Abstract:
Liquid dispensing assemblies including adhesive anchoring assemblies configured to adhere to a support surface external to a device such as a vehicle. An air vehicle includes (a) a fluid adhesive container assembly detachably attached to the air vehicle, wherein the fluid adhesive container assembly comprises: (i) an adhesive container comprising fluid adhesive; and (ii) one or more fibers, wherein the one or more fibers are configured, or a brush of fibers, or a fabric of fibers, is configured to conduct the fluid adhesive and to structurally support an adhesive bond between the one or more fibers and a surface; and (b) means for dispensing the fluid adhesive from the fluid adhesive container, to the one or more fibers.

Description:
CROSS-REFERENCE TO RELATED APPLICATION 
       [0001]    This application claims priority to and the benefit of U.S. Provisional Patent Application Ser. No. 61/264,220, filed Nov. 24, 2009, which is hereby incorporated herein by reference in its entirety for all purposes. 
     
    
     FEDERALLY SPONSORED RESEARCH 
       [0002]    The invention was made with Government support under HR0011-07-C-0075 awarded by DARPA. The Government has certain rights in the invention. 
     
    
     TECHNICAL FIELD 
       [0003]    Embodiments pertain to deployable adhesive anchoring systems and particularly to adhesive anchoring systems for aircraft. 
       BACKGROUND 
       [0004]    An unmanned aerial vehicle (UAV) may land or alight on a surface on which the UAV may slide due to gravity or other forces such as aerodynamic forces. A UAV may land or alight on, or position itself proximate to, a surface on which the UAV may be tasked to apply a liquid-based pigment to a target region of the surface. The use of beacons, antenna elements, and/or instrumentation packets may require rapid affixing of such devices to surfaces or available support structures. 
       SUMMARY 
       [0005]    Embodiments include liquid dispensing assemblies including adhesive anchoring assemblies configured to adhere to a support surface external to a vehicle. For example, an assembly may comprise: (a) an assembly housing comprising a fluid reservoir; (b) a resilient member disposed proximate to the assembly housing; and (c) a fluid conduit configured to pierce the reservoir responsive to a decompression of the resilient member. In some embodiments, the fluid may be an adhesive. In some embodiments, the assembly further comprises a liquid infusible brush. In still other embodiments, the fluid reservoir may be a liquid adhesive reservoir and the liquid infusible brush may be a liquid adhesive infusible brush. The fluid conduit may be configured to pierce the reservoir via a frusto-conical tip. 
         [0006]    Embodiments may include a system comprising a vehicle and an adhesive anchoring assembly configured to adhere to a support surface external to the vehicle. For example, a portion of the adhesive anchoring assembly may be detachable. A portion of the adhesive anchoring assembly may be configured to rotate into a deployed position. The adhesive anchoring assembly may comprise a liquid adhesive reservoir and a liquid adhesive infusible brush. 
         [0007]    Embodiments may include methods of attachment and detachable attachment. For example, a method of adhesive bonding may comprise: (a) providing an adhesive in a positive pressure reservoir having positive pressure above local atmospheric pressure to force a portion of the adhesive along a conduit to an application surface under local atmospheric pressure; and (b) releasing a resiliently loaded conduit having a tip configured to pierce the reservoir when the resiliently loaded conduit is unloaded. The exemplary reservoir may be detachably attached to a support structure, e.g., an air vehicle fuselage, and the method may further comprise detaching the reservoir from the support structure. Another exemplary method of detachably anchoring a device via adhesive bonding may comprise: (a) detachably attaching a positive pressure reservoir to a device, e.g., an air vehicle, an transmitter, or an illuminator, wherein the positive pressure reservoir contains an adhesive, and wherein the reservoir containing the adhesive has positive pressure above local atmosphere to force a portion of the adhesive along a conduit to an application surface under local atmospheric pressure; (b) releasing a resiliently loaded conduit having a tip configured to pierce the reservoir when the resiliently loaded conduit is unloaded; and (c) deploying the application surface to a surface of a support structure, e.g., a target anchoring surface. The exemplary reservoir may be fixedly attached to the support structure via the application surface connected to the conduit, itself connected to the detachable reservoir, and the method may further comprise detaching the reservoir from the device. 
