Abstract:
An airborne drone launch and recovery apparatus for selectively launching drones located on the underside of a carrier aircraft or recovering drones following flight of the drones, the airborne launch and recovery apparatus has an extensible stinger slidable along the length of a stinger sheath between a retracted position proximal the rear portion of the carrier aircraft and an extended position in front of the carrier aircraft, and a catcher shuttle carried on the forward part of the stinger for extending into the non-turbulent air in front of the carrier aircraft when the stinger is in the extended position. The carrier shuttle includes a launch/recovery assembly for selectively either having a locked condition for the recovery guide of a drone prior to the positioning of the catcher shuttle in a selected for the launch of the drone, and having an open condition for receiving the recovery guide of a drone at the termination of the flight of the drone to terminate the flight.

Description:
CROSS-REFERENCE TO RELATED APPLICATION 
       [0001]    This application claims priority to U.S. Provisional Patent Application No. 62/172,447 filed Jun. 8, 2015, which is incorporated herein by reference in its entirety. 
     
    
     BACKGROUND OF THE INVENTION 
       [0002]    Field of the Invention 
         [0003]    This invention relates to an airborne drone launch apparatus for launching and recovering unmanned aircraft or drones, and in particular to apparatus for launching drones from aircraft and for using the apparatus for recovering drones subsequent flights of the drones. 
         [0004]    Description of the Prior Art 
         [0005]    Launching and retrieving small manned aircraft from an aircraft has been tried many times in the past, mostly unsuccessfully. Later, aircraft configured to do this became obsolete as jet engines became more fuel efficient while providing far more thrust, thus eliminating the need for short range protective fighter aircraft to be carried. These attempts depended on the smaller aircraft primarily used a hook type means to attach to the parent or carrier aircraft. A prime example of this is the “parasite aircraft” called the Goblin. The hook of the “parasite aircraft” engages a trapeze suspended under the parent aircraft, and is then retracted into the belly of the carrier aircraft, hereafter called the carrier or carrier aircraft. 
         [0006]    Other systems used complex unfolding and extending frames to launch and retrieve the smaller aircraft. These attempted to launch the smaller airplane as far as possible from the carrier, outside the turbulent air around the parent. The Goblin failed exactly because of this turbulence, where it was extremely difficult to align the hook with the bar of the “trapeze” while flying in the turbulent slipstream and prop wash of the carrier aircraft. The pilot was nearly killed in the attempt to reattach to the carrier when the Goblin impacted the trapeze bar as it (the Goblin) bobbed up and down in the turbulent airflow below the carrier. Larger aircraft were launched and retrieved primarily under the carrier&#39;s center of lift because, to do otherwise would cause the carrier to become unbalanced, perhaps outside of its safe limit on center of lift movement. 
         [0007]    Other methods, for lighter than airships the larger ones could actually have slow aircraft take off and land on its upper surface, while others utilized the trapeze method to launch and recover aircraft underneath. Some examples of carrier aircraft for launching and recovering manned aircraft are the following U.S. Airforce aircraft: F84E carried underneath a bomber, XF84 carried underneath a bomber, F84 underneath B50 bomber and Arado E381 carried by the Ar234. 
       BRIEF SUMMARY OF THE INVENTION 
       [0008]    It is an object of the present invention to provide an improved apparatus for launching and recovering unmanned air vehicles, remotely piloted aircraft or drones with engines to propel the unmanned air vehicles, remotely powered aircraft or drones through the atmosphere (hereinafter “drones”) from carrier aircraft. 
         [0009]    Another object of the present invention is the provision of apparatus for launching and recovering drones from underneath carrier aircrafts. 
         [0010]    It is also an object of the present invention to provide apparatus for launching and recovering drones having extensible components for facilitating the launching and safely capturing drones in flight. 
         [0011]    A further object of the present invention is the provision of a drone launching and recovering system wherein drones are launched and recovered from beneath a carrier aircraft. 
