초록 ▼

A propeller related vehicle in accordance with one embodiment of the present invention is described as a helicopter having an airframe housing a pneumatic motor mechanism for powering a main propeller attached to a main drive shaft. The helicopter further includes a horizontal stabilizing means atta

A propeller related vehicle in accordance with one embodiment of the present invention is described as a helicopter having an airframe housing a pneumatic motor mechanism for powering a main propeller attached to a main drive shaft. The helicopter further includes a horizontal stabilizing means attached between the main propeller and the main drive shaft, which permits the main propeller to freely pivot about the main drive shaft independently from the airframe. As such when the main propeller is rotating and the main propeller begins to pitch, the rotating main propeller has a centrifugal force created by the rotation thereof and will tend to pivot about the horizontal stabilizing means in a manner that offsets the pitch such that the helicopter remains in a substantially horizontal position.

대표청구항 ▼

1. A helicopter comprising:an airframe housing at least a reservoir;a means to refill and pressurize air inside the reservoir;a pneumatic motor mechanism that utilizes pressurized air inside the reservoir to rotate a main drive shaft;a main propeller that is rotated by the main drive shaft; anda hor

1. A helicopter comprising:an airframe housing at least a reservoir;a means to refill and pressurize air inside the reservoir;a pneumatic motor mechanism that utilizes pressurized air inside the reservoir to rotate a main drive shaft;a main propeller that is rotated by the main drive shaft; anda horizontal stabilizing means attached between the main propeller and the main drive shaft, which permits the main propeller to freely pivot about the main drive shaft independently from the airframe, wherein when the main propeller is rotating and the main propeller begins to pitch, the rotating main propeller will tend to pivot about the horizontal stabilizing means in a manner that offsets the pitch such that the helicopter remains in a substantially horizontal position; andwherein the horizontal stabilizing means includes a rotor attachment that attaches directly to the main propeller, the rotor attachment includes a lower end that is pivotally connected within a joint in a first pivot direction such that when the rotor attachment pivots a predetermined amount with respect to the joint an outside surface defined by the rotor attachment will come into contact with an inside surface defined by the joint thereby preventing the rotor attachment from pivoting more than said predetermined amount; the horizontal stabilizing means further includes a yoke pivotally attached to the joint in a second pivot direction that is different than the first pivot direction and the yoke is secured to the main drive shaft. 2. The helicopter of claim 1, wherein the pneumatic motor mechanism includes:an intake manifold in communication with the reservoir, the intake manifold permits air to enter into the reservoir from an outside source, anda pneumatic motor in communication with the reservoir and the main drive shaft, the pneumatic motor utilizes pressurized air from the reservoir to rotate the main drive shaft. 3. The helicopter of claim 2, further comprising an external pumping means that is attachable to the intake manifold for pumping air into and pressurizing air inside the reservoir. 4. The helicopter of claim 1, wherein the first pivot direction is perpendicular to the second pivot direction. 5. The helicopter of claim 1, wherein the main propeller includes:a center support defined about the horizontal stabilizing means;a pair of blades extending outwardly from the center support, each blade having an end distal to the horizontal stabilizing means;a pair of crossbars extending outwardly from the center support and perpendicularly from the blades, each crossbar have an end distal from the center support; and a safety ring attached to the distal ends of each blade and crossbar. 6. The helicopter of claim 4, wherein the main propeller includes at least a pair of blades that extend outwardly from the horizontal stabilizing means such that the pair of blades pivot about the horizontal stabilizing means in the first pivotal direction. 