Abstract:
An indirect fire munition non-lethal cargo carrier mortar deploys non-lethal sub-munitions to an intended target. The cargo carrier mortar includes a deceleration system which allows for the discarded mortar to descend at a controlled non-free fall velocity thereby minimizing the risk of injury or collateral damage from the mortar. The cargo carrier mortar is adapted to be compatible with existing standard military equipment such as standard mortar caliber sizes.

Description:
FEDERAL RESEARCH STATEMENT 
     The invention described herein may be manufactured, used, and licensed by or for the U.S. Government for U.S. Government purposes. 
    
    
     BACKGROUND OF INVENTION 
     Field of the Invention 
     The present invention relates to non-lethal weapons, and more particularly to non-lethal cargo projectiles. 
     Related Art 
     In today&#39;s combat environment, soldiers are increasingly fighting in urban environments where enemy combatants may be mixed in within a civilian population. Non-lethal weapons are an effective tool where traditional munitions may not be used. In particular, non-lethal weapons allow for the suppression of targets and the ability to return fire in situations where the use of high explosives (HE) or other lethal force is not allowed. 
     Indirect fire, such as mortar fire, is an effective way to deploy non-lethal weapons to an area. However, there are downsides to such an approach when using conventional cargo carrier mortars. The body which houses the non-lethal ordinance, as well as the tail section if the indirect fire vehicle is a mortar, can cause serious damage in itself when descending to the ground after deployment. 
     To reduce the likelihood of damage from deployed shells, attempts have been made in the past to decelerate the shell. However, such attempts have been ineffective, compromised payload or were incompatible with present military standards. 
     Accordingly, there is a need for an indirect fire munition that provides today&#39;s warfighter the capability to return fire under restrictive rules of engagement (ROE) while minimizing civilian casualties and limiting collateral damage. 
     SUMMARY OF INVENTION 
     The present invention relates to an indirect fire munition non-lethal cargo carrier mortar for deploying non-lethal sub-munitions. The cargo carrier mortar includes a deceleration system which allows for the discarded mortar to descend at a controlled non-free fall velocity thereby minimizing the risk of injury or collateral damage from the mortar. The cargo carrier mortar is adapted to be compatible with existing standard military equipment such as standard mortar caliber sizes. 
     According to a first aspect of the invention, a non-lethal cargo carrier mortar is configured for delivering a non-lethal payload and descending at a non-free fall velocity. The non-lethal cargo carrier mortar includes a first parachute assembly, a second parachute assembly and a recess. The first parachute assembly further comprises a first tether coupling a first parachute to a front portion of the non-lethal cargo carrier mortar. The second parachute assembly comprises a second tether coupling a second parachute to a rear portion of the non-lethal cargo carrier mortar. The recess is formed within the front portion of the non-lethal cargo carrier mortar and is configured for supporting the first tether on an outer surface and further configured for shielding the tether from gases ejected from a supplemental charge ignited by a fuze. 
     According to a second aspect of the invention, an 81 millimeter caliber non-lethal cargo carrier mortar configured for dispersing a non-lethal payload and descending at a non-free fall velocity, the non-lethal cargo carrier mortar includes an M776 fuze, a fuze adapter, a body, a tail cone, a fin, a first parachute assembly, a second parachute assembly and a drogue parachute assembly. The M776 fuze is configured for detonating a supplemental charge at a predetermined time. The fuze adapter is configured for supporting the M776 fuze and further includes a recess formed within an outer surface of the fuze adapter. The recess is configured for supporting a first tether coiled on an outer surface of the recess and for shielding the first tether by channeling propulsive gases released from the supplemental charge through an inner surface of the recess. The body comprises a payload area formed in a cavity of the body and one or more shear pins configured for shearing in response to pressure from the propulsive gases. The first parachute assembly comprises the first tether coupling a first parachute disposed in the payload area of the body to the fuze adapter. The second parachute assembly comprises a second tether coupling a second parachute disposed in the payload area of the body to the tail cone. A drogue parachute assembly comprises a drogue parachute and a parachute bag configured for housing the first parachute and second parachute until deployment. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
       The accompanying figures further illustrate the present invention. 
