This is an experimental helicopter constructed by Mr Adam Mifka in Germany in 1985. He named it ‘Lena’ after his wife.
Registered D-HMIA c/n 1, it is on display at Schwenningen Int’l Aircraft Museum, Manfred Pflumm, Schwenningen, Germany.
This side by side two¬-seater version of the HM 81 Tomcat was announced at the finish of the 1981 and appeared early in 1982.
Engine: Cuyuna 430R, 30 hp at 5500 rpm.
Propeller diameter and pitch 54 x 36 inch, 1.37 x 0. 91 m.
V belt reduction, ratio 2.0/1.
Max static thrust 250 lb, 113 kg.
Power per unit area 0.17 hp/sq.ft, 1.8hp/sq.m.
Fuel capacity 5.0 US gal, 4.2 Imp gal, 18.9 litre.
Length overall 12.0 ft, 3.66 m.
Height overall 10.0ft, 3.05m.
Wing span 30.0ft, 9.14m.
Chord at root 4.0ft, 1.22 m.
Chord at tip 3.0 ft, 0.91 m.
Main wing dihedral 0 deg.
Main¬ wing sweep back 0 deg.
Canard span 8.0ft, 2.43m.
Canard chord 3.0ft, 0.91m.
Total wing area 175 sq.ft, 16.3sq.m.
Main wing area 125 sq.ft, 11.6 sq.m.
Canard area 25 sq.ft, 2.3 sq.m.
Total dihedral wing area 25 sq.ft, 2.3 sq.m.
Main wing aspect ratio 7.2/1.
Wheelbase 7.0ft, 2.13 m.
Nosewheel diameter overall 10 inch, 25 cm.
Main wheels diameter overall 10 inch, 25 cm.
Empty weight 245 lb, 111 kg.
Max take off weight 605 lb, 274kg.
Payload 360 lb, 163 kg.
Max wing loading 3.46 lb/sq.ft, 16.8kg/sq.m.
Max power loading 20.2 lb/hp, 9.1 kg/hp.
Load factors +5.0, 3.0 design.
Max level speed 60 mph, 97 kph.
Cruising speed 45mph, 72kph.
Stalling speed 24mph, 38kph.
Max climb rate at sea level 350 ft/min, 1.8 m/s.
Best glide ratio with power off 7/1.
Take off distance 180 ft, 55 m.
Single seat single engined high wing mono¬plane with additional dihedral wings; unconventional three axis control. main wing has unswept leading and trailing edges, and constant chord; no tall, canard wing. Pitch control by fully flying canard; yaw/roll control by control surfaces on dihedral wings; control inputs through stick for pitch/yaw/roll. Main wing braced from below by dihedral wings. Wing profile; double surface. Undercarriage has three wheels in tricycle formation; rubber suspension on main wheels. Push right go-right nosewheel steering independent from yaw control. No brakes. Aluminium tube framework, without pod. Engine mounted below main wing driving pusher propeller. Tubing in 6061T6 aluminium, anodized. Stainless steel cables. Dacron wing covering.
Robin Haynes, founder and president of the Waspair Corporation which originally produced the Tomcat, de¬signed this unique machine at the end of 1979. It only became the Tomcat after a succession of names, the first production models having been sold under the name The Baron.
At Oshkosh in 1981 the HM 81 won the EAA prize for the most outstanding new design. The aerodynamic configuration of this machine is very unusual and warrants some supplementary explanation. The Tomcat is made up of three lifting elements: the main wing (67% of the total lift), the two inclined structural wings angled at 45O and with 15O sweepback, (18% of the lift) and the canard (15% of the total lift). The main wing is fixed and devoid of control surfaces, while the inclined wings, Which he called dihedral wings, are two fixed surfaces carrying elevons, like a V tail. The canard angle of attack can be altered to control pitch, all control being by a single stick which acts as a mixer on the elevons and the canard.
At the beginning of 1982, Waspair Cor¬poration offered the standard version of the Tomcat fitted with the twin cylinder 430D 30hp engine and direct drive; with the 430R and 2/1 reduction drive, the machine was called the Tomcat Sport. However, by the end of 1982, the latter had become the standard version. Also appearing at the beginning of 1982 was a Tourer version for the heavier pilot with a heavy duty airframe and the Cuyuna 430R. It is this model on which the company is now concentrating and at the Sun ‘n’ Fun in Lakeland, in March 1983, the maker was marketing it as the standard version. In kit form it costs $4695 and pre built it costs an extra $1150.
Engine: Cuyuna 430R, 30 hp at 5500 rpm.
Propeller diameter and pitch 54 x 36 inch, 1.37 x 0. 91 m.
V belt reduction, ratio 2.0/1.
Max static thrust 250 lb, 113 kg.
