Abstract:
An in-flight refueling method may include deploying a fueling hose from a refueling aircraft. The fueling hose may have a drogue. The deployment of the fueling hose may include extending the drogue using a telescoping arm having a ring. The deployment of the fueling hose may also include passing the fueling hose through the ring to deploy the fueling hose. The in-flight refueling method may further include retrieving the fueling hose by drawing the drogue into a wire pitch mounted on the ring and collapsing the drogue in response to drawing the drogue into the wire pitch.

Description:
CROSS-REFERENCE TO RELATED APPLICATIONS 
     This application is a divisional application of and claims priority to pending U.S. application Ser. No. 11/938,636 filed on Nov. 12, 2007 and entitled DROGUE DEPLOYING/RETRIEVAL DEVICE, SYSTEM, AND METHOD, the entire contents of which is expressly incorporated by reference herein. 
    
    
     FIELD 
     The present disclosure generally relates to deploying/retrieval of items from an aircraft. More particularly, the present disclosure pertains to a device and system for deploying/retrieval a drogue from an aircraft. 
     BACKGROUND 
     Aerial refueling is presently utilized to extend the flight time and/or range of aircraft. In general, to aerially refuel an aircraft, a tanker aircraft deploys a boom or hose fitted with a coupling that is configured to mate with a receptacle on the receiving aircraft. In boom outfitted tankers, the boom is equipped with a male nozzle and the boom is typically controlled by a boom operator that guides the nozzle into a female fitting on the receiving aircraft. In hose outfitted tankers, the hose is equipped with a female coupling and a drogue. When placed in an air stream, the drogue acts to draw the hose out of the aircraft and stabilize the flight of the hose when extended. These two systems are generally not interchangeable. 
     Boom equipped tanker systems are relatively more complicated than drogue systems. In addition to the increased bulk and expense of the boom equipment, a boom operator is typically required. When the boom systems were initially introduces, boom systems could deliver greater flow rates of fuel. However, with advances in drogue systems, flow rates are generally comparable between boom and drogue systems. 
     A disadvantage of drogue systems is that during deployment and retrieval, the drogue passes though a boundary layer air. This boundary layer of air is in close proximity to the skin of the aircraft The flow of the boundary layer of air is retarded via interaction with the aircraft skin. As the drogue passes through the boundary layer, the drogue is subjected to wind shear. In addition, the drogue causes turbulence as it is introduced to airflow. These forces tend to cause the drogue, along with the hose and nozzle, to oscillate in an undesirable manner. 
     Accordingly, it is desirable to provide a drogue device and system that is capable of overcoming the disadvantages described herein at least to some extent. 
     SUMMARY 
     The foregoing needs are met, to a great extent, by embodiments of the present disclosure, wherein in one respect a drogue device and system is provided that in some embodiments decreases the effects of wind shear between the drogue and the aircraft. 
     An embodiment relates to an in-flight refueling device. The in-flight refueling device includes an arm, ring and actuator. The arm has a proximate end and a distal end. The ring is secured to the distal end and is configured to releasably secure a drogue. The actuator is secured to the proximate end and is configured to extend the arm a predetermined distance. 
     Another embodiment pertains to an in-flight refueling system. The in-flight refueling system includes a fuel supply, hose drum unit, drogue, and deploying/retrieval device. The hose drum unit is in fluid communication with the fuel supply. The hose drum unit includes a hose. The drogue is disposed upon an end of the hose and is configured to provide flight stability to the hose in response to being introduced to an air stream. The drogue has a storage conformation and a deployed conformation. The deploying/retrieval device includes an arm, ring, and actuator. The arm has a proximate end and a distal end. The ring is secured to the distal end and is configured to releasably secure the drogue. The actuator is secured to the proximate end and is configured to extend the drogue through an air boundary layer during deployment. 
     Yet another embodiment relates to a method of in-flight refueling. In this method, a fueling hose is deployed from a refueling aircraft. The fueling hose is outfitted with a drogue. In the deploying step, the drogue is extended through a boundary layer of air with a deploying/retrieval device. The deploying/retrieval device includes an arm, ring, and actuator. The arm has a proximate end and a distal end. The ring is secured to the distal end and is configured to releasably secure the drogue. The actuator is secured to the proximate end and is configured to extend and retract the arm. The fueling hose is extended and passes through the ring. The arm is retracted in response to the drogue being clear of the refueling aircraft. 
