Abstract:
A retention system includes a base supporting a wing spar and a post extending through the base from a first side of the base to a second side of the base. The post inserts through an aperture in the spar. A stop is selectively securable to the post over the second side of the base. A locking member engages the post on the first side of the base. The locking member is configured to selectively move the post from an unlocked position to a locked position in which the post is withdrawn toward the first side relative to the unlocked position. A biasing member encircles the post and is positioned between the stop and the second side. When the locking member is in a closed position the biasing member expands to engage the aperture and resist movement of the wing spar. A plurality of cradles may support the wing.

Description:
FIELD OF THE INVENTION 
     This application relates to systems and methods for storing and shipping an aerial vehicle, such as an unmanned aerial vehicle (UAV). 
     BACKGROUND OF THE INVENTION 
     The capabilities and use of UAVs has exploded in recent years. Some UAVs have the capacity of performing long distance surveillance as well as launching missiles. Inasmuch as a UAV has no pilot, it is often inconvenient to fly a UAV to a theatre of operation that exceeds the operational range of the drone. However, UAVs are very sophisticated machines and can also be very large. 
     Accordingly, it would be an advancement in the art to provide an improved means for shipping and storing a UAV. 
     SUMMARY OF THE INVENTION 
     In one aspect of the invention, one or more cradles are used to support a wing. The cradle may include first and second clamping members pivotally coupled to one another and defining a pivot axis. The first clamping member defines a first surface and the second clamping member defines a second surface. The first and second surfaces each conform to a portion of an airfoil contour of the wing and include a cushioning material. A first trough member defines a channel substantially parallel to the pivot axis and defines a third surface conforming to one of a leading edge and a trailing edge portion of the wing. In some embodiments, the trailing edge and its control surfaces are not contacted by the cradle as they are delicate. In such embodiments, the cradle contours the wing up until the control surface at which point clearance is made to avoid contact. The first trough member is positioned to engage the leading edgeportion when the wing is positioned within the first and second clamping members. A locking member engages the first and second clamping members and is configured to selectively lock the first and second clamping members having the first and second surfaces engaging the wing. 
     In another aspect of the invention, the first and second clamping members each include a frame and a layer of the cushioning material secured to the frame. In some embodiments, the frame includes first and second end plates and a plurality of rods secured between the first and second end plates and extending through the layer of cushioning material. The layer of cushioning material may include a plurality of cushioning members each having at least one surface that is substantially conformal to a portion of a contour of the wing at at least one longitudinal position. The layer of cushioning material may extend outwardly from the first and second end plates. The first and second end plates may define inward facing edges that are substantially conformal to the wing at the at least one longitudinal position. 
     Systems and methods for using the cradle are also disclosed and claimed. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
       Preferred and alternative examples of the present invention are described in detail below with reference to the following drawings: 
         FIG. 1  is a top plan view of an exemplar UAV such as might be used in accordance with an embodiment of the present invention; 
         FIG. 2  is a perspective view of a cradle for a wing in accordance with an embodiment of the present invention; 
         FIG. 3  is an isometric view of a rear clamping member in accordance with an embodiment of the present invention; 
         FIG. 4  is an isometric view of a front clamping member in accordance with an embodiment of the present invention; 
         FIG. 5  is a side view of a cradle in accordance with an embodiment of the present invention; 
         FIG. 6  is a side view of a cradle having a wing positioned therein in accordance with an embodiment of the present invention; 
         FIG. 7  is a top plan view of a disassembled UAV in accordance with an embodiment of the present invention; 
         FIG. 8  is a cross-sectional view of a spar retention system in accordance with an embodiment of the present invention; 
         FIG. 9  is an isometric view of a spar retention system in accordance with an embodiment of the present invention; 
         FIG. 10  is an isometric view of a spar retention system having a wing spar secured thereto in accordance with an embodiment of the present invention; 
         FIG. 11  is an isometric view of frame to which a spar retention system may be mounted in accordance with an embodiment of the present invention; and 
         FIG. 12  is a top plan view of a disassembled UAV secured within a container in accordance with an embodiment of the present invention. 
