Saucer-shaped gyroscopically stabilized vertical take-off and landing aircraft

• US 20100320333A1
• Filed: 07/09/2010
• Published: 12/23/2010
• Est. Priority Date: 05/07/2009
• Status: Active Grant

• Current Assignee: Herbert Martin
• Original Assignee: Herbert Martin
• Inventors: Martin, Herbert
• Granted Patent: US 8,322,649 B2
• Time in Patent Office: Days
• US Class Current: 244/23A
• CPC Class Codes: B64C 17/06 by gyroscopic apparatus
• CPC Class Codes: B64C 29/0025 the propellers being fixed relative to the fuselage
• CPC Class Codes: B64C 39/001 Flying saucers
• CPC Class Codes: F02B 27/0226 characterised by the means generating the charging effect

Abstract

An aircraft that is housed within a gyroscope providing for improved flight stability that includes an inner hull which remains stationary within a rotating outer hull. A rotating plate includes a groove that traces a sinusoidal pattern around an inside periphery of the plate. Tracking arms have a portion that fit within the groove and another portion that connects to a piston. The rotation of the plate causes the tracking arms to travel within the sinusoidal groove and impart movement on the plurality of pistons which will intake air from above the upper surface of the inner hull configuration and create a negative pressure on the aircraft. The craft contains compression chambers which receive the air and which feed the various impeller thrusters which are rotational within three-fourths of a hemisphere.

Claims

1. A vertical take-off and landing aircraft, comprising:

an outer saucer-shaped hull configured to rotate around a central axis of the aircraft thereby creating a gyroscopic effect for the aircraft;

an inner stationary hull having a central axis substantially aligned with a central axis of the outer saucer-shaped hull and configured to be positioned within an annular opening of the outer saucer-shaped hull;

a plurality of air passageways on a top of the inner stationary hull, the plurality of air passageways arranged in a circle by being equidistant from the central axis of the aircraft;

a respective piston chamber and piston associated with each of the plurality of air passageways, each piston configured to move back and forth within its respective piston chamber such that it has a displacement distance within its respective piston chamber; and

means for imparting motion onto the pistons such that the respective displacement distance associated with each of the pistons varies sinusoidally around the circle of air passageways.

2. The aircraft of claim 1, wherein the means for imparting motion include:

a sinusoidal plate having a central axis substantially aligned with the inner stationary hull and configured to fit within the inner stationary;

a motor configured to rotate the sinusoidal plate;

a groove on a surface of the sinusoidal plate, wherein a distance of a center of the groove from the central axis of the sinusoidal plate varies in a sinusoidal manner; and

a respective traveling arm coupled with each piston, each traveling arm having a first end adjacent the piston and a second end extending into the groove, and wherein rotation of the sinusoidal plate causes the respective traveling arm of associated with a particular piston to impart motion on that piston in a direction substantially perpendicular to the central axis of the inner hull.

3. The aircraft of claim 2, further comprising:

a fan having a plurality of blades positioned between the outer saucer-shaped hull and the sinusoidal plate and wherein the fan is coupled with the sinusoidal plate so as to rotate concurrent with the sinusoidal plate.

4. The aircraft of claim 2, further comprising:

a first plurality of cogs on an interior, annular cavity on the surface of the sinusoidal plate;

an intermediary gear with a second plurality cogs in mechanical communication with the first plurality of cogs; and

a drive gear coupled with the motor and having a third plurality of cogs, wherein rotation of the drive gear by the motor imparts rotation on the sinusoidal plate.

5. The aircraft of claim 2, further comprising:

a plurality of air foil propellers positioned on a top surface of the outer saucer-shaped hull and configured to be in a closed position or an open position;

6. The aircraft of claim 5, wherein in the closed position the air foil propellers resist descent of the aircraft and in the open position, the open position being adjustable such that an amount of openness controls an amount of lift acting on the aircraft.

7. The aircraft of claim 4, further comprising:

a compression chamber configured to receive air from the plurality of air passageways and exhaust the air through one or more thrusters.

8. The aircraft of claim 7, wherein the one or more thrusters include:

one or more stabilization thrusters configured to exhaust air in a direction opposite that of a direction the aircraft is rotating.

9. The aircraft of claim 7, wherein the one or more thrusters include:

one or more lift thrusters configured to exhaust air to thereby control an inclination of the aircraft.

10. The aircraft of claim 7, wherein at least one of the one or more thrusters is configurable to be in one of a plurality of different positions so as to control a direction in which the air is exhausted.

11. The aircraft of claim 7, wherein the one or more thrusters include:

one or more propulsion thrusters configured to exhaust air to thereby control a direction of the aircraft.

12. The aircraft of claim 11 wherein at least one of the propulsion thrusters includes:

a valve having a central axis and a first valve opening opposite a second valve opening, the first and second openings lying on an axis substantially perpendicular to the central axis of the valve;

a two-sided valve closer having a first side shaped to close the first valve opening and a second side shaped to close the second valve opening;

a rack and pinion gear arrangement configured to move the two-sided valve closer in a direction along the axis of the first and second valve openings to control an amount of air exhausted through the first and second valve openings.

13. The aircraft of claim 12, further comprising a spring that is biased to push the first closer towards the first valve opening and the second closer towards the second valve opening such the first and second openings are substantially closed concurrently.

14. The aircraft of claim 12, wherein the rack and pinion gearing arrangement is configured to move the two-sided valve closer so the first valve opening is substantially closed and the second valve opening is at least partially open.

15. The aircraft of claim 12, wherein the at least one propulsion thruster is swivable about an axis substantially parallel with the central axis of the outer saucer-shaped hull.

16. The aircraft of claim 9, further comprising:

a movable plate configured to cover a portion of at least one of the lift thrusters;

a control arm configured to move the movable plate to a position which blocks a portion of the lift thruster to restrict an amount of air exhausted from the lift thruster.

17. The aircraft of claim 1, wherein a first weight of the outer saucer-shaped hull is more than a second weight of the inner stationary hull whereby rotation of the outer hull provides a gyroscopic stabilizing effect on the aircraft.

18. The aircraft of claim 1, wherein the means for imparting motion includes:

a plurality of motors located between the outer saucer-shaped hull and the inner stationary hull and configured to rotate the outer saucer-shaped hull relative to the inner stationary hull; and

wherein the pistons are positioned within the inner stationary hull and configured to travel substantially perpendicular to a top surface of the inner stationary hull so as to draw air into the aircraft; and

a sinusoidal ring configured so that a height of a top surface of the ring varies in a sine-wave fashion around its perimeter, wherein the sinusoidal ring is in mechanical communication with the outer saucer-shaped hull such that rotation of the outer saucer-shaped hull results in rotation of the sinusoidal ring, and wherein the pistons are in mechanical communication with the top surface of the sinusoidal ring such that motion of each piston varies as the sinusoidal ring rotates.

19. The aircraft of claim 17, wherein a circumference of the sinusoidal ring is an integer multiple of a wavelength at which the height of the sinusoidal ring varies.

20. The aircraft of claim 17, further comprising:

a plurality of bearings positioned between the inner stationary hull and the outer saucer-shaped hull.