| (11) | EP 2 527 256 B1 |
| (12) | EUROPEAN PATENT SPECIFICATION |
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| (54) | Aerial refuelling drogue deployment system Fangtrichterausfahrsystem für Luftbetankung Système de déploiement de cône de ravitaillement en vol |
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| Note: Within nine months from the publication of the mention of the grant of the European patent, any person may give notice to the European Patent Office of opposition to the European patent granted. Notice of opposition shall be filed in a written reasoned statement. It shall not be deemed to have been filed until the opposition fee has been paid. (Art. 99(1) European Patent Convention). |
Background
[0001] Tanker aircraft are conventionally configured with a primary purpose of refueling other aircraft inflight. Due to this mission, conventional tanker aircraft are designed and manufactured to maximize the quantity of fuel stored, which includes accommodating multiple large fuel storage tanks and the corresponding fuel transfer infrastructure for refueling aircraft inflight. While aerial refueling operations are often desirable for military and potentially civilian purposes, the cost of dedicated tanker aircraft can be significant considering that the tanker aircraft may not be practical or ideally configured for missions apart from aerial refueling operations.
[0002] It is with respect to these considerations and others that the disclosure made herein is presented.
[0003] WO 02/24529 in its abstract states an integration approach in the configuration, capability, and side door, hatch, or other removable pressurized plugs, useful for mounting and operating various types of roll on roll off airborne refueling systems, spraying systems, dry particulate diffusion systems, and fluid spray dispersal systems for use with aircraft in support of search and rescue operations and other mission.
Summary
[0005] In one aspect, there is provided a system as defined in claim 1. In another aspect, there is provided a method as defined in claim 8.
Brief Description Of The Drawings
[0006]
FIGURE 1 is a block diagram of a non-tanker aircraft and drogue deployment system according to various embodiments presented herein;
FIGURE 2 is a side view of a non-tanker aircraft showing a drogue deployment system in a stowed configuration according to various embodiments presented herein;
FIGURE 3 is a side view of a non-tanker aircraft showing a drogue deployment system in a deployed configuration according to various embodiments presented herein;
FIGURE 4 is a perspective view of a drogue deployment system in a deployed configuration according to various embodiments presented herein;
FIGURE 5 is a perspective view of a drogue deployment unit in a deployed configuration according to various embodiments presented herein;
FIGURE 6 is a perspective view of a drogue deployment unit in a stowed configuration according to various embodiments presented herein;
FIGURE 7 is a flow diagram showing a method of providing aerial refueling operations with a non-tanker aircraft according to various embodiments presented herein; and
FIGURE 8 is a computer architecture diagram showing an illustrative computer hardware and software architecture for a computing system capable of implementing the embodiments presented herein.
Detailed Description
[0007] The following detailed description is directed to an aerial refueling drogue deployment system that may be retrofitted to conventional passenger and cargo aircraft to temporarily convert the aircraft for use as a tanker. As discussed above, since conventional tanker aircraft are not practical for transporting passengers and/or cargo in an efficient manner, tanker aircraft that are dedicated to aerial refueling duty may be a costly solution when aerial refueling is not a consistent concern.
[0008] Utilizing the concepts and technologies described herein, a drogue deployment system may be temporarily installed within a traditional passenger or cargo aircraft to convert the aircraft for use as an aerial refueling tanker. When refueling missions are complete, the drogue deployment system may be readily removed, returning the aircraft to a passenger or cargo transport configuration. In this manner, the drogue deployment system provides a solution to a need for part-time aerial refueling capabilities at significantly less cost than purchasing and maintaining a dedicated tanker aircraft.
[0009] In the following detailed description, references are made to the accompanying drawings that form a part hereof, and which are shown by way of illustration, specific embodiments, or examples. Referring now to the drawings, in which like numerals represent like elements through the several figures, an aerial refueling drogue deployment system and method for installing and employing the same according to the various embodiments will be described.
[0010] FIGURE 1 shows a simplified diagram of a non-tanker aircraft 102 and corresponding drogue deployment system 130 according to the embodiments described herein. For the purposes of this disclosure, the "non-tanker" aircraft 102 (generally referred to below as "aircraft 102") may be any conventional passenger or cargo aircraft having been designed primarily for operations that do not include aerial refueling, but is capable of modification to perform aerial refueling operations utilizing the systems and methods described below. The aircraft 102 may include an airframe 104, a number of systems 106, and an interior space 108. The airframe 104 includes aircraft wings 110 and a fuselage 112. Examples of high-level systems 106 include, but are not limited to, a propulsion system 116, an electrical system 118, a hydraulic system 120, and a computing system 122. The computing system 122 may be functional to control any of the other aircraft systems 106 in the manners described below.
[0011] The aircraft 102 includes a fuel system 124 having any number of fuel tanks 126 and fuel system components 128. The fuel system components 128 may include any type and number of components used to provide fuel from the fuel tanks 126 to the propulsion system 116, including but not limited to, fuel lines, pumps, sensors, valves, vents, and any other necessary or desired fuel system elements. According to the embodiments described herein, a drogue deployment system 130 may be temporarily attached to the aircraft fuel system 124 to provide the aircraft with aerial refueling capabilities. As will be described below, components of the drogue deployment system 130 may be attached to the exterior of the fuselage 112, as well as having components disposed within the interior space 108.
[0012] It should be appreciated that for the purposes of this disclosure, a "temporary attachment" or coupling of components refers to components that may be secured together using bolts, screws, fasteners, or any other securing means that would allow for repeated installation and removal of the components according to the currently assigned mission of the aircraft. Similarly, "permanent attachment" may refer to the coupling of components that will remain coupled together for all missions of the aircraft, both conventional uses and aerial refueling uses. For example, as will be described below, the primary components of the drogue deployment system 130 may be temporarily attached to the aircraft 102 to enable aerial refueling capabilities, while some minor components, such as fuel lines that couple the drogue deployment system 130 to the aircraft fuel tanks 126 may be permanently attached so that they remain with the aircraft 102 during all operations.