     There has thus been outlined, rather broadly, certain embodiments of the disclosure in order that the detailed description thereof herein may be better understood, and in order that the present contribution to the art may be better appreciated. There are, of course, additional embodiments that will be described below and which will form the subject matter of the claims appended hereto. 
     In this respect, before explaining at least one embodiment in detail, it is to be understood that the disclosure is not limited in its application to the details of construction and to the arrangements of the components set forth in the following description or illustrated in the drawings. The disclosed device and method is capable of embodiments in addition to those described and of being practiced and carried out in various ways. Also, it is to be understood that the phraseology and terminology employed herein, as well as the abstract, are for the purpose of description and should not be regarded as limiting. 
     As such, those skilled in the art will appreciate that the conception upon which this disclosure is based may readily be utilized as a basis for the designing of other structures, methods and systems for carrying out the several purposes of the various embodiments. It is important, therefore, that the claims be regarded as including such equivalent constructions insofar as they do not depart from the spirit and scope of the various embodiments. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         FIG. 1  is a simplified cross sectional view of a refueling system in accordance with an embodiment. 
         FIG. 2  is a detailed view of a deployment/retrieval device in accordance with an embodiment. 
         FIG. 3  is a detailed view of a deployment/retrieval device in accordance with another embodiment. 
         FIG. 4  is a detailed view of a deployment/retrieval device in a retracted configuration in accordance with another embodiment. 
         FIG. 5  is a detailed view of a deployment/retrieval device in an extended configuration according to  FIG. 4 . 
         FIG. 6  is a simplified view of the refueling system in an initial stage of deployment. 
         FIG. 7  is a simplified view of the refueling system in an intermediate stage of deployment. 
         FIG. 8  is a simplified view of the refueling system in an end stage of deployment. 
         FIG. 9  is a simplified view of the refueling system in an initial stage of retrieval. 
         FIG. 10  is a simplified view of the refueling system in an intermediate stage of retrieval. 
         FIG. 11  is a simplified view of the refueling system in an end stage of retrieval. 
     
    
    
     DETAILED DESCRIPTION 
     The present disclosure provides a device, system, and method for reducing the effects of wind shear between a drogue and a refueling aircraft. In general, the various embodiments reduce the effects of wind shear between the drogue and the refueling aircraft by securing the drogue until the drogue has been extended past a boundary layer of air in close proximity to the skin of the aircraft. For the purpose of this disclosure, the phrase, “boundary layer of air” refers to a layer of air flowing around the aircraft that has been retarded due to interactions with the aircraft. 
     The invention will now be described with reference to the drawing figures, in which like reference numerals refer to like parts throughout.  FIG. 1  is a simplified cross sectional view of an in-flight refueling system  10  in accordance with an embodiment. As shown in  FIG. 1 , the in-flight refueling system  10  includes a hose drum unit  12 , hose  14 , drogue  16 , and deployment/retrieval device  18 . Also shown in  FIG. 1 , the in-flight refueling system  10  is installed in a refueling aircraft  20  and is in fluid communication with a fuel source  22 . 
     The hose drum unit  12  includes a drum  24  to dispense and retract a supply of the hose  14 . In addition, the hose drum unit  12  includes a drive/controller unit  26 . The drive/controller unit  26  is configured rotate the drum  24  and/or provide sufficient torque to the drum  24  to slow or stop the rotation of the drum  24 . For example, during deployment the drogue may be urged by the air stream moving relative to the refueling aircraft  20  to draw the hose  14  out of the refueling aircraft by rotating the drum  24 . The drive/controller unit  26  may provide sufficient torque to the drum  24  to control the rate at which the hose  14  is drawn out. Once the hose  14  has extended sufficiently from the refueling aircraft  20 , the drive/controller unit  26  may provide sufficient torque to the drum  24  to balance the load supplied by the drogue  16 . 
       FIG. 1  further shows an air stream  28  moving relative to the aircraft  20 . This air stream moves relatively faster than a boundary layer of air  30  that is in close proximity to the refueling aircraft  20 . As the drogue  16  is deployed from the refueling aircraft  20 , the differences in the relative airspeed subject the drogue  16  to wind shear and can act to drive the drogue  16  towards the aircraft  20 . 
