Abstract:
A micro-unmanned aerial vehicle deployment system is provided for a cruise missile having submunition compartments. The system includes a vehicle launch module releasable from the cruise missile submunition compartment. The vehicle launch system has a control circuit and at least one micro-unmanned aerial vehicle contained therein. Structure is provided in the launch module for deploying the micro-unmanned aerial vehicle. A separable tether can be joined between the cruise missile and the vehicle launch module that separates when subjected to tension after deployment of the vehicle launch module.

Description:
STATEMENT OF GOVERNMENT INTEREST 
     The invention described herein may be manufactured and used by or for the Government of the United States of America for governmental purposes without the payment of any royalties thereon or therefor. 
    
    
     CROSS REFERENCE TO OTHER PATENT APPLICATIONS 
     None. 
     BACKGROUND OF THE INVENTION 
     (1) Field of the Invention 
     The present invention relates to a device for deployment from a cruise missile and more particularly for submunition that is capable of deploying small unmanned aerial vehicles. 
     (2) Description of the Prior Art 
     Tomahawk cruise missile variant UGM 109D is designed to deliver four payload modules of six small submunitions each to multiple targets. Submunitions are positioned in a submunition compartment with a close sliding fit and are retained in the compartment by a submunition latch. The submunition is deployed by a charge positioned in the submunition compartment which moves the submunition into the slipstream around the missile. Once the submunition enters the slipstream around the missile, aerodynamic forces pull it away from the missile. A submunition is typically an explosive weapon, however, other uses have been contemplated for this capability. 
     U.S. Pat. No. 6,498,767 to Carreiro was issued for a “Cruise Missile Deployed Sonar Buoy”. This patent teaches a sonar buoy adapted to be deployed by a cruise missile from its submunition compartment. The sonar buoy includes a flotation device for keeping a portion of the buoy afloat, a hydrophone, a transmitter for communicating contact and position information and releasable means for attaching the sonar buoy to the cruise missile. By means of this device, a means of monitoring littoral and other waters for enemy submarines and other threats is provided with a low degree of risk to friendly forces. A system for deploying this sonar buoy in a sonar buoy field is also disclosed. 
     Also relevant is U.S. Pat. No. 6,484,641 for a “Cruise Missile Downed Airman Decoy”. This patent teaches that a cruise missile, such as the Tomahawk cruise missile, can be adapted to deploy decoys in an area as the missile progresses along its preprogrammed course. Each decoy is shaped to be compatible with and ejected from the Tomahawk missile submunition compartment and has a preprogrammed control unit operating a transmitter connected to an extendible antenna. False beacon signals and/or false message signals are transmitted from each of the decoys to deceive and confuse defensive forces, such as enemy searchers looking for a downed airman. 
     Unmanned aerial vehicles have been a recent addition to ground combat. Of relevance to the current invention are micro-unmanned aerial vehicles (MUAVs). Known MUAVs are less than six inches in length, with a maximum range of approximately seven miles and flight endurance of up to one hour. The MUAV can deploy useful micro payloads to a remote or otherwise hazardous location where it may perform any of a variety of missions, including reconnaissance and tagging high-value targets, bio-chemical detection and classification, battle damage imaging and assessment and search and rescue. For these purposes, the MUAV can be equipped with an appropriate sensor joined to a transmitter. 
     The MUAV is controlled externally by directional antennas from ground, surface ship, submarine, or airborne platforms. The MUAVs, acting alone or in small, cooperative groups, can provide reconnaissance and surveillance of inner city areas, serve as communication relays and place sensors on elevated surfaces. 
     Although the MUAV serves well in its intended purpose, one serious limitation of the MUAV is its limited range and endurance. Consequently, MUAVs must be deployed relatively close to their selected area of operation. It is desired that means be provided to extend the range of operation of the weapon system, such as the weapon system deploying MUAVs. 
     SUMMARY OF THE INVENTION 
     Accordingly, it is an object of the present invention to provide means for extending the range of operation of a weapon system deploying MUAVs. 
     Another object of the present invention is to provide means for adapting a system for dispensing submunitions to dispensing submunitions such as MUAVs having a limited range. 