[0013] The drogue deployment system 130 may include any number of components, but for the purposes of this disclosure, will be discussed with respect to three units. Specifically, the drogue deployment system 130 may include a drum unit 132, a drogue deployment unit 134, and a control unit 136. As will be discussed in greater detail below, the drum unit 132 may include a retraction and deployment mechanism for the drogue hose, as well as any associated fuel pumps, pressure regulators, and control mechanisms. The drum unit 132 may be palletized and capable of rolling on and off the aircraft as needed. The drogue deployment unit 134 may be temporarily attached to the fuselage 112 and configured to rotate downward and away from the aircraft 102 to allow for separation between the drogue and the aircraft for deployment of the drogue during refueling operations. The control unit 136 may be a "suitcase" style control unit that provides the Aerial Refueling Operator (ARO) with all control functions for the drogue deployment system 130.
[0014] FIGURE 2 shows a side view of an aircraft 102 with an installed drogue deployment system 130 in a stowed configuration according to various embodiments described herein. This example shows the drogue deployment system 130 in the stowed configuration in which the drogue deployment unit 134 is retracted against the external surface of the fuselage 112. FIGURE 3 shows the aircraft 102 with the drogue deployment system 130 in a deployed configuration. When deployed, portions of the drogue deployment unit 134 extend downward away from the fuselage 112 to create a separation between the unit and the aircraft 102. The drogue 302 is positioned at a distal end of the refueling hose 304 and is configured to receive a corresponding refueling probe of an aircraft receiving fuel. The refueling hose 304 is unrolled, or otherwise deployed, from the drum unit 132 and extends from the distal end of the drogue deployment unit 134 to extend the drogue 302 rearward to a distance and position with respect to the aircraft 102 that is safe for refueling operations. The specific components and operational details of the drogue deployment system 130 will now be discussed in greater detail with respect to FIGURES 4-8.
[0015] Turning to FIGURE 4, a perspective view of the drogue deployment system 130 is shown according to various embodiments. As described above, the drogue deployment system 130 may include a drum unit 132, a drogue deployment unit 134, and a control unit 136. The drum unit 132 may include a housing 402 that encompasses a drum 404. The drum 404 may be driven by a motor, drum actuator, or other actuation mechanism (not shown) to selectively rotate in opposite directions to alternatively unroll and roll a refueling hose 304 that is coiled around the drum 404. Unrolling the refueling hose 304 allows the drogue 302 to deploy rearward into position for refueling a receiving aircraft. Rotating the drum 404 in a direction that rolls the refueling hose 304 retracts the drogue 302 into a stowed position abutting or within a drogue container 424.
[0016] The drogue deployment unit 134 includes an actuation mechanism housing 420, a drogue extension tube 422, the drogue container 424, and the drogue 302, as well as various other actuation and linkage components described below. The actuation mechanism housing 420 includes actuation components 426 that are configured to selectively deploy and retract the drogue extension tube 422. Example actuation components 426 will be described below with respect to the embodiment shown in FIGURE 5.
[0017] According to various implementations, the drum unit 132 may be configured in a relatively compact shape and size within the housing 402 to allow the drum unit 132 to be palletized for quick and efficient loading and installation within the cargo space or other interior space 108 of a passenger or cargo aircraft 102. The housing 402 may include the appropriate fuel line fittings and electrical/communication connections to couple the palletized drum unit 132 to the fuel system 124 of the aircraft 102, as well as to the installed drogue deployment unit 134 and control unit 136. According to one embodiment, the drum unit 132 may be positioned within the aft lower lobe cargo area of the aircraft 102 and connected to the center wing fuel tank 126 via fuel system plumbing. The fuel system plumbing may incorporate a permanently or fixedly installed single-walled fuel manifold 410 that is installed within the unpressurized portions of the aircraft 102. The single-walled fuel manifold 410 provides a passage for the fuel from the center wing fuel tank 126 to a fitting within the applicable pressurized cargo area.
[0018] According to various embodiments, the single-walled fuel manifold 410 is removably coupled to the refueling hose 304 within the drum unit 132 in the pressurized lower lobe cargo area via a double-walled fuel manifold 408. The removable double-walled fuel manifold 408 may be located between the forward wall of the cargo area and the drum unit 132 such that the drum unit 132 may be rolled or otherwise loaded into the cargo area, and then connected to the single-walled fuel manifold 410 within the unpressurized area of the aircraft 102 utilizing the removable double-walled fuel manifold 408. It should be appreciated that the double-walled fuel manifold 408 may be permanently coupled to the drum unit 132 and removably coupled to the single-walled fuel manifold 410, or may be removably coupled to both the single-walled fuel manifold 410 and the drum unit 132. Any type of known coupling mechanisms may be utilized for removably coupling components as described above. It should also be understood that the fuel manifolds and other components may be single walled or double walled within the scope of this disclosure and are described as being single walled or double walled due to their respective positioning within unpressurized and pressurized portions of the aircraft 102, respectively, according to current safety regulations and/or practices.
[0019] A shutoff valve 412 may be positioned within the fuel system 124 in the unpressurized area to control the flow of fuel from the center wing fuel tank 126 to the drum unit 132. In addition, a vacuum relief check valve 408 and associated plumbing may be installed in the unpressurized area to allow for drainage of fuel contained within the single-walled fuel manifold 410 when the shutoff valve 412 is closed. Although a shutoff valve 412 and vacuum relief check valve 414 are shown and described herein, any type and number of fuel system components 128 may be utilized with respect to permanent installation within the aircraft 102 and/or temporary installation with the drogue deployment system 130 to facilitate fuel transfer between the aircraft fuel tanks 126 and the drogue deployment system 130. Similarly, the drum unit 132 may further include any number and types of fuel pumps, pressure regulators, and other suitable control mechanisms for controlling the delivery of fuel from the aircraft fuel tanks 126 and through the refueling hose 304 to the drogue 302.
[0020] The drogue deployment system 130 may be communicatively coupled to the control unit 136. This coupling may be wired or wireless. As described briefly above, the control unit 136 according to one implementation includes a suitcase-style configuration in which the controls or the drogue deployment system 130 are located within a self-contained, portable case or other packaging. In this manner, the control unit 136 may be referred to as "portable." The control unit 136 may include a laptop computer or other processing means, as well as any number and type of associated input or output devices such as a mouse, a joystick, and control activation buttons for controlling the deployment and retraction of the drogue extension tube 422 and the refueling hose 304 and corresponding drogue 302. The control unit 136 may be utilized to control power input to the drogue deployment system 130 and associated one or more pumps, valves, pressure regulators, motors, actuators, and other associated components utilized to control the drogue deployment system 130 in the manner described herein. For example, the control unit 136 may be operative to activate and deactivate the drum actuation mechanism for deploying and retracting the refueling hose 304, and similarly operative to activate and deactivate the drogue extension tube actuation mechanism for deploying and retracting the drogue extension tube 422.