       FIG. 2  is a detailed view of the deployment/retrieval device  18  in accordance with an embodiment. In general,  FIG. 2  shows a drogue tunnel and the components therein. Typically, the environment of the drogue tunnel is closed to the aircraft interior. However, to simplify the figures, the environmental containment system is not shown or described herein. As shown in  FIG. 2 , the deployment/retrieval device  18  includes a ring  32 . This ring  32  releasably secures drogue  16  therein. During operation, the hose  14  passes over the ring  32 . To reduce frictional or rolling resistance of the hose  14 , the ring  32  includes a roller  34 . This roller  34  is similar to a roller  36  that may reduce friction and/or wear on the hose  14  and refueling aircraft  20 . 
     In addition to the ring  32 , the deployment/retrieval device  18  may optionally include one or more additional rings  38 . If included, these rings  38  may provide additional security during deployment/retrieval operations and may assist in guiding the hose  14  and drogue  16  into alignment. The ring  32  and, if present, rings  38  may be mounted to an arm  40 . The arm  40  is configured to be extended out from the refueling aircraft  20  to a sufficient extent that the drogue  16  passes through the boundary layer of air  30 . In addition, the arm  40  is configured to provide sufficient strength and rigidity so as to reduce or eliminate excessive movement of the drogue  16  as it is driven through the boundary layer of air  30 . In so doing, the deployment/retrieval device  18  reduces or eliminates the effects of wind shear and/or turbulence to the drogue  16  and/or underside of the refueling aircraft  20 . 
     The arm  40  may be driven by an actuator  42 . The actuator  42  includes any suitable actuating device such as, for example, a pneumatic or hydraulic piston, linear actuator, electronic or mechanical actuator, or the like. 
       FIG. 3  is a detailed view of the ring  32  in accordance with another embodiment. As shown in  FIG. 3 , the ring  32  includes a wire pitch  44 . The wire pitch  44  may be optionally included to facilitate collecting and/or collapsing the drogue  16  during retrieval. If included, the wire pitch  44  may encompass about one half the circumference of the ring  32  and may be about one half the length of the drogue  16  in height. To decrease drag, the wire pitch  44  may include relatively fine wires. 
       FIG. 4  is a detailed view of the deployment/retrieval device  18  in a retracted configuration in accordance with another embodiment. As shown in  FIG. 4 , the deployment/retrieval device  18  may include a plurality of segments  46   a  to  46   n . For example, the deployment/retrieval device  18  may include three segments  46   a  to  46   c  configured to telescope. In the refracted configuration shown in  FIG. 4 , the deployment/retrieval device  18  may be relatively compact. 
       FIG. 5  is a detailed view of the deployment/retrieval device  18  in an extended configuration according to  FIG. 4 . As show in  FIG. 5 , the deployment/retrieval device  18  may be telescopically extended. For example, fluid may be introduced to the deployment/retrieval device  18  to urge the segments  46   a  and  46   b  to extend from  46   c . Similarly, the segments  46   a  and  46   b  may be retracted by withdrawing fluid therefrom. 
     Also shown in  FIG. 5 , the arm  40  may include a backstop  48  to assist in recovery of the drogue  16 . The backstop  48  extends past the ring  32 . As the deployed drogue  16  is drawn into the ring  32  via the action of the hose drum unit  12 , the backstop  48  assists in directing the drogue  16  into the ring  32  and collapsing the drogue  16  from a deployed or expanded state into a stowed state. 
       FIG. 6  is a simplified view of the refueling system  10  in an initial stage of deployment. As shown in  FIG. 6 , the arm  40  is extended out of the refueling aircraft  20 . In so doing, the ring  32  disposed at or near the end of the arm  40  is extended past the boundary layer of air  30  and into the air stream  28 . The drogue  16  is secured or captured by the ring  32  and so is carried through the boundary layer of air  30  and into the air stream  28  as well. In order to remain captured by the ring  32 , the drive/controller unit  26  may provide sufficient torque or resistance to overcome the boundary layer of air  30  and/or air stream  28  acting on the drogue  16  to pull the drogue  16  free of the ring  32 . 
     Once the drogue  16  is within the air stream  28 , the torque supplied by the drive/controller unit  26  may be reduced to allow the drogue  16  to be pulled free of the ring  32  and deployed. 
