초록 ▼

A method comprises providing six helicopters. Each helicopter has a fuselage, a main rotor assembly extending out from the fuselage and rotatable about a main rotor axis, and four main rotor blades coupled to the main rotor assembly. The main rotor blades of each helicopter are moveable relative to

A method comprises providing six helicopters. Each helicopter has a fuselage, a main rotor assembly extending out from the fuselage and rotatable about a main rotor axis, and four main rotor blades coupled to the main rotor assembly. The main rotor blades of each helicopter are moveable relative to the main rotor assembly between a deployed position and a stowed position. The deployed position is a position in which the four main rotor blades extend radially from the main rotor. The main rotor blades have a blade rotor diameter of at least forty seven feet when in the deployed position. The four main rotor blades are coupled to the main rotor assembly when in the stowed position. The method further comprises positioning the six helicopters relative to each other such that all six of the helicopters are simultaneously contained within a parallelepiped region having a height of less than fifteen feet, a width of less than twenty feet, and a length of less than one hundred forty five feet. The four main rotor blades of each of the six helicopters are in their stowed positions when the six helicopters are simultaneously contained within the parallelepiped region.

대표청구항 ▼

1. A blade positioning mechanism for folding a helicopter main rotor blade attached to a main rotor assembly via two blade pins, the mechanism comprising:a rotor assembly connection adapted to temporarily attach to the main rotor assembly with two degrees of freedom relative to the main rotor assemb

1. A blade positioning mechanism for folding a helicopter main rotor blade attached to a main rotor assembly via two blade pins, the mechanism comprising:a rotor assembly connection adapted to temporarily attach to the main rotor assembly with two degrees of freedom relative to the main rotor assembly; a rotor blade clamp adapted to temporarily attach to the rotor blade; a clamp positioner attached to the rotor blade clamp and the rotor assembly connection, the clamp positioner being adapted to pivot with two degrees of freedom relative to the rotor blade clamp and adapted to position the rotor blade clamp a distance from the rotor assembly connection after removal of one of the blade pins, the clamp positioner comprising a threaded stud, a female knuckle, and a handle, the threaded stud having a longitudinal central stud axis, a threaded outer surface, and a journal portion journaled to one of the rotor assembly connection and rotor blade clamp for rotation of the threaded stud relative to said one of the rotor assembly connection and rotor blade clamp about the stud axis, the female knuckle engaging the threaded stud and attached to the other of the rotor assembly connection and rotor blade clamp in a manner such that rotating the threaded stud about the stud axis causes the female knuckle and said other of the rotor assembly connection and rotor blade clamp to move axially along the stud axis, the handle being connected to the threaded stud in a manner such that the female knuckle is between the journal portion and the handle. 2. A blade positioning mechanism as set forth in claim 1 wherein the handle is adapted to enable a user to grasp the handle and rotate the stud about the stud axis without engaging the threaded outer surface of the stud.3. A blade positioning mechanism as set forth in claim 2 wherein the handle is fixed to the threaded stud in a manner such that rotation of the stud about the stud axis causes rotation of the handle about the stud axis and such that rotation of the handle about the stud axis causes rotation of the stud about the stud axis.4. A blade positioning mechanism as set forth in claim 2 the handle includes a knurled outer surface.5. A retention pin assembly comprising a shank and a handle, the shank having a shank axis, the handle being operatively connected to the shank for movement of the handle relative to the shank generally along the shank axis between a first position and a second position, the second position being axially spaced from the first position, the retention pin assembly further including opposing first and second surfaces and opposing third and fourth surfaces, the first surface being spaced from the second surface when the handle is in its first position, the first surface engaging the second surface when the handle is in its second position, the third surface engaging the fourth surface when the handle is in its first position, the third surface being spaced from the fourth surface when the handle is in its second position, the retention pin assembly being configured such that movement of the handle relative to the shank along the shank axis from the first position to the second position causes the first surface to collide with the second surface in a manner to force the shank along the shank axis in a first direction, the retention pin assembly being configured such that movement of the handle relative to the shank along the shank axis from the second position to the first position causes the fourth surface to collide with the third surface in a manner to force the shank along the shank axis in a second direction opposite the first direction.6. A method comprising:providing a retention pin assembly as set forth in claim 5; inserting the shank of the retention pin assembly into at least two aligned apertures in a manner to operatively connect a main rotor blade of a helicopter to a main rotor assembly of the helicopter. 