[0021] According to various embodiments, the control unit 136 may be "plugged in" within the aircraft cockpit or other desired location in order to communicate with the various components of the drogue deployment system 130 to allow the ARO to control deployment, retraction, fuel transfer, and any other operations of the drogue deployment system 130. According to one embodiment, a cable bundle may be installed within the aircraft 102 that spans between the cockpit or desired ARO working location and the cargo area in which the drum unit 132 will be secured, which is proximate to the fuselage location in which the drogue deployment unit 134 will be installed. When these drogue deployment system 130 components are installed, they may simply be plugged into the cable bundle (not shown) to provide communications capability between the control unit 136 and the other drogue deployment system 130 components. The control unit 136 may be plugged into the onboard electrical power. By including all communication and control cables within the cable bundle, the drogue deployment system 130 does not interface with the aircraft 102 except to for powering the various system components. In this manner, design, fabrication, procurement, and training costs are minimized. The various embodiments may additionally include one or more cameras at the drogue deployment unit 134 to provide real time visual confirmation of the deployment and retraction status of the drogue extension tube 422, refueling hose 304, and drogue 302. Any number and type of sensors may be utilized to monitor the status of the various drogue deployment system 130 components and to alert the ARO accordingly. These video and/or audio components may communicate with the control unit 136 via the above-described cable bundle. The control unit 136 will be described in further detail below with respect to FIGURE 8.
[0022] Turning now to FIGURE 5, a perspective view of the drogue deployment unit 134 is shown. As previously mentioned, the drogue deployment unit 134 includes the actuation mechanism housing 420, a drogue extension tube 422, the drogue container 424, and the drogue 302, as well as any number and type of actuation components 426 that are configured to selectively deploy and retract the drogue extension tube 422.
[0023] The actuation components 426 include an actuator 502 that rotates a drive screw 504. The drive screw 504 drives a carriage assembly 506 linearly along guide rods 508. Two extension rods 510 are coupled at one end to the carriage assembly 506 and at opposing ends to the drogue extension tube 422. The actuator 502 may be electric, or may alternatively be a hydraulic, pneumatic, electromagnetic, or any other type of suitable actuation device.
[0024] When the drogue deployment unit 134 is in the stowed configuration and the actuator 502 is activated, the drive screw 504 rotates in a direction that moves the carriage assembly 506 along the guide rods 508 toward the actuator 502. Doing so applies a force to the extension rods 510 connected to the carriage assembly 506. Because the drogue extension tube 422 is rotatably attached to the actuation mechanism housing 420 at a fixed pivot end 516, the force applied to the extension rods 510 rotates the drogue extension tube 422 downward away from the actuation mechanism housing 420 and the aircraft 102.
[0025] According to various embodiments, when the drogue extension tube 422 rotates downward, the drogue container 424 attached to the distal end 518 of the drogue extension tube 422 pivots to maintain an orientation substantially parallel with the ambient airflow. To maintain the orientation of the drogue container 424 while the drogue extension tube 422 is rotating between the stowed and deployed configurations, the drogue deployment unit 134 may contain one or more drogue container rods 512. The drogue container rods 512 are rotatably attached at one end to the actuation mechanism housing 520 and at opposing ends to aft pivot fittings 514. The aft pivot fittings 514 are fixedly attached to the drogue container 424. When the drogue container rods 512 rotate downward, the aft pivot ends 514 are rotated rearward due to the fixed length of the drogue container rods 512 at a rate that approximately maintains the orientation of the drogue container 424.
[0026] The actuation mechanism housing 420 may be attached and detached to and from the aircraft fuselage 112 using bolts or other fasteners. Embodiments may include permanently installed structural attachment features (not shown) on the aircraft fuselage 112 to which the actuation mechanism housing 420 may be temporarily attached for use when refueling operations are desired. It should be appreciated that the drogue extension tube 422 provides a passageway for the refueling hose 304 and may be sized and shaped accordingly. Similarly, the drogue container 424 provides a stowage location for the drogue 302. The drogue container 424 may be configured to completely encompass the drogue 302 such that the drogue 302 is positioned entirely inside the drogue container 424 when stowed. Alternatively, the drogue container 424 may be configured to partially house the drogue 302 such that at least a portion of the drogue 302 abuts the drogue 302 but remains partially outside of the drogue container 424 when stowed.
[0027] FIGURE 6 shows a perspective view of the drogue deployment unit 134 in the stowed configuration. As seen here, the carriage assembly 506 is positioned at the ends of the guide rods 508 opposite the actuator 502. When the drogue deployment unit 134 is in the deployed configuration as shown in FIGURE 5 and the actuator 502 is activated, the drive screw 504 rotates in a direction that moves the carriage assembly 506 along the guide rods 508 away from the actuator 502. Doing so pulls on the extension rods 510 connected to the carriage assembly 506, pulling the drogue extension tube 422 upward to the stowed configuration.
[0028] Turning now to FIGURE 7, an illustrative routine 700 for providing aerial refueling operations with a non-tanker aircraft will now be described in detail. It should be appreciated that more or fewer operations may be performed than shown in the figures and described herein. These operations may also be performed in a different order than those described herein.