       FIG. 7  is a simplified view of the refueling system in an intermediate stage of deployment. As shown in  FIG. 7 , as a result of being introduced to the air stream  28  and pulled free of the ring  32 , the drogue  16  inflates or otherwise expands to stabilize the flight of the hose  14 . As the hose  14  is unwound from the drum  24 , it threads through the ring  32  and rolls against the roller  34 . The roller  34  reduces friction and wear between the hose  14  and the ring  32 . 
     Once the drogue  16  has extended past the rear of the refueling aircraft  20  or to a predetermined extent, the arm  40  may be refracted. Retracting the arm  40  reduces drag on the forward movement of the refueling aircraft  20 . It is an advantage of the embodiment described herein that, while refracted, the arm  40  and ring  32  do not impart any drag on the refueling aircraft  20 . It is another advantage that, due to the minimal frontal area of the arm  40  and ring  32 , the drag imparted on the refueling aircraft  20  is negligible during deployment and retrieval operations. It is a further advantage of the deployment/retrieval device  18  that refueling operations can take place in the event of a failure of the deployment/retrieval device  18 . That is, if the deployment/retrieval device  18  fails to extend the arm  40 , the drogue  16  can be deployed in a conventional manner. However, due to the uncomplicated design and robust nature of the components of the deployment/retrieval device  18 , it is unlikely to suffer failure. 
       FIG. 8  is a simplified view of the refueling system in an end stage of deployment. As shown in  FIG. 8 , the arm  40  may be retracted into the refueling aircraft  20  and the drag reduced accordingly. In the retracted conformation, the hose  14  may roll upon the roller  36 . Refueling operations may proceed in a conventional manner. That is, receiving aircraft may approach and attach to the hose  14  via a nozzle or coupling (not shown). Fuel may be delivered to the receiving aircraft and the receiving aircraft may depart. Following refueling operations, the hose  14  and drogue  16  may be refracted. In various embodiments, the hose  14  and drogue  16  may be partially retracted first and then the arm  40  may be extended to recover the drogue  16  or the arm  40  may be extended prior to or during retraction of the hose  14  and drogue  16  and retraction may proceed until the drogue is captured. Regardless of the order in which the steps are performed, in a preferred embodiment, the arm  40  is extended prior to the drogue  16  striking the refueling aircraft  20 . For example, as shown in  FIG. 9 , the arm  40  may be extended prior to the drogue  16  reaching the aft-most part of the refueling aircraft  20 . 
       FIG. 9  is a simplified view of the refueling system  10  in an initial stage of retrieval. As shown in  FIG. 9 , by extending the arm  40 , the hose  14  and drogue  16  may be maintained in the air stream  28  during retrieval. In this manner, the hose  14  and drogue  16  may be retrieved without striking the refueling aircraft  20 . Also shown in  FIG. 9 , as the hose  14  is drawn inward by the hose drum unit  12 , the hose  14  may roll on the roller  34  to reduce wear of the hose  14  and reduce the torque required by the drive/controller unit  26 . 
       FIG. 10  is a simplified view of the refueling system  10  in an intermediate stage of retrieval. As shown in  FIG. 10 , the backstop  48  is disposed to direct the drogue  16  up and into the ring  32 . The backstop  48  additionally assists in deflating or collapsing the drogue  16  from the deployed configuration into a storage configuration. Once secured within the ring  32  and/or rings  38 , the drogue  16  may be drawn into the refueling aircraft  20  via the action of the hose drum unit  12  and/or actuator  42 . 
       FIG. 11  is a simplified view of the in-flight refueling system  10  in an end stage of retrieval. As shown in  FIG. 11 , the drogue  16  and deployment/retrieval device  18  may be completely withdrawn into the refueling aircraft  10 . It is an advantage of the deployment/retrieval device  18  that drag on the refueling aircraft  20  is minimized by withdrawing the deployment/retrieval device  18  into the refueling aircraft  20 . In contrast, a device that resides on the exterior of the refueling aircraft  20  will generate drag and therefore impede the performance of the refueling aircraft. In addition, aerodynamic surfaces added to the exterior of a device that resides on the exterior of the refueling aircraft add weight, complexity, and expense. 
     The many features and advantages of the invention are apparent from the detailed specification, and thus, it is intended by the appended claims to cover all such features and advantages of the invention which fall within the true spirit and scope of the invention. Further, since numerous modifications and variations will readily occur to those skilled in the art, it is not desired to limit the invention to the exact construction and operation illustrated and described, and accordingly, all suitable modifications and equivalents may be resorted to, falling within the scope of the invention.