       The components in the drawings are not necessarily drawn to scale, emphasis instead being placed upon clearly illustrating the principles of the present invention. In the drawings, like reference numerals designate corresponding parts throughout the several views. 
         FIG. 1  is a diagram illustrating the components of a non-lethal cargo carrier mortar, in accordance with an illustrative embodiment of the invention. 
         FIG. 2  illustrates the various stages in the firing of a non-lethal cargo carrier mortar, in accordance with an illustrative embodiment of the invention. 
         FIG. 3  is an exploded diagram illustrating the components of a non-lethal cargo carrier mortar, in accordance with an illustrative embodiment of the invention. 
         FIG. 4  is a diagram illustrating a non-lethal cargo carrier mortar at separation, in accordance with an illustrative embodiment of the present invention. 
         FIG. 5  is a diagram illustrating a non-lethal cargo carrier mortar at deployment, in accordance with an illustrative embodiment of the present invention. 
         FIG. 6  is a diagram illustrating a non-lethal cargo carrier mortar at descent, in accordance with an illustrative embodiment of the present invention. 
         FIG. 7  is an exploded diagram illustrating the components of a non-lethal cargo carrier mortar, in accordance with an illustrative embodiment of the invention. 
     
    
    
     DETAILED DESCRIPTION 
     The present invention relates to an indirect fire munition non-lethal cargo carrier mortar for deploying non-lethal sub-munitions. The cargo carrier mortar minimizes risk of injury or collateral damage while allowing for the suppression of targets and the ability to return fire when the use of high explosive (HE) or lethal force is not authorized. The cargo carrier mortar comprises a payload area  13  for housing non-lethal sub-munitions and is configured for dispersing the non-lethal sub-munitions over an area. To further reduce the risk of injury or damage, the cargo carrier mortar further comprises a deceleration system for returning the cargo carrier mortar to the ground at a reduced velocity. Advantageously, the cargo carrier mortar minimizes the weight and size of deceleration system, thereby maximizing the payload. Further, the cargo carrier mortar meets current military specifications and may be used with existing weapon propulsion systems. 
       FIG. 1  is a diagram illustrating a non-lethal cargo carrier mortar, in accordance with an illustrative embodiment of the invention. The non-lethal cargo carrier mortar comprises a fuze  1 , a fuze adapter  2 , a body  3 , a tail cone  4 , a fin assembly  5 , retaining pins  6 , shear pins  7 , an obturator ring  8 , and fuze adapter pins  10 . The cargo carrier mortar may also comprise one or more propelling charges  9  secured around the fin assembly  5 . 
       FIG. 2  illustrates the various stages in the firing of a non-lethal cargo carrier mortar, in accordance with an illustrative embodiment of the invention. The non-lethal cargo carrier mortar is fired from an indirect firing system such as an M252 81 millimeter (mm) caliber mortar system. A primer disposed in the fin assembly  5  of the cargo carrier mortar is ignited by a firing pin in the canon tube of the mortar system. The primer subsequently ignites an ignition cartridge, also disposed in the fin assembly  5  of the cargo carrier mortar, which provides a propulsive force to the cargo carrier mortar. One or more propulsive charges secured around the fin assembly  5  of the cargo carrier mortar may be ignited by the ignition charge through holes in the fin assembly  5  to provide additional propulsive force for reaching further zones of fire. 
     At a predetermined time after propulsion, as determined by ballistic calculations to ensure a desired range and height, the fuze  1  of the cargo carrier mortar detonates a supplemental charge in a fuze adapter. For example, the fuze  1  may be set to detonate a supplemental charge at a height of 175 meters. The supplemental charge pressurizes the internal cavity of the non-lethal cargo carrier mortar and causes the internal contents of the cargo carrier mortar to be pushed toward the tail cone  4 . When the force on the tail cone  4  reaches a certain threshold, the shear pins  7  fail thereby allowing the tail cone  4  to separate from the body  3 . As this happens, split sleeves and a rear plate fall away and the non-lethal payload and deceleration system begin exiting through the opening of the body  3 . 
