The present disclosure relates generally to a projectile system and method for intercepting a drone or other flying object in flight and safely returning it to the ground.
The present system and method find particular utility in the safe capture of unmanned drones, such as quadcopters or the like, which are capable of carrying hazardous cargos such as biological (e.g., anthrax), chemical, or nuclear materials or weapons. One advantage of the present system resides in its use of a web or net to capture the object in flight and a parachute to slow the descent of the captured drone to minimize the risk that a potentially hazardous payload may break or open on impact.
In one aspect, a modular rocket system comprises a guidance module defining a nose, the guidance module including a guidance system for guiding the modular rocket system toward a target. A flight control module is removably attachable to the guidance module and includes a plurality of airfoils, the airfoils being moveable between a retracted state and an extended state. A net module is removably attached to the flight control module and includes a net and a net deployment mechanism. A rocket module is attached to the net module and includes a rocket motor configured to propel the modular rocket system.
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.
Referring now to
The nose module A includes a generally tapered outer shell construction 12 shaped to minimize aerodynamic resistance. The sensor module A includes an interior cavity or compartment 14 housing a laser ranging and guidance module 16, including a laser guidance module 18. The laser ranging and guidance module 16 also includes a range finder or optical switch comprising a laser emitter 22 and an optical sensor or receiver 24. The laser 22 sends a beam toward a target object 20 such as a drone, and reflections of the beam from the target object are detected by the optical receiver 24. The distance to the target is calculated based on the time-of-flight of the laser beam. In certain embodiments, the laser 22 emits a laser beam in a very short series of pulses, which may be encoded to assist the detector in recognizing the reflected signal.
The nose module A further includes associated processing electronics and a fuse line or actuator 26 for detonating a net discharge mechanism in the net module C when the range finder module 16 detects that the rocket 10 is within some predetermined distance from the target object 20. The predetermined distance is selected depending on the size of the target object and the size of the net to be deployed. In certain embodiments, the predetermined distance is about 5 to 30 meters, preferably about 15 meters, although other distances are contemplated.
In operation, when the rangefinder 16 determines that the rocket system 10 is within the predetermined distance from the target object, the processing electronics actuate a net firing mechanism 28 within the net module C. In certain embodiments, the net 30 is propelled from the net module C using a ballistic deployment charge, such as gunpowder or other explosive charge. In certain embodiments, the charge is shaped to cause the net to spread out when deployed. Alternatively, the net is propelled from the net module C using a compressed gas, such as a CO2 canister or the like. In still further embodiments, the net is propelled from the net module using a compressed spring mechanism. In such cases, the deploying force is preferably shaped or configured to cause the net to spread out upon deployment.
In certain embodiments, the laser guidance module 18 is provided and is configured to follow a laser designator or laser marker beam 48, e.g., a pulse encoded beam, by sensing or imaging the beam 48. In certain embodiments, the laser designator beam 48 is a near infrared beam having a wavelength of 1064 nanometer. In operation, the target object is “painted” with a targeting beam 48, e.g., a 1064 nanometer wavelength laser beam, by the operator using a laser pointer device 46. In certain embodiments, the system is used in conjunction with a weapon mounted laser pointer accessory device for generating the marker beam 48, which may be a part of a laser sight, laser range finder, weapon fire control system, or the like. In certain embodiments, the laser pointer 46 may include a ballistics computer to assist the operator in firing the missile 10 toward the target object.
The laser guidance module 18 causes the missile 10 to follow the target object 20 until the optical trigger 16 senses that the missile 10 is within the predetermined range and ignites the charge or otherwise actuates the deployment mechanism 28 to deploy the net 30. The flight control module B includes a generally cylindrical outer shell receiving a plurality of airfoils or wings 32 circumferentially spaced about the flight control module B. The wings 32 can be folded into receptacles in the body of the flight control module B to allow the assembled system 10 to fit into a missile launch system 34. In certain embodiments, the missile diameter is 40 mm and is configured to be fired from existing 40 mm launch platforms, although in certain embodiments other sizes and/or custom or dedicated firing platforms are also contemplated. The flight control module B contains processing electronics 42, such as a computer processor, microprocessor, microcontroller, etc., to steer the missile 10 toward the center of the designator beam 48 marking the target object.