     
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         [0008]    Embodiments are illustrated by way of example and not limitation in the figures of the accompanying drawings, and in which: 
           [0009]      FIGS. 1A ,  1 B, and  1 C illustrate an exemplary Vertical Take-Off and Landing (VTOL) use of an embodiment of the present invention; 
           [0010]      FIGS. 2A ,  2 B, and  2 C illustrate an exemplary fixed-wing use of an embodiment of the present invention; 
           [0011]      FIGS. 3A and 3B  illustrate an exemplary arrangement of elements of an assembly embodiment of the present invention; 
           [0012]      FIGS. 3C and 3D  illustrate exemplary detachments of portions of the elements of assembly embodiments of the present invention; 
           [0013]      FIG. 4  illustrates an assembly embodiment of the present invention; 
           [0014]      FIGS. 5A ,  5 B, and  5 C illustrate an assembly embodiment of the present invention; 
           [0015]      FIGS. 6A and 6B  illustrate another assembly embodiment of the present invention; 
           [0016]      FIGS. 7A and 7B  illustrate yet another assembly embodiment of the present invention; 
           [0017]      FIGS. 8A ,  8 B,  8 C,  8 D and  8 E illustrate stowing and rotational deployment of an embodiment of the present invention; 
           [0018]      FIG. 9  illustrates an example of a dispensing case embodiment within a cavity of an aircraft fuselage; 
           [0019]      FIG. 10  illustrates another embodiment of the adhesive anchoring assembly in a stowed position; 
           [0020]      FIG. 11  illustrates another embodiment of the adhesive anchoring assembly in a deployed position; 
           [0021]      FIG. 12A  illustrates another embodiment of the adhesive anchoring assembly showing a direction of rotation into a deployed position; 
           [0022]      FIG. 12B  illustrates the embodiment of the adhesive anchoring assembly of  FIG. 12A  showing a deployed position where the brush portion is in contact with a surface; 
           [0023]      FIG. 13A  illustrates another embodiment of the adhesive anchoring assembly in a stowed position; 
           [0024]      FIG. 13B  illustrates the embodiment of the adhesive anchoring assembly in a stowed position of  FIG. 13A  with the conduit position to allow flow of a liquid adhesive to the brush portion; 
           [0025]      FIG. 13C  illustrates the embodiment of the adhesive anchoring assembly of  FIG. 13B  showing a direction of rotation into a deployed position; 
           [0026]      FIG. 14A  illustrates in a cross-sectional view another embodiment of the present invention; 
           [0027]      FIG. 14B  illustrates in a cross-sectional view a portion of the embodiment of  FIG. 14A ; 
           [0028]      FIG. 15  illustrates a side view of the embodiment of the present invention of  FIG. 14A ; 
           [0029]      FIG. 16  illustrates a side view of a deflected embodiment of the present invention depicted in  FIG. 15 ; 
           [0030]      FIG. 17  illustrates a cross-sectional view of the deflected embodiment of the present invention depicted in  FIG. 16 ; 
           [0031]      FIG. 18  illustrates in a cross-sectional view another embodiment of the present invention; 
           [0032]      FIGS. 19A and 19B  illustrate an exemplary clasp; 
           [0033]      FIG. 20  illustrates in cross-sectional view the embodiment depicted in  FIG. 18  further comprising a clasp; 
           [0034]      FIG. 21  illustrates in a perspective view an exemplary frusto-conical tip of an embodiment of the present invention; 
           [0035]      FIG. 22  illustrates in an elevational side view an exemplary frusto-conical tip of an embodiment of the present invention; 
           [0036]      FIG. 23  illustrates in a top view an exemplary frusto-conical tip of an embodiment of the present invention; 
           [0037]      FIG. 24  illustrates in an elevational front view an exemplary frusto-conical tip of an embodiment of the present invention; 
           [0038]      FIG. 25  illustrates in a cross-sectional view another embodiment of the present invention;  FIG. 26  illustrates a cross-sectional view of the deflected embodiment of the present invention depicted in  FIG. 25 ; 
           [0039]      FIG. 27  illustrates a cross-sectional view of a portion of a deflected embodiment of the present invention depicted in  FIG. 25 ; 
           [0040]      FIG. 28  illustrates a cross-sectional view of a portion of the embodiment of the present invention depicted in  FIG. 25 ; and 
           [0041]      FIG. 29  illustrates a cross-sectional view of a portion of a deflected embodiment of the present invention depicted in  FIG. 25 . 
