The new technology needed to design any size CC Heliplane has been flying on this prototype since September 1998. It includes (1) the ultra-high-inertia rotor, (2) the rotor-wing interface control system, (3) the high efficiency CC propeller system with a computerized prop controller and (4) the ultra-high-energy absorbing landing gear system.

Structure:

• Seamless molded composite
• Length - 22 feet 4 inches (nose to trailing edge of rudders)
• Height - 10 feet 6 inches (bottom of tail booms to top of rotor cap)
• Height with landing gear in taxi position - 11 ft. 2 in.

Cabin:

• Occupants - five (2 in front, 3 on rear bench seat)
• Windshield is ¼ -inch thick acrylic (bird strike resistant)
• Pressure differential - 10 lbs / sq inch (proof tested to 25 psi)
• Voice audio alarm system for flight safety

Wings:

• Span - 32 ft
• Area - 77 sq ft.
• Wing sections outboard of tail booms are removable
• Width of aircraft with wings removed - 8½ ft (necessary for highway transport by trailer)

*Tail Booms: Extend below the prop tip so prop is protected in a wheels-up landing.

Tail:

• Large tail volume for excellent directional stability and safety considerations under certain flight conditions.
• Stabilizer - 100% moveable. 2½ ft extensions outside of vertical stabilizers are removable for highway transport by trailer.

*Rotor (bearingless):

• Diameter - 43.5 ft. (10 ft addition added 01/06/00)
• Weight - 274 lbs, less than 11% of the aircraft's empty weight (includes 130 lbs L.E. weights and rotor hub and blade pitch horn)
• Carbon composite construction with twistable carbon spar
• **Airfoil is 7-in wide at the tip and 17-in wide at the root. Unique design for flight at mu>1
• Leading edge tip-weights - 65 lbs in each blade. Inertia from weights allows the aircraft @ 3500 lbs to take off vertically and clear a 50 ft. obstacle 75 ft. away. Weights are currently made from depleted uranium but in production will be made from sintering tungsten carbide.
• Maximum pre-rotation and flight speed - 425 RPM
• Minimum rotor speed in flight - approx 80 RPM (to be determined by flight-testing

*Prop (bearingless) (shown in high-speed cruise on 3-View AutoCAD drawing):

• Diameter - 96 inches (2-inches additional added 01/06/00)
• Weight - less than 30 lbs (includes pitch change mechanism)
• Carbon composite construction with twistable carbon spar
• Chord is 21-inches at the 25% radius and 8-inches at the 75% radius
• Thrust centerline is through the aircraft's average center of gravity for safety considerations

Engine - Corvette LS1 with 2 turbos in series - Projected turbo capacity:

• 600 HP for short duration from 0-30K ft altitude
• 300 HP at 45k ft altitude

*Landing Gear -- air over hydraulic:

• Main gear retracts into the tail booms.
• 18-inch stroke can absorb a 20 feet per second impact

Fuel -- 160 gal total:

• Fuselage - 60 gal
• Center wing section (under fuselage) - 50 gal
• Outboard wing sections - 25 gal each side

Cruise Speed Projected @ 300 HP:

• 200 MPH @ sea level
• 350 MPH @ 45,000 ft.

Range Projected: 2400 miles with 45 min reserve.

Empty Weight:

• Prototype - 2500 lbs.
• Production - 2200 lbs (estimated)

Gross Weight:

• VTOL - 4200 lbs.
• STOL - 5000 lbs.

Notes (asterisks):

* Patented
** Patent Applied For