     
    
    
     DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT 
     Referring to  FIG. 1 , a UAV  10  may be embodied as a fixed-wing aircraft having a fuselage  12 . Wings  14  extend laterally from the fuselage  12  may define an airfoil contour. One or more propulsion sources  16  are mounted to the fuselage  12  or the wings  14 . The propulsion source  16  may be embodied as an internal combustion engine coupled to a propeller, turbo fan, or the like. The propulsion source  16  may also be embodied as a jet engine coupled to a propeller or turbo fan or used alone. 
     One or more tail planes  18  defining an empennage of the UAV  10  may secure to a rearward end of the fuselage  12 . The tail planes  18  may define a conventional horizontal stabilizer and vertical stabilizer with corresponding elevator and rudder control surfaces. Alternatively, tail planes  18  may include a pair of angled tail planes each with a corresponding control surface and protruding upwardly or downwardly from the fuselage  12 . 
     Referring to  FIG. 2 , a cradle  20  may include a rear clamping member  22  and a front clamping member  24 . The front clamping member  24  may pivotally secure to the rear clamping member  22  by means of a pivot  26  defining a pivot axis  28 . In the illustrated embodiment, the pivot axis  28  is substantially parallel to a longitudinal direction  30 . The longitudinal direction  30  may be defined along a longitudinal direction of a wing clamped within the cradle  20 . A vertical direction  32  may also be defined as perpendicular to the longitudinal direction  30 . The vertical direction  32  may be substantially parallel to the chord line of a wing positioned in the cradle  20 . For purposes of this disclosure “substantially” parallel or perpendicular may be interpreted as within 10 degrees of perpendicular or parallel, preferably within 5 degrees, and preferably within 1 degree, of perpendicular or parallel. Likewise, “substantially” equal to a value may mean within +/−5% of the value, preferably within 1% of the value. 
     In some embodiments, troughs  34  may extend on either side of the front and rear clamping members  22 ,  24 . The troughs  34  may be positioned on one or both sides of the clamping members  22 ,  24  along the longitudinal direction  30 . As shown in  FIG. 2 , pivot axis  28  may be located vertically adjacent the troughs  34 . Stated differently, the troughs  34  may be secured to the rear clamping member  24  near the pivot axis  28 . In some embodiments, the extent of each trough  34  in the longitudinal direction is between 0.5 and 2, preferably between 0.9 and 1, times a width of the rear clamping member  22 . In the illustrated embodiment, each trough  34  has a width substantially equal to the width of the rear clamping member  22 . 
     A locking member  36  engages the front and rear clamping members  22 ,  24 . The locking member  36  may selectively lock the front and rear clamping member  22 ,  24  relative to one another with a desired amount of locking force. For example, the locking member  36  may be any over-center latch known in the art. Inasmuch as a wing stored in the cradle  20  may be shipped by air, the over-center latch is preferably lightweight. The latching force may be defined by the latch and may be adjustable as known in the art. 
     Referring to  FIG. 3 , in some embodiments a rear clamping member  22  may be as illustrated. The rear clamping member  22  may include cushioning members  40 . For example, one or more cushioning members  40  may be positioned between end plates  38 . In the illustrated embodiments, the cushioning members  40  are sheets of a cushioning material cut to a desired shape. The illustrated rear clamping member  22  may be symmetric about a plane perpendicular to the longitudinal axis  30 . Accordingly, for the illustrated end plate  38  a corresponding end plate  38  is located on an opposite side in a mirror configuration. The plates  38  may be fastened to one another such that the cushioning members  40  are captured between the plates. For example, each rod  42  of a plurality of rods  42  may secure to both plates  38  and further extend through the cushioning members  40  positioned between the plates  38 . The rods  42  and plates  38  may be formed of a rigid but light weight material such as aluminum, a rigid plastic, composite material, or the like. The rods  42  may therefore serve to limit compression of the cushioning member  40 . The rods  42  may have circular, rectangular, or some other cross section. In the illustrated embodiment, the rods  42  are secured to the end plates  38  by means of fasteners  44  passing through end plates  38  and engaging an end portion of a rod  42 . In some embodiments, a rod  42  may define interior or exterior threads engaging corresponding threads on the fastener  44 . In other embodiments, the fasteners  44  may be embodied as star fangled nuts and a rod  42  may define a hollow end portion for securing to a star fangled nut. In some embodiments, a backing plate is secured to both end plates  38 , such as by means of welds or other fasteners, and the cushioning members  40  are secured to the backing plate by means of adhesive or some other means. 