7. An assembly comprising:a helicopter having a fuselage including a forward section and an aft section rearward of the forward section, a main rotor assembly extending out from the forward section of the fuselage, and four main rotor blades coupled to the main rotor assembly, each of the main rotor blades having a root end and a tip end, the four main rotor blades comprising a first rotor blade, a second rotor blade, a third rotor blade, and a fourth rotor blade, the four main rotor blades being in stowed positions in which each main rotor blade extends generally rearwardly from the main rotor assembly, the root end of the first rotor blade being directly connected to the main rotor assembly, the root end of the third rotor blade being directly connected to the main rotor assembly; a first swing link mechanism detachably connected to the root end of the second rotor blade and the main rotor assembly, the first swing link spacing the root end of the second rotor blade from the main rotor assembly; and a second swing link mechanism detachably connected to the root end of the fourth rotor blade and the main rotor assembly, the second swing link spacing the root end of the fourth rotor blade from the main rotor assembly. 8. A method comprising:providing a helicopter having a fuselage including a forward section and a tail section rearward of the forward section, a main rotor assembly extending out from the forward section of the fuselage, and at least one main rotor blade coupled to the main rotor assembly, a first rotor blade portion of the rotor blade being attached to a first rotor assembly portion of the main rotor assembly via a first retention pin, a second, rotor blade portion of the rotor blade being attached to a second rotor assembly portion of the main rotor assembly via a second retention pin; providing a swing link comprising a blade connection portion and a rotor assembly connection portion, the rotor assembly connection portion being spaced from the blade connection portion; removing the first retention pin in a manner such that the first retention pin is released from attaching the first rotor blade portion to the first rotor assembly portion; folding the rotor blade relative to the main rotor assembly from a first portion attachment position to a swing-link receiving position, the first portion attachment position being a position in which the first rotor blade portion is adjacent the first rotor assembly portion, the swing-link receiving position being a position in which the first rotor blade portion is spaced from the first rotor assembly portion a distance for receiving the swing link; pinning the first rotor assembly portion to the rotor assembly connection portion of the swing link at a first pin axis and pinning the first rotor blade portion to the blade connection portion of the swing link at a second pin axis; removing the second retention pin in a manner such that the second retention pin is released from attaching the second rotor blade portion to the second rotor assembly portion; moving the rotor blade relative to the main rotor assembly from a second portion attachment position to a stowed position, the second portion attachment position being a position in which the second rotor blade portion is adjacent the second rotor assembly portion, the stowed position being a position in which the second rotor blade portion is spaced a distance Ds from the second rotor assembly portion, the rotor blade pivots relative to the main rotor assembly about one of the first and second pin axes during at least a portion of the movement of the rotor blade from the second portion attachment position to the stowed position. 9. A method as set forth in claim 8 wherein the entirety of the step of moving the rotor blade from the second portion attachment position to the stowed position occurs after the step of pinning the first rotor assembly portion and the first rotor blade portion to the swing link.10. A method as set forth in claim 8 wherein the first pin axis is parallel to and spaced from the second pin axis.11. A method as set forth in claim 8 wherein the movement of the rotor blade from the second portion attachment position to the stowed position comprises a first movement portion and a second movement portion, the rotor blade pivots relative to the main rotor assembly about the first pin axis during the first movement portion, the rotor blade pivots relative to the main rotor assembly about the second pin axis during the second movement portion.12. A method as set forth in claim 11 wherein the swing link is locked to the rotor blade during the first movement portion in a manner to prevent the rotor blade from pivoting about the second pivot axis during the first movement portion, the swing link being unlocked from the rotor blade during the second movement portion.13. A method as set forth in claim 12 wherein the swing link is locked to the main rotor assembly during the second movement portion in a manner to prevent the rotor blade from pivoting about the first pivot axis during the second movement portion, the swing link being unlocked from the main rotor assembly during the first movement portion.14. A method as set forth in claim 8 wherein the step of moving the rotor blade relative to the main rotor assembly from the second portion attachment position to the stowed position comprises moving the rotor blade relative to the main rotor assembly from the second portion attachment position to a blade positioning mechanism receiving position, and moving the rotor blade relative to the main rotor assembly from the blade positioning mechanism receiving position to the stowed position, the method further comprising:providing a blade positioning mechanism comprising a rotor assembly connection adapted for connection to the main rotor assembly, a rotor blade connection adapted for connection to the rotor blade, and a threaded stud, the threaded stud having a longitudinal central stud axis, a threaded outer surface, and a journal portion journaled to one of the rotor assembly connection and the rotor blade connection for rotation of the