[0029] The routine 700 begins at operation 702, where any permanent conversion fixtures are installed within the aircraft 102 to facilitate the temporary conversions of the aircraft 102 to and from aerial refueling operational configurations. Examples of these permanent conversion fixtures may include the single-walled fuel manifold 410 and corresponding shutoff valve 412 and vacuum relief check valve 414 discussed above, which provides fuel from the aircraft fuel tanks 126 to the drum unit 132 when the drum unit 132 is installed within the cargo space. Another example of a permanent conversion fixture may be the attachment hardware on the exterior surface of the fuselage 112 that allows for the temporary connection of the drogue deployment unit 134 during aerial refueling operations. Further examples may include any electrical and communications cables between the cargo area or other installation area of the drogue deployment system 130 and the cockpit or other desired location in which the ARO will be conducting inflight refueling operations
[0030] From operation 702, the routine 700 continues to operation 704, where the drum unit 132 is loaded into the cargo space of the aircraft 102, secured in place, and attached to the fuel system 124 of the aircraft 102 via the appropriate permanent conversion fixtures described above. According to one embodiment, this connection may be made between the permanent single-walled fuel manifold 410 of the unpressurized space of the aircraft 102 and the temporary double-walled fuel manifold 408 of the drum unit 132. The routine 700 continues to operation 706, where the drogue deployment unit 134 is attached to the fuselage 112 via the appropriate permanent conversion fixtures. According to one embodiment, the actuation mechanism housing 420 is bolted onto the underside of the fuselage 112.
[0031] From operation 706, the routine 700 continues to operation 708, where the refueling hose 304 is routed from the drum 404 through the actuator mechanism housing 420, drogue extension tube 422, and drogue container 424. The drogue 302 is coupled to the end of the refueling tube 304 and positioned within the drogue container 424. At operation 710, the control unit 136 is coupled to the applicable control components of the drogue deployment system 130. As discussed above, the control unit 136 may include the appropriate input devices and corresponding computer hardware and software housed within a "suitcase" or other portable housing. This suitcase-style control unit may be carried into the cockpit or other desired location on the aircraft 102 and connected to the electrical and communication cables that are coupled to the corresponding components of the drogue deployment system 130.
[0032] The routine 700 continues from operation 710 to operation 712, where the ARO, via the control unit 136, deploys the drogue extension tube 422 and the refueling hose 304 with drogue 302 during flight and transfers fuel at operation 714 when a receiving aircraft flies a corresponding refueling probe into the drogue 302. After refueling operations are concluded, the ARO utilizes the control unit 136 to retract the refueling hose 304 with drogue 302, followed by the drogue extension tube 422 at operation 716. When it is desirable to return the aircraft 102 to a configuration for primary use for carrying passengers or cargo, then at operation 718, the drum unit 132, drogue deployment unit 134, and control unit 136 are uninstalled from the aircraft 102 and stored for future use as desired, and the routine 700 ends.
[0033] FIGURE 8 shows an illustrative computer architecture for a control unit 136 capable of executing the software components described herein for providing aerial refueling operations. The computer architecture shown in FIGURE 8 illustrates a conventional desktop, laptop computer, server computer, or any flight computer configured for use with an aircraft system and may be utilized to implement the control unit 136 and to execute any of the other software components described herein.
[0034] The computer architecture shown in FIGURE 8 includes a processor 802, a system memory 808, including a random access memory 814 (RAM) and a read-only memory (ROM) 816, and a system bus 804 that couples the memory to the processor 802. A basic input/output system (BIOS) containing the basic routines that help to transfer information between elements within the control unit 136, such as during startup, is stored in the ROM 816. The control unit 136 further includes a mass storage device 810 for storing an operating system 818, application programs, and other program modules, which will be described in greater detail below.
[0035] The mass storage device 810 is connected to the processor 802 through a mass storage controller (not shown) connected to the bus 804. The mass storage device 810 and its associated computer-readable media provide non-volatile storage for the control unit 136. Although the description of computer-readable media contained herein refers to a mass storage device, such as a hard disk or CD-ROM drive, it should be appreciated by those skilled in the art that computer-readable storage media can be any available computer storage media that can be accessed by the control unit 136.
[0036] By way of example, and not limitation, computer-readable storage media may include volatile and non-volatile, removable and non-removable media implemented in any method or technology for storage of information such as computer-readable instructions, data structures, program modules or other data. For example, computer-readable storage media includes, but is not limited to, RAM, ROM, EPROM, EEPROM, flash memory or other solid state memory technology, CD-ROM, digital versatile disks (DVD), HD-DVD, BLU-RAY, or other optical storage, magnetic cassettes, magnetic tape, magnetic disk storage or other magnetic storage devices, or any other medium which can be used to store the desired information and which can be accessed by the control unit 136. As used herein, the term computer-readable storage media does not encompass transitory signals.
[0037] According to various embodiments, the control unit 136 may operate in a networked environment using logical connections to remote computers through a network such as the network 820. The control unit 136 may connect to the network 820 through a network interface unit 806 connected to the bus 804. It should be appreciated that the network interface unit 806 may also be utilized to connect to other types of networks and remote computer systems. The control unit 136 may also include an input/output controller 812 for receiving and processing input from a number of other devices, including a keyboard, mouse, joystick, or electronic stylus (not shown in FIGURE 8). Similarly, an input/output controller may provide output to a display screen, a printer, or other type of output device (also not shown in FIGURE 8).
[0038] As mentioned briefly above, a number of program modules and data files may be stored in the mass storage device 810 and RAM 814 of the control unit 136, including an operating system 818 suitable for controlling the operation of a networked desktop, laptop, server, or other flight computer. The mass storage device 810 and RAM 814 may also store one or more program modules. In particular, the mass storage device 810 and the RAM 814 may store a deployment/retraction control application 822 executable to control the applicable components of the drogue deployment system 130 as described above. The mass storage device 810 and RAM 814 may also store other program modules and data.
[0039] In general, software applications or modules may, when loaded into the processor 802 and executed, transform the processor 802 and the overall control unit 136 from a general-purpose computing system into a special-purpose computing system customized to perform the functionality presented herein. The processor 802 may be constructed from any number of transistors or other discrete circuit elements, which may individually or collectively assume any number of states. More specifically, the processor 802 may operate as one or more finite-state machines, in response to executable instructions contained within the software or modules. These computer-executable instructions may transform the processor 802 by specifying how the processor 802 transitions between states, thereby physically transforming the transistors or other discrete hardware elements constituting the processor 802.
[0040] Encoding the software or modules onto a mass storage device may also transform the physical structure of the mass storage device or associated computer-readable storage media. The specific transformation of physical structure may depend on various factors, in different implementations of this description. Examples of such factors may include, but are not limited to: the technology used to implement the computer-readable storage media, whether the computer-readable storage media are characterized as primary or secondary storage, and the like. For example, if the computer-readable storage media is implemented as semiconductor-based memory, the software or modules may transform the physical state of the semiconductor memory, when the software is encoded therein. For example, the software may transform the states of transistors, capacitors, or other discrete circuit elements constituting the semiconductor memory.
