Abstract:
A morphing aircraft that is achieves multi-modality location and camouflage for payload emplacement The morphing aircraft includes a substantially cylindrical fuselage including a shape configured as a packaging container with a first end and a second end A set of wings is coupled to the fuselage The set of wings includes a first position where the set of wings is extended outwards from the fuselage and a second position where the set of wings is retracted inwards towards the fuselage A tail is coupled to the second end of the cylindrical fuselage The tail includes a first position where the tail is extended outward from the fuselage and a second position where the tail is retracted inward towards the fuselage A propeller is mounted to the first end of the fuselage An engine is mechanically coupled to the propeller The engine is enclosed within the fuselage and powers the propeller.

Description:
CROSS-REFERENCE TO RELATED APPLICATIONS 
     This application is based upon and claims priority from prior U.S. Provisional Patent Application No. 61/091,476, filed on Aug. 25, 2008 the entire disclosure of which is herein incorporated by reference. 
    
    
     FIELD OF THE INVENTION 
     The present invention generally relates to unmanned aerial vehicles (UAV), and more particularly relates to transformable UAVs. 
     BACKGROUND OF THE INVENTION 
     Remote control or autonomously unpiloted aircraft have been used for years. These aircraft are often referred to as UAVs or Unmanned Aerial Vehicles. UAVs are used by the military for surveillance, reconnaissance, engagement, and the like. They are also used in many civil applications such as police, firefighting, and bomb squad environments where human participant would be at risk. UAVs are equipped with sensors and cameras to detect sounds, images, chemicals, temperature, vibration, light, velocity, Doppler shift, and even biological matter. 
     UAVs are available in a variety of shapes, sizes and configurations, and characteristics using various engines including electric-powered engines, gas-powered engines and jet-powered engines to allow for controlled sustained levels of flight. When utilizing a UAV it is important to evade detection in applications such as surveillance and reconnaissance. Unfortunately, conventional UAVs are difficult to place in various environments such as urban environments without being detected. Once a UAV is detected by a human, aircraft, robot, or the like, the UAV loses its effectiveness. 
     SUMMARY OF THE INVENTION 
     A morphing aircraft that is achieves multi-modality location and camouflage for payload emplacement. In one embodiment, an unmanned aerial vehicle is disclosed. The unmanned aerial vehicle comprises a substantially cylindrical fuselage comprising a shape configured as a packaging container with a first end and a second end. A set of wings is coupled to the fuselage. The set of wings comprises a first position where the set of wings is extended outwards from the fuselage and a second position where the set of wings is retracted inwards towards the fuselage. A tail is coupled to the second end of the cylindrical fuselage. The tail comprises a first position where the tail is extended outward from the fuselage and a second position where the tail is retracted inward towards the fuselage. A propeller is mounted to the first end of the fuselage. An engine is mechanically coupled to the propeller. The engine is enclosed within the fuselage and powers the propeller. 
     In another embodiment, a rotary-wing unmanned aerial vehicle is disclosed. The rotary-wing unmanned aerial vehicle comprises a substantially cylindrical fuselage comprising a shape configured as a packaging container with a first end and a second end. At least one rotor is coupled to the first end. The at least one rotor comprises a first position where the at least one rotor is extended outwards from the fuselage and a second position where the at least one rotor is retracted inwards towards the fuselage. An engine is mechanically coupled to the at least one rotor, wherein the engine is enclosed within the fuselage and powers the at least one rotor. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
       The accompanying figures where like reference numerals refer to identical or functionally similar elements throughout the separate views, and which together with the detailed description below are incorporated in and form part of the specification, serve to further illustrate various embodiments and to explain various principles and advantages all in accordance with the present invention, in which: 
         FIG. 1  is a generalized diagram of a fix-wing aircraft according to the prior art; 
         FIG. 2  shows one example of an unmanned aerial vehicle comprising wings and a propeller extended outside a packaging container according to one embodiment of the present invention; 
         FIG. 3  shows one example of an unmanned aerial vehicle comprising a multi-joint wing in a fix-wing aircraft for extending and retracting into the fuselage according to one embodiment of the present invention; 
         FIGS. 4-6  shows various example of an unmanned aerial vehicle comprising folding wings extending and retracting into a fuselage according to one embodiment of the present invention; 
         FIGS. 7-9  shows various examples of an unmanned aerial vehicle comprising canister wings extending and retracting into a fuselage according to one embodiment of the present invention; 
         FIGS. 10-11  show various examples of an unmanned aerial vehicle comprising different wing locations on a fuselage according to one embodiment of the present invention; 
         FIGS. 12-15  show various examples of different tail configurations for an unmanned aerial vehicle according to one embodiment of the present invention; 
         FIGS. 16-19  show various examples of different propeller mounts for an unmanned aerial vehicle according to one embodiment of the present invention; 
         FIGS. 20-24  show various examples of different propellers for an unmanned aerial vehicle according to one embodiment of the present invention; 
         FIGS. 25 and 26  show examples of a an unmanned aerial vehicle comprising a set of wings each with a propeller mounted thereon according to one embodiment of the present invention; 
