Abstract:
In one aspect, a modular air sampling system includes a sensor module defining a nose, the sensor module including a sensor for sampling contaminants in the atmosphere. A processing and sending module includes processing electronics in communication with the sensor for receiving a signal from the sensor representative of sampled contaminants in the atmosphere. The processing and sending module further includes a radio frequency transmitter operably coupled to the processing electronics for transmitting a radio frequency signal representative of one or more contaminants sensed by the sensor. In another aspect, a modular air sampling system includes a sensor module containing the sensor, processing electronics, and radio frequency transmitter within the sensor module housing.

Description:
CROSS REFERENCE TO RELATED APPLICATION 
       [0001]    This application claims priority to U.S. provisional application No. 62/022,487 filed Jul. 9, 2014, which is incorporated herein by reference in its entirety. 
     
    
     INCORPORATION BY REFERENCE 
       [0002]    This application is also related to U.S. Provisional Application No. 61/638,368 filed Apr. 25, 2012, and U.S. Nonprovisional application Ser. No. 13/870,340 filed Apr. 25, 2013. Each of the aforementioned applications is incorporated herein by reference in its entirety. 
       BACKGROUND 
       [0003]    The present disclosure relates generally to a projectile system and method for detecting gaseous materials present in the atmosphere at a remote location. The present system and method find particular utility in sensing chemical and/or biological threats in atmospheric air at specific distances or locations for tactical or military defense purposes. It will be recognized, however, that the present development may also be used to identify and provide distance and location information for chemical or biological hazards in connection with natural disasters, industrial spills, leaks, or accidents, and so forth. One advantage of the present system resides in its ability to identify potential chemical or biological hazards from a remote location, thus allowing the user to best plan for use of protective equipment that the user may have at his or her disposal, such as respirator masks, self-contained breathing apparatuses, protective clothing, etc. In preferred embodiments, the environmental hazard sensing projectile system herein can be adapted for firing from preexisting launch platforms, thus reducing costs and facilitating deployment. 
       SUMMARY 
       [0004]    In one aspect, a modular projectile system comprises a chemical and/or biological sensing module defining a nose of the projectile. A flight control module is removably attachable to the sensor module and includes a plurality of airfoils, the airfoils being moveable between a refracted state and an extended state. A processing module is removably attached to the flight control module for receiving the sensor data from the sensor module and transmitting sensed chemical or biological hazard information cross-referenced with flight time and/or geolocation information to a radio receiver or communication network associated with the user. A rocket module is attached to the processing module and includes a rocket motor configured to propel the modular projectile system. A cartridge module is provided, which includes a charge of explosive material to propel the projectile system out of a launch tube or barrel of the launch platform. 
         [0005]    In another aspect, a modular projectile system comprises a unitary or combined chemical and/or biological sensing and processing module which is configured to be attached to a cartridge module with or without a rocket motor. 
     
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         [0006]    The invention may take form in various components and arrangements of components, and in various steps and arrangements of steps. The drawings are only for purposes of illustrating preferred embodiments and are not to be construed as limiting the invention. 
           [0007]      FIG. 1  is an isometric view of a modular projectile system in accordance with a first exemplary embodiment of the present disclosure, wherein the wings appear in the folded position. 
           [0008]      FIG. 2  is an isometric exploded view of the modular projectile system appearing in  FIG. 1 . 
           [0009]      FIG. 3  is an exploded side elevational view of the modular projectile system appearing in  FIG. 1 . 
           [0010]      FIG. 4  is a side elevational view of the modular projectile system appearing in  FIG. 1 , wherein the housing of the sensor module is removed, illustrating the dual air duct design of the preferred embodiment. 
           [0011]      FIG. 5  is a block diagram of the embodiment appearing in  FIG. 1 . 
           [0012]      FIG. 6  is an isometric view of a modular projectile system in accordance with a second exemplary embodiment. 
           [0013]      FIG. 7  is an exploded side elevational view of the modular projectile system appearing in  FIG. 6 . 
           [0014]      FIG. 8  is a block diagram of the embodiment appearing in  FIG. 6 . 
           [0015]      FIG. 9  illustrates the projectile system of  FIG. 6  with a launch platform. 
       