[0041] As another example, the computer-readable storage media may be implemented using magnetic or optical technology. In such implementations, the software or modules may transform the physical state of magnetic or optical media, when the software is encoded therein. These transformations may include altering the magnetic characteristics of particular locations within given magnetic media. These transformations may also include altering the physical features or characteristics of particular locations within given optical media, to change the optical characteristics of those locations. Other transformations of physical media are possible.
a drum unit (132) configured for removable coupling to the fuel system (124) of the non-tanker aircraft, the drum unit (132) comprising a drum (404) configured to rotate in a first direction to receive a refueling hose and to rotate in a second direction to deploy the refueling hose; and
a drogue deployment unit (134) configured for removable coupling to a fuselage (112) of the non-tanker aircraft, the drogue deployment unit (134) comprising:
a drogue extension tube (422) rotatably coupled to a fixed structure of the drogue deployment unit (134) at a fixed pivot end (516),
a drive screw (504);
an actuator (502) operative to rotate said drive screw (504);
at least one guide rod (508) positioned substantially parallel to the drive screw;
a carriage assembly (506) configured to translate along the at least one guide rod (508) in a first linear direction upon activation of the actuator to rotate the drive screw in a first rotational direction, and to translate along the at least one guide rod (508) in a second linear direction opposite the first linear direction upon activation of the actuator to rotate the drive screw in a second rotational direction opposite the first rotational direction;
at least one extension rod (510) coupled at a first end to the carriage assembly (506) and at a second end to the drogue extension tube (422) such that translation of the carriage assembly (506) along the at least one guide rod (508) rotates the drogue extension tube (422) around the fixed pivot end (516); and
a drogue container (424) rotatably coupled to the drogue extension tube (422) at a distal end (518) opposite the fixed pivot end (516),
wherein the drogue extension tube (422) and the drogue container (424) are configured to receive the refueling hose and to guide the refueling hose from the drum unit (132) to a deployed position external to the non-tanker aircraft.
a refueling hose (304);
a drogue (302) coupled to the refueling hose and configured to receive a refueling probe of a receiving aircraft and to provide fuel from the refueling hose to the refueling probe.
a drogue container rod rotatably attached at a first end to the fixed structure and at a second end to an aft pivot fitting (514); and
the aft pivot fitting (514) fixedly attached to the drogue container (424) such that when the drogue container rod rotates downward around the first end, the drogue container rod rotates the aft pivot fitting (514) and attached corresponding drogue container (424) at a rate that substantially maintains an orientation of the drogue container (424) with respect to an ambient airflow.
the fuselage (112) of the non-tanker aircraft;
the refueling hose (304); and
a drogue (302) attached at an end of the refueling hose and configured to receive a refueling probe of a receiving aircraft,
wherein the drum unit (132) is secured within a cargo space of the fuselage (112), and wherein the fuel system (124) comprises at least one fuel tank (126) such that the fuel system (124) and drogue deployment unit (134) provide a fuel pathway from the at least one fuel tank (126) to the drogue for transfer to the receiving aircraft.
coupling a drum unit (132) secured within a cargo area of the non-tanker aircraft to a fuel tank (126) of the non-tanker aircraft, the drum unit (132) comprising a drum (404) configured to rotate in a first direction to retract a refueling hose (304) and to rotate in a second direction to extend the refueling hose;
coupling a drogue deployment unit (134) to an external surface of a fuselage (112) of the non-tanker aircraft, the drogue deployment unit (134) comprising:
a drogue extension tube (422) rotatably coupled to a fixed structure of the drogue deployment unit (134) at a fixed pivot end (516);
a drogue container (424) rotatably coupled to the drogue extension tube (422) at a distal end (518) opposite the fixed pivot end (516);
an actuator (502) operative to rotate a drive screw (504);
at least one guide rod (508) positioned substantially parallel to the drive screw;
a carriage assembly (506) configured to translate along the at least one guide rod (508) in a first linear direction upon activation of the actuator to rotate the drive screw in a first rotational direction, and to translate along the at least one guide rod (508) in a second linear direction opposite the first linear direction upon activation of the actuator to rotate the drive screw in a second rotational direction opposite the first rotational direction;
at least one extension rod (510) coupled at a first end to the carriage assembly (506) and at a second end to the drogue extension tube (422) such that translation of the carriage assembly (506) along the at least one guide rod (508) rotates the drogue extension tube (422) around the fixed pivot end (516);
wherein the drogue extension tube (422) and the drogue container (424) are configured to receive the refueling hose and to guide the refueling hose from the drum unit (132) to a deployed position external to the non-tanker aircraft;
positioning the refueling hose around the drum and through the drogue extension tube (422);
attaching a drogue (302) to an end of the refueling hose; and
coupling a control unit (136) to the drum unit (132) and to the drogue deployment unit (134), the control unit (136) configured to control deployment and retraction of the drogue extension tube (422) and the refueling hose and to control fuel flow from the fuel tank (126) of the non-tanker aircraft to the drogue;
rotating the drogue extension tube (422) downward around a fixed pivot end (516) from a stowed position substantially parallel with the fuselage (112) of the non-tanker aircraft (102) to a deployed position;
extending the refueling hose (304) from the drum unit (132) through the drogue extension tube (422) and through the drogue container (424) such that the drogue (302) extends rearward from the drogue container (424) to a deployed position behind the non-tanker aircraft, wherein the drum unit (133) is removably coupled to the fuel system (124) of the non-tanker aircraft; and
transferring fuel from the fuel tank (126) of the non-tanker aircraft through the refueling hose to the drogue for receiving by a refueling probe of a receiving aircraft.
stopping fuel transfer;
retracting the refueling hose (304); and
rotating the drogue extension tube (422) upward around the fixed pivot end (516) from the deployed position to the stowed position.
