[0001] This application claims priority to U.S. Provisional Patent Application No. 61/61 1 158 filed on March 15, 2012 for "Vehicle Hook-Up Assembly," the entire contents of which are incorporated herein by reference.

BACKGROUND

[0002] Current practice with helicopter sling loads requires at least two individuals to be stationed directly beneath the helicopter to connect the load. Typically, one person uses a static discharge wand to prevent electric shock while the other attaches the apex fitting to the helicopter hook. Eliminating these individual roles will clearly increase safety and efficiency, and reduce cost.

[0003] No mechanical or electromechanical coupling system is currently available to allow for automatically attaching a sling load to a helicopter without manual manipulation of components. Pilotless operation of helicopters is currently inhibited by restrictions on flying pilotless helicopters in close proximity to personnel. Existing magnetic lifting rigs are not suitable for this application because of their weight and power requirements. The disclosed vehicle hook-up assembly allows for automatic connection of a sling load to vehicle, such as a helicopter, without requiring station personnel to be positioned in dangerous situations, such as underneath the helicopter, during the hook-up operation.

SUMMARY

[0004] The preferred embodiment of the hook-up assembly is used with helicopters and will be discussed relative thereto. However, embodiments can be configured for use with other suitable vehicles for transport. The disclosed hook-up assembly is operated by first attaching the pendant assembly to the helicopter hook. Employing the pendant in this manner allows the helicopter crew to more easily judge the distance between the connecting components than if the fitting were attached directly to the helicopter's cargo hook. It also allows greater flexibility and reduces the potential for the helicopter to collide with the payload.

[0005] A receiver assembly is attached to the payload fitting slings in place of the current apex fitting. The depicted receiver assembly includes a coil for generating a magnetic field and a mechanical linkage to lock the pendant male fitting in place. The coil can optionally be replaced with another magnetic field generating unit as known in the art. The receiver assembly is then typically positioned on or near the load.

[0006] With reference to the progression shown in Figures 2-6, the helicopter typically maneuvers the male fitting on the end of the pendant into range of the magnetic field generated by the receiver coil. A mechanical guide structure may optionally be installed on the receiver to aid this operation. Once the pendant is within range of the magnetic field, the magnetic pull draws it into the locking position. The linkage locks the pendant and receiver together, thereby allowing the payload to be lifted. The coil can be de-energized as soon as the pendant and receiver are locked. The payload can then be jettisoned or released using the helicopter cargo hook as typically done in the industry.

[0007] In another embodiment, the power supply can be carried on board the aircraft while the receiver assembly is suspended from the pendant with the male fitting on the payload. This embodiment functions similarly to the previous embodiment, but carries the additional advantage of allowing multistep pickups and drop offs without the need for ground crew. An additional advantage of the inventive hook-up assembly is that it allows for both vertical and horizontal approach paths.

[0008] As previously noted, a guidance system can be employed to assist in improving accuracy of alignment of the pendant and receiving unit. A guidance system can include an onboard sensor communicatively associated with a feedback display system configured to allow the helicopter pilot to view real time data of the aircraft's position and proximity to the receiver coil. A preferred embodiment of the guidance system includes a video camera capable of providing additional information such as the presence and location of personnel or hazards. The sensor/feedback system can be integrated into the helicopter avionics or function as a standalone module. [0009] Various mechanical coupling systems which feature a mechanical guide exist in the prior art (for example, a fifth wheel trailer coupling).

[0010] The individuals stationed underneath the helicopter during pickups by known methods face a variety of serious risks including being struck, crushed or electrically shocked. The inventive system eliminates these safety risks while lowering cost for each sling load by reducing required manpower. Use of the sensor and feedback component of the system could potentially reduce or eliminate the need for additional personnel.

BRIEF DESCRIPTION OF THE DRAWINGS

[0011] Figure 1 shows a perspective view of a preferred embodiment of the disclosed hook-up assembly; and

[0012] Figure 2 shows a helicopter beginning an approach to a payload, employing the disclosed hook-up assembly;

[0013] Figure 3 shows the pendant fitting and receiver assembly of the disclosed hook-up assembly being drawn together via magnetic forces;

[0014] Figure 4 shows the pendant fitting mechanically attached to the receiver assembly;

[0015] Figure 5 shows the hook-up assembly in use, with a helicopter beginning departure with a secured payload; and

[0016] Figure 6 shows the hook-up assembly in use, with the helicopter transporting a secured payload.

