US20180283828A1

US20180283828A1 - Projectile system with capture net

Info

Publication number: US20180283828A1
Application number: US15/939,725
Authority: US
Inventors: James W. Teetzel; John Kevin Dodge
Original assignee: Wilcox Industries Corp
Current assignee: Wilcox Industries Corp
Priority date: 2017-04-03
Filing date: 2018-03-29
Publication date: 2018-10-04

Abstract

A modular rocket system includes a guidance module defining a nose and including a guidance system for guiding said modular rocket system toward a target. A flight control module is removably attached to the guidance module and includes a plurality of airfoils that are controllable to control a direction of travel of the modular rocket system. A net module is removably attached to the flight control module and houses a net and a deployment mechanism. The deployment mechanism is configured to eject the net from the net module toward the target. A rocket module is removably attached to the net module, and includes a rocket motor configured to propel the modular rocket system.

Description

CROSS-REFERENCE TO RELATED APPLICATION

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.

BACKGROUND

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.

SUMMARY

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.

BRIEF DESCRIPTION OF THE DRAWINGS

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.

FIG. 1A is an exploded view of a modular rocket system in accordance with an exemplary embodiment of the present disclosure, wherein the wings appear in the folded position.

FIG. 1B is a front end view of the first rocket segment.

FIG. 1C is a side cross-sectional view of the third rocket segment, showing an exemplary net firing system.

FIG. 1D is a cross-sectional view of the third rocket segment appearing in FIG. 1C, taken in the axial direction and showing the exemplary net firing system.

FIG. 2A is a side view of the embodiment appearing in FIG. 1A, wherein the wings appear in the folded position.

FIG. 2B is an isometric view of the embodiment appearing in FIG. 2A, wherein the wings appear in the extended position.

FIG. 2C is an exploded side view of the embodiment appearing in FIG. 2A.

FIG. 3A is a front view of the embodiment appearing in FIG. 2A.

FIG. 3B is an side view of the embodiment appearing in FIG. 2A, wherein the wings appear in the folded position.

FIG. 3C is a rear view of the embodiment appearing in FIG. 3A.

FIG. 4 illustrates an exemplary process of firing the modular rocket system from an exemplary launch apparatus.

FIG. 5 illustrates an exemplary process of deployment of the net firing system from the modular rocket system, following launch of the modular rocket system herein using the launch apparatus.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

Referring now to FIGS. 1-5, there is shown exemplary modular rocket system 10, which includes a nose module A, a flight control module B, a net module C, a rocket motor module D. The rocket system 10 may further include a cartridge shell E.
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 CO₂canister 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 FIG. 2B, after firing, the wings 32 can be moved to their extended position. Each of the wings 32 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 32 are small enough to fit within the housing shell to allow the system 10 to fit within the constraints of the launching platform while providing the ability to allow the system 10 to perform banking and turning maneuvers during flight. In certain embodiments, the wings are large enough to steer the rocket system 10 around obstacles during flight. Additionally or alternatively, the system 10 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 32 extend through apertures in the shell housing and may be actuated and controlled via springs, hydraulics, pneumatics, motors, and so forth under programmed control responsive to the laser range finder to maintain the path of the rocket 10 toward the centroid of the laser designator signal reflected from the target object.
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 FIG. 4, in certain embodiments, the rocket system 10 is configured to be fired from a standard or conventional launch platform 34, such as a grenade launcher, e.g., a single shot 40 mm grenade launcher. The rearward end 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 10 out of the launch tube of the launch platform. In certain embodiments, the charge may be relatively small since it is only necessary to launch the rocket system 10 a sufficient distance away from the operator to safely fire the rocket motor D.
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 FIG. 5, in operation, the net 30 disables the target object 20 by fouling the rotor blades. Also attached to the net are one or more parachutes 38. The parachute 38 is packed so as to minimize aerodynamic drag until the collision of the net with the target object causes the parachute to unpack. After the parachute is unpacked, it creates aerodynamic resistance so that the target object will descend to the ground sufficiently slowly to prevent ground collision forces from damaging any cargo or payload on board the target object and thereby containing any hazardous payload carried by the target object. In certain embodiments, a single parachute is provided. In alternative embodiments a plurality of smaller parachutes are used. Such smaller parachutes may be spaced at points to aid in even weight distribution.
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.

Claims

What is claimed is:

1. A modular rocket system, comprising:

a guidance module defining a nose, said guidance module including a guidance system for guiding said modular rocket system toward a target;

a flight control module removably attached to the guidance module, said flight control module including a plurality of airfoils, the airfoils controllable for controlling a direction of travel of the modular rocket system;

a net module removably attached to the flight control module, said net module housing a net and a deployment mechanism, said deployment mechanism configured to eject the net from the net module toward the target; and

a rocket module removably attached to the net module, said rocket module including a rocket motor configured to propel the modular rocket system.

2. The modular rocket system of claim 1, wherein the guidance system is a laser guidance system.

3. The modular rocket system of claim 2, wherein the laser guidance system is configured to follow an infrared laser designator beam.

4. The modular rocket system of claim 2, wherein the infrared laser designator beam has a wavelength of 1064 nanometers.

5. The modular rocket system of claim 1, wherein the guidance module further comprises a laser ranging module including a laser emitter and an optical sensor, the laser ranging module configured to activate the deployment mechanism when the modular rocket system is a predetermined distance from a target.

6. The modular rocket system of claim 1, wherein the deployment mechanism is selected from the group consisting of a charge of explosive material, a source of compressed gas, and a compressed spring mechanism.

7. The modular rocket system of claim 1, wherein the net includes a plurality of weights attached thereto.

8. The modular rocket system of claim 7, wherein the deployment mechanism is shaped to cause the plurality of weights to spread out when the net is ejected from the net module.

9. The modular rocket system of claim 8, wherein the plurality of weights are formed of a material selected from the group consisting of tungsten, steel, or lead.

10. The modular rocket system of claim 1, wherein the net is formed of a material selected from the group consisting of a material having a web-like structure and a mist net material.

11. The modular rocket system of claim 10, wherein the net is 5 to 20 feet in diameter.

12. The modular rocket system of claim 11, wherein the net is 10 feet in diameter.

13. The modular rocket system of claim 1, wherein the net module further comprises at least one parachute attached to the net.

14. The modular rocket system of claim 1, wherein the net module includes a beacon device for providing an indication of a location of the net module.

15. The modular rocket system of claim 1, further comprising:

a shell chasing removably attached to the rocket module, said shell chasing including a charge of explosive material for firing the modular rocket system from a launch platform.

16. The modular rocket system of claim 15, wherein the explosive material is configured to propel the modular rocket system a distance prior to the rocket motor being fired.

17. The modular rocket system of claim 15, wherein said shell casing is a 40 mm shell casing.

18. The modular rocket system of claim 1, further comprising:

a memory storing a program of instructions for execution by the guidance system.

19. The modular rocket system of claim 1, wherein the rocket module includes a plurality of vanes for providing stability during flight.

20. The modular rocket system of claim 1, wherein said rocket motor is powered by a rocket fuel material in a form selected from the group consisting of a solid, liquid, a gel, or any combination thereof.

21. The modular rocket system of claim 1, wherein said airfoils are movable between a retracted state wherein the airfoils are retracted within a housing of the flight control module and an extended state wherein the airfoils extend through openings within the housing of the flight control.

22. The modular rocket system of claim 1, wherein the modular rocket system is configured to be fired by a conventional rocket launch platform.