threaded stud relative to said one of the rotor assembly connection and the rotor blade connection, the other of the rotor assembly connection and the rotor blade connection having a female knuckle threadably engaging the threaded outer surface of the threaded stud such that rotating the treaded stud about the stud axis causes said other of the rotor assembly connection and rotor blade connection to move axially along the stud axis; and pinning the rotor assembly connection of the blade positioning mechanism to the second rotor assembly portion of the main rotor assembly at a first mechanism pin axis and pinning the rotor blade connection of the blade positioning mechanism to the second rotor blade portion of the rotor blade at a second mechanism pin axis, the pinning of the blade positioning mechanism to the second rotor assembly portion and the second rotor blade portion occurring when the rotor blade and the main rotor assembly are in the blade positioning mechanism receiving position, the blade positioning mechanism receiving position being a position in which the second rotor blade portion is spaced a sufficient distance from the second rotor assembly portion to enable connection of the blade positioning mechanism to the second rotor blade portion and the second rotor assembly portion; wherein the step of moving the rotor blade relative to the main rotor assembly from the blade positioning mechanism receiving position to the stowed position comprises rotating the threaded stud about the stud axis in a manner to cause said other of the rotor assembly connection and rotor blade connection to move axially along the stud axis. 15. A method as set forth in claim 14 wherein the assembly connection of the blade positioning mechanism pivots relative to the second rotor assembly portion of the main rotor assembly about the first mechanism pin axis when the rotor blade is moved relative to the main rotor assembly from the blade positioning mechanism receiving position to the stowed position, and wherein the rotor blade connection of the blade positioning mechanism pivots relative to the second rotor blade portion of the rotor blade about the second mechanism pin axis when the rotor blade is moved relative to the main rotor assembly from the blade positioning mechanism receiving position to the stowed position.16. An assembly comprising:a helicopter having a fuselage including a forward section and a tail section rearward of the forward section, a main rotor assembly extending out from the forward section of the fuselage, and at least one main rotor blade, the main rotor assembly including a first rotor assembly portion having a retention-pin receiving aperture and a second rotor assembly portion having a retention-pin receiving aperture, the main rotor blade including a first rotor blade portion having a retention-pin receiving aperture and a second rotor blade portion having a retention-pin receiving aperture, the main rotor blade being adapted to be secured to the main rotor assembly in a deployed position in which the pin-receiving aperture of the first rotor blade portion is aligned with the pin-receiving aperture of the first rotor assembly portion and the pin-receiving aperture of the second rotor blade portion is aligned with the pin-receiving aperture of the second rotor assembly portion; a blade positioning mechanism comprising a rotor assembly connection adapted for connection to the main rotor assembly, a rotor blade connection adapted for connection to the rotor blade, and a threaded stud, the rotor assembly connection including a pin-receiving aperture adapted to be aligned with the pin-receiving aperture of the second rotor assembly portion when the rotor assembly connection is connected to the main rotor assembly, the rotor blade connection including a pin-receiving aperture adapted to be aligned with the pin-receiving aperture of the second rotor blade portion when the rotor blade connection is connected to the rotor blade, the threaded stud having a longitudinal central stud axis, a threaded outer surface, and a journal portion journaled to one of the rotor assembly connection and the rotor blade connection for rotation of the threaded stud relative to said one of the rotor assembly connection and the rotor blade connection, the other of the rotor assembly connection and the rotor blade connection having a female knuckle threadably engaging the threaded outer surface of the threaded stud such that rotating the treaded stud about the stud axis causes said other of the rotor assembly connection and rotor blade connection to move axially along the stud axis; a first retention pin extending through the pin-receiving aperture of the rotor assembly connection of the blade positioning mechanism and the pin-receiving aperture of the second rotor assembly portion of the main rotor assembly to connect the, rotor assembly connection to the main rotor assembly, the pin-receiving aperture of the rotor assembly connection being aligned with the pin-receiving aperture of the second rotor assembly portion; and a second retention pin extending through the pin-receiving aperture of the rotor blade connection of the blade positioning mechanism and the pin-receiving aperture of the second rotor blade portion of the rotor blade to connect the rotor blade connection to the rotor blade, the pin-receiving aperture of the rotor blade connection being aligned with the pin-receiving aperture of the second rotor blade portion. 