The HM.7 was originally designed by the Instituto Nacional de Tecnica Aeronautica (I.N.T.A.) and was first produced in 1946.
The HM.7 is a four-seat touring monoplane powered by a 240 hp Argus As 10c engine with wing and tail assemblies of wood, the fuselage of welded steel tube with fabric covering. The enclosed cabin seats four with automobile type doors. Full blind flying equipment was fitted.
No production of the HM.7 was undertaken owing to the lack of a suitable nationally designed engine.
Engine: 240 hp Argus As 10c Wingspan: 33 ft 5.5 in Length: 25 ft 9 in Height: 7 ft Empty weight: 1540 lb Loaded weight: 2640 lb Max speed: 162 mph Cruise: 118 mph
The HM-5 derivative of the Huarte-Mendicoa family of light aircraft took the air in 1943. This aerobatic single-seat monoplane was basically a scaled-down version of the HM-1 powered by the very same engine, adapted for inverted flight. With the HM’s handling horrors untouched, less wing area and the same engine (160hp Hirth 506), only two were produced.
In 1950 José L. Aresti was designated to take part at the Fête Aérienne de Villacoublay aerobatic contest with one of these, however, in the end and he was called back.
In essence a floatplane variant of the HM.1. The two HM.3’s built were tested at the end of the 1940s. Certain problems soon appeared, mainly questionable float design and lack of power. The Spanish AF didn’t show any further interest in them and that was the end of it.
The HM-2 tandem two-seat cabin monoplane was designed by the Instituto Nacional de Tecnica Aeronautica (I.N.T.A.) and the prototype, built and flown by Aeronautica Industrial sa in 1945, was powered by a Hirth HM.506 engine.
Subsequent aircraft differ from the prototype in having a cut-down rear fuselage and the nationally-designed 150 hp E.N.M.A. Tigre G-IVB engine.
The HM-2 features retractable main undercarriage and wing and tail assemblies of wood, the fuselage of welded steel tube with fabric covering.
Engine: Hirth HM.506 Wingspan: 31 ft 8 in Length: 25 ft Empty weight: 1474 lb Loaded weight: 1980 lb Max speed: 156.5 mph Cruise: 140 mph
In 1974 Aeronautica Industrial SA (AISA) started construction of the prototype AISA-GN, which was an all-metal four-seat autogyro with a small stub wing, three-blade main rotor, twin booms and a fixed tricycle undercarriage. After a long development, the prototype was first flown on 20 July 1982, powered by a 225kW Lycoming IO-540-K-1A5 engine. The prototype was damaged in September 1982, and the project was then abandoned.
AISA GN Engine: 1 x Lycoming IO-540-K-1A5, 225kW Main rotor diameter: 12.8m Fuselage length: 6.5m Height: 3.2m Wingspan: 2.6m Take-off weight: 1200kg Empty weight: 708kg Max speed: 240km/h Range: 800km
In production since 1977, the Mustang is a weight shift trike, made from certified aviation hardware and with a wing tested to +5, 43g. Car toppable with only 10 minutes rigging time.
Mustang 1 Engine: JPX 425 (424 cc) 26 hp Wing span: 10 m Length: 3.88m Empty wt: 62 kg Max wt: 162 kg Max cruise: 65 kph Range: 220 km.
Side by side two seat single engined highwing monoplane with conventional three axis control. Wing has unswept leading and trailing edges, and constant chord; cruciform tail. Pitch control by elevator on tail; yaw control by fin mounted rudder; roll control by ailerons; control inputs through stick for pitch/roll and pedals for yaw. Wing braced from above by kingpost and cables, from below by cables; wing profile double surface. Undercarriage has three wheels in tricycle formation with additional tailskid; steel spring suspension on nosewheel and torsion bar suspension on main wheels. Push right go right nosewheel steering connected to yaw control. Optional brake on nosewheel. Aluminium tube framework, with optional pod. Engine mounted below wing driving tractor propeller. Designed by Philippe Tisserand, the two seat version made its first flight in December 1982. Apart from the engine position, very few changes were deemed necessary on this machine, which is directly descended from the single seater. First sales were in February 1983. Like its elder, it is of conventional three axis control with large control surfaces. The two seater retains the advantage of being foldable to small dimensions, so it can be car topped or carried on a trailer; folded it measures 16.5 x 1.8 x 1.8ft (5.50 x 0.50 x 0.50m). It is offered as standard with the Hirth 2701R engine of 43hp or the Rotax 503 of 46 hp with toothed belt reduction. A partial fairing of the cockpit area is offered as an option. Also, Aeronautic 2000 offers it in kit form complete, for export only, a move aimed particularly at the American continent. Composed of pre formed factory built units, cut and drilled, this kit requires 100h for assembly. The Baroudeur Biplace is fitted with dual controls as standard version.