eine Trommeleinheit (132), die zum abnehmbaren Koppeln an das Treibstoffsystem (124) des Nicht-Tankflugzeugs konfiguriert ist, wobei die Trommeleinheit (132) eine Trommel (404) aufweist, die dazu konfiguriert ist, sich in einer ersten Richtung zu drehen, um einen Tankschlauch aufzunehmen, und sich in einer zweiten Richtung zu drehen, um den Tankschlauch auszufahren; und
eine Fangtrichterausfahreinheit (134), die zum abnehmbaren Koppeln an einen Rumpf (112) des Nicht-Tankflugzeugs konfiguriert ist, wobei die Fangtrichterausfahreinheit (134) aufweist:
einen Fangtrichtererweiterungsschlauch (422), der an einem festen Gelenkende (516) drehbar an eine feste Struktur der Fangtrichterausfahreinheit (134) gekoppelt ist,
eine Antriebsschraube (504);
einen Aktor (502), der dazu betreibbar ist, die Antriebsschraube (504) zu drehen;
wenigstens einen Führungsstab (508), der im Wesentlichen parallel zu der Antriebsschraube positioniert ist;
eine Schlittenanordnung (506), die dazu konfiguriert ist, sich nach Betätigung des Aktors entlang des wenigstens einen Führungsstabs (508) in einer linearen Richtung in und her zu bewegen, um die Antriebsschraube in einer ersten Drehrichtung zu drehen, und sich nach Betätigung des Aktors entlang des wenigstens einen Führungsstabs (508) in einer zweiten linearen Richtung entgegengesetzt zu der ersten linearen Richtung hin und her zu bewegen, um die Antriebsschraube in einer zweiten Drehrichtung, die zu der ersten Drehrichtung entgegengesetzt ist, zu drehen,
wenigstens einen Verlängerungsstab (510), der an einem ersten Ende an die Schlittenanordnung (506) und an einem zweiten Ende an den Fangtrichtererweiterungsschlauch (422) derart gekoppelt ist, dass die Hin- und Herbewegung der Schlittenanordnung (506) entlang des wenigstens einen Führungsstabs (508) den Fangtrichtererweiterungsschlauch (422) um das feste Gelenkende (512) herum dreht; und
einen Fangtrichterbehälter (424), der an einem distalen Ende (518) gegenüber dem festen Gelenkende (516) drehbar an den Fangtrichtererweiterungsschlauch (422) gekoppelt ist,
wobei der Fangtrichtererweiterungsschlauch (422) und der Fangtrichterbehälter (424) dazu konfiguriert sind, den Tankschlauch aufzunehmen und den Tankschlauch von der Trommeleinheit (132) in eine ausgefahrene Position außerhalb des Nicht-Tankflugzeugs zu führen.
einen Tankschlauch (304);
einen Fangtrichter (302), der an den Tankschlauch gekoppelt und dazu konfiguriert ist, eine Tanksonde eines empfangenden Flugzeugs aufzunehmen und der Tanksonde Treibstoff aus dem Tankschlauch zuzuführen.
einen Fangtrichterbehälterstab, der an einem ersten Ende an der festen Struktur und an einem zweiten Ende an einem hinteren Gelenkstück (514) drehbar befestigt ist; und
wobei das hintere Gelenkstück (514) an dem Fangtrichterbehälter (424) derart fest befestigt ist, dass, wenn sich der Fangtrichterbehälterstab um das erste Ende herum nach unten dreht, der Fangtrichterbehälterstab das hintere Gelenkstück (514) und den befestigten entsprechenden Fangtrichterbehälter (424) mit einer Geschwindigkeit dreht, die im Wesentlichen eine Ausrichtung des Fangtrichterbehälters (424) bezüglich eines Umgebungsluftstroms aufrecht erhält.
den Rumpf (112) des Nicht-Tankflugzeugs;
den Tankschlauch (304); und
einen Fangtrichter (302), der an einem Ende des Tankschlauchs befestigt und dazu konfiguriert ist, eine Tanksonde eines empfangenden Flugzeugs aufzunehmen,
wobei die Trommeleinheit (132) in einem Frachtraum des Rumpfs (112) befestigt ist, und wobei das Treibstoffsystem (124) wenigstens einen Treibstofftank (126) aufweist, derart, dass das Treibstoffsystem (124) und die Fangtrichterausfahreinheit (134) einen Treibstoffweg von dem wenigstens einen Treibstofftank (126) zu dem Fangtrichter zur Übergabe an das empfangende Flugzeug bereitstellen.
Koppeln einer Trommeleinheit (132), die in einem Frachtbereich des Nicht-Tankflugzeugs befestigt ist, an einen Treibstofftank (126) des Nicht-Tankflugzeugs, wobei die Trommeleinheit (134) eine Trommel (404) aufweist, die dazu konfiguriert ist, sich in einer ersten Richtung zu drehen, um einen Tankschlauch (304) einzuziehen, und sich in einer zweiten Richtung zu drehen, um den Tankschlauch auszufahren;
Koppeln einer Fangtrichterausfahreinheit (134) mit einer äußeren Oberfläche eines Rumpfs (112) des Nicht-Tankflugzeugs, wobei die Fangtrichterausfahreinheit (134) aufweist:
einen Fangtrichtererweiterungsschlauch (422), der an einem festen Gelenkende (516) drehbar an eine feste Struktur der Fangtrichterausfahreinheit (134) gekoppelt ist;
einen Fangtrichterbehälter (424), der an einem distalen Ende (518) gegenüber dem festen Gelenkende (516) drehbar an den Fangtrichtererweiterungsschlauch (422) gekoppelt ist;
einen Aktor (502), der dazu betreibbar ist, eine Antriebsschraube (504) zu drehen;
wenigstens einen Führungsstab (508), der im Wesentlichen parallel zu der Antriebsschraube positioniert ist;
eine Schlittenanordnung (506), die dazu konfiguriert ist, sich nach Betätigung des Aktors entlang des wenigstens einen Führungsstabs (508) in einer linearen Richtung in und her zu bewegen, um die Antriebsschraube in einer ersten Drehrichtung zu drehen, und sich nach Betätigung des Aktors entlang des wenigstens einen Führungsstabs (508) in einer zweiten linearen Richtung entgegengesetzt zu der ersten linearen Richtung hin und her zu bewegen, um die Antriebsschraube in einer zweiten Drehrichtung, die zu der ersten Drehrichtung entgegengesetzt ist, zu drehen;
wenigstens einen Verlängerungsstab (510), der an einem ersten Ende an die Schlittenanordnung (506) und an einem zweiten Ende an den Fangtrichtererweiterungsschlauch (422) derart gekoppelt ist, dass die Hin- und Herbewegung der Schlittenanordnung (506) entlang des wenigstens einen Führungsstabs (508) den Fangtrichtererweiterungsschlauch (422) um das feste Gelenkende (512) herum dreht;