         FIGS. 27-29  show various examples of propeller configurations according to one embodiment of the present invention; 
         FIG. 30  shows one example of an unmanned aerial vehicle comprising inflatable wings and tail according to one embodiment of the present invention; 
         FIGS. 31-32  show various examples of an unmanned aerial vehicle comprising wings that can be converted into a sail according to one embodiment of the present invention; 
         FIGS. 33-34  show various examples of an unmanned aerial vehicle that is configured as an airship according to one embodiment of the present invention; 
         FIGS. 35-37  show various examples of a unmanned aerial vehicle comprising wings comprising wings formed from the container acting as the fuselage according to one embodiment of the present invention; 
         FIG. 38  shows one example of an unmanned aerial vehicle comprising flappable wings according to one embodiment of the present invention; 
         FIG. 39  shows one example of an unmanned vehicle that is submersible according to one embodiment of the present invention; 
         FIGS. 40-42  show various examples of unmanned aerial vehicles comprising different forms of locomotion according to one embodiment of the present invention; 
         FIGS. 43-44  shows various examples of a drive shaft comprising extending and retracting components to fit within a container for an unmanned aerial vehicle and to work cooperatively with an insert such as that shown in  FIG. 11  according to one embodiment of the present invention; 
         FIG. 45  shows one example of an insert comprising a drive mechanism for an unmanned aerial vehicle such as that shown in  FIG. 10  according to one embodiment of the present invention; 
         FIG. 46  is a generalized diagram of a rotary-wing aircraft according to the prior art; 
         FIG. 47  shows one example of a rotary-wing aircraft with the rotor extended outside a packaging container according to one embodiment of the present invention; 
         FIG. 48  shows one example of a rotary-wing aircraft with the rotor extended and a motor and other avionics inside a packaging container according to one embodiment of the present invention; 
         FIGS. 49-50  show various examples of a flexible rotor in a rotary-wing aircraft with the rotor shaft and electronics outside a packaging container according to one embodiment of the present invention; 
         FIGS. 51-56  show various examples of a telescoping, hinged, and bendable rotor assemblies in a rotary-wing aircraft according to one embodiment of the present invention; 
         FIG. 57  shows one example of a rotary-wing aircraft with the rotor shaft extended outside a packaging container according to one embodiment of the present invention; 
         FIG. 58  shows one example of a rotary-wing aircraft with the rotor shaft, motor, and other avionics retracted inside a packaging container according to one embodiment of the present invention; 
         FIG. 59  shows one example of a rotary-wing aircraft with an insert outside a packaging container with hinged wings in a retracted position according to one embodiment of the present invention; 
         FIG. 60  shows one example of a rotary-wing aircraft with an insert outside a packaging container with hinged wings in a semi-extended position according to one embodiment of the present invention; 
         FIG. 61  shows one example of a rotary-wing aircraft with an insert inside a packaging container with hinged wings in a retracted position according to one embodiment of the present invention; 
         FIG. 62  shows one example of a rotary-wing aircraft with an insert inside a packaging container with hinged wings in a semi-extended position according to one embodiment of the present invention; 
         FIGS. 63 and 64  show examples of a rotary-wing aircraft with insert inside a packaging container with hinged wings in a fully extended position according to one embodiment of the present invention; 
     
    
    
     DESCRIPTION OF THE PREFERRED EMBODIMENTS 
     As required, detailed embodiments of the present invention are disclosed herein; however, it is to be understood that the disclosed embodiments are merely examples of the invention, which can be embodied in various forms. Therefore, specific structural and functional details disclosed herein are not to be interpreted as limiting, but merely as a basis for the claims and as a representative basis for teaching one skilled in the art to variously employ the present invention in virtually any appropriately detailed structure and function. Further, the terms and phrases used herein are not intended to be limiting; but rather, to provide an understandable description of the invention. Moreover, some statements may apply to some inventive features but not to others. In general, unless otherwise indicated, singular elements may be in the plural and vice versa with no loss of generality. 
     The terms “a” or “an”, as used herein, are defined as one or more than one. The term plurality, as used herein, is defined as two or more than two. The term another, as used herein, is defined as at least a second or more. The terms including and/or having, as used herein, are defined as comprising (i.e., open language). The term coupled, as used herein, is defined as connected, although not necessarily directly, and not necessarily mechanically. The terms “bottle”, “beverage container”, “container”, “can”, and the like are used interchangeably herein to refer to any a portable container or box or package for holding liquids and solids. In one embodiment, the container characteristically has a neck and mouth and typically made of plastic or aluminum. However, this is only one example of a container applicable to various embodiments of the present invention. It should be noted that a container is not limited to having a neck and/or a mouth and being made of plastic or aluminum. 
     Various embodiments of the present invention have many advantages over conventional UAVs. One or more embodiments of the present invention provide a UAV that can transform or morph and into a common object that does not look like an aircraft and therefore avoids detection. This transformation is repeatable several times during the mission. 