     In a like manner, a trough  34  may be defined by cushioning members  48  defining the contour of the trough  34 . The cushioning members  48  may be captured between an end plate  38  and an end plate  46 . Likewise, rods  50  may secure to the end plate  38  and the plate  46  in order to capture the cushioning members  48 . The rods  50  may pass through the cushioning members  48 . The rods  50  may secure to the end plate  46  and end plate  38  by any of the fastening means noted above, such as fasteners  52  embodied as star fangled nuts or some other fastener. 
     In some embodiments, a locking member  36  may mount to the rear clamping member  22  by means of a lock mount  54  secured thereto. In the illustrated embodiment, one or more of the cushioning members  40  may define a cutout portion  56  for receiving the lock mount  54 . As is apparent in  FIG. 3 , the cutout portion  56  does not extend completely through the cushioning member such that the hard material forming the lock mount  54  does not contact a wing positioned in the cradle  20 . Stated differently, a portion of one or more of the cushioning members  40  remains positioned between the lock mount  54  and a wing positioned between the clamping members  22 ,  24 . 
     The lock mount  54  may include a back plate  58  and side plates  60  extending outwardly from the back plate  58 . The side plates  60  may secure to the back plate  58  by means of screws, bolts, welds, or some other fastening means. In some embodiments, the back plate  58  and side plates  60  are formed from one monolithic member, such as a channel or rectangular tube having one wall removed. In the illustrated embodiment, the side plates  60  secure to the end plates  38  by means of rods  62  extending through one or more of the cushioning members and secured to the end plates  38  and plates  60  by means of fasteners  64 , such as star fangled nuts or some other fastening means. One or both of the end plates  38  and side plates  60  may define an aperture  66  for receiving a pivot  26 , such as one or more pivot pins  26 , extending through the apertures  66 . 
     Referring to  FIG. 4 , in some embodiments a front clamping member  24  may be as illustrated. The front clamping member  24  may include cushioning members  70 . For example, one or more cushioning members  70  may be positioned between end plates  68 . In some embodiments, the cushioning members  40 ,  48 ,  70  may include a polymer, such as a foam polymer, that has a modulus of elasticity of between 0.001 and 1 GPa, and preferably between 0.01 and 0.1 GPa. This modulus of elasticity may refer to the polymer itself or the polymer after any foaming process. The illustrated front clamping member  24  is symmetric about a plane perpendicular to the longitudinal axis  30 . Accordingly, for the illustrated end plate  68  a corresponding end plate  68  is located on an opposite side in a mirror configuration. The plates  68  may be fastened to one another such that the cushioning members  70  are captured between the plates  68 . For example, each rod  72  of a plurality of rods  72  may secure to both plates  78  and further extend through the cushioning members  70  positioned between the plates  68 . The rods  72  may have circular, rectangular, or some other cross section. In the illustrated embodiment, the rods  72  are secured to the end plates  68  by means of fasteners  74  passing through end plates  68  and engaging an end portion of a rod  72 . In some embodiments, a rod  72  may define interior or exterior threads engaging corresponding threads on a fastener  74 . In other embodiments, the fasteners  74  may be embodied as star fangled nuts and the rods  72  may define a hollow end portion for securing to a star fangled nut. In some embodiments, a backing plate is secured to both end plates  68 , such as by means of welds or other fasteners, and the cushioning members  70  are secured to the backing plate by means of adhesive or some other means. 