    
    
     DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS 
       [0016]    Referring now to  FIGS. 1-5 , there is shown an exemplary modular air sampling system  100 , which includes a sensor module A, a flight control module B, a processing and sending module C, a motor or rocket booster module D, and a cartridge shell E. 
         [0017]    The sensor module A includes a generally rounded, conical or otherwise tapered outer shell construction  10  shaped to minimize aerodynamic resistance and defining a nose cone of the rocket system  100 . The sensor module A includes an interior cavity or compartment  11  housing one or more chemical or biological sensors  12 . Such sensors include electrochemical sensors, metal oxide semiconductor sensors, spectroscopic gas sensors, and so forth. The one or more sensors  12  may include an array of sensors configured to detect a broad range of biological and/or chemical contaminants. Alternatively, the sensor(s)  12  could be configured to sense a one or a limited number of biological and/or chemical contaminants. For example, a system could be provided with a plurality of different sensor modules A each having different sensing capabilities, wherein the sensor module A can be selected for a particular application based on a biological or chemical contaminant that is expected in a given area or situation. 
         [0018]    The sensor module A includes a pair of air intake ducts  14 . The ducts  14  are disposed on opposite sides of the module A. Each duct  14  includes an adjacent air flow directing surface  16 . The air flow directing surfaces  16  may have an airfoil-like shape and are configured to direct a flow of air through the ducts  14  and into the interior compartment of the sensor module A where it impinges on the one or more sensors  12 . The air flow directing surfaces  16  may configured as a so-called submerged inlet, NACA duct or NACA scoop, or other low drag air inlet configured to allow air to flow into the ducts  14  where it contacts the one or more sensors  12 . 
         [0019]    The module A includes a rear connector  19  which is complementary with and removably attachable to a forward facing connector  21  on the flight control module B. The rear connector  19  and the forward connector  21  may include complementary and aligned facing surfaces. In the illustrated embodiment, the rear connector  19  includes keyed projections  23  which are received in complementary openings, channels or grooves (see  FIG. 3 ) to allow the units A, B to be inserted and then twisted into the locked position. Other bayonet or keyed connections are contemplated. In certain embodiments, markings or indicia may be provided on adjacent modules to show proper alignment as described in the aforementioned commonly owned U.S. application Ser. No. 13/870,340. 
         [0020]    In certain embodiments, an electrical interface is provided within the forward and rear connectors  19 ,  21  to provide a conductive pathway for sending an electrical signal to a processing unit  27  in the processing and sending module C when the modules A, B, and C are connected properly. The electrical connections between adjacent attached members may also be provided to ensure that a given rocket construction prepared using the present modular components comprises a proper configuration of modules. In a preferred embodiment, the electrical connections between the adjacent modules serve as an interlock mechanism preventing the system  14  from booting up unless the attached components are properly attached and in a proper configuration. Alternatively, or in addition, the keyed projections  23  and receptacles  25  on the connecting ends of each module may be keyed with distinct geometry to inhibit the improper attachment or combination of modules. 
         [0021]    The flight control module B includes a generally cylindrical outer shell housing  34  receiving a plurality of airfoils or wings  36  circumferentially spaced about the flight control module B. The wings  36  can be folded into receptacles  38  in the body of the flight control module B to allow the assembled system  100  to fit into a launch platform, which is discussed below, prior to launch of the unit  100 . As seen in  FIG. 1 , when the wings  36  are in the folded state, the wings  36  are received in the openings  38  in the body of the module B. 
         [0022]    The flight control module B may also include a positioning system  18 , which may be an absolute or relative positioning system. Exemplary positioning systems include, for example, a navigational system, such as Global Positioning System (GPS) based systems, Global Navigation Satellite System (GLONASS) based systems, etc., inertial systems, etc. In alternative embodiments, the positioning system  18  may employ a clock to record time of flight. In this manner, the relative position of the unit  100 , e.g., the distance from the user at a given time, can be calculated based on time of flight and known trajectory or ballistic characteristics of the unit  100 . In still further embodiments, the positioning system  18  may include an accelerometer provided to count the number of axial rotations of the unit  100  during flight, wherein the distance of the unit  100  from the user at a given time can be calculated based on the number of rotations and known trajectory or ballistic characteristics of the unit  100 . In certain embodiments, the flight control module B also includes a guidance control computer or processor  20  for guiding the rocket system along a programmed fight path. 
         [0023]    In certain embodiments, the flight control module B includes a flight control processor  20  and an associated electronic memory operably coupled thereto for storage and execution of flight control instructions or algorithms. 
