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Aircraft Designs Aircraft Designs Inc Company type - Private company Industry - Aerospace Founded - 1976 Defunct - 2012 Products - Gyroplanes / Motorgliders Owner - Martin Hollmann Aircraft Designs Inc was a US aircraft design and manufacturing firm founded in Monterey, California by Martin Hollmann in 1976. Apart from working on its own designs, the firm provides design and engineering analysis to other aerospace ventures. Hollmann and his company carried out much subcontract work, particularity in his areas of expertise, including aeroelasticity and structural analysis. He also designed a number of gyroplanes. The company was dissolved on 30 January 2012 and owner Martin Hollmann died 12 October 2012 of cancer. Aircraft Summary of aircraft built by Aircraft Designs Model name - First flight - Number built - Type ADI Sportster - 1974 - _ - Single-engine two-seat gyroplane plans ADI Condor - 1981 - _ - Single-engine, twin boom, two-seat motorglider ADI Bumble Bee - 1983 - _ - Single-engine single-seat gyroplane ADI Stallion - 1994 - _ - Single-engine six-seat touring light aircraft ADI Bumble Bee ADI Bumble Bee Role - Ultralight autogyro Manufacturer - Aircraft Designs Inc Designer - Martin Hollmann First flight - 1983 Status - Plans available The ADI Bumble Bee (sometimes Hollmann Bumble Bee) is an ultralight gyrocopter marketed by Aircraft Designs Inc (ADI). It was the first of its kind when it flew in 1983 and is still available in plans form for homebuilding. It was designed by Martin Hollmann after a back injury (sustained in the crash of the ADI Condor) prevented him from flying his previous design (the ADI Sportster) on account of not being able to lift the rotor assembly. Design and development The Bumble Bee is a simple and lightweight design that can be built to comply with the US FAR 103 Ultralight Vehicles rules, including the category's maximum empty weight of 254 lb (115 kg). The aircraft has a standard empty weight of 253 lb (115 kg). The aircraft consists of an open frame based on a keel tube, which supports the nose wheel at the front and the tail at the back. The pilot's seat, the engine and rotor assembly are bolted to the same keel tube. A control stick cyclically controls rotor pitch angle. The powerplant specified is a 40 hp (30 kW), twin-cylinder, two-stroke, air-cooled, single ignition Rotax 447 mounted in pusher configuration. The 38.5 hp (29 kW) Kawasaki 440 engine has also been used. The landing gear is of tricycle configuration, uses plastic-spoked wheels to reduce weight and does not include suspension. A horizontal tailplane maintains the aircraft pitch angle in flight and a large fin and rudder is provided. The main rotor system is of low-inertia and requires pilot skill to manage energy on landing. The aircraft plans cost US$160 in 2001. Construction time is estimated as 400 hours, much of which is consumed fabricating the composite rotor blades. Specifications (ADI Bumble Bee) (Data from Bumble Bee Performance and Stress Analysis) General characteristics Crew: 1 Length: 10 ft (3.0 m) Height: 7 ft 6 in (2.29 m) Empty weight: 213 lb (97 kg) Gross weight: 500 lb (227 kg) Powerplant: 1 × Rotax 447 2-cylinder air-cooled 2-stroke in-line piston engine, 40 hp (30 kW) Main rotor diameter: 23 ft (7.0 m) Propellers: 2-bladed fixed-pitch propeller Performance Maximum speed: 49 kn (56 mph, 91 km/h) Range: 56 nmi (64 mi, 104 km) Service ceiling: 16,000 ft (4,900 m) Rate of climb: 1,500 ft/min (7.6 m/s) Disk loading: 1.2 lb/sq ft (5.9 kg/m2) Power/mass: 0.08 hp/lb (0.13 kW/kg) ADI Condor Condor Role - Motor glider National origin - United States Manufacturer - ADI First flight - 1981 Number built - 1 The ADI Condor was a motor glider of unusual configuration built in the United States in 