         [0012]    It is still a further object of the present invention to provide apparatus for launching and recovering drones from a carrier aircraft capable of holding and recovering a series of drones. 
         [0013]    It is yet an additional object of the present invention to provide apparatus for launching and recovering drones using apparatus wherein the portion of the apparatus for engaging the drones does so in non-turbulent air ahead of the carrier aircraft. 
         [0014]    An additional object of the present invention is the provision of a drone launching and recovery apparatus including conveying means for quickly and precisely moving drones either from storage to a launch position, or from flight to a storage location. 
         [0015]    A still further object of the present invention is the provision of apparatus for launching and recovering drones having structure which can be readily installed on carrier aircraft. 
         [0016]    A general object of the present invention is the provision of apparatus for launching and recovering drones which is safe, efficient and effective in manufacture and in use. These and other objects may occur to those skilled in the art from the application to follow and from the appended claims. 
     
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         [0017]    The present invention may take physical forms in certain parts and arrangements of parts, the preferred embodiments of which will be described in detail in the specification and illustrated in the accompanying drawings which form a part hereof, and wherein: 
           [0018]      FIG. 1  is a schematic plan view of a manta ray shaped carrier aircraft carrying an airborne drone launch and recovery apparatus as shown in  FIG. 1 , with a drone shown ahead of the airborne drone launch and recovery apparatus. 
           [0019]      FIG. 2  is a schematic side view of an airborne drone launch and recovery apparatus mounted on the underside of a carrier aircraft and shown lowered in the extended position according to a preferred embodiment of the invention. 
           [0020]      FIG. 3  is a schematic plan view of a stinger having extending therefrom a catcher shuttle according to a preferred embodiment of the invention, and  FIG. 3A  is a side view of the product shown in  FIG. 3 . 
           [0021]      FIG. 4  is a partial, schematic front view of a drone being launched or recovered in apparatus according to a preferred embodiment of the invention. 
           [0022]      FIG. 5  is a partial, schematic side view of a stinger extended from a stinger sheath on the underside of a carrier aircraft with a drone being launched or recovered according to a preferred embodiment of the invention. 
           [0023]      FIG. 6  is a partial, schematic perspective view of a stinger sliding within a stinger sheath which is in turn attached to a transverse linear drive assembly according to a preferred embodiment of the invention. 
           [0024]      FIG. 7  is a schematic front view of a traditional aircraft such as a C-130 used as a carrier aircraft having an airborne drone launch and recovery apparatus extending below it according to a preferred embodiment of the invention. 
           [0025]      FIG. 8  is a schematic side view of a stinger holding a catcher shuttle and extending from a stinger sheath, with interior components shown in dotted lines, according to a preferred embodiment of the invention, and  FIG. 8A  is an enlarged detail of an interior component shown in  FIG. 8 . 
           [0026]      FIG. 9  is a partial, schematic front view of a stinger sheath in which is disposed a stinger holding a catcher shuttle with a drone being launched or recovered according to a preferred embodiment of the invention. 
           [0027]      FIG. 10  is a schematic partial perspective view of a portion of the airborne drone launch and recovery apparatus forming part of a carrier aircraft, with some interior components and drones shown in dotted lines, according to a preferred embodiment of the invention, and  FIG. 10A  is a detailed, schematic, partial perspective view of a catcher shuttle, stinger and stinger sheath shown in  FIG. 10 . 
           [0028]      FIG. 11  is a schematic, partial cross section of a drone being launched or recovered by a catcher shuttle on a stinger mounted on a forward transverse linear drive system shown in  FIG. 10, and 11A  is an enlarged detail from  FIG. 11 . 
           [0029]      FIG. 12  is a schematic, partial cross section of a catcher shuttle on a stinger mounted on a rearward transverse linear drive assembly shown in  FIG. 10  with a drone being launched or recovered, and  FIG. 12A  is an enlarged detail from  FIG. 12 . 