         [0024]    After firing, the wings  36  can be moved to their extended position, as shown in the broken lines appearing in  FIG. 1 . Each of the wings  36  is independently controllable and may be rotated or tilted as ailerons to provide maneuverability/steering control as well as stability of the sensing system during flight. The wings  36  are small enough to fit within the housing shell  34  to allow the system  100  to fit within the constraints of the launching platform while providing the ability to allow the system  100  to perform banking and turning maneuvers during flight and, in preferred embodiments, are large enough to steer the rocket system  100  around obstacles during flight. Additionally or alternatively, the system  100  may be maneuvered by a conventional thrust vector control system, e.g., of the type using a gimbaled booster nozzle to steer the weapon. The wings  36  may be actuated and controlled via springs, hydraulics, pneumatics, motors, and so forth. 
         [0025]    The processing/sending module C houses the processing unit  29  and a radio frequency (RF) transmitter or transceiver  45  and includes an outer shell  44 , a front connector  46  for removable attachment to a rear connector  48  of the flight control module B, and a rear connector  50  for connection to a front connector  52  of the booster module D. The manner of connection may be generally as detailed above, and the connectors may in include the projections  23  and complementary receivers  25  as detailed above, although the geometry of the connection may be different to avoid attaching the modules improperly, e.g., in terms of sequence or compatibility. 
         [0026]    Electrical connections are provided between the attached modules A, B, and C for transmission of data to the RF transmitter/transceiver  45 . The processor  20  receives raw sensor data from the sensor  12 , which can be correlated with positional data from the positioning system  18  (or alternatively time of flight or spin count data) to identify the presence (and optionally concentration) of an identified airborne hazard and to provide a signal representative of the same correlated to position and/or distance from the user. The position- and/or distance-correlated contaminant data is transmitted via the transmitter  45  to an RF receiver associated with the user. In certain embodiments, the RF receiver may be a radio frequency receiver contained within a life support unit. The received data may be output to a human viewable display. Information concerning the identity and position/distance of airborne hazards allows the user to best use the breathing devices at his or her disposal. 
         [0027]    The housing shells, wings, vanes, etc., of the present system may be formed of a metal or metal alloy material or a composite material comprising a fiber reinforced polymer material as are known in the aerospace industry. 
         [0028]    The rocket booster module D includes an outer shell housing  58  defining a rocket motor configured with a rocket-based propulsion system  60  as would be generally known in the art. The rocket motor  60  may be powered by any suitable rocket fuel in any suitable form, including solid, liquid, gel, or any combination thereof. In certain embodiments, a plurality of retractable air vanes or fins  62  are folded into receptacles  64  in the housing shell  58  and are extended for stability during flight. In certain embodiments or configurations, the rocket module D may be provided with fixed vanes or fins. 
         [0029]    In certain embodiments, the rocket system  100  may be configured to be fired from a standard or conventional launch platform, such as a grenade launcher  250  (see  FIG. 9 ), e.g., a single shot 40 mm grenade launcher. The rearward end  66  of the motor module D is received within a 40 mm shell casing or cartridge E, which includes a charge of explosive material to propel the rocket system  100  out of the launch tube of the launch platform. In certain embodiments, the charge may be relatively small, since for rocket boosted configurations it is only necessary to launch the rocket system  100  a sufficient distance away from the operator to safely fire the rocket motor D. In alternative embodiments, the rocket motor may be omitted and a larger charge of explosive material in the cartridge E may be used. 
         [0030]    In preferred embodiments, the launch platform is an M320 grenade launcher module, although it will be recognized that the present system may be adapted for use with other calibers and/or launch platforms, including shoulder fired, stationary, etc. 
         [0031]      FIGS. 6-8  illustrate an alternative embodiment sensing projectile system  200  wherein the sensor module  10  of the sensor module A as described above, and the position and/or timing module  18  of the flight control module B as described above, and the processor  27  and RF transmitter  45  of the processing/sending unit C as described above are combined into a single module F, wherein the above described hardware modules are within a single housing  70 . The module F is attached to shell cartridge or casing G, such as a 40 mm cartridge casing or shell. The casing G differs from that casing E described above by way of the system  100  in that the casing F is configured to contain a larger explosive charge, in that the charge needs to be sufficient to launch the sensing projectile system  200  to the desired remote location where air sampling is desired to occur. 
         [0032]    Referring now to  FIG. 9 , there is shown a grenade launcher  250 . The sensing systems  100 ,  200  herein are advantageous in that they can be adapted for use with an existing launch platform, such as grenade launcher  250 . Advantageously, the grenade launcher  250  is based on the M320 platform and preferably the Heckler &amp; Koch HK M320. However, it is also contemplated that the modular air sampling system of this disclosure could be adapted for use with other standard launch platforms or with a custom or dedicated launch platform. In certain embodiments having retractable wings, such as the steering wings  36  or the stabilizing wings  62 , a safety interlock may be provided for preventing movement of said wings to the extended state when the modular air sampling system is received in a launch platform. 
         [0033]    The invention has been described with reference to the preferred embodiments. Obviously, modifications and alterations will occur to others upon reading and understanding the preceding detailed description. It is intended that the invention be construed as including all such modifications and alterations.