DETAILED DESCRIPTION

[0017] As can be seen in Figure 1 , an embodiment of the inventive hook-up system 10 comprises a pendant assembly 12 configured for mating with a receiver assembly 14. Embodiments also include a guidance system (described in further detail below; not depicted in Figure 1 ). As shown, one preferred embodiment of the pendant assembly 12 includes a line 16 which extends from a proximal end having an eye 18 to a distal end with a fitting element 20. This specific configuration of the pendant assembly 12 is obviously not limiting. [0018] The line or cable 16 can comprise natural or synthetic fibers as known in the field, as appropriate for the desired or required maximum weight capacity of the load to be transported. The eye 18 is preferably sized to interface with a cargo hook commonly found on helicopters. The eye 18 can be formed as a loop in the cable 16 or a separate component and securely attached to the cable.

[0019] With further reference to Figure 1 , the fitting element 20 of the pendant is sized and shaped to mate and lock into a portion of the receiver 14 during typical operation. The fitting element 20 is typically made of a steel alloy having a size, contour and strength appropriate for the desired maximum payload capacity for the particular system. The fitting element 20 can also incorporate a flange 22 for assisting in mechanically locking the pendant fitting 20 into a portion of the receiver assembly 14, and thereafter lifting the load 24, as well as an interfacing with the cable 16. The flange 22 can include an optimally angled lower face for aiding entry into and engagement with the coupler, as will be discussed below.

[0020] As shown in Figure 1 , the receiver assembly 14 comprises a coupling mechanism 26 supported on a base 28. The coupling mechanism 26 is preferably secured via an appropriate interface to a suspension sling 42 (see Figures 5 and 6) or similar element for carrying a load. A power source 31 is electrically connected to a magnetic coil 30 positioned within the coupling mechanism 26 or base 28. Notably, the power source can be positioned physically separated from the receiver assembly 14, as depicted in Figure 1 , or connected therewith. Another embodiment exists wherein the power source is positioned on board the aircraft with an electrical connection to the pendant, as opposed to the coupling mechanism, as will be discussed further below.

[0021] A physical guide element, such as a track, may optionally be included for assisting in an efficient and secure mating between the coupling mechanism 26 and the pendant fitting 20. The coupling mechanism 26 preferably includes a coil assembly 30 or similar element for generating a magnetic field when energized (by the power source 30 in this embodiment). The physical guide may also be employed to assist initial positioning of the pendant 20 within appropriate range of the magnetic field. A mechanical mating unit locks the male fitting flange in place once it is drawn into position by the magnetic field.

[0022] In this embodiment, the mating unit comprises a plurality of peripheral clamping members 32 with teeth 34 extending inwardly. The clamping members 32 are configured to flex outwardly when the pendant fitting 20 is drawn to the coil 30 by the force of the pendant and flange 22 to accommodate at least a portion of the ridge defined by the flange. Once the flange 22 passes the teeth 34, the clamping members 32 return to their initial position (depicted in Figure 1 ) mechanically locking the pendant fitting 20 to the coupler 26 via the overlapping mating interface of the teeth 34 and flange 22. Preferably, the inner contour of the coupler 26 is sized and shaped to correspond generally to the outer contour of the pendant fitting 20, thereby assisting in creating a stronger and more reliable connection.

[0023] In another embodiment, the mechanical linkage between the flexing clamping members 32 and pendant 20 is adapted to an actuated linkage system to lock the pendant 20 with the coupler 26. For example, an electronic controller may be provided in electrical connection with the coupler 26. As the pendant 12 approaches the payload 24 and receiver, the controller is activated and actuates the clamping members 32 outward to an opened position to accommodate entry of the pendant 20 into the coupler 26. Once the pendant flange 22 is appropriately within the interior space of the coupler 26, the clamping members 32 are actuated inwardly to a closed position mechanically mating the pendant 20 with the coupler 26 by way of the teeth 34 locking the flange 22 from above. The controller can be manually activated or automatic (i.e., the controller sends a signal to close the clamping members 32 upon detection of the pendant fitting 20 in a predetermined position relative to the coupler 26).

[0024] As shown, the receiver assembly 14 also includes a base 28 to assist in properly positioning the receiver assembly relative to the payload 24 in a position allowing sufficient access to the coupler 26 for receipt of the pendant 20. The base 28 (and therefore receiver assembly 14) may be mounted or secured on the payload 24 (shown) or free-standing in close proximity to the payload (not shown). In a preferred embodiment, the receiver assembly 14 is securely attached (often at the base 28) to a suspension sling or cargo net 42 for lifting the payload 24 after attachment of the pendant 12 to the receiver assembly 14. The depicted embodiment of cooperating male pendant fitting 12 and female coupler 26 has been shown to be advantageous because the parts are shaped and sized to mate without necessitating manual manipulation. Other embodiments exist that employ different mechanical connection configurations between the pendant and coupler, such as latching, clasping, hooking and the like.