           [0030]      FIG. 13  is a schematic, partial perspective view of a carrier aircraft having an alternative to the embodiment shown in  FIG. 10 , with a drone being launched, and  FIG. 13A  is an exploded view of the alternative airborne drone launcher and recovery apparatus as shown in  FIG. 13 . 
       
    
    
     DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS 
       [0031]    Referring first to  FIG. 1 , a carrier aircraft  1  is shown. Carrier aircraft  1  includes apparatus  100  for launching and recovering one or more drones  3  while carrier aircraft  1  is in flight. The primary operative part of the invention is an extensible stinger  5  which is part of a stinger assembly  59  as explained below, and has mounted thereon catcher shuttle  9 . Catcher shuttle  9  includes an open-ended, forward vee tip  7 . Referring to  FIG. 3 , extensible stinger  5  is shown in this plan view, and catcher shuttle  9  mounted on stinger  5  has two elongated longitudinal, laterally disposed catcher shuttle members  11 ,  12  having outwardly inclined forward members  13  and  15  defining forward vee tip  7 . Vee tip  7  is shown not only in  FIG. 3 , but also in  FIGS. 1, 2, 5, 8, 10 and 10A . 
         [0032]      FIG. 2  shows carrier aircraft  1  as being somewhat shaped like a “manta ray” structure in which extensible stinger  5 , which is extensible by a relatively long distance L of between fifteen and thirty feet from a stinger sheath  25 , is disposed in a spaced relation from the underside of carrier aircraft  1 . Open ended vee tip  7  is mounted on catcher shuttle  9  as noted above. Catcher shuttle  9  has a wide forward part  19  ( FIG. 3 ) which engages a recovery guide  21  ( FIGS. 2, 4, 5, 9, 11-13 ) located on the bottom of drone  3 . 
         [0033]    As mentioned above, extensible stinger  5  extends some distance ahead of carrier aircraft  1  as shown in  FIGS. 1 and 2 , and therefore forward vee tip  7  of catcher shuttle  9  is located in undisturbed non-turbulent air. The undisturbed air permits drone  3  to be launched and recovered in non-turbulent air ahead of carrier aircraft  1 , the body of which is surrounded by turbulent air which is caused by the passage of carrier aircraft  1  through the air and with high speed jet exhaust or prop wash. 
         [0034]    Stinger  5  includes within its structure, a first linear drive  23  which is shown in  FIGS. 3 and 8 . First linear drive  23  is attached to catcher shuttle  9  whose vee tip  7  faces forward into the airstream for enabling the controlled movement of catcher shuttle  9  along nearly the full length from end to end of extensible stinger  5 . 
         [0035]    Stinger  5  and catcher shuttle  9  are partially enveloped in long stinger sheath  25  as shown, for example, in  FIGS. 1, 2, 5, 6 and 8 .  FIG. 6  does not include catcher shuttle  9 . Extensible stinger  5  is shown in detail in  FIGS. 3 and 5 .  FIG. 3  is a plan view as indicated earlier, and as also explained above has at its forward end outwardly inclined forward members or catcher shuttle arms  13  and  15 . Catcher shuttle arms  13  and  15  are slanted outwardly to form a slot, trough or opening  27 . Slot  27  forms a narrow linear opening as it proceeds rearwardly in catcher shuttle  9 . A pair of forwardly facing cameras  29  and  31  to enable binocular forward vision are mounted on opposite sides of catcher shuttle  9  distal from opening  27  at the beginning of flat sides  33  and  35  of catcher shuttle  9 . First linear drive  23  is preferably a drive chain or drive belt  37 , which is driven around an idler  39  by a drive motor  41  as shown in  FIG. 8 . 
