The R-22 is a single-engined helicopter with a semi-rigid two-bladed main rotor and a two-bladed tail rotor. The main rotor provides a teetering hinge and two coning hinges. The tail rotor provides only a teetering hinge.
The normal production variant has skid landing gear. The Mariner version provided floats. Wheeled gear is not available.
The basic structure is welded chromoly steel tubing. The forward fuselage is made of fiberglass and aluminum with a Plexiglas canopy. The tailcone, vertical and horizontal stabilizers are aluminum. It has an enclosed cabin with side-by-side seating for a pilot and passenger. The doors may be removed for flight, and are often done so for photographic flights, interior cooling in high temperatures, or a 10.4 lb weight saving.
The first version was produced as the R22, followed by the R22 HP, R22 Alpha, R22 Beta and R22 Beta II. Superficially, the aircraft appear similar. The R22 HP was fitted with a 160 bhp Lycoming 0-320-B2C engine, an increase of 10 bhp (7.5 kW) over the original R22. The landing skid assembly on the R22 Alpha was modified by extending the rear struts, giving it a slightly nose-down attitude on the ground and better matching its attitude in a low altitude hover with two people onboard. The R22 Beta added an engine speed governor (optional), rotor brake and auxiliary fuel tank (optional). The battery was moved from below the instrument cluster to the engine compartment for better balance. It has been offered as an instrument trainer version, with optional fixed floats as the R22 Mariner, and other special configurations for police work, electronic news gathering, and so on. The R22 Beta II added a Lycoming 0-360 engine, remade of lightweight materials and derated for sealevel operation. It allows greater altitudes for hovering in and out of ground effect (HIGE/HOGE). The R22 Beta II also made the engine speed governor standard and included a "carb heat assist" which correlates adding carb heat with decrease in collective control. Only the basic skid style is currently being sold. The R44 is available as the Clipper with floats, and as police and electronics news configurations.
Data from Robinson R22 Pilot's Operating Handbook. Current versions of the R22 vary slightly.
Length: 28 ft 8 in (8.7 m)
Rotor diameter: 25 ft 2 in (7.7 m)
Height: 8 ft 11 in (2.7 m)
Disc area: 497 ft² (46.2 m²)
Empty weight: 796 lb (389 kg)
Loaded weight: 920 lb (417 kg)
Max. takeoff weight: 1,370 lb (635 kg)
Powerplant: 1 × Lycoming O-320-A2B or -A2C flat 4 piston engine, 124 hp (93 kW)
Main tank total capacity: 19.8 US gallons (75 liters)
Main tank usable capacity: 19.2 US gallons (73 liters)
Optional aux tank total capacity: 10.9 US gallons (41 liters)
Optional aux tank usable capacity: 10.5 US gallons (40 liters)
Never exceed speed: 117 mph, 189 km/h, 102 kts
Cruise speed: 110 mph, 177 km/h, 96 kts
Range: 240 mi (386 km)
Service ceiling: 14,000 ft (4,267 m)
Rate of climb: 1,200 ft/min (6.1 m/s)
Disc loading: 2.61 lb/ft² (13.7 kg/m²)
Power/mass: 0.095 hp/lb (0.147 kW/kg)
Endurance: approx. 2 hours, with 30-minute reserve
In 1955, Hughes Tool Company's Aircraft Division (later Hughes Helicopters) carried out a market survey which showed that there was a demand for a low-cost, lightweight two-seat helicopter. The division began building the Model 269 in September 1955. The prototype flew on 2 October 1956, but it wasn't until 1960 that the decision was made to develop the helicopter for production.
On 9 April 1959, the 269 received certification from the Federal Aviation Administration (FAA) and Hughes continued to concentrate on civil production. With some design changes, deliveries of the Model 269A version began in 1961. By mid-1963 about 20 aircraft were being produced a month and by the spring of 1964, 314 had been built. Hughes had successfully captured a large portion of the civilian helicopter market with an aircraft that would prove itself popular in agriculture, police work and other duties.
In 1964, Hughes introduced the slightly-larger three-seat Model 269B which it marketed as the Hughes 300. That same year, the Hughes 269 set an endurance record of 101 hours. To set the record, two pilots took turns piloting the aircraft and hovered in ground-effect for fueling. To ensure no cheating, eggs were affixed to the bottom of the skid gear to register any record-ending landing.