     As the internal contents of the cargo carrier mortar exit from the force of the supplemental charge, the non-lethal sub-munitions are deployed and the deceleration system is engaged. The deceleration system slows the descent of a forward portion of the cargo carrier mortar and a rear portion of the cargo carrier mortar to a reduced speed from free fall velocity. 
       FIG. 3  is an exploded diagram illustrating the components of a non-lethal cargo carrier mortar, in accordance with an illustrative embodiment of the invention. The fuze  1  is disposed in the front of the cargo carrier mortar and is configured for igniting a supplemental charge  11  at a predetermined time in the flight of the cargo carrier mortar. The fuze  1  may be a mechanical time super quick (MTSQ) M776 fuze currently employed by the United States Army. The fuze  1  is configured for igniting the supplemental charge  11  at a predetermined time or altitude in the mortar&#39;s flight based on ballistic equations to achieve a payload distance. 
     The fuze  1  and supplemental charge  11  are set in a fuze adapter  2 . In addition to supporting the fuze  1  and supplemental charge  11 , the fuze adapter  2  is configured for funneling the propulsive gases of the supplemental charge  11  toward the rear of the cargo carrier mortar and supporting a first tether  14  of a first parachute assembly, as will be described in further detail below. The fuze adapter  2  is connected to the body  3  of the cargo carrier mortar. 
     The body  3  of the cargo carrier mortar forms an inner cavity housing a first plate  12 , a second plate  12 , a payload area  13 , a first split sleeve  15  and a second split sleeve  15 . The first plate  12  is configured for receiving the pressure built up from the fuze and supplemental charge and transferring it to the sub-munitions. The second plate  12  sits under the sub-munitions and receives the force from the front plate  12  and transfers the force to the front split sleeve  15  and second split sleeve  15 . The front split sleeve  15  and the second split sleeve  15  surround the parachute assembly and transfer the force from the first plate  12  and second plate  12  to the tail cone thereby causing the shear pins to fail and the mortar carrier to separate. 
     One or more non-lethal sub-munitions are housed in the payload area  13 . Advantageously, the payload area  13  provides an increased volume and payload potential due to the deceleration design reducing both the weight and volume of the deceleration system. In an embodiment of the invention, the payload area  13  houses fourteen (14) flash bang sub-munitions. While throughout this specification, the payload is described as one or more flash bang sub-munitions, the cargo carrier mortar is not limited to housing flash bang sub-munitions. The payload area  13  may house any non-lethal cargo including cargo that can be ignited by the flash from a fuze. For example, the payload area may contain stink bombs, marking dye and whistles. 
     The first split sleeve  15  and second split sleeve  15  are configured for protecting the parachute while also transferring force directly to the tail cone. 
     The first parachute assembly, second parachute assembly and drogue parachute assembly comprising a parachute bag comprise the deceleration system of the cargo carrier mortar. The front parachute assembly is configured for slowing the descent of the front portion of the cargo carrier mortar to a velocity lower than free fall velocity. The second parachute assembly is configured for slowing the descent of the rear portion of the cargo carrier mortar to a velocity lower than free fall velocity. The parachute bag houses a first parachute  21  of the first parachute assembly and a second parachute  22  of the second parachute assembly prior to deployment. 
     The first parachute assembly comprises a first parachute  21  connected to the front portion of the cargo carrier mortar via a first swivel  17  and a first tether  14 . In an embodiment of the invention, the first parachute  21  is a parachute of a size and dimension typically used for an 81 mm illumination mortar, such as an M853A1 81 mm illumination round currently in use by branches of the United States military. The first parachute  21  is connected to the first swivel  17  which is connected to the first tether  14 . The first tether  14  attaches to the fuze adapter  2  via a first fuze adapter pin  10 . In an embodiment of the invention, the fuze adapter further comprises a steel alloy pin extending from a surface of the fuze adapter and the first tether is looped around the steel alloy pin. 
     Prior to deployment, the first tether  14  is wrapped around a recessed surface of the fuze adapter  2 . The recess surface shields the tether from propulsive gases travelling from the fuze  1  of the cargo carrier mortar toward the body  3  of the cargo carrier mortar. Further, coiling the tether within the recess surface of the fuze adapter prevents tangling of the tether and non-deployment of the first parachute  21 . 