In certain embodiments, the flight control module B includes a flight control processor and an associated electronic memory operably coupled thereto for storage and execution of flight control instructions or algorithms, responsive to signals or instructions from the laser guidance system.
As illustrated in
The rocket booster module D includes an outer shell housing defining a rocket motor configured with a rocket-based propulsion system as would be generally known in the art. The rocket motor 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 (e.g., spring biased) are folded into receptacles in the rocket booster module housing and are extended for stability during flight. In certain embodiments or configurations, the rocket module D may be provided with fixed vanes or fins 44. As illustrated in
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.
In certain embodiments, the net 30 is formed of a web-like structure formed of strong fine threads or fibers. In certain embodiments, the web is formed of polymeric fibers, such as aramid (e.g., KEVLAR(™)) fibers or the like. In certain embodiments, the net is formed of materials commonly used for “mist nets” of the type used for catching birds in flight, such as a nylon or polyester mesh material.
In certain embodiments, the net is about 5 to 20 feet (1.5 to 6 meters) in diameter. In preferred embodiments, the diameter of the net is about 10 feet (3 meters). In certain embodiments, the net has a two-dimensional web structure. In certain embodiments, the net has a three-dimensional web structure. In the illustrated embodiment, a plurality of weights or masses 36, which may be formed, e.g., of tungsten, steel, lead, and so forth, are fixed at points spaced equally around the outer perimeter of the net. Preferably, the net is packed and the charge or other deploying force is shaped such that the weights spread out uniformly after the net is discharged from the net module housing to increase the odds of catching the target object. The kinetic energy of the weights also assists in causing the net to wrap around the target object when the net collides with the target object.
As illustrated in
In certain embodiments, the parachute includes a beacon device 40 to allow the operator to locate the target object 20 after it has fallen. Upon deployment of the parachute, the beacon device 40 sends out a signal to assist an operator in locating the device. In certain embodiments, the beacon device 40 is an optical beacon to provide a visual indication of the target object's 20 location. In certain embodiments, the optical beacon emits a human viewable signal. In certain embodiments, the optical beacon may emit an optical signal that is detectable with visible or infrared sensing equipment.
In certain embodiments, the beacon device 40 is an electronic, i.e., radio frequency (RF) beacon. In certain embodiments, the beacon device 40 includes a radio transmitter broadcasting a radio signal that can be detected by a directional antenna. In certain embodiments, the RF beacon includes an RF transponder that communicates with a seeking transponder system for locating the beacon device. In an exemplary embodiment, the beacon device 40, upon deployment of the parachutes 38, sends out an identification signal. The seeking transponder then responds by querying the beacon device, e.g., as to direction, location, distance or the like. The beacon device 40 then responds to this query with the requested information.
In certain embodiments, The rear portion of the module A is removably connected to the front portion of the flight control module B via complimentary fasteners; the rear portion of the flight control module B is removably connected to the front portion of the net module C via complimentary fasteners; and the rear portion of the net module C is removably connected to the front portion of the motor module D via complimentary fasteners. In certain embodiments, the complimentary fasteners include cam lock mechanisms. Alternatively, the fasteners connecting the module A to B, B to C, and C to D include bayonet type connectors. In certain embodiments, the fasteners connecting the module A to B, B to C, and C to D include a combination of cam lock type connectors and bayonet type connectors. Electrical connectors and conductive pathways may be provided on the module housing sections to allow for power, signals and data to be transmitted between the electronics within the flight control module B and the range finding module A.
All numbers herein are assumed to be modified by the term “about,” unless stated otherwise. The recitation of numerical ranges by endpoints includes all numbers subsumed within that range (e.g., 1 to 5 includes 1, 1.5, 2, 2.75, 3, 3.80, 4, and 5).
The invention has been described with reference to the preferred embodiment. Modifications and alterations will occur to others upon a reading and understanding of the preceding detailed description. It is intended that the invention be construed as including all such modifications and alterations insofar as they come within the scope of the appended claims or the equivalents thereof.
This application claims the priority benefit of U.S. Provisional Application No. 62/480,866 filed Apr. 3, 2017 (Attorney Docket No. 107512). The aforementioned application is incorporated herein by reference in its entirety.
Number | Date | Country | |
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62480866 | Apr 2017 | US |