The Hughes 300 was followed in 1969 by the improved Hughes 300C (sometimes 269C), which first flew on 6 March 1969 and received FAA certification in May 1970. This new model introduced a more powerful 190 hp (140 kW) Lycoming HIO-360-D1A engine and increased diameter rotor, giving a payload increase of 45%, plus overall performance improvements. It was this model that Schweizer began building under license from Hughes in 1983.
In 1986, Schweizer acquired all rights to the helicopter from McDonnell Douglas, which had purchased Hughes Helicopters in 1984. After Schweizer acquired the FAA Type Certificate, the helicopter was known for a short time as the Schweizer-Hughes 300C and then simply, the Schweizer 300C. The basic design remained unchanged over the years, despite Schweizer making over 250 minor improvements.
Between Hughes and Schweizer, and including foreign-licensed production civil and military training aircraft, nearly 3,000 units of the Model 269/300 have been built and flown over the last 50 years. Schweizer continued to develop the Model 300 by adding a turbine and redesigning the body to create the Schweizer 330. Further developing the dynamic components to take greater advantage of the power of the turbine engine led to the development of the Schweizer S-333.
Schweizer was purchased on August 26, 2004, by Sikorsky Aircraft. The Schweizer 300 models fill a gap in the Sikorsky helicopter line, which is known for its medium and heavy utility and cargo helicopters.
Specifications (Schweizer 300C)
Data from International Directiory of Civil Aircraft
Crew: 1 pilot
Capacity: 2 passengers
Payload: 950 lb (431 kg)
Length: 30 ft 10 in (9.4 m)
Rotor diameter: 26 ft 10 in (8.2 m)
Height: 8 ft 9 in (2.7 m)
Disc area: 565 ft2 (52.8 m2)
Empty weight: 1100 lb (499 kg)
Loaded weight: 2050 lb (930 kg)
Max. takeoff weight: 2050 lb (930 kg)
Powerplant: 1 × Textron Lycoming HIO-360-D1A 4 cylinder, horizontally opposed, 190 hp (141 kW)
Maximum speed: 95 kts (109 mph, 176 km/h)
Cruise speed: 86 kts (99 mph, 159 km/h)
Range: 195 nm (204 miles)
Rate of climb: 750 ft/min (3.82 m/s)
Enstrom’s piston-powered “Falcon” F-28F and “Shark” 280FX are nicknamed for their sleek aerodynamic styling. However, with power, aggressiveness and superior handling agility, the same could describe each aircraft’s overall performance. Add Enstrom’s reputation for safety, value and low maintenance costs, and you’ll discover why we set the standard in the light helicopter market.
Both the Falcon and Shark models deliver sports car handling to the piston-powered helicopter segment with excellent performance, an enviable safety record and low direct operating costs. The turbo-charged power plant provides excellent high altitude performance. Stability and safety are delivered through our high inertia, fully articulated rotor system, which provides an unusually smooth ride and exceptional autorotative capabilities. Our unblocked tail rotor provides exceptional yaw control in the windiest conditions. Plus, comfort is king in our spacious cabin with NASA inspired seating.
The Falcon and Shark features include:
Roomy cabin for 2-3 people
Custom paint designs with unlimited color schemes
Powerful, turbo charged, Textron Lycoming HIO-360-F1AD engine
240º pilot visibility with chin and overhead windows
High skids allow for police, medical and military equipment
Low maintenance with excellent parts availability
High-inertia rotor system greatly benefits auto rotation capability
Unblocked tail rotor provides excellent control in high winds from any angle
Excellent Hot and High Perfomance
Enstrom Helicopters have made their unique mark all over the world–offering safety, value and reliability for military pilot training, speed and agility for law enforcement and emergency medical use, and workhorse capabilities for the commercial and agriculture markets. In addition to this functionality, Enstrom builds a fun helicopter to fly for the private pilot. All Enstroms are proudly made in the USA with domestic parts and labor.
