AFDA 8M PROTOTYPE

PROTOTYPE AFDA 8 M PROJECT SEQUENCE PHASES

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PHASE ONE:
 

• ACTUAL ORGANIZATION SET-UP

Phase 1. 1 The various general arrangement designs and description Details are being laid down for six major AFDA types along with a descriptive document of each that will be available under the WEB site ‘www@universalflyingdisc.com’.

Phase 1.2 THE FLYING DISC is a variation of Flying Saucers, with new adapted propulsion concepts and designs. 

Our primary objective is to realize a prototype : 

TO PROVE THE FEASIBILITY OF THE VERTICAL LIFT ELECTRIC ROTATING CROWN WINGLET SYSTEM, INTEGRATED WITH A VENTURI COMPRESSED AIR SYSTEM FOR LIFT-OFF PROPULSION.

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      It requires particular knowledge and advice from field experts in electro and aerodynamic Technologies. In the setting-up and analysis of project requirements, we need to establish Contacts with Investors, Aerospace Industry and local suppliers of materials and Technical resources. 

 

• ORGANIZING A PROJECT TEAM WORK AND OBTAIN FINANCING ARE THE KEYS.

Phase 1.3 UNIVERSAL AFDA 8 M IS THE BASIC FEASIBLE ‘PROTOTYPE’ 
FOR AN 8 PASSENGER TYPE URBAN AIR-TAXI, OR
A SMALL AUTOMATED LOW ALTITUDE AIR PERSONAL LEISURE CRAFT.  
 

Phase 1.4 DESIGN OF GENERAL ARRANGEMENT PLANS FOR THE AFDA 8 M 
Aft and Port Side Views & Top and Bottom Views
 

Phase 1.5 CONCEPTION OF WEB SITE FOR PUBLIC REFERENCE:

www.universalflyingdisc.com 

 

• LIST OF CONSTRUCTION REQUIREMENTS

 

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• CONTACT WITH INVESTORS AND GOVERNMENTS 

       POTENTIAL FINANCIAL SUBSIDY PROVIDER 

 

• CONTACT WITH THE LOCAL AEROSPATIAL INDUSTRY √
   

Research of Enterprises in the Canadian Aerospace Industry
Universities, Aerospace Start-ups, Potential Collaborators, Material Suppliers

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• ORGANIZING THE PROJECT TEAM WORK

 

• LOCATION OF SUITABLE SPACE AREA IN SHERBROOKE: About 300 m² 

AIM: EXPERIMENTAL DUAL OPPOSITE ELECTRIC INBOARD ROTOR CROWN WINGLETS AND THEIR CIRCULAR STATOR
 

 

PROTOTYPE MOCKUP PLAN DIMENSIONS

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• PROTOTYPE CONSTRUCTION PLANS AND TIME SHEET

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• PROTOTYPE MODULAR CONSTRUCTION 

 

• TO ACCOMMODATE A WORKING STRUCTURE DIAMETER OF 5 METER DIAMETER, PROTOTYPE BASIC EXPERIMENTAL ELECTRIC ROTATING CROWN WINGLETS AND VENTORI AIR COMPRESSED MANEUVER SYSTEM.

 

BUILDING SPECIFICATIONS

   BATTERY PACKS WITH Li-ION BATTERIES

ELECTRICAL SUITABILITY OF ROTATING CROWNS PRINCIPLE AND MECHANICAL PERFORMANCE OF COMPRESSED AIR VENTURI MANEUVER SYSTEM.

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CONSTRUCTION MATERIALS, TOOLS AND TECHNICAL EQUIPMENT

 

 

 

PHASE TWO:

THE VERTICAL LIFT AND MANEUVER SYSTEM EXPERIMENTAL MOCKUP

Phase 2.1 THE EXPERIMENTAL MOCKUP OF PROTOTYPE ‘AFDA 8 M’. The Rotating crown Rotors, magnet circuits and Stators when completed are to be patented. The initial STRUCTURAL MOCKUP easy workable circular frame dimensions have a diameter of 6.12 m (20 Ft) and a height of 1.8 m (6 Ft) over the vertical skid Stabilizers.

Phase 2.2 THE ELECTRIC POWER PLANT consists of a given number of super power Li-Ion rechargeable battery packs with overheat protection and installed in the outer surrounding Propulsion Bay space, for weight distribution.

Phase 2.3 the project is to validate the AFDA trials for its electric and aerodynamic feasibility and get it patented by 2023. It consists of dual opposite electric INBOARD ROTOR CROWN WINGLETS and their circular stator, integrated with a compressed air VENTURI MANEUVER SYSTEM that provides vertical lift.

