ELECTRIC PROPULSION
1- ELECTRICAL POWER PLANT
BATTERY PACKS & RECHARGING STATION
Number & safe positioning of Battery Packs
Battery Recharging Device & Facilities
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TWO LIQUID HYDROGEN GENERATORS
Located on the outer part of each Engine support bulkhead
Liquid Hydrogen Cylindrical Tank in the perimeter of the craft
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AIRCRAFT POWER DISTRIBUTION
Vertical Lift opposite Inboard Rotating Crown Winglets
Horizontal Thrust Top Dual Propulsion Systems
Inboard Automated Avionics & Navigation systems,
Inner & Outer Lights, Comfort Air & safety Systems
Automated Sensors & Function Actuators
Inboard Robotic services & Ethical Hologram crew
2- INBOARD VERTICAL LIFT ROTATING CROWN WINGLETS
Take-off & Landing vertical Lift Power consists of DUAL OPPOSITE INBOARD ROTATING CROWN ROTORS set in motion by 16 inner and 22 outer Coil Magnets, each equally positioned in adjacent watertight spaces to the crown compartment and powered by Electric Induction Stators embedded into fixed circular Crown Magnetic Tracks.
Each of the two opposite rotating crown have 16 Inner and 22 outer winglets of various Length and Width, depending on a 2.5 ratio and specific to the Aircraft size considered.
Crown Winglets can also be phased a few degrees from the radial axis as necessary, to restrain the centrifugal force. The upper crown can also be used with a variable pitch if necessary.
3- VERTICAL LIFT COMPRESSED AIR MANEUVER SYSTEM
The Compressed Air Venturi Maneuver System is integrated with the vertical Lift rotating crown and consist of Directional Group Maneuver Air Baffle Quadrantal Actuators: Forward or Aft, Port or Starboard.
Each Quadrantal group consists of four Air Baffle Components that have rotating axes at their two ends and rotated individually by two actuators.
The advantage of the baffle triangular shape is to create when closed, a clean surface for flight and a watertight device with the hull bottom.
The actuators are kept in the neutral opened position during Take-Off or Landing and Stationary flight. The activation of a sensor control to forward, Aft, Right or Left will produce the closing action of Air Baffles of a Quadrantal group and induce a Motion of the aircraft in this chosen longitudinal Forward or Aft or lateral Port or Starboard direction
4- DUAL HORIZONTAL THRUST PROPULSION REQUIREMENTS
The Dual Electric Fan Propulsion Engines are fitted longitudinally and sideway to the Cabin, to provide horizontal Thrust during the intended voyage. They seat over vertical reinforced Port and Starboard side Bulkheads.
Each electric Fan consists of two pairs of Rotors each having 32 rotating winglets. These rotors are paired using opposite rotating direction so as to increase the output of thrust through their special Venturi tubes.
5- HORIZONTAL THRUST ENGINE VERTICAL DEFLECTORS
Twin Electric Fan Engines are fitted to provide the aircraft with an added Vertical thrust Power requirement with Compressed Air Deflectors, used to provide vertical lift during take-off & landing manoeuvers.
6- CONVENTIONAL SURFACE FLIGHT CONTROLS
Side ailerons and spoilers, and double flaps forward & aft Surface Controls are fitted over the Upper Hull section only. This is to maintain Buoyancy and Watertight integrity of an Amphibian aircraft. Dual Ailerons and one Spoiler on each lateral upper side and dual Flaps Forward and Aft in upper end.
The extension of Spoilers in the upward position at high speed, will help reduce the aircraft Velocity during Descent.
The Extension of Ailerons and Flaps in the upward position only, differ from those used on fuselage aircrafts. Ailerons are used for directional purposes only and Flaps for Climb or Descent.
The Right pair of Ailerons when lifted will Bank the aircraft to the Right for an alteration of Course to starboard and the Left pair of Ailerons when lifted will Bank the aircraft to the Left for an alteration of Course to Port.
The Forward pair of Flaps when lifted will trim the aircraft for Descent and the aft pair of Flaps when lifted will trim the aircraft to Climb.
The use of the Forward an Aft Flaps simultaneously at a safe Operation speed, will induce a stable Descent in Altitude.
7- VERTICAL SKID-KEEL STABILIZERS WITH RUDDER AND HYDROFOILS
The twin Vertical Skid-Keels relative dimensions are:
Height of each keel is about 1 quarter the maximum bulkiness of the Hull;
The longitudinal Length is about 2 third the aircraft diameter;
The transversal distance apart is about 1 third the aircraft diameter.
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The two structural skid-keels also act as Aircraft Vertical Stabilizers. Their inner side is framed with the strengthened transversal bulkhead connected to the horizontal Thrust Engines.
They are fitted with a rudder on each side, efficient during flight or when afloat over a body of water. The rudder length is same as the keel’s height and the rudder height is half its length.
The outer side of each skid-keel is fitted with a pair of large and small fixed Hydrofoils that provide a valuable lift when the craft lands or takes-off.
The bottom part of the Skid-Keel sabot is covered with a highly resistant material allowing the craft to land over an opened field.
The area contained in between the two keels covers over one third of the Amphibian hull area and when using the Forward and Aft quadrant Air Baffles in high compressed inward position, the compressed air actually creates an Air cushion Dynamic, making it to operate as an Hovercraft.
8- LANDING GEAR FIXED AND DIRECTIONAL PAIRS OF WHEELS
The Landing Gear consists of 2 pairs of wheels, a pair of fixed differential wheels aft and another pair of Directional wheels forward. They are spaced at a distance that is 1 quarter of the Aircraft’s diameter.
Each wheel has a vertical rod inserted into a telescopic hydraulic system. The aft wheels and the forward wheels operate by pairs and all together.
The forward two wheels are directional and are fitted with a mechanism that is used to direct the aircraft on the ground.