PERFORMANCE (STANDARD DAY)
Gross Weight 2,600 lbs 1,179 kg 2,350 lbs 2,600 lbs
Empty Weight (Std. Equip.) 1,640 lbs 744 kg
Useful Load 960 lbs 435 kg Never Exceed Speed 97 kts / 112 mph 74 kts / 85 mph
Maximum Cruise Speed (TAS @ 3,000 ft.) 100 kts / 115 mph 75 kts / 87 mph
2 Interconnected Tanks 40 gal 151 lit
Service Ceiling 12,000 ft / 3,658 m 9,000 ft / 2,743 m
Lycoming HI0-360-F1AD Maximum Rate of Climb @ SL 1,450 fpm / 7.4 m/sec 1,150 fpm / 5.8 m/sec
Power Available 225 shp 167 kw
In Ground Effect (IGE) 13,200 ft / 4,023 m 7,700 ft / 2347 m
Out of Ground Effect (OGE) 8,700 ft / 2,652 m N/A
Range and Endurance (No Reserve)
Maximum Range @ 3,000 ft. 229 nm / 424 km N/A
Maximum Endurance @ 3,000 ft. 3.5 hrs N/A
The Cabri G2 is a two-seat light helicopter with a three-bladed fully articulated main rotor and a Fenestron-type tail rotor. It has a skid landing gear and side-by-side seating for a pilot and passenger. Powered by a 180 hp (134 kW) Lycoming O-360 piston engine derated to 145 hp (108 kW), it first flew in March 2005. Its development was preceded by a prototype Cabri G1, which flew for the first time in April 1992.
In 2006 the Cabri G2 set three world records in the sub-500 kg helicopter class. Altitude without a payload 6,658 m (21,844 ft); Time to climb to a height of 3000 m (9840 ft) in 6 min 42 secs, and Time to climb to a height of 6000 m (19680 ft) in 22 min 6 sec.
It was awarded an EASA Type Certificate in December 2007. The first production aircraft was delivered at the end of 2008 to Ixair (France). Two helicopters have been ordered by Eurocopter for basic training, the first of which was delivered in December 2009. The company has also signed a deal with Eurocopter to develop an unmanned variant.
Data from EASA Type Certificate Data Sheet
Crew: 2 (Removable controls for left seat)
Length: 6.31 m (20 ft 8 in)
Main rotor diameter: × 7.2 m (23 ft 7 in)
Width: 1.24 m (4 ft 1 in)
Height: 2.37 m (7 ft 9 in)
Gross weight: 700 kg (1543 lb)
Maximum speed: 185 km/h (115 mph)
Cruising speed: 166 km/h (104 mph)
Range: 700 km (380 Nautical miles)
Endurance: 5.8 hours
Service ceiling: 3963 m (13,000 ft)
In 1989 EliSport, who became Heli-Sport in 1997, bought the rights to the Cicare CH-6, a small single seat open cockpit helicopter designed in Argentina by Augusto Cicaré. It was developed by Josi and Claudio Barbero and, with the help of the sports car designer, Marcello Gandini who produced a new, enclosed, cabin, marketed from 1992 as the CH-7 Angel. Its commercial success led to a tandem two seat version with a stretched cabin and bigger engine named the CH-7 Kompress and, in 2005, a further refinement designated the CH-7 Kompress Charlie.
The piston engined CH-7 ultralight series use the traditional "penny-farthing" layout with two bladed main and tail rotors. The main rotor is formed from composites and is a teetering, semi-rigid design with 6° of twist. The tail rotor is aluminium. The pod and boom fuselage has a glass fibre cabin built on a steel tube frame, with a long transparent forward opening canopy. The steel frame also carries the engine, semi-exposed behind the accommodation and connected to the main rotor shaft by a belt drive. A slender aluminium boom, strengthened by a pair of long struts to the lower fuselage frame, carries both the tail rotor and swept fins. The upper fin is topped with a short horizontal tailplane, with small endplate fins, and the lower one ends with a tailskid. The CH-7 uses a simple aluminium skid undercarriage, which may be fitted with small wheels for ground handling or multi-tube inflatable floats for flying off water. In this last form the CH-7 is called the Mariner. The Kompress Charlie has faired, wide chord carbon fibre skid legs.
The Kompress and Kompress Charlie are sold in kit form for home assembly, the manufacturers quoting a 200-hour building time. A fast build kit, with more components pre-assembled, is claimed to need 85 hours.