     In accordance with the present invention, there is provided a micro-unmanned aerial vehicle deployment system for a cruise missile having submunition compartments. The system includes a vehicle launch module releasable from the cruise missile submunition compartment. The vehicle launch system has a control circuit and at least one micro-unmanned aerial vehicle contained therein. Structure is provided in the launch module for deploying the micro-unmanned aerial vehicle. The system can include a separable tether joined between the cruise missile and the vehicle launch module that separates when subjected to tension after deployment of the vehicle launch module. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
       Other objects, features and advantages of the present invention will become apparent upon reference to the following description of the preferred embodiments and to the drawings, wherein corresponding reference characters indicate corresponding parts throughout the several views of the drawings and wherein: 
         FIG. 1  illustrates some of the features of a cruise missile (specifically the Tomahawk UGM-109D variant or the like); 
         FIG. 2  generally illustrates features of the payload module of the cruise missile; 
         FIG. 3  generally illustrates a Micro Unmanned Aerial Vehicle (MUAV) module; 
         FIG. 4  schematically illustrates the MUAV module of the present invention prior to the deployment thereof; 
         FIG. 5  schematically illustrates a flight path of a cruise missile dispensing multiple MUAVs there along; 
         FIG. 6  illustrates details associated with the MUAV module ejection; 
         FIG. 7  illustrates the MUAV module status following ejection thereof from the missile; and 
         FIG. 8  illustrates the MUAV module status after an associated parachute has been deployed. 
     
    
    
     DETAILED DESCRIPTION OF THE INVENTION 
     As discussed previously, deploying multiple Micro-Unmanned Aerial Vehicle (MUAV) has many benefits, but there are limitations concerning its range of operation. The present invention eliminates the range limitation by adapting a system for dispensing multiple short range vehicles, into a known submunition deployment system. The known submunition deployment system utilizes a cruise missile, such as a Tomahawk variant UGM 109D. This type of missile can be launched from submarine, surface or airborne locations. The present invention allows the MUAV to be insertable into and ejected from enclosed spaces of the missile both in a close sliding fit. More particularly, the present invention eliminates the problem of limited range by employing a cruise missile to dispense multiple MUAVs. The operation of the present invention may be better understood by first referring to  FIG. 1 . 
       FIG. 1  generally illustrates a cruise missile  10  that has payload bays, such as the known Tomahawk variant UGM 109D cruise missile, which features four payload bays  12   1 ,  12   2 ,  12   3 ,  12   4  displaced about the fuselage of the cruise missile  10 . The payload modules  12   1 ,  12   2 ,  12   3 ,  12   4  are enclosed by defined spaces of the Tomahawk missile  10  having predetermined dimensions. The features of the payload modules  12   1 ,  12   2 ,  12   3 ,  12   4  may be further described with reference to  FIG. 2  generally illustrating a payload module  12   1 . 
     As seen in  FIG. 2 , the payload module, such as  12   1 , has six submunition compartments  14   1 ,  14   2 ,  14   3 ,  14   4 ,  14   5  and  14   6 . Each of the six submunition compartments can hold a submunition that is separately ejectable from the defined payload module identified typically at  12   1 . In general, the present invention provides a module assembly that allows one submunition to support and dispense multiple micro-unmanned aerial vehicles. 
       FIG. 3  and  FIG. 4  show the module assembly  16  that has exterior dimensions that substantially match the interior dimensions of one submunition compartment  14   1  . . .  14   6 . Assembly  16  should have a close, sliding fit within a submunition compartment. This allows assembly  16  to be inserted into and to be ejectable from the enclosed submunition compartment  14   1  . . .  14   6 . One module assembly  16  can be positioned in each submunition compartment  14   1  . . .  14   6 . The details of the module assembly  16  of the present invention may be further described with reference to  FIG. 4 , which is a cross-sectional representation of the module assembly  16  prior to deployment. 