wobei der Fangtrichtererweiterungsschlauch (422) und der Fangtrichterbehälter (424) dazu konfiguriert sind, den Tankschlauch aufzunehmen und den Tankschlauch von der Trommeleinheit (132) in eine ausgefahrene Position außerhalb des Nicht-Tankflugzeugs zu führen;
Positionieren des Tankschlauchs um die Trommel herum und durch den Fangtrichtererweiterungsschlauch (422);
Befestigen eines Fangtrichters (302) an einem Ende des Tankschlauchs; und
Koppeln einer Steuereinheit (302) an die Trommeleinheit (132) und an die Fangtrichterausfahreinheit (134), wobei die Steuereinheit (136) dazu konfiguriert ist, das Ausfahren und Einziehen des Fangtrichtererweiterungsschlauchs (422) und des Tankschlauchs zu steuern und den Treibstofffluss von dem Treibstofftank (126) des Nicht-Tankflugzeugs an den Fangtrichter zu steuern;
Drehen des Fangtrichtererweiterungsschlauchs (422) um ein festes Gelenkende (516) nach unten von einer verstauten Position im Wesentlichen parallel zu dem Rumpf (112) des Nicht-Tankflugzeugs (102) in eine ausgefahrene Position;
Ausfahren des Tankschlauchs (304) von der Trommeleinheit (132) durch den Fangtrichtererweiterungsschlauch (422) und durch den Fangtrichterbehälter (424) derart, dass sich der Fangtrichter (302) von dem Fangtrichterbehälter (424) nach hinten in eine ausgefahrene Position hinter dem Nicht-Tankflugzeug erstreckt, wobei die Trommeleinheit (133) abnehmbar an das Treibstoffsystem (124) des Nicht-Tankflugzeugs gekoppelt ist; und
Übergeben von Treibstoff von dem Treibstofftank (126) des Nicht-Tankflugzeugs durch den Tankschlauch an den Fangtrichter zur Aufnahme durch eine Tanksonde eines empfangenden Flugzeugs.
Anhalten der Treibstoffübergabe;
Einziehen des Tankschlauchs (304); und
Drehen des Fangtrichtererweiterungsschlauchs (422) nach oben um das feste Gelenkende (516) von der ausgefahrenen Position in die verstaute Position.
une unité de tambour (132) configurée pour s'accoupler de façon amovible au circuit de carburant (124) de l'avion non ravitailleur, l'unité de tambour (132) comprenant un tambour (404) configuré pour tourner dans une première direction afin de recevoir un tuyau de ravitaillement, et pour tourner dans une seconde direction afin de déployer le tuyau de ravitaillement ; et
une unité de déploiement (134) de l'entonnoir de ravitaillement en vol, ladite unité étant configurée pour s'accoupler de façon amovible à un fuselage (112) de l'avion non ravitailleur, l'unité de déploiement (134) de l'entonnoir de ravitaillement en vol comprenant :
un tube de rallonge (422) de l'entonnoir de ravitaillement en vol, ledit tube de rallonge, au niveau d'une extrémité de pivot fixe (516), étant couplé en rotation à une structure fixe de l'unité de déploiement (134) de l'entonnoir de ravitaillement en vol ;
une vis d'entraînement (504) ;
un actionneur (502) fonctionnant pour faire tourner ladite vis d'entraînement (504) ;
au moins une tige de guidage (508) positionnée pratiquement de façon parallèle à la vis d'entraînement ;
un ensemble chariot (506) configuré pour se déplacer en translation le long de l'au moins une tige de guidage (508), dans une première direction linéaire lors de l'activation de l'actionneur pour faire tourner la vis d'entraînement dans une première direction de rotation, et pour se déplacer en translation le long de l'au moins une tige de guidage (508), dans une seconde direction linéaire opposée à la première direction linéaire lors de l'activation de l'actionneur pour faire tourner la vis d'entraînement dans une seconde direction de rotation opposée à la première direction de rotation ;
au moins une tige de rallonge (510) couplée, au niveau d'une première extrémité, à l'ensemble chariot (506) et, au niveau d'une seconde extrémité, couplée au tube de rallonge (422) de l'entonnoir de ravitaillement en vol, de manière telle que le mouvement de translation de l'ensemble chariot (506) le long de l'au moins une tige de guidage (508) fasse tourner le tube de rallonge (422) de l'entonnoir de ravitaillement en vol autour de l'extrémité de pivot fixe (516) ; et
un conteneur (424) de l'entonnoir de ravitaillement en vol, ledit conteneur étant couplé en rotation au tube de rallonge (422) de l'entonnoir de ravitaillement en vol, au niveau d'une extrémité distale (518) placée à l'opposé de l'extrémité de pivot fixe (516),
où le tube de rallonge (422) de l'entonnoir de ravitaillement en vol et le conteneur (424) de l'entonnoir de ravitaillement en vol sont configurés pour recevoir le tuyau de ravitaillement et pour guider le tuyau de ravitaillement à partir de l'unité de tambour (132) jusqu'à une position déployée à l'extérieur de l'avion non ravitailleur.
un tuyau de ravitaillement (304) ;
un entonnoir de ravitaillement en vol (302) couplé au tuyau de ravitaillement et configuré pour recevoir une sonde de ravitaillement d'un avion récepteur et pour fournir du carburant à la sonde de ravitaillement, à partir du tuyau de ravitaillement.
une tige de conteneur de l'entonnoir de ravitaillement en vol, ladite tige, au niveau d'une première extrémité, étant fixée en rotation à la structure fixe, et, au niveau d'une seconde extrémité, fixée en rotation à un raccord de pivot arrière (514) ; et
le raccord de pivot arrière (514) est monté fixement sur le conteneur (424) de l'entonnoir de ravitaillement en vol, de manière telle que, lorsque la tige du conteneur de l'entonnoir de ravitaillement en vol tourne vers le bas autour de la première extrémité, la tige du conteneur de l'entonnoir de ravitaillement en vol fasse tourner le raccord de pivot arrière (514) et le conteneur correspondant fixé (424) de l'entonnoir de ravitaillement en vol, à une vitesse qui maintient sensiblement une orientation du conteneur (424) de l'entonnoir de ravitaillement en vol, par rapport à un flux d'air ambiant.