The Kompress series may be fitted with a hook for lifting loads of up to 100 kg (220 lb), or fitted with spray bars for agricultural work.
Specifications (Kompress Charlie, European specification)
Data from Jane's All the World Aircraft 2010/11
Length: 7.05 m (23 ft 2 in) overall, rotors turning; fuselage length 5.31 m (17 ft 5 in)
Height: 2.35 m (7 ft 9 in)
Empty weight: 275 kg (606 lb)
Max takeoff weight: 450 kg (992 lb)
Fuel capacity: 60 L (15.8 US gal, 13.2 Imp gal) usable standard, further 19 L (5.0 US gal, 4.2 Imp gal) in optional auxiliary tank.
Powerplant: 1 × Rotax 914 , 84.6 kW (113.5 hp)
Main rotor diameter: 6.20 m (20 ft 4 in)
Cruising speed: 160 km/h (99 mph; 86 kn)
Never exceed speed: 192 km/h (119 mph; 104 kn)
Range: 480 km (298 mi; 259 nmi) with standard fuel load
Endurance: 3 hr
Service ceiling: 5,000 m (16,404 ft) service; hover ceiling out of ground effect is 2,500 m (8,200 ft)
The Mosquito is one of the worlds lightest manned Helicopters that has been designed and developed over the past 10 years to deliver performance, reliability and easy of flight. Ken Armstrong of Kit Planes Magazine said that the "Mosquito is convincing - it's as close as you can come to real flying with almost no means of support, and the view is at least as good as a bird". He also said that "Flying the refined Mosquito Ultralight was the most fun I've ever had with a Helicopter!".
The Mosquito frame is made up of Aircraft Grade 6061-T6 aluminum and utilities a simple triangulated structure with straight tubing throughout to maximize strength, reduce weight and simplify construction. The additional use of a Carbon Fiber tail boom and support struts adds to the Mosquito's structural rigidity and further improved its power to weight ratio.The Mosquito's tripod legs are equipped with small skid pads to help reduce lateral movement during engine run-up to lift off stage. Ground handling wheels are also available to easy ground transport.
The Mosquito is powered by Compact Radial Engine's - MZ202, 60-hp, a two cycle, two cylinder engine with the highest power to weight ratio on the market today. This engine employes Reed Induction which yields a very flat torque curve ensuring power is delivered constantly over the required operating range. The MZ202 also has a lower operating speed of 6000 rpm when compared to other engines with similar power range that typically operate at 6500 to 7000 rpm resulting in less stress on the engine and improving reliability.The complete engine package only weighs 69 pounds and comes with a 180-watt alternator that provides power to run the electrical system which also features and an electric start system.
The primary reduction is bolted directly to the engine. A centrifugal clutch on the engine crankshaft permits start up of the engine without the load of the rotor. Power is transmitted from the clutch to the driven pulley of the reduction through an HTD cog belt, one of the highest power to weight ratio power transmission methods available. The driven pulley houses the sprage clutch which permits the rotor to over speed the engine during auto-rotation.
Length: Frame 16 ft., Overall 20 ft. Width: 72 in., Height: 83 in.
Rotor Diameter: Main 18 ft., Tail 40 in.
Empty Weight: 254 lb.
Gross Weight: 530 lbs., Useful (Pilot) Load: 250 lbs.
Fuel Capacity: 5 US gallons (as required by FAA Part 103, Ultralight Regulations)
Fuel Flow at Cruise: Approximately 4.5 U.S. Gallons per hour
Flight Duration Time: Approx. 60 minutes depending on conditions, loading, speed, etc.
Engine: Compact Radial Engines MZ202, 2 cylinder, 2 stroke, rated 60 HP (45kW)
Electrical System: 12 volt DC battery, starter, 180 watt alternator
Rotor Speeds: Main 540 rpm, Tail 2500 rpm
Performance: Hover in ground effect: 8,000 ft. (estimated)
Hover out of ground effect: 6,500 ft. (estimated)
Max Speed: 70 MPH
“The A600 Talon is the first of a new generation of RotorWay machines, built on a tradition of delivering on our promises,” said CEO Grant Norwitz, as the machine went through its paces for the cameras early in the Arizona morning of the fifth of July. “With our new facilities, our new programs, and our commitment to establishing an atmosphere in which certification of future designs will be fulfilled, the Talon exemplifies the spirit of RotorWay: strong traditions and fresh thinking.”
