The apparatus of the invention enables a two-brake torque limiting device to fix the position of one or more flaps and/or slats on an airplane wing when unplanned or abnormal conditions exist. The two-brake torque limiting device may include a trigger brake, a lock down brake, and a speed-increasing
The apparatus of the invention enables a two-brake torque limiting device to fix the position of one or more flaps and/or slats on an airplane wing when unplanned or abnormal conditions exist. The two-brake torque limiting device may include a trigger brake, a lock down brake, and a speed-increasing device. The trigger brake may use an electromagnetic brake to apply a braking force to the lock down section. The braking force transferred to the lock down section from the trigger section may be transferred through a speed-increasing device. The speed-increasing device allows for the use of a small and a lightweight electromagnetic brake. The invention also provides a method for reducing asymmetry in the wings of an aircraft using an asymmetry detection device, using a trigger brake, using a speed-increasing gear, and using a lock down brake.
대표청구항▼
The apparatus of the invention enables a two-brake torque limiting device to fix the position of one or more flaps and/or slats on an airplane wing when unplanned or abnormal conditions exist. The two-brake torque limiting device may include a trigger brake, a lock down brake, and a speed-increasing
The apparatus of the invention enables a two-brake torque limiting device to fix the position of one or more flaps and/or slats on an airplane wing when unplanned or abnormal conditions exist. The two-brake torque limiting device may include a trigger brake, a lock down brake, and a speed-increasing device. The trigger brake may use an electromagnetic brake to apply a braking force to the lock down section. The braking force transferred to the lock down section from the trigger section may be transferred through a speed-increasing device. The speed-increasing device allows for the use of a small and a lightweight electromagnetic brake. The invention also provides a method for reducing asymmetry in the wings of an aircraft using an asymmetry detection device, using a trigger brake, using a speed-increasing gear, and using a lock down brake. crossbar having an end proximal secured to the crossbar joint and a distal end; a circular safety ring secured to the distal ends of each crossbar and having pivots for receiving the distal ends of each blade; and a flybar extending outwardly both from a leading edge and a trailing edge defined in each blade, each flybar extending along said horizontal plane, 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 blades about the horizontal stabilizing means in a manner that offsets the pitch such that the helicopter remains in a substantially horizontal position. 6. The helicopter of claim 1, wherein the main propeller includes: two pair of blades pivotally extending outwardly along a horizontal plane from the horizontal stabilizing means, such that one pair of blades is perpendicular to the other pair of blades, each blade having an end proximal to the horizontal stabilizing means and a distal end; a circular safety ring having pivots for receiving the distal ends of each blade; and a flybar extending outwardly from a leading edge defined in each blade, 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 blades about the horizontal stabilizing means in a manner that offsets the pitch such that the helicopter remains in a substantially horizontal position. 7. The helicopter of claim 4, 5, or 6, wherein the flybars include weighted ends to increase the centrifugal force created by the rotation thereof. 8. The helicopter of claim 1, wherein the horizontal stabilizing means is defined as a pivotal main rotor head mounted to the main drive shaft, and a main propeller mount extending downwardly from the main propeller; the main propeller mount pivotally mounted to the pivotal main rotor head such that the main propeller may pivot about the main drive shaft. 9. A self-stabilizing propeller for use in an rotary-type aircraft wherein the propeller is rotatably attached to a drive shaft and rotates in a plane, the propeller comprising: a pair of blades extending outwardly from each other along a single axis, each blade having a leading edge, a proximal end defined as an end proximal to the other blade, and a distal end; and a safety arc attached to the proximal and distal ends of each blade and positioned in front of the leading edge of each blade, each safety arc having a predetermined weight, wherein when the propeller is rotating the weight of the safety arcs creates a centrifugal force that tends to offset a pitch force exhibited by the propeller when rotating such that the propeller has a tendency to remain in substantially the same plane. 10. The helicopter of claim 9, wherein the safety arc has a diameter that transitions from a relatively flat horizontal surface by the proximal end into a wider vertical surface by the distal end. 11. An aircraft having an airfame housing a motor mechanism for powering at least one substantially horizontal orientated propeller, each propeller is attached to a corresponding drive shaft that extends vertically through the airframe, the aircraft further comprising at least one horizontal stabilizing means attached between one of the propellers, of the at least one propeller, and the corresponding drive shaft, which permits the propeller to freely pivot about the corresponding drive shaft independently from the airframe, wherein when said propeller is rotating and said rotating propeller begin to pitch, the rotating propeller having a centrifugal force created by the rotation thereof 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. 12. The helicopter of claim 11, wherein at least one of the at least one
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