17. An assembly as set forth in claim 16 wherein the blade positioning mechanism further comprises a lock mechanism connected to said one of the rotor assembly connection and the rotor blade connection, the lock mechanism being adapted to pivot relative to said one of the rotor assembly connection and the rotor blade connection between a locked position and an unlocked position, the locked position being a position in which the lock mechanism engages the threaded stud in a manner to prevent rotation of the threaded stud relative to said one of the rotor assembly connection and the rotor blade connection, the unlocked position being a position in which the lock mechanism is disengaged from the threaded stud to permit rotation of the threaded stud relative to said one of the rotor assembly connection and the rotor blade connection.18. A method comprising:providing a helicopter having a fuselage including a forward section and a tail section rearward of the forward section, a main rotor assembly extending out from the forward section of the fuselage, and at least one main rotor blade coupled to the main rotor assembly, a first rotor blade portion of the rotor blade being attached to a first rotor assembly portion of the main rotor assembly via a first retention pin, a second rotor blade portion of the rotor blade being attached to a second rotor assembly portion of the main rotor assembly via a second retention pin; providing a blade positioning mechanism comprising a rotor assembly connection adapted for connection to the main rotor assembly, a rotor blade connection adapted for connection to the rotor blade, and a threaded stud, the threaded stud having a longitudinal central stud axis, a threaded outer surface, and a journal portion journaled to one of the rotor assembly connection and the rotor blade connection for rotation of the threaded stud relative to said one of the rotor assembly connection and the rotor blade connection, the other of the rotor assembly connection and the rotor blade connection having a female knuckle threadably engaging the threaded outer surface of the threaded stud such that rotating the treaded stud about the stud axis causes said other of the rotor assembly connection and rotor blade connection to move axially along the stud axis; removing the second retention pin in a manner such that the second retention pin is released from attaching the second rotor blade portion to the second rotor assembly portion; moving the rotor blade relative to the main rotor assembly from the second portion attachment position to a blade positioning mechanism receiving position, the blade positioning mechanism receiving position being a position in which the second rotor blade portion is spaced a sufficient distance from the second rotor assembly portion to enable connection of the blade positioning mechanism to the second rotor blade portion and the second rotor assembly portion; pinning the rotor assembly connection of the blade positioning mechanism to the second rotor assembly portion of the main rotor assembly at a first mechanism pin axis and pinning the rotor blade connection of the blade positioning mechanism to the second rotor blade portion of the rotor blade at a second mechanism pin axis, the pinning of the blade positioning mechanism to the second rotor assembly portion and the second rotor blade portion occurring when the rotor blade and the main rotor assembly are in the blade positioning mechanism receiving position; moving the rotor blade relative to the main rotor assembly from the blade positioning mechanism receiving position to a stowed position, the stowed position being a position in which the second rotor blade portion is spaced a distance DS from the second rotor assembly portion, the step of moving the rotor blade from the blade positioning mechanism receiving position to the stowed position comprising rotating the threaded stud about the stud axis in a manner to cause said other of the rotor assembly connection and rotor blade connection to move axially along the stud axis until the rotor blade and the main rotor assembly are in the stowed position. 19. A method as set forth in claim 18 wherein the assembly connection of the blade positioning mechanism pivots relative to the second rotor assembly portion of the main rotor assembly about the first mechanism pin axis when the rotor blade is moved relative to the main rotor assembly from the blade positioning mechanism receiving position to the stowed position, and wherein the rotor blade connection of the blade positioning mechanism pivots relative to the second rotor blade portion of the rotor blade about the second mechanism pin axis when the rotor blade is moved relative to the main rotor assembly from the blade positioning mechanism receiving position to the stowed position.20. A method as set forth in claim 18 wherein the blade positioning mechanism further comprises a lock mechanism connected to said one of the rotor assembly connection and the rotor blade connection, the lock mechanism being moveable relative to said one of the rotor assembly connection and the rotor blade connection between a locked position and an unlocked position, the locked position being a position in which the lock mechanism engages the threaded stud in a manner to prevent rotation of the threaded stud relative to said one of the rotor assembly connection and the rotor blade connection, the unlocked position being a position in which the lock mechanism is disengaged from the threaded stud to permit rotation of the threaded stud relative to said one of the rotor assembly connection and the rotor blade connection, the method further comprising:maintaining the lock mechanism in the unlocked position during the step of moving the rotor blade relative to the main rotor assembly from the blade positioning mechanism receiving position to a stowed position; moving the lock mechanism to the locked position when the rotor blade is in the stowed position to lock the rotor blade in the stowed position. 