         [0036]    Catcher shuttle  9  has at its uppermost portion the pair of opposing, laterally movable catcher shuttle arms  13  and  15  mentioned above. Referring to  FIGS. 4 and 9 , each drone  3  has on its underside a recovery guide  21  which in the preferred embodiment, forms in cross section, an inverted T. Recovery guide  21  can take many forms, and is operatively engageable by catcher shuttle  9  to contribute to the launching and/or recovery of drone  3 . Catcher shuttle  9  includes a launch/recovery assembly  22  for cooperating with recovery guide  21  to launch and recover drones  3 . Launch/recovery assembly  22  is part of catcher shuttle  9  and in the preferred embodiment includes a support  43 , for supporting arms  44  and  45 , defining a recess  53 . When recovery guide  21  is disposed in a recess  53  of launch/recovery assembly  22 , and arms  44  and  45  of launch/recovery assembly  22 , which arms  44 ,  45  are movable between open and closed positions shown by arrows  46  ( FIG. 9 ), are in their closed positions, drone  3  cannot be moved in the vertical direction to be free from launch/recovery assembly  22 . 
         [0037]    Stinger  5  is held in stinger sheath  25 . Stinger sheath  25  is an elongated member having opposing lateral sides  56  and  57  shown most clearly in  FIGS. 4, 6 and 9 . Stinger sheath sides  56  and  57  engage opposing sides of stinger  5  to enable the longitudinal sliding movement of stinger  5  within stinger sheath  25 . Stinger  5  and stinger sheath  25  are part of stinger assembly  59  explained above. Stinger assembly  59  includes a forward cross support  61  and a rearward cross support  63  illustrated in  FIG. 10  joined together by a longitudinal support member  55  to form an “H” shaped straight line. Forward cross support  61  has a forward transverse linear drive assembly  65  ( FIGS. 10, 11 ), and rearward cross support  63  has a rearward transverse linear drive assembly  67  ( FIGS. 10, 12 ). Forward transverse linear drive assembly  65  includes a screw drive  69  which is driven by an actuator  71  as shown in  FIG. 11 . Likewise, rearward transverse linear drive assembly  67  includes a screw drive  73  which is rotated by an actuator  75  depicted in  FIG. 12 . Stinger assembly  59  is moved in the lateral directions as indicated by arrows  77  under the control of forward transverse linear drive assembly  65  and rearward transverse linear drive assembly  67  of stinger assembly  59 , and as shown by arrows  79  with respect to rearward transverse linear drive assembly  67 . 
         [0038]    When drone launcher and recovery apparatus  100  is not in use, stinger assembly  59  is held close to the underside of carrier aircraft  1  or may be contained within carrier aircraft  1 &#39;s structure in retracted position shown in  FIG. 10 . When stinger assembly  59  is in use for either launching drones  3  or recovering drones  3 , stinger assembly  59  is lowered from the bottom of carrier aircraft  1 . One embodiment for doing this is shown in  FIG. 10 . A pair of front extendable arms  83  and  85  are attached to the opposite ends of forward cross support  61 . Likewise, rear extendable arms  87  and  89  are attached to the opposite ends of rearward cross support  63 . Extendable arms  83 ,  85 ,  87  and  89  could be hydraulically driven telescoping arms as shown. Extendable arms  83 ,  85  are used to raise or lower stinger assembly  59 . Stinger  5  with catcher shuttle  9  is permitted to be angled upwards or downwards or angled up or down to match the angle of attack of drone  3 . Tilting apparatus is employed to tilt longitudinal support member  55  and stinger sheath  25  to properly orient catcher shuttle  9  to receive drone  3  from controlled flight or to launch drone  3  into the atmosphere. Hinges  92  and  94  fixed to carrier aircraft  1  are connected respectively to the upper parts of extendable arms  83  and  85 . Hinges  92  and  94  pivot the upper parts of extendable arms  83  and  85  in the directions shown by arrows  96  and  98 . Extendable arms  87  and  89  do not pivot. When extendable arms  83  and  85  pivot clockwise with their respective lower portions moving towards extendable arms  87  and  89 , longitudinal support member  55 , stinger sheath  25  and stinger  5  are pivoted counter clockwise about the bases of respective extendable arms  87  and  89 , to angle upward or downward catcher shuttle  9 . The amount that catcher shuttle  9  is raised or lowered increases the ability of catcher shuttle  9  to be in the correct angular position for receiving drone  3  from controlled flight or to launch drone  3  into the undisturbed air ahead of carrier aircraft  1 . The vertical movement of longitudinal support member  55 , stinger sheath  25  and stinger  5  is indicated by arrow  110 . 