     Prior Art Fixed-Wing Aircraft 
       FIG. 1  is a generalized diagram of a fix-wing aircraft  100  according to prior art. The fuselage or body  102  of the aircraft  100  holds various items and payloads. Attached to either side of the fuselage  102  is a set of wings  104  that provides most of the lift for the fix-wing aircraft  100 . A set of horizontal stabilizers  112  for controlling pitch or wings  106  are typically attached to the rear portion of the fuselage  102 , although there are designs with other placements. A vertical stabilizer  108  for controlling yaw is attached to the rear portion of the fuselage  102 , and again there is known designs with other placements and designs that combine the function of the wing  106 , horizontal stabilizers  112 , and vertical stabilizer  108 . In many common designs a set of elevators  110  to adjust pitch is hinged to the vertical stabilizer and a set of flaps  114  is hinged to the wings  104  change lift and drag is hinged each wing  104 . 
     Morphing Fixed Wing UAV 
       FIG. 2  illustrates one embodiment of a morphable fixed-wing UAV  200 . In particular, the embodiment of  FIG. 2  comprises a morphable fixed-wing UAV  200  having wings and a propeller that extend outside a beverage container according to one embodiment of the present invention. In this embodiment, a beverage container such as a Gatorade® plastic bottle is used as a fuselage  202 . It should be noted that various embodiments of the present invention are not limited to bottles or containers resembling bottles or cans. For example, other types of containers such as boxes, bags, other packaging containers, and the like can also be used as a morphable fixed-wing UAV. 
     The fuselage  202  is substantially cylindrical and configured in a shape of a beverage container with a first end  201  for a propeller and a second end  203  for horizontal  206  and vertical  208  stabilizers. The beverage container&#39;s external trade dress and lettering are designed to resemble a given consumer brand of beverage, which in this case a Gatorade® plastic bottle. In one embodiment, the fuselage is an actual consumer beverage container. In another embodiment, the material of the container/fuselage  202  is not limited to the material from which the actual container is generally made from. For example, a Gatorade® bottle is usually made from plastic. However, in some embodiments, the container  202  can comprise other materials such as metals, alloys, carbon fiber, other synthetic materials, and the like. In these embodiments, the container  202  comprises substantially the same shape, size, coloring, graphics, trade dress, and/or lettering of a given container such as a Gatorade® bottle. Therefore, the container  202  is made of materials that enhance the UAV  200 , but maintains the appearance of the common container. 
     The embodiment of  FIG. 2  shows a set of wings  204  that are extended outside the fuselage  202  along with horizontal stabilizer  206  and vertical stabilizer  208  mounted on an extension  209 . The extension  209  extends from the second end  203  of the fuselage  202 . In one embodiment, the extension  209  retracts into and extends out of an inner portion  205  of the fuselage  202 . The horizontal stabilizer  206  and vertical stabilizer  208 , in this embodiment, are bendable and/or foldable so that they are able to fit inside the inner portion  205  of the fuselage  202  when the extension  209  is retracted into the inner portion  205 . Alternatively, the horizontal stabilizer  206  and vertical stabilizer  208  are configured to wrap around an outer portion  207  of the fuselage  202  when the extension  209  is retraced into the inner portion  205 . In another embodiment, the horizontal stabilizer  206  and vertical stabilizer  208  are created from a portion of the fuselage  202 . In this embodiment, the container/fuselage  202  comprises two or more pieces that separate from each other when the extension  209  is extended. One of these portions becomes the fuselage  202  and the other one of these portions becomes the horizontal stabilizer  206  and vertical stabilizer  208 . In this embodiment, the extension  209  is coupled to the portion comprising the fuselage  202  and is also coupled to the other portion that is the horizontal stabilizer  206  and vertical stabilizer  208 . 
     A propeller  222  is also shown coupled to the outside of the fuselage  202 . In one embodiment, the propeller  222  is coupled to the first end  201  of the fuselage  202 . In the example of  FIG. 2 , the propeller  222  is coupled to the cap  211  of the container which forms the fuselage  202 . It should be noted that this is only an example and the propeller  222  can be coupled to other areas of the container as well. In one embodiment, the propeller  222  is formed from the cap  211 . In another embodiment, the propeller  222  is a separate component that is configured to substantially resemble a cap  209  of the container and replaces the original cap  211  when in use. 
     It is important to note that when the UAV  200  is ready for flight the wings  204 , extension  209  with the horizontal stabilizer  206  and vertical stabilizer  208  mounted thereon, and the propeller is configured at a first position as shown in  FIG. 2 . For example, the wings  204  are shown as being extended; the extension  209  is extended which configures the horizontal stabilizer  206  and vertical stabilizer  208  mounted on the extension  209  for flight; and the propeller is extended (e.g., the blades are extended). 