1981. While most motor gliders follow traditional sailplane layout, the Condor was of twin-boom configuration, with twin, inwardly canted tail fins joined at their tips by a common horizontal stabilizer. A pusher propeller driven by a converted Volkswagen engine was mounted at the rear of the central nacelle that seated the pilot and passenger in tandem. Construction throughout was of composite materials. The single example of the aircraft was destroyed in a crash in late 1982 after an engine failure. Specifications General characteristics Crew: One pilot Capacity: 1 passenger Wing area: 130 sq ft (12.1 m2) Powerplant: 1 × converted Volkswagen automotive engine, 65 hp (48 kW) Performance Rate of climb: 1,000 ft/min (5.1 m/s) Inline landing gear with on-wingtip resting is typical of sailplanes ADI Sportster Sportster Role - Autogyro Manufacturer - Aircraft Designs Designer - Martin Hollmann First flight - 1974 Number built - 65 (2005) The ADI Sportster is a two-seat gyroplane that has been marketed in plans form for homebuilding since 1974 by Aircraft Designs Inc. It was the first homebuilt gyrocopter design to be able to carry a passenger. The design first flew in 1974 and is built from bolted and riveted dural aluminium sheet. The rotor blades use an NACA 8H12 airfoil. Specifications (Data from Bertrand and Kitplanes) General characteristics Crew: one Capacity: one passenger Length: 12 ft 0 in (3.66 m) Height: 8 ft 0 in (2.44 m) Airfoil: NACA 8H12 Empty weight: 650 lb (295 kg) Gross weight: 1,100 lb (499 kg) Fuel capacity: 17 U.S. gallons (64 L; 14 imp gal) Powerplant: 1 × Lycoming O-320 4-cyl. air-cooled horizontally opposed piston engine, 150 hp (110 kW) Main rotor diameter: 28 ft 0 in (8.53 m) Main rotor area: 616 sq ft (57.2 m2) Performance Maximum speed: 90 mph (140 km/h, 78 kn) Cruise speed: 75 mph (121 km/h, 65 kn) Range: 150 mi (240 km, 130 nmi) Service ceiling: 12,000 ft (3,700 m) Rate of climb: 1,000 ft/min (5.1 m/s) Disk loading: 1.8 lb/sq ft (8.8 kg/m2) Power/mass: 0.14 hp/lb (0.22 kW/kg) Avionics - none ADI Stallion Stallion Role - Light utility aircraft National origin - United States of America Manufacturer - Aircraft Designs Inc Designer - Martin Hollmann First flight - July 1994 Number built - 7 (2007) The ADI Stallion is a US civil utility aircraft that first flew in July 1994. It is marketed in kit form for homebuilding by Aircraft Designs Inc. Design and development The Stallion is a single-engined high-winged monoplane, with wings based on those of the Lancair ES and a retractable tricycle landing gear from the Lancair IV. It has a steel-tube fuselage center section, with the remainder of the airframe of composite construction, and is designed to be powered by engines of 230-350 hp (172-261 kW). The recommended engine is the 300 hp (224 kW) Continental IO-550, but engines as powerful as the 750 hp (559 kW) Walter M601 have been used. It is available in two versions, the four seat ADI Stallion and the six-seat Super Stallion. Operational history Seven examples had been completed and flown by December 2007. Specifications (ADI Super Stallion - 350 hp engine) (Data from Jane's All The World's Aircraft 2003-2004) General characteristics Crew: one pilot Capacity: 5 passengers Length: 25 ft 0 in (7.62 m) Wingspan: 35 ft 0 in (10.67 m) Height: 9 ft 6 in (2.90 m) Wing area: 140.1 sq ft (13.00 m2) Aspect ratio: 8.8:1 Empty weight: 2,200 lb (998 kg) Max takeoff weight: 3,800 lb (1,784 kg) Powerplant: 1 × Continental TSIO-550-B air-cooled turbocharged flat-six engine, 350 hp (224 kW) Performance Maximum speed: 306 mph (493 km/h, 266 kn) Cruise speed: 295 mph (474 km/h, 256 kn) Stall speed: 71 mph (115 km/h, 62 kn) Range: 2,700 mi (4,345 km, 2,346 nmi) Service ceiling: 32,000 ft (9,750 m) Rate of climb: 2,600 ft/min (13.2 m/s) Related development Lancair IV |