         [0039]    An alternative to extendable arms  83 ,  85 ,  87  and  89  is shown in  FIG. 13 . In  FIG. 13 , there is illustrated front pivoting arms  95  and  97 , and rear pivoting arm  99  and  101 . Front pivoting arms  95  and  97  have upper connection portions  101  and  103  which are attached to carrier aircraft  1  on opposite side portions of carrier  1 . Front pivoting arm  95  has a connection portion  105  which has an orifice for receiving a cylindrical connection member  107  extending from forward cross support  61 . The remaining pivoting arms are all connected to the respective cross pieces in the same manner. 
         [0040]    Drones  3  are preferably stored in an interior or hull or bay  113  of carrier aircraft  1  as indicated in  FIGS. 10 and 13 . A pair of bay doors  109  and  111  open and close bay  113  from which drones  3  can be withdrawn from or moved to their storage space in carrier aircraft  1 . When one of drones  3  is to be launched, bay doors  109  and  111  are moved to their open position as shown in  FIG. 10 , and vee tip  7  of catcher shuttle  9  is moved into recess  53  of catcher shuttle  9  after catcher arms  44  and  45  are moved to their open positions as shown in dotted lines in  FIG. 9 . After recovery guide  21  of drone  3  is moved into recess  53 , catcher arms  44  and  45  are moved to their closed position to retain drone  3  on catcher shuttle  9  and held longitudinally by pivoting members  137 ,  139 . Stinger assembly  59  is initially located adjacent the underside of carrier  1 . Either extendable arms  83 ,  85 ,  87  and  89  (or pivoting arms  95 ,  97 ,  99  and  101 ) move stinger assembly  59  to the active position as shown in  FIG. 2 . Drone  3  is thus located in rearmost portion of slot  27  of catcher shuttle  9  between elongated, longitudinal, laterally disposed catcher shuttle members  11  and  12 . A second linear drive  24 , discussed hereinafter, then extends the stinger  5  until the tip of the stinger  5  is clear of the turbulent air surrounding the carrier aircraft  1 . First linear drive  23  moves catcher shuttle  9  forwardly along with drone  3  located thereon to the forward end of stinger  5  out of the turbulent air surrounding carrier aircraft  1  and into the undisturbed air ahead of carrier aircraft  1 . Drone  3  is then launched as shown in  FIG. 5 . 
         [0041]    Returning to  FIG. 11 , forward cross support  61  includes a pin  115  shown in  FIG. 11  A which extends through a short longitudinal slot  117  connected to stinger sheath  25 , which lies along the longitudinal axis of stinger sheath  25  to permit it to be angled laterally as required by the airflow. Referring to  FIG. 12 , rearward transverse linear drive assembly  67  in connected to stinger sheath  25  by means of a rear pin  119  shown in  FIG. 12A  which is then constrained within a circular hole  121  so that stinger sheath  25  pivots around pin  119 . 
         [0042]    Referring to  FIG. 10 , front extendable arms  83  and  85  are attached to coaxial pins  123 . The axis of pins  123  is perpendicular to the longitudinal axis of carrier aircraft  1 , and the opposite ends of pins  123  (only coaxial pin  123  of arm  83  is visible) are connected to forward cross support  61 . Rearward cross support  63  has similar pins which are connected to rear extendable arms  87  and  89 , and rearward cross support  63  in the same manner. Arms  87  and  89  always extend equally. Similarly, arms  83  and  85  also extend equally, but may extend differentially to rearward arms  87  and  89  as needed to launch or recover drone  3 . As explained previously, stinger sheath  25  can be extended downwardly to an operative location, and stinger  5  is partially extended out of stinger sheath  25 , with catcher shuttle  9  and its vee tip  7  at zero angle of attack in the undisturbed air ahead of carrier aircraft  1 , by extending partially both the front extendable arms  83  and  85 , and operating forward transverse linear drive assembly  65  and rearward transverse linear drive assembly  67 . The orientation and position of vee tip  7  can then be adjusted to recover a drone  3  by changing the lengths of respective front extendable arms  83 ,  85  and rear extendable arms  87 ,  89 . 