     In the case when the UAV is not flying, such as resting on the ground, the wings  204 , the horizontal stabilizer  206  and the vertical stabilizer  208  mounted on the extension  209 , and the propeller  222  retract internally into the fuselage in a second position. For example, the wings  204  retract through one or more areas  213  on the fuselage  202  and/or can fold/wrap around and/or adjacent to the fuselage  202 . The extension  209  retracts into the fuselage  202  as discussed above. If the propeller  222  is formed from the container such as from the cap  209  and/or the another portion of the container, the propeller  222  can retract inside the fuselage  202  or fold around and/or adjacent to the fuselage  202 . The propeller  222  can also be detachable as discussed above and replaced with an original part of the container such as the cap  209 . 
     A motor  220  internal to the fuselage and mechanically coupled to the propeller  220  is also labeled. Other avionics, controls and sensors (not shown) as positioned inside the fuselage  202  include cameras, microphones, chemicals sensors, biological sensors, location sensors such as Global Positioning Satellite modules, heat sensors, and the like. The engine  202  can be an electric engine and/or a gas engine. In addition to these items, the morphable UAV  200  can also include various weapons such as explosives. The morphable UAV  200  can also include various evasion weapons such as flares, chaff, smoke, and the like. The morphable UAV  200  can also include tracking modules that can be dropped on or attached to a target for tracking. 
     The wings  204 , horizontal and vertical stabilizers  106 ,  108 , and propellers  222  are configured to extend and retract using a variety of mechanisms.  FIGS. 3-11  illustrate a few embodiments used with a fixed winged UAV  200 . To begin,  FIG. 3  illustrates one embodiment of comprising a multi-joint wing  304  in a fix-wing UAV that extends and retracts into the fuselage  302 . The multi-joint wing  304  is configured to fold into the container forming the fuselage  202  and then extend from the container. The multi-joint configuration allows the length of the wings  304  to be several times the overall length of the bottle and to be hidden to maintain the original appearance of the container. 
     In particular,  FIG. 3  shows that each wing  304  comprises a first portion  324  and at least a second portion  326  that are pivotally coupled to each other via a pivoting mechanism  328 . The second portion  326  can pivot/rotate in a direction that is away from or towards the fuselage  302 . This decreases the length of the wing  304  and allows the wing  304  to retract into an internal portion  330  of the fuselage  302 . The first portion  324  of the wing  304  is pivotably coupled to a portion  332  of the fuselage  302  and can pivot/rotate in a direction that is away from or towards the fuselage  302  as well. 
       FIG. 4  illustrates another embodiment of a wing configuration. For example,  FIG. 4  shows a foldable wing extending and retracting around the fuselage in a fix-wing UAV. The folding wing is designed to fold around the curvature of the container upon landing and then extend for flight. One example of a foldable wing is disclosed in U.S. Pat. No. 7,331,546, entitled Bendable Wing for Micro Air Vehicle, filed Aug. 25, 2006, with inventors Peter Iflju et al., and commonly assigned herewith to the University of Florida Research Foundation, Inc. and the teachings of which is hereby incorporated by reference in its entirety. 
     In particular,  FIG. 4  shows a front view of the fuselage  402  of an UAV  400 . The wings  404  comprise a foldable/bendable material that allows the wings  404  to fold around the container forming the fuselage  402 .  FIG. 5  shows a side view of the fuselage  402  with the wings  404  in a partially folded configuration.  FIG. 6  shows a top of the fuselage  402  with the wings  404  in an extended position ready for flight. In one embodiment, the wings  404  comprise coloring, graphics, trade dress, and the like that substantially match and continue the design of the container forming the fuselage. For example, when the wings  404  are in a folded position, the coloring, graphics, trade dress, and the like of the wings  404  maintain the original appearance of the container. 
       FIG. 7  shows another embodiment of an extendable/retractable wing for a UAV  700 . In particular,  FIG. 7  shows a front cross-sectional view of a container forming a fuselage  702  with the wings  704  extended.  FIG. 8  shows a top of the container forming a fuselage  702  with the wings  704  extended. In one embodiment, the wings  704  are canister wings or wings that “roll” inside of an internal mechanism  734  of the fuselage  702 . In one embodiment, the wings  704  are mechanically coupled to a rolling/winding mechanism  736  that “rolls” or “winds” the wings  704  within the internal mechanism  734  that acts as a storage bin. The wings  704  enter the fuselage  702  through one or more areas  713 . When the wings  704  are retracted into the fuselage  702  they can be extended either manually, for example, by pulling the wings  704  outwards from the fuselage  702  or the wings  704  can be automatically extended using a motor or other mechanical device.  FIG. 9  shows the wings  704  retracted into the fuselage  702 . 
     In all the embodiments discussed herein the wing location is not required to always be in a forward position as shown in  FIG. 10 . Other wing locations, such as a rear wing, are shown in  FIGS. 10-11 . For example,  FIG. 11  shows a wing  1104  coupled to the second portion  1103  of the fuselage  1102 . In this example, the second potion  1103  is a rear portion and the wing  1104  is a rear wing. 