     In some embodiments, a locking member  36  may mount to the front clamping member  24  by means of a lock mount  76  secured thereto. In the illustrated embodiment, one or more of the cushioning members  70  may define a cutout portion  78  for receiving the lock mount  76 . As is apparent in  FIG. 3 , the cutout portion  78  does not extend completely through the cushioning member  70  such that the hard material forming the lock mount  76  does not contact a wing positioned in the cradle  20 . Stated differently, a portion of the cushioning member  70  is interposed between the lock mount  76  and a wing clamped by the front clamping member  24 . 
     The lock mount  76  may include a back plate  80  and side plates  82  extending outwardly from the back plate  80 . The side plates  82  may secure to the back plate  80  by means of screws, bolts, welds, or some other fastening means. In some embodiments, the back plate  80  and side plates  82  are formed from one monolithic member, such as a channel or rectangular tube having one wall removed In the illustrated embodiment, the side plates  82  secure to the end plates  68  by means of rods  84  extending through one or more of the cushioning members  70  and secured to the end plates  68  and plates  82  by means of fasteners  86 , such as star fangled nuts or some other fastening means. One or both of the end plates  68  and side plates  82  may define an aperture  86  for receiving a pivot  26 , such as one or more pivot pins  26 , extending through the apertures  86  and the apertures  66  of the rear clamping plate  22 . 
     In some embodiments, a bushing  90  extends between the side plates  82 . A rod  90  may pass between opposing end plates  68  and pass through the bushing  90  as well as the side plates  82 . The rod  90  may secure to the end plates  68  by means of fastener  92  in the same manner of other rods discussed hereinabove. 
     Referring to  FIG. 5 , the front clamping member  24  pivotally secures to the rear clamping member  22  by means of the pivot  26 . In this manner, the front clamping member  24  may be pivoted away from the rear clamping member  22  in order to permit insertion of a wing, as shown by the dotted representation  102  of the front clamping member. 
     The cushioning members  40  of the rear clamping member  22  and the cushioning members  70  of the front clamping member  24  define conformal surfaces  96 ,  100  that are shaped to conform to surfaces of a wing. Likewise, the cushioning members  48  of the trough  34  define conformal surfaces  100  conforming to one of a leading edge portion and a trailing edge portion of a wing. As noted above, in some embodiments, contact between the cradle  20  and the trailing edge of the wing  14  and any control surfaces is avoided. As known in the art, the cross-sectional shape of a wing preferably varies along the length thereof. Accordingly, the conformal surfaces  96 ,  98 ,  100  may conform to the surface of a wing at a particular longitudinal position. Likewise, for a given cradle  20 , the plurality of cushioning members  40  may each have a unique corresponding conformal surface  96  corresponding to a contour of the wing at a particular longitudinal position. Likewise each of the plurality of cushioning members  48  may have a unique conformal surface  100  and each of the plurality of cushioning members  70  may have a unique conformal surface  98 . In some embodiments, the conformal surfaces  96 ,  98 ,  100  are cut such that they are contoured in both vertical  32  and horizontal directions (e.g. in the plane of the page of  FIG. 5 ) and the longitudinal direction  30  in order to conform to variation in the contour of the wing in three dimensions. In other embodiments, the conformal surfaces  96 ,  98 ,  100  are uniform in the longitudinal direction such that the conformal surfaces  96 ,  98 ,  100  are contoured in only two dimensions (horizontal and vertical). For example, the arbitrary contours of the conformal surfaces  96 ,  98 ,  100  may be machined using a water jet cutter or other machining process that may machine precise contours in two dimensions. 