[0025] As described above, in this embodiment, the magnetic coil 30 is energized by activation of a power source 31 . Of course other suitable tools for activating a magnetic field generator may be employed in place of the power supply 31 . The power supply 31 and coil 30 are typically configured to cooperate appropriately to generate a predetermined size and intensity of the magnetic field. Any known power source, such as for example vehicle, generator, or battery, can be employed to supply power to the coil 30. A break-away electrical connection 36 can be positioned appropriately between the power source 31 and coil 30 to allow lifting of the payload 24 and physically disengagement from the power supply 30 without damaging the system. To reduce the mass of a payload or helicopter, it can be advantageous to employ a disengagable external power supply rather than an on-board or attached power supply.

[0026] In another embodiment, a receiver assembly similar to that depicted as reference numeral 14 is aircraft mounted with power supplied to the coil from the aircraft. In this embodiment, the pendant (with male fitting) is mounted on the support structure with the payload— i.e., the male magnetically attractive pendant fitting and the magnetic field generating element in the receiver are reversed from the depiction of Figure 1 . Operation of the system is otherwise similar to the previous embodiments.

[0027] A preferred guidance system for use with the disclosed hook-up system comprises a sensor element or package and a user interface or display. A sensor package can include a live-feed camera as well as additional sensing elements to assist an aircraft crew with guiding the pendant to the receiver assembly according to the herein description and Figures. Mounting for the sensor package can be tailored to each aircraft being used with the disclosed system. By mounting the sensor package, the need for modification to the aircraft frame is thereby minimized. The user interface may consist of a standalone tablet form factor or other unit used in the industry, which provides visual and/or audio direction to allow the aircraft pilot to guide the pendant toward the receiver. Alternately, the user interface may be integrated into the aircraft's standard avionics.

[0028] Figures 2-6 collectively depict a typical operation of the disclosed hook-up system 10 including approach, attachment and then transport of a payload. The pendant 12 is attached extending from the aircraft (i.e., helicopter) 40. At a predetermined point in time, the power source 31 connected to the coupler coil 30 is activated to energize the coil and generate a magnetic field (identified generally as reference figure M). Here, the guidance system, identified generally as reference figure G, assists a pilot in guiding the helicopter 40 to position the pendant fitting 20 within range of the magnetic field M.

[0029] As shown in Figure 3, the magnetically attractive pendant fitting

30 is drawn to the coupler 26 by the magnetic field M for attachment therewith, as discussed in detail above.

[0030] Figure 4 depicts the system 10 in the attached position with the pendant fitting 20 mated mechanically with the coupler 26 prior to the helicopter 40 lifting the payload 24 for transport.

[0031] Figure 5 shows initial lift of the pendant fitting 20 and attached coupler 26. In this embodiment, the coupler 26 is attached to the cargo net 42 and disengagable from the base 28. As depicted, the base 28 remains securely on the interior of the cargo net 42 after the coupler 26 disengages from base 28. The base 28 can be fixed on the surface of the payload 24. In this embodiment, the coil 30 is fixed to the base 28 and disengagable from the coupler 26. Once the pendant fitting 20 is mechanically attached to the coupler 26 by engagement with the clamping members 32, the power source

31 is deactivated, thereby de-energizing the coil 30 and the magnetic field. Deactivation of the magnetic field M allows the mechanically attached coupler 26 and pendant fitting 20 to disengage from the base and coil portion of the receiver assembly 14. The payload 24 is then maintained and carried by mechanical forces. [0032] Notably, other embodiments exist wherein the coil portion of the receiver assembly 14 disengages from the base 28 along with the coupler 26 and attached pendant fitting 20. In such embodiments, the coil 30 can be de- energized by deactivation of the power source prior to the coupler 26 and coil 30 being lifted by the mechanically attached pendant fitting 20. Alternatively, in the case of an on board power source, the coil 28 can remain energized, the magnetic forces thereby assisting the secure mechanical connection between the coupler 26 and pendant fitting 20.

[0033] Figure 6 depicts the helicopter 40 in flight with the payload 24 securely held in the cargo net 42. As shown, the pendant fitting 20 and coupler 26 remain mechanically attached as described above, while the power supply disengages by way of the breakaway connector (not depicted in Figure 6). The receiver assembly base 28 remains attached to the surface of the payload 24.

[0034] While a preferred embodiment has been set forth for purposes of illustration, the foregoing description should not be deemed a limitation of the invention herein. Accordingly, various modifications, adaptations and alternatives may occur to one skilled in the art without departing from the spirit of the invention and scope of the claimed coverage.