     As with the wing, different tail configurations are within the true scope and spirit of various embodiments of the present invention. For example,  FIGS. 12-15  illustrate various tail configurations in a fixed-wing UAV. In particular,  FIG. 12  shows a front view of a circular tail  1238 . In one embodiment, the circular tail  1238  is mechanically coupled to the extension  1209 . When the extension  1209  is retracted into the fuselage  1202 , the circular tail  1238  can either fold/bend to allow the tail to fit inside a container such as a beverage container forming the fuselage. The circular tail  1238 , in one embodiment, fits the inner diameter of the bottle and can utilize the rounded surface area as both a vertical and horizontal tail. 
     If the circular tail  1209  is made from a rigid material, a hinged area  1240  can be included that allows the circular tail  1238  to fold. In another embodiment, the circular tail  1238  is formed from a bottom portion of the container forming the fuselage. In this embodiment, when the extension  1209  is retracted into the fuselage, the circular tail  1238  forms the bottom portion (e.g., the portion of the container that rests on the ground when the container is in an upright position.) of the container. 
       FIG. 13  illustrates an expandable tail  1340  comprising a spring loaded mechanism  1342 . The spring loaded mechanism  1342 , which can be coupled to the extension  1309 , enables the arms  1344 ,  1346 ,  1348  of the tail  1342  to vary their position so that the tail  1342  is retractable as the tail  1342  is drawn into the container forming the fuselage  202 . The spring loaded mechanism  1342  also enables the arms  1344 ,  1346 ,  1348  of the tail  1342  to vary their position so that the tail  1342  can be expanded into a conventional tail for flight when withdrawn from inside of the container forming the fuselage  202 . The arms  1344 ,  1346 ,  1348  of the tail  1342  are able to be positioned to match the inner dimensions of the container forming the fuselage  1402 , as shown in  FIG. 14  or they can completely collapsed as shown in  FIG. 15 . 
     Turning now to propeller mounts,  FIGS. 16-19  illustrate various alternative positions for a propeller where the propeller extends through an opening in the wing. For example,  FIG. 16  shows a front view of the fuselage  1602 . In particular, a propeller  1622  is coupled to the first portion  1601  of the fuselage  1602 . Although, the propeller  1622  can also be coupled to a second portion or rear portion of the fuselage  1602  or anywhere in between (as shown in  FIG. 17 ) as well. The wing  1604  resides at a position that extends over the propeller  1622  as shown in  FIGS. 16 and 17 . However, the wing  1604  comprises an opening  1648 , as shown in  FIG. 18 , that allows the propeller  1622  to pass through the wing  804 . For example, as a motor  1650  turns a drive shaft  1652 , as shown in  FIGS. 17 and 19 , the propeller  1622  rotates and passes through the opening  1648  in the wing  1604 . 
     Different types of foldable and extendable propeller can be used as shown in  FIGS. 20-24 . For example,  FIG. 20  illustrates a foldable propeller  2022  comprising foldable blades  2054 ,  2056 . The foldable blades allow the propeller to fold, extend, or both upon increasing throttle. The centrifugal force acts on the propeller  2022  by bringing the blades  2054 ,  2056  out of a folded configuration into a flyable-configuration. In one embodiment, a hinged member  2058 ,  2060  pivotably coupled the blades  2054 ,  2056  to the propeller  2022 . The extendable propeller  2022 , in one embodiment, is converted by a runner-track system  2062 , as shown in  FIG. 21 , that allows the outer section  2064  of a blade  2054  to slide over the inner section  2066  of the blade  2054 . An elastic band  2068  also connects two sections  2064 ,  2066  of a blade  2054  for the purposed of inducing retraction, as shown in  FIGS. 21 and 22 .  FIG. 23  shows a propeller  2322  positioned at a rear portion  2303  of a container forming the fuselage  2302 .  FIG. 24  shows a propeller  2422  positioned at a front portion  2401  of a container forming the fuselage  2402 . 
       FIGS. 25 and 26  show another embodiment of a morphable UAV  2500 .  FIG. 25  shows a side view of the morphable UAV  2500  and  FIG. 26  shows a front view of the morphable UAV  2500 . The morphable UAV  2500  of  FIGS. 25 and 26  comprise a plurality of propellers  2522 ,  2535  and associated motors. In one embodiment, each of the plurality of propellers  2522 ,  2535  are coupled to a respective wing  2504 . The plurality of propellers  2522 ,  2535  provides more flight power and can be independently operated (e.g., one propeller can be operated at a slower speed than the other propeller) for controlling the yaw of the morphable UAV  2500 . 
       FIGS. 27-29  show additional embodiments for a propeller or a rotor. In particular,  FIG. 27  shows the blades  2754 ,  2756  of a propeller/rotor  2722  comprising multiple hinged sections  2727 ,  2729 . These multiple hinged sections  2727 ,  2729  are able to rotate/pivot and fold to decrease the size/length of the blades  2754 ,  2756  to fit inside of a container. As the propeller/rotor  2722  spins, the centripetal force extends the blades  2754 ,  2756  to full length. 