       
    
    
     DETAILED DESCRIPTION 
       [0042]    Reference is made to the drawings that illustrate exemplary embodiments of the present invention.  FIGS. 1A ,  1 B, and  1 C illustrate an exemplary embodiment of the present invention where, in  FIG. 1A , a vertical takeoff and landing craft (VTOL) aircraft  110  such as a helicopter descends to a landing surface  120 . A contact member  130  is extended in  FIG. 1B  from the aircraft  110  until the contact member makes contact with a portion of the landing surface  120 . The contact member  130 , either before or after making contact with the portion of the landing surface  120 , may be infused or otherwise provided with an adhesive liquid causing the contact member  130  to bond with the portion of the landing surface  120 . An attachment member  140  connects the contact member  130  to the aircraft  110 . Accordingly, the aircraft  110  may be adhesively anchored to the landing surface  120 . The attachment member  140  may detachably attach to either the aircraft  110 , the contact member  130 , or both. In particular, the attachment member  140  may detach from the aircraft  110  or the contact member  130 , and the aircraft  110 , being no longer anchored to the landing surface  120 , may resume flight as shown in  FIG. 1C . Similarly,  FIGS. 2A ,  2 B, and  2 C illustrate an exemplary embodiment of the present invention where, in  FIG. 2A , a fixed wing aircraft  210  descends to a landing surface  120 . In  FIG. 2B  a contact member  130  is extended from the aircraft and contacts a portion of the landing surface  120 . The contact member  130  may be detachably attached from the aircraft  210  and the detached aircraft  210  may free to resume flight as shown in  FIG. 2C . 
         [0043]      FIG. 3A  shows an assembly comprising an aircraft  310  attached to a liquid adhesive reservoir by an attachment_ 1   320 . A channel or conduit  330  may be provided between the liquid adhesive reservoir  340  and a brush assembly  350  such as a filament array, bristle array, or an array of bundles, strips of fabric, cotton balls, or clumps of cloth. The liquid adhesive reservoir  340  may be attached by attachment_ 2   360  to the filament array  350 . Before or after the filament array  350  contacts the anchoring surface  370 , the liquid adhesive may flow from the liquid adhesive reservoir  340  to the filament array  350  via the conduit  330  as shown in  FIG. 3B . The filament elements of the filament array  350  having liquid adhesive provide the anchoring surface  370  with bonding areas. Once elements of the filament array  350  have bonded to the anchoring surface  370 , the aircraft may be adhesively anchored to the anchoring surface  370 . To free itself from the anchor provided by the bonded elements of the filament array  350 , the aircraft may be detached via release of attachment_ 1   320  as shown in  FIG. 3C  or release of attachment_ 2   360  as shown in  FIG. 3D , or combinations thereof. 
         [0044]      FIG. 4  shows an assembly comprising a cylinder  410  for containing a liquid adhesive reservoir where the assembly further comprises an attachment joint  420  at a proximal end of the cylinder and an array of filaments  430 , bristles, or fabric strips, at the distal end of the cylinder. A channel or conduit may be provided within the cylinder  410  between the liquid adhesive reservoir and the filament array  430  for conducting the flow of the liquid adhesive to the filament array, where the filament array may be in contact with a surface for anchoring.  FIG. 4  also shows the assembly may be stowed, prior to deployment, in a dispensing case  440 . 