     In some embodiments, some or all of the conformal surfaces  96 ,  98 ,  100  may include a pattern of ridges or other protuberances that are positioned to be located over structural reinforcements under the skin of the wing  14  at the longitudinal location at which the conformal surfaces  96 ,  98 ,  100  engage the wing  14 . In this manner, pressure exerted on the wing is more concentrated on those areas that are better able to bear such pressure. 
     In some embodiments, the end plates  38 ,  46 ,  68  may define conformal edges  104 ,  106 ,  108  respectively that extend along the conformal surfaces  96 ,  98 ,  100 . The conformal edges may substantially conform to a surface that is offset from a contour of the wing contour by some constant or variable gap, such that during use, the cushioning members  40 ,  48 ,  70  will not compress to the point that the wing contacts the end plates  38 ,  46 ,  68  under expected compression forces and amounts. As noted above, the various cushioning members  40 ,  46 ,  70  of a cradle may not all have conformal surfaces  96 ,  98 ,  100  of the same shape. In such embodiments, each end plate  38  may have a conformal edge  104 ,  106 ,  108  that is offset from the conformal surface  96 ,  98 ,  100  of the cushioning members  40 ,  46 ,  70  adjacent thereto (e.g. the outermost cushioning members  40 ,  46 ,  70 . 
     Referring to  FIG. 6 , in use a wing  14  may be placed between the front and rear clamping members  22 ,  24  and the front clamping member  24  may be pivoted toward the rear clamping member  22 . As shown in  FIG. 6 , the leading edge portion of the wing  14  rests in a concave portion of the rear clamping member  22  and the trough  34 . The locking member  36  ( FIG. 2 ) may then be engaged to apply a consistent clamping force between the clamping members  22 ,  24 . As a result of the clamping force, the cushioning members  40 ,  46 ,  70  may compress due to engagement of the wing  14  with the conformal surfaces  96 ,  98 ,  100 . As noted above, the compression is preferably such that the wing  14  does not contact the end plates  38 ,  46 ,  68 . 
     Referring to  FIG. 7 , to facilitate shipping and storage, the UAV  10  may be disassembled. As shown in  FIG. 7  at least the wings  14  may be removed to reduce the footprint of the UAV  10 . Other parts of the UAV  10  such as the propulsion source  16  and tail planes  18  may also be removed. The wings  14  may secure to the fuselage by means of a wing spar  120 . As known in the art, a wing spar  120  provides structural rigidity to the wing  14  for transferring lift forces to the fuselage  12 . In some embodiments, wings  14  may secure by some other means or interface other than wing spars  120 , such as a plate or other structure defining a hole pattern for receiving fasteners. Following shipment or storage according to methods disclosed herein, the wings  14  may be reattached to the fuselage  12  using the wing spars  120  in order to deploy the UAV  10 . 
     The fuselage  12  may have indexing members  122  fastened thereto using a fastening system  124 . The fastening system  124  may be a fastening system and corresponding indexing members  122  as disclosed in U.S. application Ser. No. 13/974,350 filed Aug. 23, 2013 and entitled FUSELAGE INDEXING SYSTEM AND METHOD, which is hereby incorporated herein by reference. 
     Referring to  FIG. 8 , as noted above, the wings  14  may be supported by means of cradles  20  as described herein. As also noted above, the cradles  20  may not provide significant resistance to longitudinal movement of the blade  20 . Accordingly, the wing spar  120  may be fastened to a storage container by means of a spar retention system  130 . The spar retention system  130  may be understood with respect to a longitudinal direction  132  that is substantially parallel to the longitudinal axis of the wing  14  used with the spar retention system  130 . A vertical direction  32  may be defined as substantially parallel to a line parallel to a line normal to a surface on which the spar retention system  130  is resting. 
     The spar retention system  130  may include a lock down clamp  134  and a post  136 . The lock down clamp  134  may be any lock down clamp  134  known in the art. As known in the art, a lock down clamp  134  has an open position and a closed position. The lock down clamp  134  provides a determined amount of travel between the open and closed position and may be adjustable as to travel and clamping force in the closed position. The post  136  is coupled to the lock down clamp  134 , such as by means of a fastener  138 . The post  136  is translated upward when the clamp  134  is moved from the closed to the open position and translated downward when the clamp  134  is moved from the open to the closed position. 