       FIG. 28  shows the blades  2854 ,  2856  of the propeller/rotor  2822  comprising one or more extendable/retractable sections  2827 ,  2829  that extends from/retracts into another section  2831  of the blade  2854 ,  2856 .  FIG. 29  shows a blade  2954 ,  2956  of the propeller/rotor  2922  comprising a bendable/foldable/resilient material. This blade  2954 ,  2956  is able to wrap around the propeller/rotor  2922  so that the propeller/rotor  2922  and blade  2954  can fit inside of a container. It should be noted that a combination of these blade types can be used as well. 
       FIG. 30  shows a morphable UAV  3000  comprising inflatable wings  3004 , horizontal stabilizers  3006 , and vertical stabilizers  3008 . In particular, the wings  3004 , horizontal stabilizers  3006 , and vertical stabilizers  3008  are stored within the container  3002  and can be manually and/or mechanically inflated. This inflation process causes the wings  3004 , horizontal stabilizers  3006 , and vertical stabilizers  3008  to extend out from the container  3002 , as shown in  FIG. 30 . In one embodiment, an air cartridge can be included within (or outside of) the container  3002  to inflate the wings  3004 , horizontal stabilizers  3006 , and vertical stabilizers  3008 . Once deflated, the wings  3004 , horizontal stabilizers  3006 , and vertical stabilizers  3008  can be stored within the container  3002 . 
       FIG. 31  shows another embodiment of a morphable UAV  3100 . In particular,  FIG. 31  shows a morphable UAV  3100  comprising a set of wings  3104  coupled to the container  3102 . These wings  3102  are rotatable upwards, via one or more rotation mechanisms  3141 , to create a sail  3137 , as shown in  FIG. 32 . This allows the morphable UAV  3100  to be deployed in the air and then the water or vice versa. In one embodiment, a retractable keel  3139  can retract from within the container  3102  or from an outside portion of the container  3102  as well. This retractable keel  3139  can be used to stabilize the morphable UAV  3100  when in the water (or even in the air). 
       FIGS. 33-34  show yet another embodiment of a morphable UAV  3300 . In particular,  FIG. 33  shows a container  3302  morphed into an airship. The container  3300  comprises a bladder  3343  that is stored within the container  3302 , as shown in  FIG. 34 . The bladder  3343  comprises horizontal stabilizers  3306  and vertical stabilizers  3308 . The bladder  3343 , horizontal stabilizers  3306 , and vertical stabilizers  3308  can be manually and/or mechanically inflated. This inflation process causes the bladder  3343 , horizontal stabilizers  3306 , and vertical stabilizers  3308  to extend out from the container  3202 , as shown in  FIG. 32 . In one example, the container  3302  comprises a hinged section  3445 , as shown in  FIG. 34 , that opens up to allow the bladder  3343  to extend out from the container  3302 . In one embodiment, an air cartridge can be included within (or outside of) the container  3202  to inflate the bladder  3343 , horizontal stabilizers  3306 , and vertical stabilizers  3308 . Once deflated, the w bladder  3343 , horizontal stabilizers  3306 , and vertical stabilizers  3308  can be stored within the container  3302 . A propeller similar to those discussed about can be coupled to the container  3302  or a nacelle  3347  can alternatively be used. 
       FIGS. 35-37  show additional embodiments for wings/rotors. In particular,  FIG. 35  shows a container  3502  comprising a first portion  3549  and a second portion  3651 , which formed from the actual sides of the container  3502 . In one embodiment, the first portion  3549  and the second portion  365  extend away from the container  3502 , as shown in  FIG. 36 . These extended portions  3549 ,  3651 , as shown in  FIG. 4 , become the wings of the morphable UAV  3500 . Alternatively, the extended portions  3549 ,  3651  can also become rotors as shown in  FIG. 37 . 
       FIG. 38  shows another embodiment of a morphable UAV  3800 . In particular,  FIG. 28  shows a container  3802  comprising a set of wings  3804 . These wings  3804  are configured to flap. In other words, the wings  3804  move in an up and down direction with respect to the ground.  FIG. 39  shows a morphable UAV  3900  that can be deployed underwater. This morphable UAV  3900  can be anyone of the airborne UAVs discussed above that transforms into a submersible UAV or can be a standalone submersible UAV as well. In one embodiment, the morphable UAV  3900  comprises a propeller  3922  coupled to a rear portion  3903  of the container  3902 . The morphable UAV  3900  also comprises an internal ballast bladder  3953  that fills with water to submerge the UAV  3900  or fills with air to add buoyancy to the UAV  3900 . The UAV  3900  also comprises wings or stabilizers  3904  that stabilize the UAV  3900  in the water. Ballast inlets  3955  allow water or air to enter/leave the ballast bladder  3953 . 
       FIGS. 40-42  show various locomotion embodiments of a morphable UAV. These locomotion embodiments allow a morphable UAV to be deployed in one or more environments such as air, land, subterranean, and water. For example,  FIG. 40  shows a set of wheels  4057  that can be stored/retracted within the container  4057  and extended from the container  4057  when in use. This allows the morphable UAV  4000  to traverse land.  FIG. 41  shows morphable UAV  4100  comprising a container  4102  with one or more tread/track mechanisms  4157  which propels the morphable UAV  4100 . The tread/track mechanism  4157  comprises a set of rotating members  4159  that rotate a tread/track  4161 . The tread/track mechanism  4157 , in one embodiment, is retractable so that it is stored within the container  4102  when not in use. 