         [0045]      FIG. 5A  shows in cross-section the cylinder  510  having a plunger  511  with a shaft  512  piercing a stopper  513 .  FIG. 5B  shows the liquid adhesive  520  may be expressed from the cylinder  510  as the plunger  511  moves toward the opening  514 .  FIG. 5C  shows the brush  530  of the distal portion  515  of the cylinder  510  may disperse its fibers or filaments in such a fashion as to provide contact with uneven surfaces  540 .  FIG. 6A  shows in cross-section the cylinder  610  having a pointed spring-loaded shaft  611  held in place by a pin  612 .  FIG. 6B  shows that with the pin removed, the pointed spear  611  may pierce a seal  613  of the liquid adhesive reservoir, allowing the liquid glue to flow to the bundle of bristles or filaments  530 .  FIG. 7A  shows the cylinder  710  having a threaded shaft  711  with a threaded seal/stopper  712 . A liquid adhesive reservoir  720  is shown disposed between the threaded seal/stopper  712  and the brush assembly  530 .  FIG. 7B  shows that a rotation  713  of the threaded shaft  711  causes the threaded seal  712  to translate toward the distal end  715  of the cylinder  710 , thereby expressing the liquid adhesive  730  from the reservoir  720 .  FIG. 8A  shows in perspective view a dispensing case  810  comprising three rotatably and detachably attached brush-cylinder systems  821 - 823 .  FIG. 8B  shows a rotational degree of freedom of a cylinder glue dispensing embodiment  821  of the present invention.  FIG. 8C  shows a dispensing case  810  in a top view with a first cylinder  821  elevated.  FIG. 8D  shows in a side view a dispensing case  810  mounted within a body  820  with the distal brush element  830  of the cylinder  821  rotationally brought into contact with a surface  840 . A leg  850  is shown attached to the body  820  providing elevational support of the body  820  from the contact surface  840 .  FIG. 8E  shows a portion of the dispensing case assembly  810  where a drive gear assembly effects  860  the rotation of a worm gear  861  causing a threaded shaft  862  to rotate a first cylinder  821 , and if the threaded shaft is further rotated, to disengage the joint of the cylinder  821 —leaving the cylinder  821  mechanically disconnected from the dispensing case. Further rotation of the drive gear causes the next cylinder  822  to rotationally extend.  FIG. 9  shows a dispensing case  810  disposed on the underside of an aircraft  920 . Shown also in  FIG. 9  are four legs  931 - 934  extending from the body of the aircraft. 
         [0046]      FIG. 10  shows an embodiment of the liquid adhesive storage and deployment assembly  1000  where the liquid adhesive reservoir  1010  and the conduit and brush assembly portion  1020  are stowed parallel to one another. The conduit  1021  has a piercing aperture  1022  disposed on a gooseneck conduit  1023 . The conduit and brush assembly portion  1020  may be rotated, e.g., by a released spring-loaded rotating joint assembly, into and piercing a seal  1011  of a liquid adhesive reservoir  1010 . The contents  1012  of the reservoir  1010 , or glue packet may be under pressure via a clamp spring  1030 . The contents  1012  of the reservoir  1010  may be under pressure, e.g., via a clamp via a gas bladder, where such embodiments may be applicable in environments with nominal atmospheric pressure variation.  FIG. 11  shows the conduit and brush assembly  1020  having rotated approximately  90  degrees causing the piercing aperture  1022  to pierce the seal  1011  of the liquid adhesive reservoir  1010  and set up a path for the adhesive to flow to the bristles or filaments of the brush  1140 .  