         [0043]    Reference is now made to  FIG. 8 . An angle of attack sensor  125 , and a yaw sensor  144  only senses the airflow at the end of stinger  5  to enable catcher shuttle  9  and launch/recovery assembly  22  to be positioned to better engage recovery guide  21  of drone  3 . Spring loaded latching assembly  137  and  137 ′ within catcher shuttle  9  captures and hold retrieval guide  21  of drone  3 . Spring loaded latching assembly  137  is discussed below. Spring loaded latching assembly  137  includes a pivoting member  138 . Pivoting member  138  has a downwardly extending (as shown in  FIG. 8 ) and an inwardly extending latching arm  139  integral with downwardly extending arm  139 . Pivoting member  138  is mounted about a pivot  141 , and is biased in a clockwise direction by a spring  143 . A similar pivoting assembly  137 ′ having like components is provided inwardly under catcher shuttle  9  but facing outwardly towards pivoting member  137  and having a similar function as pivoting assembly  137 . Pivoting assembly  137 ′ has components corresponding to those of pivoting assembly  137  and given the same identifying numbers but with a prime (′) suffix. Latching assemblies  137  and  137 ′ are used to hold a drone  3  atop catcher shuttle  9  to either move a drone  3  from storage to a launch position, or to move a captured drone from catcher shuttle  9  to storage such as in the bay of a carrier aircraft  1 . 
         [0044]    When drone  3  is to be engaged or captured by launch/recovery assembly  22  of catcher shuttle  9 , stinger  5  with catcher shuttle  9  moved to near the free end of stinger  5  extends out to engage recovery guide  21  of drone  3 . The vertical stem of recovery guide  21  will then slide between catcher arms  44  and  45  and the horizontal part of recovery guide  21  will be trapped securely by two inwardly facing latching arms  139  and  139 ′ which are spring loaded by springs  143 . When drone  3  is securely attached to the top of catcher shuttle  9 , drone  3  can be moved to a location below bay  113  through the turbulent air surrounding carrier aircraft  1 . 
         [0045]    If drone  3  is to be launched aft, after lowering drone  3  out of bay  113  to an optimal attitude with regards to the slipstream, recovery guide  21  is initially securely held between latching arms  139 ′ and  139 , a retract hydraulic cylinder  129 ′ then lowers arm  139 ′ and catcher shuttle  9  travels rapidly forwardly along stinger  5  to eject drone  3  from catcher shuttle  9 . 
         [0046]    Normally, if drone  3  is to be launched forward, stinger  5  with the catcher shuttle  9  with captive drone  3  on top held captive between latching arms  139  and  139 ′ is lowered out of the bay  113  to an optimal attitude with the slipstream, then stinger  5  is extended out of the turbulent air around carrier aircraft  1 , and catcher shuttle  9  is rapidly driven to the forward end of stinger  5 . Just before catcher shuttle  9  reaches the forward end, retract cylinder  129  retracts latching arm  139  and releases drone  3  into free flight. 
         [0047]    Yaw sensor  144  is included on stinger  5  for measuring the angular velocity of respective drones  3  to be used as part of the launching and recovery procedures. Thus, feedback from angle of attack sensor  125  and yaw sensor  144  enables stinger  5  to be oriented into the flight path of carrier aircraft  1  for optimal launching and recovery of drones  3 . 