Power per unit area 0.17 hp/sq.ft, 1.8hp/sq.m.
Fuel capacity 5.0 US gal, 4.2 Imp gal, 18.9 litre.
Length overall 12.0 ft, 3.66 m.
Height overall 10.0ft, 3.05m.
Wing span 30.0ft, 9.14m.
Chord at root 4.0ft, 1.22 m.
Chord at tip 3.0 ft, 0.91 m.
Main wing dihedral 0 deg.
Main¬ wing sweepback 0 deg.
Canard span 8.0ft, 2.43m.
Canard chord 3.0ft, 0.91m.
Total wing area 175 sq.ft, 16.3sq.m.
Main wing area 125 sq.ft, 11.6 sq.m.
Canard area 25 sq.ft, 2.3 sq.m.
Total dihedral wing area 25 sq.ft, 2.3 sq.m.
Main wing aspect ratio 7.2/1.
Wheelbase 7.0ft, 2.13 m.
Nosewheel diameter overall 10 inch, 25 cm.
Main wheels diameter overall 10 inch, 25 cm.
Optional floats, length 11.0 sq.ft, 3.35 m.
Optional skis, length 3.0 ft, 0.91 m.
Empty weight 235 lb, 107 kg.
Max take off weight 595 lb, 270 kg.
Payload 360 lb, 163 kg .
Max wing loading 3.40 lb/sq.ft, 16.6 kg/sq.m.
Max power loading 19.8 lb/hp, 9.0kg/hp.
Load factors +6.0, 4.0 design; +8.0, 6.0 ulti¬mate.
Max level speed 60 mph, 97 kph.
Never exceed speed 65 mph, 105 kph.
Max cruising speed 45 mph, 72 kph.
Economic cruising speed 40mph, 64kph.
Stalling speed 27 mph, 43 kph.
Max climb rate at sea level 800 ft/min, 4.1 m/s.
Min sink rate 250 ft/min at 30 mph, 1.3 m/s at 48 kph.
Best glide ratio with power off 8/1 at 30 mph, 48 kph.
Take off distance 90 ft, 27 m.
Landing distance 125 ft, 38 m.
Service ceiling 15,000 ft, 4570 m.
Range at average cruising speed 125 mile, 201 km.
1983-4: Midwest Microlites, 1351 W Second Street. Oconomowoc, Wisconsin 53066, USA.
Circa 1998
Cycle: 4 stroke
No cylinders: 2 rotor
Compression: 9.5
Displacement: 588 cc
Cooling: Air Liquid
Ignition: DCDI
Reduction: Mechanical Integral damper 2.968/1
Dimension: 720 x 410 x 480 mm
Weight: 53 kg
Max pwr: 100 hp
Max torque: 94
1998:
Hanger SE 38
Gloucestshire Airport
GL51 6SR
Staverton
UK
The company was founded by Diamond Aircraft Industries and partners. The products are reciprocating engines and Wankel engines. The Wankel aero-engines are developed from the MidWest AE series engines developed at Staverton by MidWest, a UK firm that was bought by Diamond.
It was in 2017 that China-based Wanfeng Aviation Industry acquired full ownership of the Austria-based Diamond Aircraft Group. Wanfeng’s acquisition also included Diamond’s sister company and diesel aerospace engine maker Austro Engine.
A 1934 glider.
Developments:
Shultz ABC
The Cubby is 75% of the original J-3 Piper cub. With modern materials and technology the performance has been improved, and the Cubby uses automotive fuel as opposed to AVGAS.
The Cubby can be registered as a three axis micro-light or a non type certified light aircraft. The Cubby was available in tri-gear or tail dragger. The 2009 Price was dependable on the choice of engine. The option to have the Cubby interchangeable between tri-gear and tail dragger was also available on request as an option.
The factory is up to CAA standards. All upgrade and changes requested by CAA has been done and communicated to all Cubby owners. All correspondence of changes and upgrades are posted to Cubby owners with a newsletter.
There were 26 flying in South Africa and 3 on order. The Cubby was available in kit form, fast built and basic kit, or as ready to fly or fully built but without engine, radio and instruments.
