AirShip Endurance VTOL UAV and Solar Turbine Clean Tech Propulsion

• US 20140103158A1
• Filed: 10/12/2012
• Published: 04/17/2014
• Est. Priority Date: 10/12/2012
• Status: Abandoned Application

• Current Assignee: Benjamin Lawrence Berry
• Original Assignee: Benjamin Lawrence Berry
• Inventors: Berry, Benjamin Lawrence
• Application Number:
  US13/650,508
• Publication Number:
  US 20140103158A1
• Time in Patent Office: Days
• US Class Current: 244/2
• CPC Class Codes: B60F 5/02 convertible into aircraft
• CPC Class Codes: B64C 29/0016 the lift during taking-off being created by free or ducted propellers or by blowers
• CPC Class Codes: B64C 29/0025 the propellers being fixed relative to the fuselage
• CPC Class Codes: B64C 29/0033 the propellers being tiltable relative to the fuselage
• CPC Class Codes: B64D 27/24 using steam or spring force jet aircraft B64D27/16
• CPC Class Codes: Y02T 50/40 Weight reduction
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

An aircraft with a wide fuselage having a longitudinal axis, a left and right forward swept wing mounted well back on the fuselage, a tail section extending from the aft portion of the fuselage, a first and second brushless ducted fan with air accelerator ring stationary and integrated into the left and right lateral fuselage, a third brushless ducted fan with integrated air accelerator ring rotatable mounted to the aft tail portion, a solar turbine based external solar film applied on the fuselage and wing surfaces and lateral fan regenerative drive that powers all ducted electric fans, that powers one internal-mounted central master impeller motor, that powers a brushless electric motor that spins three supercharger impellers via pulley chains to enable all three air accelerator rings with super compressed forced air thrust, that recharges ultracapacitors for aircraft propulsion of persistent flight endurance targeted for 30 to 90 days.

Claims

1. An aircraft comprising:

a fuselage having a longitudinal axis;

a left low aspect forward swept wing mounted well back on said fuselage;

a right low aspect forward swept wing mounted well back on said fuselage;

a tail section extending from a aft portion of said fuselage;

a first electric regenerative ducted fan with integrated air accelerator ring embedded stationary from aerial through anterior to said left fuselage;

a second electric regenerative ducted fan with integrated air accelerator ring embedded stationary from aerial through anterior to said right fuselage;

a third electric ducted fan with integrated air accelerator ring rotatable and mounted to the aft tail swivel cross bar, and

a solar turbine powered master impeller motor disposed centrally in said fuselage, said motor comprising an electric-drive impeller contained in a compression chamber having an axis of rotation oriented perpendicular to said longitudinal axis of said fuselage, and said motor powered by electricity from solar film (thin film) integrated on the entire upper and lower surface of said fuselage and exterior wings; and

said master impeller motor alternatively powered by electricity storage from internal rechargeable ultracapacitors mounted inside fuselage

a major air shaft leading from the said master impeller motor chamber to a narrowed minor air shaft that forces super compressed air thrust through the narrowed air shaft inner lining of each said lateral and aft ducted integrated air accelerator rings;

a belt-driven electric micro impeller supercharger motor forcing ingress and egress of super compressed accelerated air thrust through each said ducted integrated air accelerator ring, and

wherein said lateral left ducted fan comprises a differential operable connected between left and right counter rotating lateral fan blades;

wherein said lateral right ducted fan comprises a differential operable connected between right and left counter rotating fan blades;

wherein the most narrowed end of said major and minor air shafts is directly connected to said first lateral narrowed ducted air accelerator ring;

wherein the most narrowed end of said major and minor air shafts is directly connected to said second lateral narrowed ducted air accelerator ring;

wherein the most narrowed end of said major and minor air shafts is directly connected to said aft narrowed ducted air accelerator ring.

2. The aircraft of claim 1 wherein said solar turbine electric motor comprises a plurality of master impeller motor and micro supercharger impeller motors connected to said electric ducted fans with integrated air accelerator rings.

3. The aircraft of claim 2 wherein said plurality of motors comprises a first motor type and a second motor type.

4. The aircraft of claim 3 wherein said first motor type comprises a master electric impeller motor and said second motor type comprises three micro supercharger impeller motors.

5. The aircraft of claim 4 wherein said solar turbine electric motor has a first mode in which said electric motor drives said lateral and aft ducted fans with integrated air accelerator rings, and a second mode in which said solar turbine electric motor serves as a generator driven by said first mode and charges ultracapacitors electrically connected to said electric motor.

6. The aircraft of claim 5 wherein said solar turbine electric motor operates in said first mode during daylight take-offs, flight and landings;

and said solar turbine electric motor operates in said second mode during nighttime take-offs, flight and landings.

7. The aircraft of claim 1 wherein each of said lateral and aft ducted fans with integrated air accelerator rings comprises an aerodynamic lifting intake portion having a top portion that serves as air ingress (entrance), and wherein said bottom portion serves as an air egress (departure).

8. The aircraft of claim 1 wherein the fuselage and low aspect forward swept retractable wings are scaled larger to carry people and/or cargo that serve as a combination air transit with alternative turbo shaft engine propulsion and ground transit with in-wheel electric wheel drive.