Aeronautics and astronautics – Aircraft structure – Passenger or cargo loading or discharging
Reexamination Certificate
1998-10-16
2001-02-20
Poon, Peter M. (Department: 3644)
Aeronautics and astronautics
Aircraft structure
Passenger or cargo loading or discharging
C244S137400, C244S118100
Reexamination Certificate
active
06189834
ABSTRACT:
BACKGROUND OF THE INVENTION
1. Field of the Invention
The present invention relates generally to systems for transporting payloads on aircraft. More specifically, the invention relates to a system for attaching and selectively releasing multiple cargo payloads which are transported by being suspended beneath an aircraft such as a helicopter.
2. Relevant Technology
Aircraft such as helicopters have long been used to deliver payloads of different size and shape. Traditionally, a cable is suspended from a helicopter with a hook attached to one end of the cable. By attaching the hook to a payload, the helicopter is able to transport the payload to a desired location. Suspending the payload beneath a helicopter permits the helicopter to transport oversized cargo, such as a jeep or other large hardware.
Furthermore, the helicopter is able to deliver the payload to unique and specific locations, such as on top of a building or in rugged terrain, where an airplane could not land. In addition, the use of a suspended cable permits the helicopter to deliver or recive cargo without actually having to land. By lowering the cable, a receiving party can remove or attach a payload to the hook. This is most beneficial with regard to emergency rescues and in delivering payloads in congested areas.
Although there are numerous benefits in using a conventional hook and cable assembly to deliver a payload suspended beneath a helicopter, several shortcomings are also found. For example, using a single cable and hook assembly typically permits the transport of only a single payload per flight. Such an assembly necessitates numerous flights, costing both time and money, to deliver multiple payloads which cannot simultaneously be attached to a single hook.
Furthermore, to remove a payload from a conventional hook and cable assembly, either the helicopter must land or the payload must be lowered to the ground and manually removed from the hook. Such procedures require both a certain amount of time and the necessity of a receiving party at the unloading location to remove the payload. The necessity of a receiving party to remove the payload is detrimental in an emergency situation where it is preferable to jettison the payload during flight or where it is desirable to release a payload at a location where there is no receiving party.
In an attempt to alleviate these problems, carrousel hook systems have been made. The carrousel hook systems comprise a frame having a plurality of hooks attached thereto. The frame is suspended from a helicopter by a support cable. Likewise, an electrical cable extends from the helicopter to each of the hooks. By triggering a switch within the helicopter, the hooks can be consecutively opened, thereby releasing the attached loads.
Several problems or shortcomings, however, have also been encountered with carrousel hook systems. Forces such as the wind and movement of the aircraft can result in rotation of the carrousel frame which in turn applies a torsional force on the support cables and the helicopter. Such a force can damage the cables and the connection to the helicopter. Likewise, the torsional force can affect the navigation ability of the helicopter.
Conventional carrousel systems are also designed to carry multiple payloads so that the frame is evenly balanced. When only a single load is being carried, the unbalanced force of the payload can produce detrimental stresses on the frame.
Carrousel systems also have the drawback in that the hooks can only be activated consecutively and not selectively. That is, carrousel hooks can only be opened in sequential order. At times, it is desirable to be able to selectively open any desired hook.
Finally, an additional problem with some carrousel systems is that they are difficult to transport other than below a helicopter. That is, carrousel systems are often too big to fit within a helicopter or in the bed of a pickup truck. Since helicopters travel slower when the carrousel system is suspended below, it is desirable to be able to store the system within the helicopter when it is not required.
Accordingly, there is a need for an improved system for transporting cargo suspended from an aircraft that overcomes or avoids the above problems.
OBJECTS AND BRIEF SUMMARY OF THE INVENTION
Accordingly, it is an object of the present invention to provide a system for carrying and selectively releasing multiple payloads suspended from an aircraft.
A further object of the invention is to provide an apparatus for carrying payloads that can rotate freely along with the payloads relative to a connecting cable when suspended from an aircraft, thereby preventing a torsional force from being applied to the cable, aircraft, and apparatus.
Another object of the present invention is to provide an apparatus as above wherein the frame of the system is configured to carry one or several payloads while minimizing stresses and particularly moment arm forces on the frame.
Finally, another object of the present invention is to provide apparatus as above which are large enough to carry multiple payloads but which can be easily collapsed so as to fit within a helicopter or in the back of pickup truck.
To achieve the forgoing objectives and in accordance with the invention as disclosed herein, a cargo management system is provided. The cargo management system includes an elongated support cable configured for suspension from a helicopter and an airframe removably attached to the end of the support cable. The airframe includes a collapsible loading frame that is coupled with the support cable through a hub assembly. The loading frame is configured having a stabilized open position and a collapsed closed position. The loading frame is constructed from a plurality of horizontal struts interconnected at corner assemblies in a horizontal plane. A plurality of vertical struts project from each corner assembly to the hub assembly.
In the open position, the loading frame has a substantially tetrahedral shape. The loading frame has various hinged portions to allow the loading frame to fold into the closed position. For example, the lower struts are each formed with a hinged middle portion. Furthermore, each end of the horizontal and vertical struts is hingedly attached to a corner assembly or the hub assembly.
The hub assembly includes a spindle assembly coupled with an attachment assembly by a universal joint. The attachment assembly comprises brackets that are coupled with the upper end of the vertical struts. The spindle assembly is configured to facilitate annular rotation of the loading frame and the universal joint relative to the to the support cable. The spindle is attached to the support cable by a shackle having a load cell coupled therewith.
The universal joint permits pivoting movement of the load frame relative to the spindle assembly. The universal joint pivots around a central point. Each of the vertical struts has a longitudinal axis that intersects with the central point. As such, moment arm stresses are reduced on the load frame.
In one embodiment, a center strut vertically extends down from the attachment assembly. Connected to the end of the center strut is an electrically operated payload hook. A plurality of hinged tension members extend from the center strut to each of the corner assemblies.
Also attached to each corner assembly is an electrically controlled payload hook that is capable of attaching and selectively releasing a payload. Each payload hook is attached to the corner assembly by a universal joint which enables the payload hook to maintain a substantially vertical orientation as the loading frame is tilted. Each universal joint bends at a load point. The longitudinal axis of each vertical strut and each horizontal strut intersects with the load point, thereby further minimizing any moment arm forces on the load frame.
A plurality of support legs are rotatably attached to the loading frame. The support legs can be selectively moved and locked into a variety of different positions depending on the intended use of the airframe.
The p
Cox Donald P.
Dietz Phillip
Haroldsen James T.
Dinh Tien
Kirton & McConkie
Krieger Michael F.
Poon Peter M.
Skyhook Technologies, Inc.
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