     A stop  140  may be selectively secured to the post  136 . For example, the stop  140  may define a slot  142  sized to receive a distal portion of the post  136 . The post  136  may define a distal portion that is wider than the slot  142  to hinder removal of the stop  140 . For example, in the illustrated embodiment, a washer  144  or other structure secures to a distal end of the post  136 , such as by means of a fastener  146 , e.g. screw. In some embodiments, the stop  140  includes a seat, e.g. countersink, sized to receive the washer  144  or other widening structure. Inasmuch as the stop  140  is removable from the post, the stop  140  may include an aperture  150  or other structure for receiving a lanyard (not shown). The lanyard may be anchored to an anchor  152  secured to a base  154 . 
     The base  154  may support a wing spar  120  secured using the spar retention system  130 . The base  154  may define a rigid and substantially planar surface or have a contour corresponding to a contour of a wing spar  120 . For example, the base  154  may be embodied as an aluminum plate. The base  156  may be interposed between the stop  140  and the clamp  134 . The base  156  may define an aperture  156  through which the post  136  passes. In some embodiments, a cushioning member  158  secures to an upper surface of the plate  154 , e.g. opposite the clamp  134  and facing the stop  140 . The cushioning member  158  may define an aperture  160  through which the post  136  passes. The cushioning member  158  may be include a flexible polymer such as polyurethane or the like. The cushioning member  158  may have a modulus of elasticity such that the cushioning member  158  deforms in response to clamping force exerted by the clamp  134  on the stop  140 . For example, the cushioning member  158  may have a module of elasticity of between 0.001 and 1 GPa and, preferably between 0.01 and 0.1 GPa. In some embodiments, the stop  130  may also have a modulus of elasticity within either of these ranges and may include the same or different material and have the same or different modulus of elasticity as the cushioning member  158 . 
     A die spring  162  may encircle the post  136 . The die spring  162  may be compressed by the stop  140  when the clamp  134  is in the closed position. As a result of the compression, the die spring  162  may also expand outwardly from the post  136 . In some embodiments, the cushioning member  158  may define a seat  164 , e.g. counterbore, that has a diameter that is larger than an undeformed diameter of the die spring  162 . The seat  164  may receive a bushing or other structure secured to a wing spar  120  used in combination with the spar retention system  130 . In some embodiments, the aperture  160  defined by the cushioning member  158  is slightly smaller (e.g. between 5 and 10% smaller) than an undeformed diameter of the die spring  162  passing there through. In this manner, the cushioning member  158  may hinder movement of the die spring  162  when the post  136  is moved upward and downward. 
     In some embodiments, the spar retention system  130  may be mounted to a container or other storage facility directly or by means of one or more intervening members. For example, the spar retention system  130  may mount to a beam  166  that secures to a container or secures to some other member mounted to the container. 
     Referring to  FIGS. 9 and 10 , in use the stop  140  may be removed from the post  136  as shown by the dotted representation  168 . Removing the post  136  may be accomplished by sliding the post  136  out of the slot  142 . Where the stop  140  includes a seat  148 , the stop  140  may be slid downwardly to disengage the washer  144  from the seat  148  prior to sliding the post  136  out of the slot  142 . In preparation for placement of the wing spar  120 , the clamp  134  may be placed at or near the open position such that the top of the post  136  is elevated above the base  154  and cushioning member  158  is not compressed and therefore small enough to insert through the wing spar  120 . 