Cubby
Stall: 40 kt / 46 mph / 74 kmh
Cruise: 74 kt / 85 mph / 137 kmh
VNE: 113 kt / 130 mph / 209 kmh
Empty Weight: 260 kg / 573 lbs
MTOW Weight: 500 kg / 1102 lbs
Climb Ratio: 1200 ft/min / 6 m/s
Take-off distance (50ft obstacle): 660 ft / 200 m
Landing distance (50ft obstacle): 820 ft / 250 m
Tri-cubby
Stall: 45 kt / 52 mph / 83 kmh
Cruise: 100 kt / 115 mph / 185 kmh
VNE: 130 kt / 150 mph / 241 kmh
Empty Weight: 260 kg / 573 lbs
MTOW Weight: 500 kg / 1102 lbs
Climb Ratio: 1200 ft/min / 6 m/s
Glide Ratio: 10:1
Take-off distance (50ft obstacle): 330 ft / 100 m
Landing distance (50ft obstacle): 490 ft / 150 m
The initial Microturbo product offering was the “Noelle” starter turbine, which led to a number of starter / APUs such as the “Emeraude”, “Espandon”, and “Saphir”. The Emeraude led to the company’s first turbojet, the small and simple Eclair, intended for self-launching sailplanes.
Based on the gas generator section of the Microturbo Emeraude starter and APU for Concorde prototypes, the Eclair is an ultra-small single-shaft turbojet designed to power pilot-less drones and for use in sailplanes.
The engine is also capable of in-flight starting to provide powered flight in an emergency. Initial installation was in the Fauvel Aile Volante AV 45-01R single-seat tailless self-launching sailplane which first flew with the Eclair 012-01 in late 1967.
Height: 12.7 in / 312 mm
Width, including accessories: 19.9 in / 501 mm
Length overall: 23.9 in / 607 mm
Weight: 77 lb / 35 kg
TO pwr 47 000 rpm: 176 lb / 80 kg
Fuel at TO pwr: 198 lb/hr / 90 kg/hr
The Microturbo TRS 18 is a small, low thrust turbojet designed and built in France in the 1970s. It was installed on both manned and unmanned aircraft.
The TRS 18 was originally designed for self-launching motor gliders but was adapted to power conventional ultralight aircraft and unmanned vehicles (RPV). It was originally designed and developed by Sermel, a competitor company to Microturbo which the latter took over in 1971. It is a simple, low thrust, reverse flow single shaft engine with a centrifugal compressor and axial turbine. It is built in three modules: an intake section containing starter and lubrication systems; a centre section with compressor and turbine on ball bearings; and an aft section with the folded combustion chambers and tail-pipe.
Early microjets developed 200 lbs thrust, while the newer TRS 18-1 engine develops 325 lbs thrust with nearly identical in dimension & weight.
It gained its US Federal Aviation Administration type certificate E13CE on 25 May 1976.
Variants:
TRS 18-046
Production version, primarily intended for manned applications with full self start provision, oil lubrication and temperature and pressure transducers.
TRS 18-056
Cut down gas generator or core engine version, fuel lubricated and only 62% the weight of the 18-046 version but the same thrust; intended for RPVs.
TRS 18-075
Intended respectively for the Flight Refuelling ASAT target drone. Includes an engine driven alternator and fuel and oil lubrication pumps. Dry weight as 18-046. Take-off thrust increased to 1.15 kN (260 lb st) and maximum continuous thrust to 1.10 kN (247 lb st).
TRS 18-076
Intended for the Meteor-Mirach 100. Includes an engine driven alternator and fuel and oil lubrication pumps. Dry weight as 18-046. Take-off thrust increased to 1.15 kN (260 lb st) and maximum continuous thrust to 1.10 kN (247 lb st).
Applications:
Manned
Bede BD-5J
Caproni Vizzola A-21SJ
Chagnes Microstar (version of Rutan VariViggen)
EFF Prometheus 19
EFF Prometheus 12
Microjet 200
NASA AD-1 slew wing
Unmanned
Flight Refuelling ASAT
France-engins Mitsoubac
Meteor-Mirach 100
Specifications:
Microturbo TRS 18-1
Thrust: 325 lbs
Max Running Altitude: 30,000 ft.
Weight : 84.88 lbs.
Length : 27 in.
Diameter: 13 in.
Fuel Types: Jet A, JP4-JP5
Oil Types: MIL-L-23699
Fuel Consumption (Max Power): 283 lbs./hr.
TRS 18-046
Type: Single shaft centrifugal turbojet.
Length: 650 mm (25.59 in)
Diameter: 325 mm (12.80 in) wide × 350 mm (13.78 in) high.
Dry weight: 37 kg (81.6 lb) dry, basic, no jet pipe.
Compressor: Centifugal; one piece with diffuser and straightener vanes.
Combustors: Folded, with ten spill type burners.
Turbine: Axial.
Fuel type: Electric pump.
Oil system: Submerged pump in tank on front underside; filter and pressure transducer on upper side. Closed circuit with high pressure supply to rotor and gearbox bearings.
Maximum thrust: Take-off 1.10 kN (247 lb st). Maximum continuous 1.00 kN (225 lb st).
Specific fuel consumption: 35 mg/N/s (1.24 lb/h/lb st).
Maximum altitude: 9000 m