Engine: Rotax 503, 46hp at 6500rpm Propeller diameter: 63 in, 1.6 m Reduction ratio: 2.5/1 Max static thrust: 287 lb, 130 kg Power per unit area: 0.30hp/sq.ft, 3.3hp/sq.m Fuel capacity main: 5.3 US gal, 4.4 Imp gal, 20.0 lt Fuel capacity reserve: 6.6 US gal, 5.5 Imp gal, 25.0 lt Length overall: 18.1 ft, 5.5 m Height overall: 8.2 ft, 2.5 m Wing span: 29.6 ft, 9.0 m Constant chord: 5.1ft, 1.55m Dihedral: 2 degs Sweepback: 0 degs Tailplane span: 7.9ft, 2.40 m Total wing area: 151 sq.ft, 14.0 sq.m Total aileron area: 16.2 sq.ft, 1.5 sq.m Rudder area: 7.5 sq.ft, 0.7 sq.m Fin area: 4.3 sq.ft, 0.4 sq.m Tailplane area: 16.2 sq.ft, 1.5 sq.m Total elevator area: 9.7 sq.ft, 0.9 sq.m Wing aspect ratio: 5.78/1 Wheel track: 4.5 ft, 1.35 m Wheelbase: 4.9 ft, 1. 45 m Nosewheel dia. Overall: 12 in, 30 cm Main wheels dia. Overall: 12 in, 30cm Empty weight: 287 lb, 130kg Max take off weight: 662 lb, 300kg Payload: 375 lb, 170kg Max wing loading: 4.38 lb/sq.ft, 21.4kgsq.m Max power loading: 14.4 lb/hp, 6.5kg/hp Load factors: +6, 2.5 design Max level speed: 62 mph, 100 kph Never exceed speed: 71 mph, 115 kph Max cruising speed: 56 mph, 90 kph Economic cruise: 50 mph, 80 kph Stalling speed: 24 mph, 40 kph Max climb rate SL: 600ft/min, 3.0m/s Min sink speed: 37 mph, 60 kph Min sink rate: 350 ft/min, 1.7 m/s Best glide ratio: 10/1 at 37 mph, 60 kph Take off distance: 165 ft, 50 m. Land¬ing distance: 165 ft, 50 m Service ceiling: 10,000ft, 3050 m Range at ave. cruise: 186 mile, 300 km
Single seat single engined high wing mono¬plane with conventional three axis control. Wing has unswept leading and trailing edges, and constant chord; cruciform tail. Pitch control by elevator on tail; yaw control by fully flying rudder; roll control by ailerons; control inputs through stick for pitch/roll and pedals for yaw. Wing braced from above by kingpost and cables, from below by cables; wing profile double surface. Undercarriage has three wheels in tricycle formation with additional tailskid; suspension on all wheels Push right go right nosewheel steering connected to yaw control. Optional brake on nosewheel. Aluminium tube/fabric framework, partially enclosed. Engine mounted below wing driving pusher propeller. Baroudeur prototype number 01 made its first flights in September 1981. The machine had been designed by a specialist team directed by Henri de Beaufort with Philippe Tisserand, and coupled a fully flying wing, free to move in three axes, with fixed tail surfaces. Next came serial 02, with wing warping and fully flying elevator. After various modifications this became prototype 03, eventually being succeeded by 04, which appeared with ailerons and a classic empennage. The structure of this was re used for the fifth, similar prototype, and fitted with a stick which was articulated from above the pilot. At the same time, 06 was built with a stick placed conventionally, between the pilot’s knees. These latter two were pre production aircraft. Designed for low power engines, the Baroudeur was initially fitted with the flat twin French JPX PUL425 engine, developing 26 hp at 4600 rpm with toothed belt reduction. It was offered with a Robin EC34PM, Robin EC44 or Hirth HL2701 RR179 engine. On sale since February 1982, the machine has acquired a reputation for robustness and ease of operation and rigging. It has also been designed with military uses in mind. Options include a cockpit, a special pod, a nosewheel brake and resin reinforced leading edges. The Baroudeur is transportable on a trailer or on a roof rack. Folded dimensions are 16.5 x 1. 8 x 1. 8 ft (5.0 x 0.5 x 0.5m).
Engine: Hirth HL2701 RR179, 40 hp at 3800 rpm Prop¬eller diameter: 47 in, 1.20m Reduction, ratio: 2.0/1 Max static thrust: 199 lb, 90 kg Power per unit area: 0.26hp/sq/ft, 2.9 hp/sq.m Fuel capacity main: 7.9 USG, 6.6 Imp gal, 30.0 lt Fuel capacity reserve: 6.6 USG, 5.5 Imp gal, 25.0 lt Length overall: 16.5 ft, 5.0 m Height overall: 8.2ft, 2.5m Wing span: 29.6ft, 9.0m Constant chord: 5.1ft, 1.55m Dihedral: 2 degs Sweepback: 0 degs Tailplane span: 7.9ft, 2.40 m Total wing area: 151 sq.ft, 14.0 sq.m Total aileron area: 16.2 sq.ft, 1.50 sq.m Rudder area: 7.5 sq.ft, 0.70 sq.m Tailplane area: 16.2 sq.ft, 1.50 sq.m Total elevator area: 9.7 sq.ft, 0.9 sq.m Wing aspect ratio: 5.78/1 Wheel track: 4.9 ft, 1.50 m Wheelbase: 5.3 ft, 1.6 m Nosewheel dia. Overall: 12 in, 30 cm Main wheels dia. Overall: 12 in, 30cm Empty weight: 220 lb, 100kg Max take off weight: 552 lb, 250kg Payload: 332 lb, 150kg Max wing loading: 3.65 lb/sq.ft, 17.9 kg/sq.m Max power loading: 13.8 lb/hp, 6.25 kg/hp Load factors: +6.0, 2.5 ultimate Max level speed: 63 mph, 100 kph Never exceed speed: 71 mph, 115 kph Max cruising speed: 56 mph, 90 kph Economic cruise: 50 mph, 80 kph Stalling speed: 22 mph, 35 kph Max climb rate SL: 690 ft/min, 3.5 m/s Min sink rate: 335 ft/min, 1.7 m/s Min sink speed: 37 mph, 60 kph Best glide: 10/1 at 37 mph, 60 kph Take off distance: 130 ft, 40 m Land¬ing distance: 130 ft, 40 m Service ceiling: 13,120 ft, 4000 m Range ave. cruise: 373 mile, 600 km
