NZ794216B2 - Lift fan position lock mechanism - Google Patents

Lift fan position lock mechanism

Info

Publication number
NZ794216B2
NZ794216B2 NZ794216A NZ79421617A NZ794216B2 NZ 794216 B2 NZ794216 B2 NZ 794216B2 NZ 794216 A NZ794216 A NZ 794216A NZ 79421617 A NZ79421617 A NZ 79421617A NZ 794216 B2 NZ794216 B2 NZ 794216B2
Authority
NZ
New Zealand
Prior art keywords
lock mechanism
magnet assembly
ring structure
rotating magnet
rotor lock
Prior art date
Application number
NZ794216A
Other versions
NZ794216A (en
Inventor
Geoffrey Alan Long
Robert Wayne Moore
Original Assignee
Wisk Aero Llc
Filing date
Publication date
Priority claimed from US15/372,125 external-priority patent/US9783288B1/en
Application filed by Wisk Aero Llc filed Critical Wisk Aero Llc
Publication of NZ794216A publication Critical patent/NZ794216A/en
Publication of NZ794216B2 publication Critical patent/NZ794216B2/en

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
    • B64C2027/8236—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft including pusher propellers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
    • B64C2027/8263—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft comprising in addition rudders, tails, fins, or the like
    • B64C2027/8272—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft comprising in addition rudders, tails, fins, or the like comprising fins, or movable rudders
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
    • B64C2027/8263—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft comprising in addition rudders, tails, fins, or the like
    • B64C2027/8281—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft comprising in addition rudders, tails, fins, or the like comprising horizontal tail planes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
    • B64C27/24—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with rotor blades fixed in flight to act as lifting surfaces
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
    • B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
    • B64C27/30—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with provision for reducing drag of inoperative rotor
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors
    • B64C27/322—Blade travel limiting devices, e.g. droop stops
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors
    • B64C27/46—Blades
    • B64C27/473—Constructional features
    • B64C27/48—Root attachment to rotor head
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
    • B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
    • B64C29/0016—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
    • B64C29/0025—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers the propellers being fixed relative to the fuselage
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
    • B64C29/0091—Accessories not provided for elsewhere
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01F—MAGNETS; INDUCTANCES; TRANSFORMERS; SELECTION OF MATERIALS FOR THEIR MAGNETIC PROPERTIES
    • H01F7/00—Magnets
    • H01F7/02—Permanent magnets [PM]
    • H01F7/0205—Magnetic circuits with PM in general
    • H01F7/0226—PM with variable field strength
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01F—MAGNETS; INDUCTANCES; TRANSFORMERS; SELECTION OF MATERIALS FOR THEIR MAGNETIC PROPERTIES
    • H01F7/00—Magnets
    • H01F7/02—Permanent magnets [PM]
    • H01F7/0231—Magnetic circuits with PM for power or force generation
    • H01F7/0247—Orientating, locating, transporting arrangements
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02K—DYNAMO-ELECTRIC MACHINES
    • H02K49/00—Dynamo-electric clutches; Dynamo-electric brakes
    • H02K49/10—Dynamo-electric clutches; Dynamo-electric brakes of the permanent-magnet type

Abstract

lift fan position lock mechanism is disclosed. In various embodiments, a position lock mechanism includes a ring structure having a first surface, the ring structure including one or more detents defined in the first surface of the ring structure. For each detent, the lock mechanism includes a stationary magnet coupled fixedly to the ring structure at a location adjacent to the detent. The lock mechanism further includes a rotating magnet assembly comprising a magnet of opposite magnetic polarity to at least one of the stationary magnets and a mechanical stop structure of a size and shape to fit into a corresponding detent and engage mechanically with a surface defining at least one extent of said corresponding detent when the rotating magnet assembly is in a locked position. By doing this, it reduces the unwanted drag of the vertical fans.

Claims (20)