     The module assembly  16  comprises a shell  18  which has the substantially same external dimensions as the internal dimensions of submunition payload  14   1  . . .  14   6 . The shell  18  provides environmental protection to the internal components and acts as a launch platform for MUAVs. These MUAVs are shown in  FIG. 4  as MUAV  20   1 ,  20   2 ,  20   3  and  20   4 . MUAVs  20   1 ,  20   2 ,  20   3  and  20   4  are shown with a propeller and wings; however, another propulsion means such as a ducted fan, jet engine, rocket engine or the like could be used. MUAVs can have sensors  21  positioned thereon. MUAVs can be remotely controlled and have transmitters allowing them to transmit sensor signals. 
     The internal volume of module assembly can be divided by shell  18  into five compartments  22   2 ,  22   2 ,  22   3 ,  22   4  and  22   5 . Compartments  22   2 ,  22   2 ,  22   3 , and  22   4  can be occupied by a respective MUAV  20   2 ,  20   2 ,  20   3  and  20   4 . Compartment  22   5  is occupied by a parachute  24 . 
     Spacers  26   11 ,  26   22 ,  26   22 ,  26   22 ,  26   32 ,  26   32 ,  26   42  and  26   42 , stacked alternately in compartments  22   2 ,  22   2 ,  22   3 , and  22   4 , to hold MUAVs  20   2  . . .  20   4 . More particularly, compartment  22   2  holds spacer  26   22  and  26   22 , compartment  22   2  holds spacers  26   22  and  26   22 , compartment  22   3  holds spacers  26   32  and  26   32 , and compartment  22   4  holds spacers  26   42  and  26   42 . Each of the spacers  26   22  . . .  26   42  is preferably comprised of an elastomeric material and each pair of spacers  26   22  and  26   22 ;  26   22  and  26   22 ;  26   32  and  26   32 ; and  26   42  and  26   42  are oppositely facing each other and confine the movement of their respective MUAV  20   2 ,  20   2 ,  20   3  and  20   4 . 
     The fuselage of each MUAV  20   1 ,  20   2 ,  20   3  and  20   4  contains a normally closed plunger-type activation switch  28 . When compressed by the elastomeric spacers  26   11  . . .  26   42  within the MUAV compartments, the switches  28  remain in the open, or off position. When extended, by the separation of the spacers  26   11  . . .  26   42  and MUAVs,  20   1  . . .  20   4  to be further described hereinafter, the switches  28  extend so as to activate the internal propulsion motor of their respective MUAV  20   1  . . .  20   4 . 
     The parachute compartment  22   5  contains the parachute  24 , a lanyard  30  and an arming-switch  32 . The lanyard  30  attaches to the wall of parachute compartment  22   5 , loops under the parachute  24  and exits the compartment  22   5  through a slot  34  in a tear-through cover  36  of the compartment  22   5 . The tear-through cover  36  holds the parachute  24  in the compartment  22   5  prior to deployment to be further described hereinafter. Both the parachute  24  and the arming-switch  32  are secured to the lanyard  30 . 
     The module assembly  16  shown in  FIG. 4  further comprises a control unit  38  and a battery  40 . The control unit  38  provides all internal control for the module assembly  16  and has timing means for ejecting the respective module assembly  16  from the submunition compartment  14  at selectable times. Assembly  16  ejection can also be controlled by remote communication from a support platform. The battery  40  provides all of the internal power necessary to operate the module assembly  16 . 
     The module assembly  16 , in particular the shell  18 , has walls with four-spaced apart corners  42   1 ,  42   2 ,  42   3 , and  42   4  each having a latch  44 . The latches  44  operate in their off-state to hold the walls of the shell  18  together and when in their on-state cause the walls to separate from each other. The latches  44  can be pyro-activated devices. When activated (on-state), the latches  44  allow complete separation of the walls of the shell  18 . 
     The launching platform plots waypoints for a flight path over the desired area, or areas, and launches the cruise missile  10  outfitted with module assembly  16  shown in  FIGS. 3 and 4 .  FIG. 5  shows an example mission profile  46 . More particularly,  FIG. 5  illustrates the mission profile  46  as including an initial position  48  of the cruise missile  10  and a final position  50  of the cruise missile  10 . The mission profile  46  further includes multiple waypoints  52 . The cruise missile can eject one module assembly  16  between waypoints  52 . Further details of the operation of the present invention may be described with reference to  FIG. 6 . 
