초록 ▼

Flying Car, roadable aircraft, amphibian, multimode, multifunctional, composite versatile personal transport vehicle with twin, parallel fuselages, hulls, each with inflatable pontoons and/or wheels below and a cabin. Combined, aircraft, airplane, aeroplane, flying, air, aerial, airborne vehicle wit

Flying Car, roadable aircraft, amphibian, multimode, multifunctional, composite versatile personal transport vehicle with twin, parallel fuselages, hulls, each with inflatable pontoons and/or wheels below and a cabin. Combined, aircraft, airplane, aeroplane, flying, air, aerial, airborne vehicle with variable, folding wings which is convertible via automatic transformation to a land vehicle and to a sea vessel. Two wings are stored between the fuselages. They extend on a system of rails, pivots and counter-rotating, fuselage-mounted arms which then sink flush into the wings' undersides and lock for flight. Upon wing extension and retraction, controls for road transport and flight controls alternately emerge or are stowed inoperably, as needed. Engine power alternately drives a propeller for flight, wheels for road travel and a separate, submersible, marine propeller for water transport.

대표청구항 ▼

1. A roadable aircraft comprising: two parallel fuselages connected by a connecting beam between the two fuselages,wherein each fuselage comprising at least two road wheels mounted one behind the other longitudinally on their undersides of the fuselage; andat least two wings coupled to the fuselages