7. An aircraft having a pneumatic motor mechanism for powering a horizontal orientated propeller, the propeller is attached to a drive shaft that is rotated by said pneumatic motor mechanism, the aircraft further comprising a horizontal stabilizing means attached between the propeller and the drive shaft, which permits the propeller to freely pivot about the drive shaft independently from the airframe, and wherein when said propeller is rotating and said rotating propeller begins to pitch, the rotating propeller will tend to pivot about the horizontal stabilizing means in a manner that offsets the pitch such that the aircraft remains in a substantially horizontal position, andwherein the horizontal stabilizing means includes a rotor attachment that attaches directly to the main propeller, the rotor attachment includes a lower end that is pivotally connected within a joint in a first pivot direction such that when the rotor attachment pivots a predetermined amount with respect to the joint an outside surface defined by the rotor attachment will come into contact with an inside surface defined by the joint thereby preventing the rotor attachment from pivoting more than said predetermined amount; the horizontal stabilizing means further includes a yoke pivotally attached to the joint in a second pivot direction that is different than the first pivot direction and secured to the drive shaft. 8. The aircraft of claim 7 further comprising:a reservoir housed within the airframe to store a pressurized fluid that is used by the pneumatic motor mechanism to rotate the propeller. 9. The aircraft of claim 8, wherein the pneumatic motor mechanism includes:an intake manifold in communication with the reservoir and having a means to attach to an external pump, which is used to pump air into and pressurize air inside the reservoir; anda pneumatic motor in communication with the reservoir and the drive shaft. 10. The aircraft of claim 7, wherein the propeller includes:a center support defined about the horizontal stabilizing means;a pair of blades extending outwardly from the center support, each blade having an end distal to the horizontal stabilizing means;a pair of crossbars extending outwardly from the center support and perpendicularly from the blades, each crossbar have an end distal from the center support; anda safety ring attached to the distal ends of each blade and crossbar. 11. The aircraft of claim 10, wherein the pair of blades are parallel to the first pivot direction and the first pivot direction is perpendicular to the second pivot direction. 12. A self-stabilizing aircraft comprising:a reservoir for storing a pressurized fluid;a pneumatic motor mechanism in communication with the reservoir, the pneumatic motor mechanism having a pneumatic motor that uses pressurized fluid contained in the reservoir to rotate a drive shaft;a horizontal rotatable propeller that is rotated when the drive shaft rotates; anda horizontal stabilizing means attached between the main propeller and the drive shaft, the horizontal stabilizing means pivotally attached to the main propeller in a first pivot direction and pivotally attached to the drive shaft in a second pivot direction, the first pivot direction being parallel to a pair of blades defined by the propeller and the second pivot direction is perpendicular to the first pivot direction, andwherein the horizontal stabilizing means includes a rotor attachment that attaches directly to the main propeller, the rotor attachment includes a lower end that is pivotally connected to a joint in a first pivot direction, and includes a yoke pivotally attached to the joint in a second pivot direction that is different than the first pivot direction and secured to the drive shaft, and further includes a means for preventing the rotor attachment from pivoting more than a predetermined amount. 13. The aircraft of claim 12 further including an inlet assembly in communication with the reservoir, the inlet assembly having a means to permit an external pump to attach thereto, such that the external pump may pump air into and pressurize air inside the reservoir. 14. The aircraft of 13 , wherein the main propeller further includes a pair of crossbars perpendicular to the blades and includes a safety ring attached to ends defined by the blades and crossbars, the ends of the blades and crossbars are distal to a center support area that attaches to the horizontal stabilizing means. 15. The aircraft of claim 13, wherein the main propeller includes:a pair of blades extending outwardly from the horizontal stabilizing means along a horizontal-plane, each blade having a leading edge, a proximal end defined as an end proximal to the horizontal stabilizing means and a distal end;a safety arc attached to the proximal and distal ends of each blade and positioned in front of the leading edge of each blade; anda pair of flybars extending outwardly from the horizontal stabilizing means along said horizontal plane, each flybar having a weighted end, wherein when the main propeller is rotating and the main propeller begins to pitch, the flybars having an increased centrifugal force created by the rotation thereof will tend to pivot the main propeller in a manner that offsets the pitch such that the helicopter remains in a substantially horizontal position.