21. A blade positioning mechanism for folding a helicopter main rotor blade attached to a main rotor assembly, the main rotor blade including first and second pin-receiving openings adapted to align with first and second pin-receiving openings of the main rotor assembly, the pin-receiving openings of the main rotor blade and the main rotor assembly being sized and adapted for receiving retention pins when the first and second pin-receiving openings of the main rotor blade are aligned with the first and second pin-receiving openings of the main rotor assembly, the blade positioning mechanism comprising:a rotor assembly connection having a pin-receiving opening, the pin-receiving opening being sized and adapted for receiving a retention pin to enable the rotor assembly connection to be pinned to the main rotor assembly when the pin-receiving opening of the rotor assembly connection is aligned with the first pin-receiving opening of the main rotor assembly; a rotor blade connection having a pin-receiving opening, the pin-receiving opening being sized and adapted for receiving a retention pin to enable the rotor blade connection to be pinned to the main rotor blade when the pin-receiving opening of the rotor blade connection is aligned with the first pin-receiving opening of the main rotor blade, one of the rotor assembly connection and the rotor blade connection constituting a first connection, the other of the rotor assembly connection and the rotor blade connection constituting a second connection; a threaded stud, the threaded stud having a longitudinal central stud axis, a threaded outer surface, and a journal portion journaled to the first connection for rotation of the threaded stud relative to the first connection, the second connection having a female knuckle threadably engaging the threaded outer surface of the threaded stud such that rotating the treaded stud about the stud axis causes the second connection to move axially along the stud axis; and a lock mechanism connected to the first connection, the lock mechanism being moveable relative to the first connection between a locked position and an unlocked position, the locked position being a position in which the lock mechanism engages the threaded stud in a manner to prevent rotation of the threaded stud relative to the first connection, the unlocked position being a position in which the lock mechanism is disengaged from the threaded stud to permit rotation of the threaded stud relative to the first connection. 22. A blade positioning mechanism as set forth in claim 21 wherein the lock mechanism is pivotally connected to the first connection.23. A blade positioning mechanism as set forth in claim 21 wherein the threaded stud includes a hex-head, the lock mechanism being adapted to engage the hex-head when the lock mechanism is in the locked position, the lock mechanism being disengaged from the hex-head when the lock mechanism is in the unlocked position.24. A method comprising:providing a helicopter having a fuselage including a forward section and a tail section rearward of the forward section, a main rotor assembly extending out from the forward section of the fuselage, at least one main rotor blade coupled to the main rotor assembly, and a removable link, the rotor blade having first and second rotor blade portions, the rotor assembly having first and second rotor assembly portions, the first rotor blade portion being adapted for attachment to the first rotor assembly portion via a pin, the second rotor blade portion being adapted for attachment to the second rotor assembly portion via another pin, the removable link comprising a blade connection portion and a rotor assembly connection portion, the rotor assembly connection portion being spaced from the blade connection portion, the first rotor assembly portion being pinned to the rotor assembly connection portion via a first retention pin at a first pin axis, the first rotor blade portion being pinned to the blade connection portion via a second retention pin at a second pin axis, the rotor blade being moveable relative to the main rotor assembly between a second portion attachment position and a spaced position, the second portion attachment position being a position in which the second rotor blade portion is adjacent the second rotor assembly portion, the spaced position being a position in which the second rotor blade portion is spaced a distance from the second rotor assembly portion, the rotor blade pivoting about at least one of the first and second pin axes when the rotor blade is moved relative to the main rotor assembly between the second portion attachment position and the spaced position; providing a blade attachment mechanism, the blade attachment mechanism having a pin-engaging portion and a handle portion extending from the pin-engaging portion, the pin-engaging portion being sized and adapted to simultaneously engage the first and second retention pins when the first and second retention pins are located relative to the rotor blade and the rotor assembly at the first and second pin axes; engaging the first and second retention pins with the pin-engaging portion in a manner such that the handle extends generally laterally away from the first and second pin axes when the rotor blade is in the spaced position; applying a force to the handle to exert forces on the retention pins in a manner to at least assist in moving the rotor blade from the spaced position to the second portion attachment position. 25. A method as set forth in claim 24 wherein:the second rotor blade portion includes a pin-receiving aperture, the second rotor assembly portion includes a pin-receiving aperture, and the pin-receiving aperture of the second rotor blade portion is aligned with the pin-receiving aperture of the second rotor assembly portion when the rotor blade is in the second portion attachment position; and the step of applying a force to the handle to exert forces on the retention pins comprises applying forces on the handle to at least assist in moving the rotor blade relative to the main rotor assembly in a manner to align the pin-receiving aperture of the second rotor blade portion with the pin-receiving aperture of the second rotor assembly portion.