FIG. 12A  shows the liquid adhesive reservoir  1010  and the conduit and brush assembly portion  1020  are stowed parallel to one another within a portion of an aircraft fuselage  1200  having fixed pedestal legs  1211 ,  1212 , and that the conduit and brush assembly portion  1020  may rotate to a position orthogonal and extending from the fuselage  1200 . The conduit and brush assembly portion  1020  may rotate before or after the aircraft lands on a contact surface.  FIG. 12B  shows an example of the brushes of the assembly in contact with the contact surface  1220 .  FIG. 13A  shows another embodiment of the liquid adhesive storage and deployment assembly  1300  having a spring-loaded conduit and brush assembly portion  1320  having a loaded spring  1321  that may be held in place by a pin  1322  and solenoid or servo actuated  1323 . The brush assembly may be further bundled via a brush filament conduit such as a silicone conduit having a distal end, for example, a brush tip. For some embodiments, the brush filament conduit may be comprised of a wrapped KEVLAR tube.  FIG. 13B  shows that with the pin  1322  retracted, the conduit and brush assembly  1320  has been thrust into and has penetrated the liquid adhesive reservoir seal  1011 .  FIG. 13C  shows the liquid adhesive reservoir and the conduit and brush assembly portion of the embodiment  1301  of  FIG. 13B  rotated to extend the brush portion  1350  out of the fuselage  1200  and onto a contact surface  1220 . Rather than pivoting about a point of rotation, the assembly may be configured so that a portion of the assembly rotates or bends to deploy the brush assembly. 
         [0047]      FIG. 14A  shows in a cross-sectional view another embodiment of the liquid adhesive storage and deployment assembly  1400  where a flexible lineal conduit  1421  has a piercing aperture  1422  proximate to the liquid adhesive reservoir  1410 . A collar member  1480  is shown external to a brush filament conduit  1451 . The brush filament bundle  1450  is shown extending from the end of the brush filament conduit  1451  distal from the liquid adhesive reservoir  1410 .  FIG. 14B  shows in a cross-sectional view the distal portion of the assembly of  FIG. 14A  where the flexible lineal conduit  1421  terminates before the end of the brush filament conduit  1451  and where a portion of a spring wire  1481 , as an example of a resilient member, is in contact with, or fixed to, the collar  1480 .  FIG. 15  shows in a side view the spring wire  1481  in contact with the collar  1480 , where the collar is disposed about the brush filament conduit  1451 . Another portion of the spring  1583  is disposed on a mounting sleeve or mounting case  1590  as seen in  FIG. 15 . The spring wire  1481  is compressed and held in place by a pin  1582 .  FIG. 16  shows in a side view the spring wire  1481  is in a restored, i.e., uncompressed, position and the brush filament conduit  1451  is deflected thereby reorienting the brush filament bundle  1450 .  FIG. 17  illustrates in a cross-sectional view the deflection of the brush filament conduit  1451  which places pressure in the distal end portion of the flexible lineal conduit  1421 , a pressure that works to drive the piercing aperture  1422  into the liquid adhesive reservoir  1410  via a pierced seal  1711 . Accordingly, the assembly  1700  is shown in a deployed state having a brush filament bundle  1450  receiving liquid from the reservoir  1410  and positioned for application to an exemplary surface  1701 .  FIG. 18  illustrates in a cross-sectional view a portion of an exemplary assembly  1800  where an adhesive reservoir  1810  may comprise a threaded portion  1811  for secure assembly.  FIG. 19A  illustrates in a front view a reservoir spring clasp  1900 .  FIG. 19B  illustrates in a side view a reservoir spring clasp  1900 .  FIG. 20  illustrates in a cross-sectional view a portion of an exemplary assembly  1800  where an adhesive reservoir  1810  may have a reservoir spring clasp  1900  apply pressure to the reservoir  1810 . 