     Referring specifically to  FIG. 10 , with the stop  140  removed, a wing spar  120  may be positioned over the post  136  and die spring  162 . For example, the wing spar  120  may define an aperture  170  and in the open position of the clamp  134 , the uncompressed (or less compressed due to an open position of the clamp  134 ) die spring  162  may be sized to fit through the aperture  170  as is the washer  144 . The stop  140  may be placed in the position shown having the washer  144  in the seat  148  as shown in  FIG. 8  by sliding the post  136  into the slot  142 . The clamp may then be moved to the closed position as shown in  FIG. 10 . In the closed position, the die spring  162  may be deformed such that it presses against the aperture  170  and if unconstrained by the aperture  170  would be larger than the aperture  170 . In some applications, the aperture  170  is tapered or has some shape other than cylindrical. The deformation of the die spring  162  may accommodate this geometry by expanding to at least partially fill part of the aperture  170  and thereby hinder movement of the wing spar  120 . The resilience of the cushioning member  158  and the stop  140  may result in deformation of these members due to the clamping force of the clamp  134  thereby reducing any scratching or denting of the wing spar  120  and providing additional grip on the wing spar  120 . 
       FIG. 11  illustrates an example use for the spar retention system  130 . As illustrated the beams  166  form part of a frame  172  that is mounted to a container. In some embodiments, the frame  172  may include structures for retaining or supporting other parts of the UAV  10 . For example, the frame  172  may include tail plane supports  174  that are angled or otherwise positioned to support the tail planes  18  of the UAV. The tail plane supports  174  may include cushioning surface made having some or all of the properties of other cushioning materials described herein. Also shown in  FIG. 11  is a lanyard coupled to the stop  140 , such as by means of the aperture  150 . The lanyard may also be connected to some other portion of the frame  172  or spar retention system  130 , such as the anchor  152  ( FIG. 8 ). 
     Referring to  FIG. 12 , the cradles  20  as disclosed herein above may be used in the storing and shipping of a UAV  10 . For example, a container  178  may store a disassembled UAV  10 . In such embodiments, a plurality of cradles  20  may secure to the container  178  either directly or indirectly by means of a fixture or frame member. The wing  14  mounts within the cradles  20  as described herein and is thereby retained against movement during shipping. In some embodiments, the cushioning members  40 ,  48 ,  70  may be configured relative to the end plates  38 ,  46 ,  68  such that the wing will not contact the plates  38 ,  46 ,  68  in response to deflection of the cushioning members  40 ,  48 ,  70  due to expected acceleration of the container  110 . The remainder of the UAV  10  may also secure within the container  178 , including the fuselage  12 . 
     As noted above, the fuselage  14  may have a fastening system  124  and indexing members  22  secured thereto as described U.S. application Ser. No. 13/974,350 filed Aug. 23, 2013 and entitled FUSELAGE INDEXING SYSTEM AND METHOD, which is hereby incorporated herein by reference. 
     The container  178  may further have receivers  180  for engaging the indexing members  122  and a corresponding frame  182  mounting the receivers to the container  178  as described in U.S. application Ser. No. 13/974,350 filed Aug. 23, 2013 and entitled FUSELAGE INDEXING SYSTEM AND METHOD, which is hereby incorporated herein by reference. 
     The container  178  may be a container as described in U.S. application Ser. No. 13/974,322 filed Aug. 23, 2013 and entitled CLOSURE SYSTEM FOR CONTAINERS, which is hereby incorporated herein by reference. 
     The spar  120  of the wing  14  may be further restrained by means of the spar retention system  130  as described hereinabove. In this manner, movement of the wing  14  transverse to the longitudinal axis thereof may be restrained by means of the cradles  14  and movement along the longitudinal axis may be restrained by the spar retention system  130 . 
     While the preferred embodiment of the invention has been illustrated and described, as noted above, many changes can be made without departing from the spirit and scope of the invention. For example, although the cradle described herein is shown being used for a wing of a fixed wing aircraft, the cradle may also be used for wings of a rotary wing aircraft, windmill blades, or other long and/or delicate structures. Accordingly, the scope of the invention is not limited by the disclosure of the preferred embodiment. Instead, the invention should be determined entirely by reference to the claims that follow.