     The second parachute assembly comprises a second parachute  22  connected to the rear portion of the cargo carrier mortar via a second swivel  17  and a second tether  18 . The second parachute  22  is connected to the second swivel  17  which is connected to the second tether  18 . In an embodiment of the invention, the second parachute  22  is a parachute of a size and dimension typically used for a sixty mm illumination mortar. The second parachute  22  is connected to the second swivel  17  which is connected to the second tether  18 . The second tether  18  attaches to the fin via an eyebolt threaded to the fin. 
     To ensure the proper strength of the tethers, the first tether and the second tether may be formed from a material comprising Kevlar fibers, Technora fibers or steel. In an embodiment of the invention, the first tether and the second tether are wrapped in a low friction tape configured for preventing abrasion 
     The cargo carrier mortar further comprises a drogue parachute  20  and a parachute bag  16 . The parachute bag  16  holds both the first parachute  21  of the first parachute assembly and the second parachute  22  of the second parachute assembly prior to deployment. The parachute bag  16  is tethered to the drogue parachute  20 . 
       FIG. 4  is a diagram illustrating a non-lethal cargo carrier mortar at separation, in accordance with an illustrative embodiment of the present invention. At fuze detonation, the fuze  1  detonates a supplemental charge  11  causing the front of the round to pressurize. If required, the supplemental charge  11  may also ignite the payload. The pressure from the supplemental charge  11  provides a force on the contents within the body  3  toward the rear of the cargo carrier mortar. Once enough force is applied to the tail cone  4 , the shear pins  7  fail which allows the rear portion of the cargo carrier mortar, specifically the tail, to separate from the front portion of the cargo carrier mortar, specifically, the body  3 . As the tail is separating from the body  3 , the split sleeves  15  and rear plate  12  fall away. The remaining contents disposed in the body  3 , exit through the rear opening of the body  3 . 
       FIG. 5  is a diagram illustrating a non-lethal cargo carrier mortar at deployment, in accordance with an illustrative embodiment of the present invention. As the contents of the cargo carrier mortar exit from the force of the supplemental charge  11 , the drogue parachute assembly, including the first parachute  21  and the second parachute  22 , are pulled out from the tail cone  4  as the tension increases on the first tether  14  and second tether  18 . Once the drogue parachute  20  is in the wind stream, it opens and begins to pull the parachute bag  16  away from the first parachute  21  and the second parachute  22 . The plates  12 , split sleeves  15  and payload descend without a decelerator. 
       FIG. 6  is a diagram illustrating a non-lethal cargo carrier mortar at descent, in accordance with an illustrative embodiment of the present invention. After the parachute bag  16  is pulled away, the first parachute  21  and the second parachute  22  inflate and decelerate the front portion and rear portion of the cargo carrier mortar, respectively. The front portion and the rear portion descend at a predetermined velocity. The payload is delivered to the intended area. 
       FIG. 7  is an exploded diagram illustrating the components of a non-lethal cargo carrier mortar, in accordance with an illustrative embodiment of the invention. In an embodiment of the invention, the non-lethal cargo carrier mortar may be from an indirect firing system of a smaller caliber, such as an M224 or M224A1 60 caliber mortar system. In such a caliber indirect mortar system, the smaller size and lighter weight of the cargo carrier mortar allows for the drogue parachute  20  to operate as the second parachute system in the deceleration system. 
     In this embodiment, the fuze  1 , fuze adapter  2 , body  3 , tail and fin function similar to the previous embodiment. The fuze  1  is disposed in the front of the cargo carrier mortar and is configured for igniting a supplemental charge  11  at a predetermined time in the flight of the cargo carrier mortar. The fuze  1  may be a MTSQ M776 fuze currently employed by the United States Army. The fuze  1  is configured for igniting the supplemental charge  11  at a predetermined time or altitude in the mortar&#39;s flight based on ballistic equations to achieve a payload distance. 
     The fuze  1  and supplemental charge  11  are set in a fuze adapter  2 . In addition to supporting the fuze  1  and supplemental charge  11 , the fuze adapter  2  is configured for funneling the propulsive gases of the supplemental charge  11  toward the rear of the cargo carrier mortar and supporting a second tether  18  of a second parachute assembly, as will be described in further detail below. The fuze adapter  2  is connected to the body  3  of the cargo carrier mortar. 
