converted from wheels to floats or skis. All materials are standard off-the-shelf or easily obtainable. Industrial mild steel tubing in the fuselage keeps costs at a minimum; all parts can be made in a small workshop with just hand tools and a welder. No machining is required.
The Christavia was designed in 1982 as a mission field workhorse. Design requirements were short take-off and landing, small engine (low fuel consumption), low stall speed, good cruise speed and rate of climb, large cabin area, low maintenance and high safety factor. The Christavia is easy to fly, and the Iarge cabin makes long flights very comfortable.
Over 1000 sets of the plans have been sold for the MK1 (two place tandem), MK2 (two place side-by-side), and Christavia MK4 (four place).
For the MK-2 side by side seating version of the MK-1, increase all crossmembers in the fuselage by 35% for approximate materials requirements. No separate materials list is available for the MK-2.
Aircraft Spruce & Specialty Co. has acquired the design rights to the popular Christavia MK1, Christavia MK2, and Christavia MK4 homebuilt aircraft from the designer, Ron Mason of Elmwood Aviation in Canada.
Mk.1
Engine: Continental, 65 hp
HP range: 65-100
Height: 7 ft
Length: 21 ft
Wing span: 32.5 ft
Wing area: 146.2 sq.ft
Weight empty: 720 lbs
Gross: 1500 lbs
Fuel cap: 19 Imp.G
Speed max: 118 mph
Cruise: 105 mph
Range: 315 sm
Stall: 40 mph
ROC: 900 fpm
Take-off dist: 300 ft
Landing dist: 600 ft
Service ceiling: 14,000 ft
Seats: 2 tandem
Landing gear: tail wheel.
Mk.2
Seats: 2 Side by Side
Mk.4
Engine: Lycoming, 150 hp
Height: 7 ft
Length: 22 ft
Wing span: 35.5 ft
Wing area: 177.5 sq.ft
Weight empty: 1100 lbs
Gross: 2150 lbs
Fuel cap: 37 Imp.G
Speed max: 128 mph
Cruise: 118 mph
Range: 400 sm
Stall: 40 mph
ROC: 800 fpm
Take-off dist: 450 ft
Landing dist: 800 ft
Service ceiling: 19,000 ft
Seats: 4
Landing gear: tail wheel.