       FIG. 42  shows a morphable UAV  4200  that comprises a container  4202  comprising one or more walking leg mechanism  4263 . The walking leg mechanism  4263 , in one embodiment, comprises a rotating member  4265  with a plurality of extensions  4267 ,  4269 ,  4271 ,  4273 . The walking leg mechanism  4263  allows the morphable UAV  4200  to traverse rough terrain. For example, the walking leg mechanism  4263  allows the morphable UAV  4200  to climb over rocks and other objects. The walking leg mechanism  4263 , in one embodiment, is retractable so that it is stored within the container  4202  when not in use. 
       FIGS. 43 and 44  show various embodiments of a drive shaft  4300 . The drive shaft  4300  extends and retracts components to fit within a container in a fix-wing UAV and to work cooperatively with an insert  1133  such as that shown in  FIG. 11 .  FIG. 43  shows the drive shaft  4300  comprising an outer housing  4370 . A gear  4372  is mechanically coupled to the outer housing  4370  and to a threaded rod  4374  within the outer housing  4370 . The threaded rod  4374  is mechanically coupled to a fixed nut  4376 , which mechanically couples an inner shaft  4378  to the threaded rod  4374 . 
     In this embodiment, the drive shaft  4300  is configured to act as a linear actuator. As the drive gear turns  4372 , the threaded rod  4374  transfers motion to the fixed nut  4376  attached to the inner shaft  4378 . As a result, the inner shaft  4378  can extend and retract in/out of the outer housing  4370  accordingly. In one embodiment the retraction mechanism of  FIGS. 43-44  is configured such that one end  4580  of the bottle forming the fuselage  4502  is removed and the insert  4533  is slide inside the bottle, as shown in  FIG. 45 . The insert  4533  is then connected by two hand points  4582 ,  4584  via one or more fastening mechanisms  4586 ,  4588 : one at the bottle cap  4545  and the second at the bottom  4580  of the bottle. An insert  4533  can comprise all of the wings, motor, avionics, and the like to transform a container into a morphable UAV. In other words, the insert  4533  is modular and allows an ordinary container to be morphed into a UAV. 
       FIG. 46  is a generalized diagram of a rotary-wing aircraft according to the prior art. Shown is a main rotor  4622  attached to a drive shaft  4623  which is mechanically coupled to a motor  4620  that is internal to the craft  4602 . A tail boom  4609  and tail rotor  4624  are attached to the craft  4602 . 
     Morphing Rotary Wing UAV 
       FIG. 47  illustrates a rotary-wing UAV  4700  according to one or more embodiments of the present invention.  FIG. 47  shows the rotary-wing UAV  4700  with the rotor  4721 ,  4722  extended outside a beverage container  4702  according to one embodiment of the present invention. Shown is a rotor  4721 ,  4722  attached to a drive shaft  4723 . This embodiment uses a two-blade system to provide stability without requiring a tail. However, various embodiments of the present invention are not limited to this embodiment. 
     The components  4790  of the rotary-wing UAV  4700  that morph a beverage container  4702  into a rotary-wing UAV  4700  have two positions. A first position for extending the components needed for lift and propulsion and second position for the avionics to be retracted to fit inside a beverage container  4702 . In one embodiment, the components  4790  are a single unit  4725  that can be inserted into any beverage container  4702  of appropriate size. The beverage container  4702  comprises external trade dress and lettering to resemble a given consumer brand of beverage. In one embodiment, the beverage container  4702  is an actual drink container. Similar the fix-wing embodiment discussed above, the rotor(s)  4721 ,  4722  of the rotary wing UAV is retractable. For example, the rotors  4721 ,  4722 , comprise a first position, which is open for use during flight, and a second position, which is retracted within the fuselage (e.g., retracted inside the beverage container  4702 ) when not in flight. 
     In one embodiment, the blades  4754 ,  4756  of the rotors  4721 ,  4721  are foldable as discussed above. Also, the drive shaft  4723  can be retracted into the beverage container  4702 . In one embodiment, the motion of the drive shaft  4723  being retracted into the beverage container  4702  causes the rotors  4721 ,  4722  to fold so that they can fit within the beverage container  4702 . Inside the body  4702  is an engine in  4720  that is mechanically coupled to the shaft  4723  for turning the retractable rotors  4721  and  4722 . The engine  4720  is an electric engine and/or a gas engine. Other avionics controls, and sensors (not shown) that can be positioned inside the body  4725  include cameras, microphones, chemicals sensors, biological sensors, location sensors such as Global Positioning Satellite modules, heat sensors, and the like. 
       FIG. 48  is a picture of a rotary-wing UAV  4800 . The rotary-wing UAV  4800 , in the example of  FIG. 48 , has the rotor(s)  4821 ,  4822  extended and a motor  4820  and other avionics situated inside the beverage container  4802 . Unlike the embodiment in  FIG. 48 , the beverage container  4802  is included with the rotary-wing craft. No separate body  4825  is needed. 