le fuselage (112) de l'avion non ravitailleur ;
le tuyau de ravitaillement (304) ; et
un entonnoir de ravitaillement en vol (302) fixé au niveau d'une extrémité du tuyau de ravitaillement et configuré pour recevoir une sonde de ravitaillement d'un avion récepteur,
système dans lequel l'unité de tambour (132) est fixée à l'intérieur d'un espace de fret du fuselage (112), et où le circuit de carburant (124) comprend au moins un réservoir de carburant (126), de manière telle que le circuit de carburant (124) et l'unité de déploiement (134) de l'entonnoir de ravitaillement en vol fournissent une voie de carburant à partir de l'au moins un réservoir de carburant (126) jusqu'à l'entonnoir de ravitaillement en vol, pour transfert jusqu'à l'avion récepteur.
le couplage d'une unité de tambour (132) fixée dans une zone de fret de l'avion non ravitailleur, à un réservoir de carburant (126) de l'avion non ravitailleur, l'unité de tambour (132) comprenant un tambour (404) configuré pour tourner dans une première direction afin de rentrer un tuyau de ravitaillement (304) et pour tourner dans une seconde direction afin de déployer le tuyau de ravitaillement ;
le couplage d'une unité de déploiement (134) de l'entonnoir de ravitaillement en vol, à une surface extérieure d'un fuselage (112) de l'avion non ravitailleur, l'unité de déploiement (134) de l'entonnoir de ravitaillement en vol comprenant :
un tube de rallonge (422) de l'entonnoir de ravitaillement en vol, ledit tube de rallonge, au niveau d'une extrémité de pivot fixe (516), étant couplé en rotation à une structure fixe de l'unité de déploiement (134) de l'entonnoir de ravitaillement en vol ;
un conteneur (424) de l'entonnoir de ravitaillement en vol, ledit conteneur étant couplé en rotation au tube de rallonge (422) de l'entonnoir de ravitaillement en vol, au niveau d'une extrémité distale (518) placée à l'opposé de l'extrémité de pivot fixe (516) ;
un actionneur (502) fonctionnant pour faire tourner une vis d'entraînement (504) ;
au moins une tige de guidage (508) positionnée pratiquement de façon parallèle à la vis d'entraînement ;
un ensemble chariot (506) configuré pour se déplacer en translation le long de l'au moins une tige de guidage (508), dans une première direction linéaire lors d'une activation de l'actionneur pour faire tourner la vis d'entraînement dans une première direction de rotation, et pour se déplacer en translation le long de l'au moins une tige de guidage (508), dans une seconde direction linéaire opposée à la première direction linéaire lors d'une activation de l'actionneur pour faire tourner la vis d'entraînement dans une seconde direction de rotation opposée à la première direction de rotation ;
au moins une tige de rallonge (510) couplée, au niveau d'une première extrémité, à l'ensemble chariot (506) et, au niveau d'une seconde extrémité, couplée au tube de rallonge (422) de l'entonnoir de ravitaillement en vol, de manière telle que le mouvement de translation de l'ensemble chariot (506) le long de l'au moins une tige de guidage (508) fasse tourner le tube de rallonge (422) de l'entonnoir de ravitaillement en vol autour de l'extrémité de pivot fixe (516) ;
où le tube de rallonge (422) de l'entonnoir de ravitaillement en vol et le conteneur (424) de l'entonnoir de ravitaillement en vol sont configurés pour recevoir le tuyau de ravitaillement et pour guider le tuyau de ravitaillement à partir de l'unité de tambour (132) jusqu'à une position déployée à l'extérieur de l'avion non ravitailleur ;
le positionnement du tuyau de ravitaillement autour du tambour et à travers le tube de rallonge (422) de l'entonnoir de ravitaillement en vol ;
la fixation d'un entonnoir de ravitaillement en vol (302) au niveau d'une extrémité du tuyau de ravitaillement ; et
le couplage d'une unité de commande (136) à l'unité de tambour (132) et à l'unité de déploiement (134) de l'entonnoir de ravitaillement en vol, l'unité de commande (136) étant configurée pour commander le déploiement et la rétraction du tube de rallonge (422) de l'entonnoir de ravitaillement en vol et du tuyau de ravitaillement, et pour contrôler le débit de carburant à partir du réservoir de carburant (126) de l'avion non ravitailleur, jusqu'à l'entonnoir de ravitaillement en vol ;
la rotation du tube de rallonge (422) de l'entonnoir de ravitaillement en vol, vers le bas autour d'une extrémité de pivot fixe (516), à partir d'une position repliée pratiquement parallèle au fuselage (112) de l'avion non ravitailleur (102), jusqu'à une position déployée ;
le déploiement du tuyau de ravitaillement (304) à partir de l'unité de tambour (132), à travers le tube de rallonge (422) de l'entonnoir de ravitaillement en vol et à travers le conteneur (424) de l'entonnoir de ravitaillement en vol, de manière telle que l'entonnoir de ravitaillement en vol (302) se déploie vers l'arrière à partir du conteneur (424) de l'entonnoir de ravitaillement en vol, jusqu'à une position déployée se trouvant derrière l'avion non ravitailleur, où l'unité de tambour (133) est couplée de façon amovible au circuit de carburant (124) de l'avion non ravitailleur ; et
le transfert de carburant à partir du réservoir de carburant (126) de l'avion non ravitailleur, ledit transfert étant réalisé à travers le tuyau de ravitaillement jusqu'à l'entonnoir de ravitaillement en vol, pour réception par une sonde de ravitaillement d'un avion récepteur.
l'arrêt du transfert de carburant ;
la rétraction du tuyau de ravitaillement (304) et la rotation du tube de rallonge (422) de l'entonnoir de ravitaillement en vol, vers le haut autour de l'extrémité de pivot fixe (516), à partir de la position déployée jusqu'à la position repliée.
REFERENCES CITED IN THE DESCRIPTION
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Patent documents cited in the description