         [0048]    Also disposed on catcher shuttle  9  are frontwardly facing cameras  29  and  31  mentioned above, which are on both sides of vee tip  7  to enable binocular vision and enable depth perception of drone  3  when drone  3  is flying ahead of carrier aircraft  1  under the control of carrier aircraft  1 . The latter enables the measurement of the separation between vee tip  7  and the drone  3 , since this can be detected prior to stinger  5  extending further to engage drone  3  by recovery guide  21 . That is, stinger  5  can engage drone  3  by recovery guide  21  of drone  3 , with vee tip  7  of catcher shuttle  9  when catcher shuttle  9  is at the end of its forward travel on stinger  5 . 
         [0049]    In order to launch one of drones  3 , stinger  5  is held against or within the bottom of carrier aircraft  1 , and recovery guide  21  of drone  3  is placed within slot  27  while drone  3  is within the hull of carrier aircraft  1 . Drone  3  is held in position on catcher shuttle  9  by spring loaded assemblies  137  and  137 ′ linear drive  23  and a second linear drive  24  as shown in  FIG. 8 . The position and velocity of catcher shuttle  9  is controlled by means of first linear drive  23  within stinger  5  which is actuated by means of actuator motor  41 . Second linear drive  24  includes a drive chain or drive belt  151  which is controlled by an actuator motor  153  for stinger  5 , both of which are located within stinger sheath  25 . Actuator motor  41  for catcher shuttle  9  preferably has an extension rate of a moderate one foot per second. However, the burst speed would be about two feet per second in order to recover a drone as discussed below. 
         [0050]    As indicated above, in order to launch a drone  3 , stinger  5  is located at the bottom of carrier aircraft  1 , and recovery guide  21  of drone  3  is placed within slot  27  of catcher shuttle  9  while drone  3  is within the hull of carrier aircraft  1 , and catcher shuttle  9  is held in position by first linear drive  23  within stinger  5  and second linear drive  24  within stinger sheath  25 , as well as by forward transverse linear drive assembly  65  and rearward transverse linear drive assembly  67 . Latching arms  139  and  139 ′ serve as raised blockages and are located in front of and behind recovery guide  21  of a drone  3  being held within slot  27  of catcher shuttle  9 . 
         [0051]    Front and rear extendable arms  83 ,  85 ,  87  and  89  are used to lower stinger sheath  25 , stinger  5  and catcher shuttle  9 , along with drone  3 . The engine of drone  3  is then started, and when the thrust provided by the engine of drone  3  overcomes the drag of the slipstream as might be measured by a force sensor in contact with the rear part of recovery guide  21  of drone  3 . The thrust of the engine of drone  3  is then further increased and first linear drive  23  of stinger  5  is used to accelerate drone  3  on catcher shuttle  9  forwardly to the end of the stinger  5 , ejecting drone  3  from stinger  5  into free flight into non-turbulent air ahead of carrier aircraft  1  where drone  3  can accelerate away to perform its mission. 
         [0052]    Alternatively, the engine of drone  3  can be set to idle, and blockage  157  at the rear of slot  27  of catcher shuttle  9  of stinger  5  can be retracted, and drone  3  can forcefully be ejected backwards out of the rear of slot  27  by any combination of drag forces and a combination of first linear drive  23  and second linear drive  24  (which could be an induction motor or other means), and then drone  3  is far enough away, drone  3  can accelerate away to perform its mission. Tests should be performed to verify that this mode of launching drone  3  through the particular carrier aircraft  1 &#39;s turbulence slipstream is feasible, as each body shape, velocity, angle of attack, etc. combination produces different patterns of turbulence which may direct drone  3  to impact against the body of carrier aircraft  1 . 