     The body  3  of the cargo carrier mortar forms an inner cavity housing a first plate  12 , a second plate  12 , a payload area  13 , a first parachute assembly, a second parachute assembly, a drogue parachute assembly, a first split sleeve  15  and a second split sleeve  15 . The first plate  12  is configured for receiving the pressure built up from the fuze and supplemental charge and transferring it to the sub-munitions. The second plate  12  sits under the sub-munitions and receives the force from the front plate  12  and transfers the force to the front split sleeve  15  and second split sleeve  15 . The front split sleeve  15  and the second split sleeve  15  surround the parachute assembly and transfer the force from the first plate  12  and second plate  12  to the tail cone thereby causing the shear pins to fail and the mortar carrier to separate. 
     One or more non-lethal sub-munitions are housed in the payload area  13 . Advantageously, the payload area  13  provides an increased volume and payload potential due to the deceleration design reducing both the weight and volume of the deceleration system. In an embodiment of the invention, the payload area  13  houses fourteen (14) flash bang sub-munitions. While throughout this specification, the payload is described as one or more flash bang sub-munitions, the cargo carrier mortar is not limited to housing flash bang sub-munitions. In another embodiment, the payload area  13  may house. 
     The first split sleeve  15  and second split sleeve  15  are configured for protecting the parachute while also transferring force directly to the tail cone. 
     The first parachute assembly comprises a first parachute  21  connected to the front portion of the cargo carrier mortar via a first swivel and a first tether. The first parachute  21  is a parachute typically used in 60 mm Illumination mortar. The first parachute  21  is connected to the first swivel which is connected to the first tether  14 . The first tether  14  attaches to the fuze adapter via a first fuze adapter pin  10 . Prior to deployment, the first tether  14  is wrapped around the recessed surface of the fuze adapter  2 . This recess surface shields the tether  14  from propulsive gases travelling from the fuze  1  of the cargo carrier mortar toward the body  3  of the cargo carrier mortar  1 . Further, coiling the tether  14  within the recess of the fuze adapter  2  prevents tangling of the tether  14  and non-deployment of the first parachute  21 . 
     The drogue parachute assembly comprises a drogue parachute  22  connected to the parachute bag. The parachute bag  15  is connected to the rear portion of the cargo carrier mortar via a swiveling eyebolt  17  and a second tether  18 . The swiveling eyebolt  17  is connected to the fin assembly  5  of the cargo carrier mortar. The parachute bag  15  is then connected to the swiveling eyebolt  17  via a tether  18 . In an embodiment of the invention, the drogue parachute  21  is a parachute of a size and dimension larger than those typically used for other sixty millimeter mortar rounds. 
     At fuze detonation, the fuze  1  detonates a supplemental charge  11  causing the front of the round to pressurize. If required, the supplemental charge  11  may also ignite the payload. The pressure from the supplemental charge  11  provides a force on the contents within the body  3  toward the rear of the cargo carrier mortar. Once enough force is applied to the tail cone  4 , the shear pins  7  fail which allows the rear portion of the cargo carrier mortar, specifically the tail, to separate from the front portion of the cargo carrier mortar, specifically, the body  3 . As the tail is separating from the body  3 , the split sleeves  15  and rear plate  12  fall away. The remaining contents disposed in the body  3 , exit through the rear opening of the body  3 . 
     As the contents of the cargo carrier mortar exit from the force of the supplemental charge  11 , the drogue parachute assembly, including the first parachute  22 , are pulled out from the tail cone  4  as the tension increases on the first tether  14  and second tether  18 . Once the drogue parachute  20  is in the wind stream, it opens and begins to pull the parachute bag  16  away from the first parachute  22 . The plates  12 , split sleeves  15  and payload descend without a decelerator. 
     After the parachute bag  16  is pulled away, the first parachute  22  inflates and decelerates the rear portion of the cargo carrier mortar. The drogue parachute decelerates the front portion of the cargo carrier mortar. The front portion and the rear portion descend at a predetermined velocity. The payload is delivered to the intended area.