 

PHASE THREE:

THE HORIZONTAL POWER THRUST PROPULSION SYSTEM  

Phase 3.1 TWO THRUST ENGINE ELECTRIC TURBO-FANS
The horizontal thrust is achieved with twin powerful ELECTRIC TURBO-FANS capable for the aircraft to achieve a speed of at least 200 knots and EQUIPPED WITH VERTICAL DEFLECTOR that are enabled during vertical take-off and landing. 

Phase 3.2 THE FITTING OF VERTICAL DEFLECTORS from Twin Engine turbo-fans.

Phase 3.3 SUITABILITY OF TWO LIQUID H2 HIGH POWER GENERATORS
The POWER PLANT for the H2 turbo-Fans will consist of two Liquid HYDROGEN GENERATORS installed on either side of the Craft Cabin and behind the protective vertical wall and underneath the engines layout. The fitting and securing of the Li-Ion BATTERY PACKS in the outer surrounding Propulsion Bay upper space and the Fitting of the LIQUID HYDROGEN CYLINDRICALTANK 0.28 m diameter, 22.75 m (74.6 Ft) perimeter and a Volume of 1.4 m³ (1400 ℓ) 308 Gal Imp or 370 Gal US in the lower part of compartment. 

 

PHASE FOUR:

THE COMPLETION OF AIRCRAFT BASIC HULL INSTALLATION 

Phase 4.1 HULL COMPLETION WITH DOOR, CABIN AND FLIGHT CONTROLS 

Phase 4.1 Phase 4.2 THE WIRING AND PLUMBING through the duct systems. 

Phase 4.3 FITTING the UNDERCARRIAGE with 2 fixed telescopic wheels aft and two directional telescopic wheels forward.

Phase 4.4 Fitting of retractable independent WATER DAMPERS in the Forward, aft, port and starboard under hull of Air Maneuver Venturi Sections. Fitting of a Closure device on the air all-round Intake of the electric Rotating Crowns.

Phase 4.5 Welding of fixed AIRFOILS on the inner section of the vertical skid keels and flat skid ski pads on the underneath part, with water spreader in the forward sections for each of them.

Phase 4.6 THE FITTING OF THE FOUR MODULAR EDGE STRUCTURES of 1 m (3.28 Ft) by 3.7 m (12 Ft) on the surrounding 25 m (82 Ft) perimeter edge, containing the Conventional upper surface Flight controls, the de-icing system, a shock-absorber Belt and in the after part, a passenger boarding retractable ladder.  

Phase 4.7 Fixing the Cabin Canopy and the Boarding access Door.

Phase 4.8 Make the flooring, Finish the walls and Install a 1.5 ton deadweight and later the Passenger seats. 

 

PHASE FIVE:

THE AIRCRAFT INSTRUMENTS AND EQUIPMENT AUTOMATION SYSTEMS 

Phase 5.1 THE SAFE DOUBLING of navigation & satellite instruments, equipment & systems.

Phase 5.2 ALL OPERATION SYSTEMS to be linked with the ‘COMPUTER PILOT CONTROLLER’. This ‘Computer Pilot Controller’ (CPC) is automated by artificial intelligence, processing the data with the aid of dedicated algorithms simulating functions of human intelligence, regarding all aspects of:  1. Safety Procedures, 2. Geographical Position Coordinates, 3. Three axes Flight Controls for Stability, 4. Constant assessment of the Four Aerodynamic Forces and 5. The five basic True Navigation Parameters of Automatic Pilotage.

 

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• AIRCRAFT TRIALS IN ALL SITUATIONS AND CONDITIONS

4. FINAL RESULTS & FEASIBILITY REPORT

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PROTOTYPE CONSTRUCTION AND TRIALS

STATEMENTS OF TIME SHEET REQUIREMENTS AND POSSIBLE DELAYS

ESTIMATE OF EXPECTED RESULTS FROM THE UNIVERSAL AFDA 8 M PROTOTYPE

           
EXPERIMENTAL TRIALS OF ROTATING CROWNS AND RESULTS

EXPERIMENTAL TRIALS OF COMPRESSED AIR VENTURI MANEUVER SYSTEM

CONSTRUCTION OF THE OUTER SECTION PERIMETER OF FLYING DISC AIRCRAFT

TRIAL OF AIRCRAFT ON VARIOUS EVTOL MANEUVERS ON TERRAIN

TRIAL OF AIRCRAFT ON VARIOUS EVTOL MANEUVERS ON WATER

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ALL INFORMATION ON WORLD WIDE WEB TO EVTOL MANUFACTURERS AND MAJOR LEADERS IN THE AEROSPATIAL INDUSTRY