       FIG. 6  generally illustrates the payload module  12   1 , previously discussed with reference to  FIG. 2 .  FIG. 6  further illustrates the module assembly  16  described with reference to  FIGS. 3 and 4 , ejected from the submunition compartment  14   1 . 
       FIG. 6  further illustrates the payload module  12   1  as housing module assemblies  16  in submunition compartments  14   1 ,  14   2 ,  14   4 ,  14   5  and  14   6  of  FIG. 2 . The location for submunition compartments  14   3  and  14   4  is shown as being partially broken away so as to illustrate further details of both the payload module  12   1  and the module assembly  16 . 
     As seen in  FIG. 6 , the module assembly  16  has tear-through cover  36  (previously discussed with reference to  FIG. 4 ) that allows the exit of the lanyard  30  from opening  34  (both previously discussed with reference to  FIG. 4 ). The lanyard  30  has a weak point  56  (to be further described with reference to  FIGS. 7 and 8 ) and has its distal end attached to latch  58  of the payload module  12   1 . 
     As further seen in  FIG. 6 , the payload module  12   1  comprises control lines  60 , closure doors  62 , and hinges  64  operatively cooperating with respective closure doors  62 , and mounting lugs  66 . Prior to deployment, the exterior surface of assembly  16  acts as the exterior surface of missile  10 . After deployment, closure door  62  must be moved into place in order to preserve missile  10 &#39;s aerodynamic characteristics. 
       FIG. 6  primarily illustrates the status of the module assembly  16  just after ejection. The module assembly  16  operation during and after ejection, is similar to the operation of known systems such as that used on the Tomahawk cruise missile variant UGM-109D. Unlike the known system, the current invention allows ejection of less than all of the module assemblies. 
     Upon ejection, the lanyard  30 , of the present invention, tethers the module assembly  16  that is ejected to the respective payload module closure door  62 . As seen with simultaneous reference to  FIGS. 6 and 7 , when taut, the lanyard  30  pulls the respective closure door  62  shut, while simultaneously forcing the parachute  24  through the tear-through cover  36  and also pulling the pin  68  on the arming switch  32  thereby activating the control unit  38 . 
     With the closure door  62  shut and the parachute  24  clear of the module assembly  16 , as seen in  FIG. 7 , the lanyard  30  breaks at the weak-point  56  leaving the module assembly  16  to fall and deploy the parachute  24 . A closure door latch  58 , shown in  FIG. 6 , holds the closure door  62  closed. Once closed and latched, the closure door  62  aerodynamically fairs with the airframe of the missile  10  for the rest of the flight shown in  FIG. 5 . 
     With the parachute  24  deployed, as shown in  FIG. 8 , the module assembly  16  floats toward earth. After a brief delay, when the module assembly  16  reaches a pre-programmed altitude, or on remote command, the control unit  38  fires the latches  44  thereby separating the walls of the shell  18 . Falling free of the module assembly  16 , the stacked MUAVs  20   1 ,  20   2 ,  20   3 , and  20   4  separate from their elastomeric isolators  26   22  . . .  26   42  extending their activation switches  28  and starting the respective motors enclosed in the MUAVs  20   2 ,  20   2 ,  20   3 , and  20   4 . 
     It should now be appreciated that the practice of the present invention provides a module assembly  16  that adapts a system employed for dispensing submunitions from a cruise missile to a micro-unmanned aerial vehicle system having a limited range capability. The module assembly  16  allows the range of the system to be increased to that of the range utilized by the cruise missile, while at the same time providing for the proper dispensing of submunitions, that is, MUAVs. 
     It should be further appreciated that although the invention has been described for adapting the utilization of Tomahawk missile to the needs of a weapon system employing MUAVs other vehicles such as those found in airborne applications may be utilized to increase the present limited operating range of the weapon systems employing MUAVs. 
     It will be understood that many additional changes in the details, materials, steps and arrangement of parts, which have been herein described and illustrated in order to explain the nature of the invention, may be made by those skilled in the art within the principle and scope of the expressed in the appended claims.