The A600 Talon is a top-to-bottom redesign, incorporating many customer-initiated requests, advanced electronics, engineering, and convenience items. The cockpit is now all-glass, using the MGL Avionics system. The completely redesigned and tuned FADEC system now has a secondary FADEC as a clone of the primary. Any failure of the primary unit will be imperceptible to the engine informing the pilot on the MGL display. The 162’s primary drive chain is replaced by a heavy-duty cog belt for ease of maintenance and longevity.
The useful load is 535 pounds, including a 100-pound luggage compartment. Economy cruise is a practical 90mph and fast long-distance cruise has already been demonstrated at 100 plus, with the doors off! The landing gear is 10 inches wider, 10 inches longer, and 7” higher than its smaller predecessor the Exec 162. This enables improvements in strength and stability, while offering greater accessibility underneath for the optional accessory luggage pod.
Process controls and designs with the new Talon’s manufacture at Rotorway’s new factory, are specifically aimed at the company’s plan to develop and deliver a certified helicopter. The A600 Talon is to be built in the new facility, on the new line, under the new processes that are being set up and proven to enable the certified machine to follow as early as 2011 in the United States. These new processes, materials, and documentation on the experimental, owner-built A600 Talon are designed to mesh into the processes and controls to be used on the future certified machine. The result is that the Talon will be built to type certified standards, of certified materials and with all the processes and controls expected of a manufacturer with the pedigree of RotorWay – and yet will be sold at kit prices.
The RotorWay success story is the culmination of over 4 decades of perseverance, progress in design and engineering development. Today RotorWay continues to be driven by individuals that believe in the company's mission -- To provide the rotorcraft customer worldwide with a safe, affordable way to experience their dream of rotary wing flight.
Powerplant RI 600N / 147HP
Gross Weight 1500 lbs. (680 kg)
Empty Weight 965 lbs. (438 kg)
Equipped Useful Load 535 lbs. (243 kg)
Pilot and Passenger Load 450 lbs. (204 kg)
Fuel Capacity 17 U.S. Gallons (64 liters)
Rate of Climb 1000 fpm
Hover In Ground Effect (HIGE) 6000 ft
Hover Out Of Ground Effect (HOGE) 4000 ft
Service Ceiling 10,000 ft.
Max. Fuel Cruise 2 hrs.
Normal Cruise 100 mph (87 knots)
Max. IAS, Sea Level/Standard Day 115 mph (100 knots)
Main Rotor Diameter 25 ft. (7.6 meters)
Tail Rotor Diameter 50-1/4 in. (1.2 meters)
Length, Nose to Tail 22 ft. (6.7 meters)
Overall Length 29-1/2 ft. (9 meters)
Cabin Width 44 in. (1.1 meters)
Skid Width 72 in. (1.8 meters)
Height 103 in. (2.6 meters)
FEATURES & IMPROVEMENTS
Next Generation FADEC
Shaft Driven Tail Rotor
Cog Belt Drive with Hydraulic Tensioner
Glass Cockpit - HSI, CDI, GPS, TAWS, etc.
Electric Water Pump
Safer, Wider, Higher Landing Gear
External Battery Connection
MGL - Glass PFD, HSI, GPS, DG & More
Inertia Seat Belts
Fuel Tank Drain
Reinforced Tail Boom with Cherry Max Rivets
Low RPM Warning System
Lighter, More Powerful Battery
The AK1-3 Helicopter is a lightweight helicopter that has been designed and built for a wide range of practical purposes including:
· Surveillance, monitoring of borders, facilities and territories;
· search missions;
· geological exploration, aerial photography;
· pilot training;
· aerial spraying (crops);
· business and pleasure flights;
· aerial sports competitions.
The AK1-3 helicopter conforms to International Airworthiness Regulations (FAR, Part 27) for normal category rotorcraft and international noise abatement regulations. The AK1-3 is certified under The State Administration of Ukraine for Aviation Safety Oversight and bears a Type Certificate Number ТП 0008.
When empty, the helicopter weighs 390 kg. This allows it to be transportable by a small trailer attached to a car. The trailer serves as a mobile landing strip for the helicopter.
