Teeter flap lock
A teeter flap lock for an aircraft may include at least one pair of diametrically positioned teeter flap lock plates extending from a rotor teetering hinge, spaced apart from a rotor mast of the aircraft. A teeter flap lock block is positioned about the rotor mast and is configured to fit between the teeter flap lock plates and the rotor mast. The teeter flap lock block fits between and contacts the teeter flap lock plates in an engaged position, and is movable between the engaged position and a disengaged position relative to the teeter flap lock plates. The teeter flap lock enables flapping of rotors coupled to the rotor mast via the teetering hinge when the teeter flap lock block is in the disengaged position and disables flapping of the rotors when the teeter flap lock block is in the engaged position.
1. A teeter flap lock for an aircraft comprising:
at least one pair of diametrically positioned teeter flap lock plates extending from a rotor teetering hinge, spaced apart from a rotor mast of the aircraft; and
a teeter flap lock block positioned about the rotor mast, the teeter flap lock block configured to fit between the teeter flap lock plates and the rotor mast and fit between and contact the teeter flap lock plates in an engaged position, and movable between the engaged position and a disengaged position relative to the teeter flap lock plates, the teeter flap lock enabling flapping of rotors coupled to the rotor mast via the teetering hinge when the teeter flap lock block is in the disengaged position and disabling flapping of the rotors when the teeter flap lock block is in the engaged position.
2. The teeter flap lock of claim 1 , further comprising an engagement mechanism linked to the teeter flap lock block and configured to slide the teeter flap lock block along the rotor mast to engage and disengage the teeter flap lock.
3. The teeter flap lock of claim 1 , further comprising a plurality of rollers on the teeter flap lock block, the rollers configured to align the teeter flap lock block and the teeter flap lock plates and contact the teeter flap lock plates, in a single axis, when the teeter flap lock block is moved to the engaged position.
4. The teeter flap lock of claim 3 , wherein the rollers are spring biased.
5. The teeter flap lock of claim 1 , further comprising a protective wear sleeve disposed between the teeter flap lock block and the mast.
6. The teeter flap lock of claim 1 , wherein the aircraft is a tiltrotor aircraft, and the rotor mast is a fixed vertical rotor mast.
7. A propulsion assembly for an aircraft, comprising:
a rotor mast;
a rotor teetering hinge coupled to the rotor mast and a pair of rotor blades, the rotor teetering hinge having a rotor teetering degree of freedom relative to the rotor mast, the rotor teetering hinge comprising at least one pair of diametrically positioned teeter flap lock plates extending from the rotor teetering hinge, spaced apart from the rotor mast; and
a teeter flap lock block positioned about the rotor mast, the teeter flap lock block configured to fit between the teeter flap lock plates and the rotor mast and fit between and contact the teeter flap lock plates in an engaged position, and movable between the engaged position and a disengaged position relative to the teeter flap lock plates, the teeter flap lock enabling flapping of the rotors when the teeter flap lock block is in the disengaged position and disabling flapping of the rotors when the teeter flap lock block is in the engaged position.
8. The propulsion assembly for an aircraft of claim 7 , further comprising an engagement mechanism linked to the teeter flap lock block and configured to slide the teeter flap lock block along the rotor mast to engage and disengage the teeter flap lock.
9. The propulsion assembly for an aircraft of claim 7 , further comprising a plurality of rollers on the teeter flap lock block, the rollers configured to align the teeter flap lock block and the teeter flap lock plates and contact the teeter flap lock plates, in a single axis, when the teeter flap lock block is moved to the engaged position.
10. The propulsion assembly for an aircraft of claim 9 , wherein the rollers are spring biased.
11. The propulsion assembly for an aircraft of claim 7 , further comprising a protective wear sleeve disposed on the rotor mast between the teeter flap lock block and the mast.
12. The propulsion assembly for an aircraft of claim 7 , wherein the aircraft is a tiltrotor aircraft, the rotor mast is a fixed vertical lift rotor mast and the teeter flap lock disables flapping of the rotors when the teeter flap lock block is in the engaged position.
13. The propulsion assembly for an aircraft of claim 12 , wherein the teeter flap lock is a single axis teeter flap lock, and the teeter flap lock block is only engageable to disable flapping of the rotors when the rotors driven by the rotor mast are stopped and aligned with a fuselage of the tiltrotor aircraft for horizontal flight.
14. An aircraft, comprising:
a fuselage; and
a plurality of rotors coupled to the fuselage, some of the rotors comprising two-bladed teetering rotors, each two-bladed teetering rotor comprising a single-axis flap lock.
15. The aircraft of claim 14 , wherein the flap lock enables flapping of the two-bladed teetering rotor with the flap lock disengaged when the two-bladed teetering rotor is providing lift for vertical takeoff and/or landing.
16. The aircraft of claim 14 , wherein:
the aircraft is a tiltrotor aircraft that further comprises a wing coupled to the fuselage;
the two-bladed teetering rotors are coupled to the fuselage and/or the wing coupled to the fuselage; and
the flap lock enables flapping of the two-bladed teetering rotor when the flap lock is disengaged when the two-bladed teetering rotors are providing lift when the tiltrotor aircraft is in vertical takeoff and/or landing modes.
17. The aircraft of claim 16 , wherein the flap lock disables flapping of the two-bladed teetering rotor when the flap lock is engaged when the two-bladed teetering rotors are stopped and aligned with a fuselage of the tiltrotor aircraft for horizontal flight.
18. The aircraft of claim 14 , wherein each two-bladed teetering rotor comprises:
a rotor mast;
a rotor teetering hinge coupled to the rotor mast and a pair of rotor blades, the rotor teetering hinge having a rotor teetering degree of freedom relative to the rotor mast; and
the single-axis flap lock comprising:
at least one pair of diametrically positioned teeter flap lock plates extending from the rotor teetering hinge, spaced apart from the rotor mast of the aircraft; and
a teeter flap lock block positioned about the rotor mast, the teeter flap lock block configured to fit between the teeter flap lock plates and the rotor mast and fit between and contact the teeter flap lock plates in an engaged position, and movable between the engaged position and a disengaged position relative to the teeter flap lock plates, the teeter flap lock enabling flapping of the rotors when the teeter flap lock block is in the disengaged position and disabling flapping of the rotors when the teeter flap lock block in the engaged position.
19. The aircraft of claim 18 , wherein the teeter flap lock block further comprises a plurality of rollers the rollers configured to align the teeter flap lock block and the teeter flap lock plates and contact the teeter flap lock plates, when the teeter flap lock block is moved to the engaged position.
20. The aircraft of claim 18 , further comprising an engagement mechanism linked to the teeter flap lock block and configured to slide the teeter flap lock block along the rotor mast to engage and disengage the teeter flap lock.