1. A roadable aircraft comprising: two parallel fuselages connected by a connecting beam between the two fuselages,wherein each fuselage comprising at least two road wheels mounted one behind the other longitudinally on their undersides of the fuselage; andat least two wings coupled to the fuselages;wherein the at least two wings coupled to the fuselage;wherein the at least two wings are deployable between a longitudinal, stored position and a lateral, spread position; and,wherein the at least teo wings are stored at least partially between the fuselage in the stored position. 2. The roadable aircraft of claim 1, comprising: at least one motor located between the two fuselages; andwherein the at least one motor powers at least two of the wheels, andwherein the at least one motor is connected via a drive shaft, running parallel with and between the two fuselages, to lateral drive shafts which drive the wheels. 3. The roadable aircraft of claim 2, wherein the at least one motor also powers at least one airscrew via a direct drive or belt-drive; and wherein the at least one airscrew comprises at least two blades. 4. The roadable aircraft of claim 1, comprising a cockpit in at least one of the two fuselages configured to receive a driver/pilot, and controls in the cockpit, the controls comprising a set of driving controls consisting of steering wheel, brake pedal and accelerator pedal and a set of flying controls comprising a joystick, and left and right rudder pedals, each with toe brakes; wherein the set of controls not currently in use resides away from the driver/pilot in the direction of the front of the roadable aircraft out of reach and immobilized; andwherein the set currently in use resides toward the driver/pilot in the direction of the aft of the roadable within reach and activated. 5. The roadable aircraft of claim 4, wherein the cockpit comprises a floor surface at a floor level, a front wall, a rear wall, and left and right outer cockpit walls, whereby the rudder pedals stow at floor level up against the front wall of the cockpit and deploy aft along longitudinally oriented rails located at floor level near the left and right outer cockpit walls respectively, configured to reach the position of a driver-pilot's left and right feet respectively; and wherein, in juxtaposition thereto, the accelerator and brake pedals move as a block together between their deployed position, which is located on the right side of the cockpit at the position of the driver-pilot's right foot, on a rail curving convexly toward a mid-line of the fuselages and forward toward the front middle of the cockpit where they stow up against the front cabin wall. 6. The roadable aircraft of claim 5, whereby the brake and accelerator pedal are attached to a first end of at least one bar configured to rotate around floor-mounted pivots in the cockpit, where a second, opposite end of said at least one bar is attached to the rudder pedals. 7. The roadable aircraft of claim 4, whereby the joystick comprises a hinged base and is configured to fold forward over its hinged base into a rut in a floor of the cockpit when not in use. 8. The roadable aircraft of claim 1, comprising a control lever with three ranges: the control of an automatic automobile transmission via notched settings in a lower range of the control lever;the extension and retraction of aircraft wings via notched settings in a middle range of the control lever; andat least the thrust of an aircraft's propeller and control of airscrew angle of attack via an upper, variable range of the control lever. 9. The roadable aircraft of claim 1, whereby during road transport all control surfaces of the at least two wings located on all planes between the fuselages are set in such a way that they deflect the relative wind so as to enhance the roadable aircraft's road grip. 10. The roadable aircraft of claim 1, further comprising: a rearwardly extendable, longitudinal empennage beam movably coupled to each of the two fuselages,wherein the at least two wings are rotatably coupled to the empennage beams with at least two pivot-joints,wherein the at least two wings deploy from the stored position wholly or partially between said fuselages to the spread position via a longitudinal motion of the empennage beams and the at least two wings, followed by a lateral, swinging motion of the at least two wings about the pivot-joints. 11. The roadable aircraft of claim 10, further comprising: an empennage assembly joining the empennage beams to each other;wherein the empennage assembly comprises: at least one plane, andat least on control surface; andwherein a root of each said wing is rotatably attached via the pivot-joints to a trolley running in a rail located longitudinally along the empennage beam which is on the respective side of the deployment for the wing. 12. The roadable aircraft of claim 11, whereby the longitudinal, backward movement of the empennage beams is effected at an inclined angle such that, when the backward movement has been completed, the wings after they have been laterally rotated for flight and the empennage assembly are respectively higher and lower in relation to an intermediate point of the empennage beams; and wherein the fuselage comprises an empennage support structure and a hinge rotatably coupled to an empennage support structure, the empennage support structure configured to support the empennage beams and rotate about the hinge to effect rotation of the empennage beams, and where the intermediate point of each of the empennage beams is located at or near the rear end of each fuselage such that the empennage beams and laterally extended wings may be rotated upward or downward around said intermediate points in a see-saw-type motion about the hinge, thereby enabling wing spar stubs to be rocked in a see-saw type motion into receiving cavities located either within the fuselages or within the connecting beam between the fuselages. 13. The roadable aircraft of claim 12, wherein the empennage support structure comprises a sub-support and a rail extension beam connected to the empennage beam, the rail extension beam configured to engage the hinge to allow rotation of the empennage beams. 14. The roadable aircraft of claim 11, where each empennage beam is enclosed within one of the two fuselages during storage. 15. The roadable aircraft of claim 10, comprising: a first swinging arm, anda second swing arm,wherein the first and second swinging arms are for wing deployment,wherein a first end of the first swinging arm is attached to one of the two fuselages by a first support pivot-joint and a second end of the first swinging arm is attached to a first wing pivot-joint on the underside of one wing of the at least two wings and wherein a root of the one wing is attached to and during deployment revolves around a first root pivot-joint running on a trolley in a rail which is mounted substantially longitudinally along the roadable aircraft or along one of the empennage beams; andwherein a first end of the second swinging arm is attached to the other of the two fuselages by a second support pivot-joint and a second end of the second swinging arm is attached to a second wing pivot-joint on the underside of a second wing of the at least two wings, and wherein a root of the second wing is attached to and during deployment revolves around a second root pivot-joint running on a trolley in a rail which is mounted substantially longitudinally along the roadable aircraft or along one of the empennage beams; andwherein the pivot-joints on the undersides of the first and second wings run on a trolley within a rail which lies substantially along the span of the respective wing undersides. 16. The roadable aircraft of claim 15, wherein the first and second swinging arms are sunk into and flush with the underside of the first and second wings of the at least two wings when the at least two wings are in the spread position. 17. The roadable aircraft of claim 15, in which the first and second support pivot-joints are mounted to the two fuselages at such an angles as to allow the first and second swinging arms together with the wings they support to rotate laterally in slightly skewed, parallel planes to one another without interfering with one another during wing deployment from the stored position to the spread position. 18. The roadable aircraft of claim 17, comprising trolleys running along two upward rails mounted to the two fuselages or the connecting beam, wherein the support pivot-joints are movably mounted on the trolley running along the upward rails, the support pivot-joints configured to move along the upward rails as the at least two wings transition between the stored position and the spread position; whereby one end of each of the the upward rails is curved causing the support pivot-joint to skew when the support pivot-joints move along the curved portion of the upward rails, thereby causing the wings to be stored at a position which is not level allowing the wings to rotate past each other; andwhereby movement of said trolleys along said upward rails out of its curved part into an adjacent straight part of the upward rails causes the support pivot-joints to align themselves vertically, one above the other, thereby substantially leveling the wings. 19. The roadable aircraft of claim 18, in which said substantially upward rails curve at the one end of the rail to which the trolley is rolled in order to position the wings for flight at such an angle as to give the wings dihedral. 20. The roadable aircraft of claim 1, wherein the connecting beam comprises a central main-wing connecting the fuselages at a roof level of the fuselages, and wherein, with the at least two wings in the spread position, one of the at least two wings is mounted to a first end of the central main-wing and another of the at least two wings is mounted to a second, opposite end of the central main-wing. 21. The roadable aircraft of claim 20, further comprising a canard wing extending between the two fuselages at a lower front portion of the two fuselages. 22. The roadable aircraft of claim 20, wherein the central main-wing comprises: a first cavity about the first end of the central main-wing, anda second cavity about the second, opposite end of the central main-wing;wherein the first cavity is configured to receive a root of the one of the at least two wings in the spread position; andwherein the second cavity is configured to receive a root of a second of the at least two wings in the spread position.