     The rotor(s)  4721 ,  4722  and shaft are designed to extend and retract using a variety of mechanisms.  FIGS. 49-50  illustrate a few embodiments. For example,  FIG. 49  illustrates a flexible rotor(s)  4921 ,  4922  with the rotor shaft  4923  and motor/electronics  4920  outside a beverage container  4902 . The flexible rotor(s)  4921 ,  4922 , rotor shaft  4923 , and motor/electronics  4920  are configured to fit inside of the beverage container  4902 , as shown in  FIG. 50 . As can be seen in  FIG. 50 , the flexible rotor(s)  4921 ,  4922  bend to conform to the inner dimension(s) of the beverage container  4902 . 
       FIGS. 51-56  illustrate a variety of embodiments for the rotor(s). In one embodiment, a rotor  5121  is an extendable or telescopic rotor.  FIG. 51  shows a rotor  5121  comprising a plurality of sections  5127 ,  5129 ,  5131 . One of more of these sections  5127 ,  5129 ,  5131  can retract into one or more of the other sections  5127 ,  5129 ,  5131  and/or slide over one or more of the other sections  5127 ,  5129 ,  5131 , as shown in  FIG. 52 .  FIG. 53  shows a hinged rotor  5321 in an extended position. The hinged rotor  5321  comprises a plurality of sections  5327 ,  5329 ,  5331 . One or more of these sections  5327 ,  5329 ,  5331  are pivotably coupled to at least one other of these sections  5327 ,  5329 ,  5331 . This pivotably coupling allows these sections  5327 ,  5329 ,  5331  to be retracted onto each other as shown in  FIG. 54 .  FIG. 555  shows a foldable/bendable rotor  5521  that is able to conform to the inner dimensions of a beverage container  5502 , as shown in  FIG. 56 . 
       FIG. 57  illustrates one embodiment of a rotary-wing UAV  5700  with the rotor shaft  5723  extended outside a Monster® beverage container  5702 . In particular,  FIG. 57  shows the shaft  5723  extended upwards out of the container  5702 . As can be seen in  FIG. 57 , the engine/avionics/sensors  5720  are partially situated within the container  5702  and ready for flight. The rotors are not shown as being attached to the shaft  5723  in  FIG. 57 . In one embodiment, the rotor(s)  5721 ,  5722  are detachable and can be stored within the beverage container  5702 , as shown in  FIG. 57 . Alternatively, the rotor(s)  5721 ,  5722  can fold/bend/retract/pivot so that they can fit within the beverage container  5702 , as discussed above.  FIG. 58  shows the shows the shaft  5823  retracted into the container  5802 . As can be seen in  FIG. 58 , the engine/avionics/sensors situated within the Monster® beverage container  5802 . It should be noted that the engine/avionics/sensors  5720  of  FIG. 57  can also reside within the beverage container  5802 , as shown in  FIG. 58 , when ready for flight as well. The shaft  5823 , in this embodiment, is able to extend to a distance out of the container  5802  so that the rotors are able operate and give the container  5802  flight. 
       FIG. 59  shows another embodiment of a rotary-wing UAV  5900 . In particular,  FIG. 59  the insert  5933  outside of the container  5902  with hinged wings/blades/rotors  5921  in a retracted position.  FIG. 60  shows the hinged wings/blades/rotors  5921  in a semi-extended position according to one embodiment of the present invention.  FIG. 61  illustrates one embodiment of a rotary-wing UAV  6100  with the insert inside the container  6102  with hinged wings/blades/rotors  6121  in a retracted position.  FIG. 62  shows the wings/blades/rotors of the UAV  6100  in a semi-extended position according to one embodiment of the present invention.  FIGS. 63 and 64  illustrate one embodiment of a rotary-wing UAV  6300  with the insert  6333  inside the container  6302 .  FIGS. 63 and 64  also shows the hinged wings/blades/rotors  6321 ,  6322  in a fully extended position according to one embodiment of the present invention. 
     Non Limiting Examples 
     The technology of a fix-wing and rotary-wing craft morphs from a beverage container. Although the container is shown as part of the UAV, it is important to note that a single unit that can inserted into any actual beverage container of appropriate size. Therefore, the technology uses the beverage container to avoid detection when not in flight. 
     Although the UAVs described herein can have a variety of shapes and configurations, it is important to note other types of UAVs including fixed-wing, rotary-wing, flapping-wing, ducted-fan type are within the true scope and spirit of the present invention. 
     Moreover, although a beverage container have been described, it is important to note that containers including pipes, boxes and other shapes may be advantageously used with the present invention. 
     Further, even though a specific embodiment of the invention has been disclosed, it will be understood by those having skill in the art that changes can be made to this specific embodiment without departing from the spirit and scope of the invention. The scope of the invention is not to be restricted, therefore, to the specific embodiment, and it is intended that the appended claims cover any and all such applications, modifications, and embodiments within the scope of the present invention.