         [0048]      FIG. 21  illustrates in a perspective view an exemplary frusto-conical tip  2100  of an embodiment of the present invention that may be disposed on an end of an adhesive flow conduit  1421 . The exemplary frusto-conical tip  2100  is depicted as including a cylindrical attachment band portion  2110 . The exemplary frusto-conical tip  2100  may be embodied having opposing teardrop-shaped apertures where a first teardrop-shaped aperture  2120  is shown in  FIG. 21  depicted having opposing teardrop-shaped apertures, the narrow portions of the teardrop distal from the conduit, the wider portions of the teardrop proximate to the cylindrical band, and where the teardrop-shaped apertures are shown disposed on the conic portion of the tip.  FIG. 22  illustrates in an elevational side view an exemplary frusto-conical tip  2100  of an embodiment of the present invention having a teardrop-shaped aperture  2120 .  FIG. 23  illustrates in a top view an exemplary frusto-conical tip  2100  of an embodiment of the present invention and depicts the first teardrop-shaped aperture  2120  opposing a second teardrop-shaped aperture  2121 .  FIG. 24  illustrates in an elevational front view an exemplary frusto-conical tip  2100  of an embodiment of the present invention. 
         [0049]      FIG. 25  illustrates in a cross-sectional view another embodiment of the present invention comprising an adhesive flow conduit  1421  having a frusto-conical tip  2100  proximate to the adhesive reservoir seal  1711 .  FIG. 26  illustrates a cross-sectional view of the deflected embodiment of the present invention depicted in  FIG. 25  where the frusto-conical tip  2100  is shown piercing the adhesive reservoir seal  1711 . 
         [0050]      FIG. 27  illustrates a cross-sectional view of a portion of a deflected embodiment of the present invention depicted in  FIG. 25  where the frusto-conical tip  2100  has pierced the adhesive reservoir seal  1711  and where the adhesive of the reservoir flows into the conduit  1421  via the teardrop-shaped apertures  2120 ,  2121  of the frusto-conical tip  2100 . Expanded depictions are shown in  FIGS. 28 and 29  where in  FIG. 28  is illustrated a cross-sectional view of a portion of the embodiment of the present invention depicted in  FIG. 25 , and where in  FIG. 29  is illustrated a cross-sectional view of a portion of a deflected embodiment of the present invention depicted in  FIG. 25 . 
         [0051]    Accordingly, embodiments of the present invention may provide a system for use in temporarily affixing an aircraft to the ground and in which the aircraft has a removable gripper, or anchor unit attached to the undercarriage. The anchor or gripper unit has a frame containing three ground-lock tubes. Each tube connects to an actuation system configured to extend the tube down such that a brush portion at the end of the tube is pressed against the tube, splaying the brush filaments on the ground. Embodiments of the invention include an adhesive reservoir that may be a tube having an inner piston configured to eject an adhesive such as, for example, a tenacious adhesive type substance, which is stored within the tube, out of the tube and through the brush portion. For example, cyanoacrylate is the generic name for cyanoacrylate-based, fast-acting glues such as methyl-2-cyanoacrylate, ethyl-2-cyanoacrylate (commonly sold under trade names like The Original Super Glue® and Krazy Glue), n-butyl-cyanoacrylate (used in the veterinary glues Vetbond and LiquiVet and skin glues like Indermil and Histoacryl).  2 -octyl cyanoacrylate is the medical grade glue encountered under various trade names, e.g. SurgiSeal™, FloraSeal™, Dermabond™, and Nexaband™. The liquid adhesive such as a cyanoacrylate adhesive binds the plane to the ground once the adhesive dries. To provide the aircraft with stability during windy conditions, the ground point to which the brush attaches may be located directly below the aircraft center of drag, or proximate to that location. The tube actuation system may be configured to release the tube when it is time for the aircraft to be released from the ground. 
         [0052]    It is contemplated that various combinations and/or sub-combinations of the specific features and aspects of the above embodiments may be made and still fall within the scope of the invention. Accordingly, it should be understood that various features and aspects of the disclosed embodiments may be combined with or substituted for one another in order to form varying modes of the disclosed invention. Further it is intended that the scope of the present invention herein disclosed by way of examples should not be limited by the particular disclosed embodiments described above.