         [0053]    In order to recover a drone  3 , drones  3  are directed to carrier aircraft  1  to fly to a proximate location relative to carrier aircraft  1 . Particular drone  3  to be recovered is further directed and flown under the control of carrier aircraft  1 , into a position in front of carrier aircraft  1  such that its recovery guide  21  is as closely as possible, directly in front of stinger  5  as viewed by cameras  29  and  31 , which is substantially extended, and positional feedback is used to keep drone  3  on a stable flight path just prior to its recovery. Other drones  3  yet to be recovered are meanwhile positioned in a stable pattern or flock relative to carrier aircraft  1  through a feedback and control loop. 
         [0054]    Stinger  5  can then be extended forward to engage recovery guide  21  using depth perceiving binocular vision cameras  29  and  31  on the forward end of catcher shuttle  9 . Stinger  5  would then be adjusted by moving stinger  5  angularly and vertically up and down by use of extendable arms  83 ,  85 ,  87  and  89  and sideways by forward transverse linear drive assembly  65  and rearward transverse linear drive assembly  67  as appropriate. 
         [0055]    Small alignment lights such as light emitting diodes (infrared lights may be used at night) may be placed on drone  3  to allow night operations together with other sensors, or drone  3  may be illuminated from carrier aircraft  1 . The alignment lights would be seen by cameras  29  and  31  on tip of stinger  5 , together with telemetry from drone  3 , and they can be used to place drone  3  in proper alignment. When drone  3  is properly aligned to be received by the catcher shuttle  9  at the tip of stinger  5 , stinger  5  is speedily extended further from stinger sheath  25  to engage recovery guide  21  of drone  3 . When drone  3  is securely engaged, drive motor  41  is used to activate first linear drive  23  to move drone  3  to the rear of stinger  5 , and hold drone  3  stationary in such a position that when the end of forward members  13 ,  15  engaging support structure on drone  3  is raised towards the bottom of carrier aircraft  1 , drone  3  is properly positioned to enter bay  113  after bay doors  109  and  111  are opened. This completes the retrieval process which, for the maximum possible rate to be achieved should be automated. 
         [0056]    As a safety measure, if drone  3 , for various reasons, is contacted by stinger  5  improperly and begins to angle upwards into the path of carrier aircraft  1 , angle of attack sensors  125  on board drone  3  will sense this and cause drone  3  to accelerate out of contact with stinger  5  and re-stabilize the flight path of drone  3  relative to carrier aircraft  1  prior to another retrieval attempt. 
         [0057]      FIG. 7  illustrates the use of a traditional carrier aircraft  1 ′ for holding apparatus  100 ′ for launching and recovering drones. Nose landing gear  159  have to be displaced to the side, so as not to obstruct the operations of the launch and recovery system of carrier aircraft  1 ′. The number of drones  3  may have to be limited to, say 20, if they are stacked four high with five stacks. Launch and recovery stingers  5  are shown extended. A roller shutter type door  163  can be used to pass drones in an out of the hull of carrier aircraft  1 ′ which may be, transport aircraft such as the Airbus A400M, Alenia C-27, Boeing C-17, EADS CASA C-295, de Havilland Canada C-7, Kawasaki C-2, Lockheed C-130 or Short Skyvan. 
         [0058]    In these aircraft which all have a rear ramp very rapid deployment of drones  3  by the same method as used for air dropped cargo, i.e. a drogue parachute attached to the rear of drone  3  is ejected and drags drone  3  out of the rear ramp, then the drogue parachute is discarded. As the technology of linear induction motors advances it may enable recovery guide  21  of drone  3  to be engaged by, and moved directly within the stinger  5  as shown in  FIG. 12 , where recovery guide  21  is the forcer, and stinger  5  that holds within it the platen of an induction motor, and electromagnetic forces move or hold the recovery guide anywhere along the length of stinger  5 . When such an advance in the technology of linear induction motors occurs, catcher shuttle  9  may be replaced by electromagnetic forces to position, accelerate, decelerate and capture drone  3  obviating the need for many mechanical actuator systems used in the current preferred embodiment. 
         [0059]    The invention has been described with particular reference to its preferred embodiments, but variations and modifications within the spirit and scope of the invention may occur to those skilled in the art to which the invention pertains.