The AK1-3 Helicopter is designed according to the one-airscrew scheme with the rudder airscrew consisting of skid-equipped landing gear, a tubular chassis, power-plant, main reducer, main rotor and braced tail beam with a rudder reducer and plumage and a power floor on which the cabin is installed. The cabin is made of composite materials.
The cabin of the helicopter provides free accommodation for two members of the crew. The width of the cabin at shoulder level is 1200 mm (at helicopter R.22 - 1055 mm).
The large windows provide good visibility in all directions. The pilot seats are adjustable on the ground and are equipped with waistband and humeral seat belts.
The pilotage-navigating equipment of the helicopter allows for daytime flights in simple meteorological conditions according to the rules of visual flights. At the request of the customer, the system of onboard navigation GPS can be installed. The system of onboard registration of parameters of flight is in a stage of development.
The airscrew consists of three blades with elastic fastening blades. The blades are made of composite materials with a nonlinear construction.
The rudder airscrew consists of two blades with one general horizontal hinge. Blades of the rudder airscrew are made from composite materials.
In the helicopter, the power-plant on the basis of the piston internal-combustion engine with liquid cooling ЕJ-25 "Subaru" is installed. The engine uses automobile gasoline with fuel performance number 95.
Power from the engine is transmitted through a belt drive with overrunning clutch to a power shaft of the main reducer.
Main rotor diameter 6.84 m (22ft 5.5”)
Number of rotor blades 3 – composite material with -9.5° non liner twist
Rotor head type Bearing-less design using laminated steel torsion bars
Rotor tip speed 205 m/sec. (672 ft/sec)
Blade chord 0.17 m (6.7”)
Blade profile NACA 63012/63015 Rectangular shape
Disc area 36.745 ml (399.48 ftl)
Tail rotor diameter 1.28 m (4’ 2.4”)
Blade number 2
Blade chord 0.115 m (4.5”)
Blade profile NACA 63012
Blade tip speed 186.3 m/s (611ft/sec)
Engine type & make Piston, Fuel-injected, EJ-25 Subaru 2457cc
Layout Flat-four cylinder OHC 4 valves per cylinder
Engine power 115kw (156 hp)
Full power duty limitation Continuous
General dimensions All bolts sizes on airframe and engine are metric
Cabin width 1.722 m (5’ 7.8”)
Skid width 8.096 m (26’ 6.6”) tip of front rotor to tip of tail rotor
Total overall length 1.936 m (6’ 4.2”)
Height of rotor head above ground 2.270 m (7’ 5.4”)
Tail fin area 0.267 ml
Horizontal stabilizer area 0.15 ml
Gross weight (Passenger mode) 650 kg (1431 LB)
Dry weight 395 kg (869LB)
Empty weight (Oils, coolant, reserve fuel) 410 kg (902LB)
Fuel tank capacity 72L (19.1 US gallons) (53 kg)
Fuel type 95 octane unleaded petrol
Useful load @ 650 kg gross weight 240 kg (528 LB)
Maximum level speed 650 kg @ SL 180 kmh (112mph) (97knts)
Cruising speed 650 kg @ 75% power 157 kmh (97mph) (85knts)
Vne 650 kg @ SL 180 kmh (112mph) (97knts)
Vne @ SL (Doors removed) 150 kmh (93mph) (81knots)
Max rate of climb at 630 kg @ SL 9 m/s (1770 ft/min)
Service ceiling @ 650 kg 3000 m (9,850 ft)
Hover ceiling in-ground-effect @ 650kg 2200 m (7,000 ft)
Hover ceiling out of ground effect @ 650kg 1550 m (5,100 ft)
Min rate of decent in autorotation @ 650kg 9 m/s (1800ft/min) @ 85kmh (53mph) (46 knts)
Max endurance @ 45 knots 3.2 hours
Max range @ 65 knots (Best range speed) 350 km (200 SM)
Max range @ 85 knot cruise speed 270 km (160 SM)
CROP SPRAY VERSION
Gross weight 740 Kg (1630 LB)
Useful load @ 740 kg gross weight 367 kg (808 LB)
Maximum level speed 740 kg @ SL 135 kmh (84 mph) (73 knots)