1. A rotor lock mechanism, comprising: a ring structure having a first surface, the ring structure including one or more detents defined in the first surface of the ring structure; for each detent, a stationary magnet coupled fixedly to the ring structure at a location adjacent to the detent; and a rotating magnet assembly comprising a magnet of opposite magnetic polarity to at least one of the stationary magnets and a mechanical stop structure of a size and shape to fit into a corresponding detent and engage mechanically with a surface defining at least one extent of the corresponding detent when the rotating magnet assembly is in a locked position, wherein the mechanical stop structure comprises a substantially cylindrical element extending beyond a plane associated with the magnet comprising the rotating magnet assembly.
2. The rotor lock mechanism of claim 1, wherein a longitudinal axis of the substantially cylindrical element is oriented at an acute angle to the plane associated with the magnet comprising the rotating magnet assembly.
3. The rotor lock mechanism of claim 1 or 2, wherein the detent comprises a v-shaped notch in the first surface of the ring structure.
4. The rotor lock mechanism of any one of the preceding claims, wherein the rotating magnet assembly comprises an arm integrated with the mechanical stop structure, wherein the arm is attached to a mount portion of the rotating magnet assembly such that the arm and the mechanical stop structure are configured to rotate relative to the mount portion.
5. The rotor lock mechanism of any one of the preceding claims, wherein, when the rotating magnet assembly is in an unlocked position, the mechanical stop portion rides on a top surface of the ring structure and the magnet of the rotating magnet assembly is positioned at an angle away from the ring structure.
6. The rotor lock mechanism of any one of the preceding claims, wherein, when the rotating magnet assembly is in an unlocked and fully disengaged position, the mechanical stop portion is disengaged from the ring structure and the magnet of the rotating magnet assembly is positioned at an angle away from the ring structure.
7. The lock mechanism of any one of the preceding claims, wherein the rotating magnet assembly is configured to be attached fixedly to a rotor via a base structure with respect to which at least a portion of the rotating magnet assembly that includes the magnet and the mechanical stop structure is connected via a pin or other axially oriented structure in a manner such that at least said portion remains free to rotate about an axis associated with the pin or other axially oriented structure.
8. The rotor lock mechanism of claim 7, wherein a center of mass of the portion of the rotating magnet assembly is substantially aligned with the axis in a plane substantially parallel to a plane of the ring structure when the rotating magnet assembly is in the locked position.
9. The rotor lock mechanism of claim 8, wherein the center of mass the portion of the rotating magnet assembly is located at a non-zero distance d from the plane substantially parallel to the plane of the ring structure when the rotating magnet assembly is in an unlocked position in which the mechanical stop structure is no longer in the detent.
10. The rotor lock mechanism of any one of the preceding claims, wherein the rotor lock mechanism includes a plurality of stationary magnets, including a first subset having a first magnetic polarity and a second subset having a second magnetic polarity opposite to the first magnetic polarity.
11. The rotor lock mechanism of any one of the preceding claims, wherein the rotating magnet assembly includes a spring configured to apply a spring force in a direction associated with the locked position.
12. The rotor lock mechanism of any one of the preceding claims, wherein the rotating magnet assembly is attached to a rotor of an aircraft lift fan and the ring structure is attached fixedly to a non-rotating element of the aircraft lift fan.
13. The rotor lock mechanism of claim 12, wherein the aircraft lift fan is operated under control of a control module comprising a processor configured to perform an unlock sequence to transition the aircraft lift fan from a locked state in which the rotor lock mechanism is in a locked position to an unlocked state in which the rotor lock mechanism is not in the locked position, and to perform a lock sequence to transition the aircraft lift fan from the unlocked state to the locked state.
14. The rotor lock mechanism of claim 13, wherein performing the unlock sequence includes applying a torque that is equal to or greater than a break free torque associated with the rotor lock mechanism.
15. The rotor lock mechanism of claim 13 or 14, wherein performing the lock sequence includes causing the rotor to rotate through one or more revolutions under a torque that is less than a break free torque associated with the rotor lock mechanism.
16. The rotor lock mechanism of claim 15, wherein the performing the lock sequence includes estimating an angular position of the rotor.
17. The rotor lock mechanism of any one of the preceding claims, wherein the ring structure comprises one or more of an axis symmetric ring; a substantially flat ring; and a conical annulus.
18. The rotor lock mechanism of any one of the preceding claims, wherein the ring structure is a stationary ring.
19. A system comprising: an aircraft lift fan; and a rotor lock mechanism comprising: a ring structure having a first surface, the ring structure including one or more detents defined in the first surface of the ring structure; for each detent, a stationary magnet coupled fixedly to the ring structure at a location adjacent to the detent; and a rotating magnet assembly comprising a magnet of opposite magnetic polarity to at least one of the stationary magnets and a mechanical stop structure of a size and shape to fit into a corresponding detent and engage mechanically with a surface defining at least one extent of the corresponding detent when the rotating magnet assembly is in a locked position, wherein the mechanical stop structure comprises a substantially cylindrical element extending beyond a plane associated with the magnet comprising the rotating magnet assembly, wherein the rotating magnet assembly is attached to a rotor of the aircraft lift fan and the ring structure is attached fixedly to a non-rotating element of the aircraft lift fan.
20. The system of claim 19, further comprising a control module comprising a processor configured to perform an unlock sequence to transition the aircraft lift fan from a locked state in which the rotor lock mechanism is in a locked position to an unlocked state in which the rotor lock mechanism is released from the locked position.
NZ794216A 2017-11-07 Lift fan position lock mechanism NZ794216B2 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US15/372,125 US9783288B1 (en) 2016-12-07 2016-12-07 Lift fan position lock mechanism
NZ768826A NZ768826A (en) 2016-12-07 2017-11-07 Lift fan position lock mechanism

Publications (2)

Publication Number Publication Date
NZ794216A NZ794216A (en) 2023-12-22
NZ794216B2 true NZ794216B2 (en) 2024-03-26

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