The subject matter disclosed herein generally relates to an aircraft, and more particularly, to a system for steering a grounded aircraft to park the aircraft within a hangar.
Alignment and parking of a shipboard aircraft at a desired location within a hangar on a ship or vessel requires substantial maneuvering of the aircraft. The ship typically includes a rapid securing device (RSD) for detecting that an aircraft has landed on the deck of the ship and then automatically securing the aircraft to the deck. The aircraft includes a recovery assist, secure, and traverse (RAST) probe configured to cooperate with the RSD to move the aircraft fore and aft along the deck. In addition, multiple winches mounted to the deck are attached to one or more tie down rings of the aircraft and move the aircraft laterally. The fore and aft and lateral movement of the aircraft may be coordinated through multiple maneuvers to cause the nose landing gear of the aircraft to castor until the aircraft is arranged at a desired position within the hangar. However, this movement of the aircraft is complex and time consuming, and the forces applied by the winches to turn the aircraft can exceed the structural capability of the tie down rings.
According to one embodiment, a steering assembly includes a movable anchor. Movement of the anchor in a first direction is restricted. A first linkage is coupled to the anchor and a second linkage is movably coupled to the first linkage. The second linkage is configured to couple to a contactor. A drive mechanism moves the second linkage relative to the first linkage. At least one of moving the second linkage and moving the anchor maneuvers the contactor to a desired position.
In addition to one or more of the features described above, or as an alternative, further embodiments at least one of moving the second linkage relative to the first linkage and moving the anchor is operated remotely.
In addition to one or more of the features described above, or as an alternative, further embodiments the drive mechanism includes a pulley operably coupled to the second linkage, and a belt drive for driving moving the second linkage relative to the first linkage.
In addition to one or more of the features described above, or as an alternative, further embodiments the drive mechanism includes a hydraulic or pneumatic actuator.
In addition to one or more of the features described above, or as an alternative, further embodiments the anchor is arranged within a track.
In addition to one or more of the features described above, or as an alternative, further embodiments the second linkage is connected to an axle of the contactor.
In addition to one or more of the features described above, or as an alternative, further embodiments the contactor is a landing gear of an aircraft.
In addition to one or more of the features described above, or as an alternative, further embodiments the aircraft is a rotary wing aircraft.
In addition to one or more of the features described above, or as an alternative, further embodiments the aircraft is a fixed wing aircraft.
According to another embodiment, a method of maneuvering an aircraft into a desired position includes affixing a steering assembly to a contactor of the aircraft. The steering assembly includes an anchor, a first linkage connected to the anchor, and a second linkage coupled to the first linkage. The second linkage is moved relative to the first linkage to steer the contactor of the aircraft.
In addition to one or more of the features described above, or as an alternative, further embodiments the anchor is configured to move fore and aft with the aircraft, and wherein at least one of moving the second linkage relative to the first linkage and moving the anchor is controlled remotely.
In addition to one or more of the features described above, or as an alternative, further embodiments moving the second linkage is driven by a drive mechanism.
In addition to one or more of the features described above, or as an alternative, further embodiments the steering assembly is affixed to an axle of the contactor
In addition to one or more of the features described above, or as an alternative, further embodiments the second linkage is affixed to the contactor.
In addition to one or more of the features described above, or as an alternative, further embodiments at least one of moving the second linkage and moving the anchor is repeated.
The subject matter, which is regarded as the disclosure, is particularly pointed out and distinctly claimed in the claims at the conclusion of the specification. The foregoing and other features, and advantages of the disclosure are apparent from the following detailed description taken in conjunction with the accompanying drawings in which:
The detailed description explains embodiments of the disclosure, together with advantages and features, by way of example with reference to the drawings.
Referring now to
The steering assembly 30 additionally includes a first linkage 36 and a second linkage 38. The first linkage 36 is pivotally mounted at a first end 40 to the anchor 32 such that as the anchor 32 translates in a first direction, such as defined by track 34, the first linkage 36 may rotate relative thereto. A first end 42 of the second linkage 38 is configured to couple to a movable contactor 24, such as a landing gear of an aircraft 10. As shown, the distal end 42 of the second linkage 38 may include a gear interface 44 connectable to one or both sides of an axle 26 of the landing gear 24 adjacent the nose of the aircraft 10, to apply a force to the landing gear 24 to move the aircraft 10 in a desired direction. The second ends 46, 48 of the first linkage 36 and second linkage 38 are movably connected to one another, such as with a pin (not shown) for example. As a result of this connection between the first and second linkage 36, 38, the second linkage 38 may be movable, such as rotatable for example, between a retracted position, substantially parallel to and in a generally overlapping arrangement with the first linkage 36, and an extended position, where the second linkage 38 is arranged at an angle to the first linkage 36. The second linkage 38 may be arranged in the retracted position for storage, or when the steering assembly 30 is not in use.
A drive mechanism 50 is configured to drive rotation of the second linkage 38 relative to the first linkage 36 to move the landing gear 24 towards a desired position. In the illustrated, non-limiting embodiment, the drive mechanism 50 includes a motor 52 configured to drive a continuous belt or chain 54 about two or more pulleys or sprockets 56. Although illustrated as a separate component, in other embodiments, the motor 52 may be integrally formed into one of the pulleys 56. The motor 52 may be connected to external power source, illustrated schematically at P in
By mounting one of the pulleys or sprockets 56 at the connection between the first and second linkages 36, 38, operation of the motor 52, and therefore rotation of the pulley 56 driven by the belt 54, causes a similar rotation of the second linkage 38. In one embodiment, the motor 52 is configured to drive the belt 54 in a forward and backwards direction to move the second linkage 38 between the retracted and extended positions. It should be understood that the drive mechanism 50 illustrated and described herein is intended as an example only, and that other types of drive mechanisms 50, such as a hydraulic or pneumatic actuator for example, are also within the scope of the disclosure.
As best shown in
With reference again to
The steering assembly 30 illustrated and described herein is smaller, lighter weight, and more easily maneuvered than conventional steering systems. The remote operability of the steering assembly 30 eliminates the need for personnel on the deck after the initial set up of the steering assembly 30 is complete, resulting in increased safety to the operator. In addition, because the steering assembly does not couple to the aircraft tie down rings, the previous failure due to overloading of these rings is eliminated.
While the disclosure has been described in detail in connection with only a limited number of embodiments, it should be readily understood that the disclosure is not limited to such disclosed embodiments. Rather, the disclosure can be modified to incorporate any number of variations, alterations, substitutions or equivalent arrangements not heretofore described, but which are commensurate with the spirit and scope of the disclosure. Additionally, while various embodiments of the disclosure have been described, it is to be understood that aspects of the disclosure may include only some of the described embodiments. Accordingly, the disclosure is not to be seen as limited by the foregoing description, but is only limited by the scope of the appended claims.
This application claims the benefit of U.S. provisional patent application Ser. No. 62/293,115 filed Feb. 9, 2016, the entire contents of which are incorporated herein by reference.
This invention was made with Government support under Technology Investment Agreement No. W8470-01MP01/001. The Government has certain rights in the invention.
Number | Date | Country | |
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62293115 | Feb 2016 | US |