METHOD FOR DESTROYING THE ENEMY TARGETS USING HEAVY DUTY WEAPON LAUNCHED FROM RIGID MULTICOPTER DRONES CAPABLE OF BEING STORED INSIDE SOLDIERS' PACKBACKS

Abstract

A method for destroying enemy targets is disclosed which comprises the following steps: (a) carrying a multicopter drone in a backpack of a first soldier; (b) removing the multicopter drone from the backpack, unfolding, and coupling a weapon to the multicopter drone capable of carrying more than 12 kg; (c) remote controlling the multicopter drone to search for the enemy targets using a remote control; and (d) launching the missile from the multicopter drone when the enemy targets are detected.

Claims

1. A method for detecting and/or destroying enemy targets, comprising: (a) carrying a multicopter drone in a backpack of a first soldier; (b) removing said multicopter drone from said backpack, unfolding, and removably coupling said weapon to said multicopter drone; and (c) controlling said multicopter drone to search and attack said enemy targets using a remote control, wherein said multicopter drone is a rigid drone having a wingspan of at least 1.2 m when fully extended.

2. The method of claim 1 wherein said weapon is carried by a military vehicle.

3. The method of claim 1 wherein said multicopter drone further comprises: a hub; a main body having a first set of folding joints; a plurality of rigid flight arms having a second set of folding joints, and a plurality of rigid stands having a third set of folding joints, wherein said first set of folding joint, said second set of folding joints, and said third set of folding joints are designed so as said multicopter drone is folded to fit inside said backpack of said first soldier.

4. The method of claim 3 wherein said step of unfolding further comprises: deploying said multicopter drone by expanding said main body from said first set of folding joints, said plurality of rigid arms from second set of folding joints, and said plurality of stands from said third set of folding joints.

5. The method of claim 4 wherein said enemy targets are selected from tanks, military vehicles, troops, and military facilities.

6. The method of claim 5 further comprising: (d) launching said weapon from said multicopter drone to destroy said enemy targets when said enemy targets are detected.

7. The method of claim 6 wherein said step (d) further comprises detecting said enemy targets using wireless signals transmitted from said hub.

8. The method of claim 7 wherein said step (d) further comprises using said hub to (i) detecting Geographic Positioning Satellite (GPS) coordinates of said enemy targets; and (ii) transmitting said GPS coordinates back to said remote control.

9. The method of claim 8 wherein said step (d) further comprises using said remote control to trigger said hub to launch said weapon to destroy said enemy targets.

10. The method of claim 9 wherein said step (d) further comprises using said hub to: recognize and destroy said enemy targets.

11. The method of claim 7 further comprising displaying said enemy targets on a display panel on said remote control.

12. The method of claim 7 wherein said hub further comprises a memory for storing operation data, a processor processing information transmitted and received from said remote control; and a communicating unit for communicating with said remote control.

13. The method of claim 12 wherein said hub further comprises a weapon coupler, for coupling said weapon into said multicopter drone, electronically controlled by said hub and said remote control.

14. The method of claim 13 wherein said step of coupling said missile to said multicopter drone further comprises using a gimbal coupler.

15. The method of claim 14 wherein said multicopter drone is capable of carrying a load between 12 kg to 60 kg.

16. The method of claim 15 wherein said unfolding step in step (b) further comprises: unfolding said main body outward at said first set of folding joints located substantially close to two opposite sides of said hub; unfolding said plurality of rigid flight arms at said second set of folding joints outward from said main body; unfolding said plurality of rigid stands at said third set of folding joints outward from said elongate main body; and unfolding propellers from said plurality of flight arms.

17. The method of claim 1 further comprising: flying said multicopter drone back to a location of said first soldier using said remote control after a mission is completed; folding up said multicopter drone; and storing said multicopter drone into said backpack of said first soldier.

18. The method of claim 17 wherein said folding up said multicopter drone further comprises: folding up said propellers into said plurality of arms; folding up said plurality of stands into said plurality of flight arms together with said propellers using said third set of folding joints; folding up said plurality of rigid flight arms together with said plurality of rigid stands and said propellers into said rigid body using said second set of folding joints; and folding up said rigid body together with said plurality of rigid flight arms, said plurality of rigid stands and said propellers into said hub using said first set of folding joints.

19. The method of claim 18 wherein said multicopter drone is characterized by having a volume reduction ratio of more than 90%.

20. The method of claim 19 wherein said multicopter drone is a quadcopter.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0030] The accompanying drawings, which are incorporated in and form a part of this specification, illustrate embodiments of the invention and, together with the description, explain the principles of the invention.

[0031] FIG. 1 is a flow chart of a method for destroying various enemy targets using a heavy duty weapon launched from a multicopter drone carried in a backpack of a soldier in accordance with an exemplary embodiment of the present invention.

[0032] FIG. 2 is diagram illustrating the portability of the multicopter drone in a folded state used in the method of the present invention.

[0033] FIG. 3 is a flow chart of a method of designing a multicopter drone that is used to implement the method of FIG. 1 in accordance with an aspect of the present invention.

[0034] FIG. 4 is a perspective diagram of a multicopter drone designed by the method of FIG. 3 in a fully extended state in accordance with an exemplary embodiment of the present invention.

[0035] FIG. 5 is a perspective diagram showing locations of the geometrical structure and placements of the folding joints and landing gears of a multicopter drone designed by the method of FIG. 3.

[0036] FIG. 6 is a perspective diagram of the multicopter drone designed by the method of FIG. 3 in a folded (stowed) state showing minimal waste space that results in a significant volumetric reduction between an operational state and a stowed state in accordance with an aspect of the present invention.

[0037] FIG. 7A includes diagrams illustrating the process of deploying a multicopter drone from a backpack of a soldier wherein the multicopter drone can carry a weapon such as a missile in accordance with an aspect of the present invention.

[0038] FIG. 7B is a diagram of a top-down view of a fully assembled multicopter drone ready for deployment in accordance with an aspect of the present invention; and

[0039] FIG. 8 illustrates a battlefield scenario wherein the soldiers realize the method of the present invention to destroy the enemy's tanks and other military targets.

[0040] The figures depict various embodiments of the technology for the purposes of illustration only. A person of ordinary skill in the art will readily recognize from the following discussion that alternative embodiments of the structures and methods illustrated herein may be employed without departing from the principles of the technology described herein.

DETAILED DESCRIPTION OF THE INVENTION

[0041] Reference will now be made in detail to the preferred embodiments of the invention, examples of which are illustrated in the accompanying drawings. While the invention will be described in conjunction with the preferred embodiments, it will be understood that they are not intended to limit the invention to these embodiments. On the contrary, the invention is intended to cover alternatives, modifications and equivalents, which may be included within the spirit and scope of the invention as defined by the appended claims. Furthermore, in the following detailed description of the present invention, numerous specific details are set forth to provide a thorough understanding of the present invention. However, it will be obvious to one of ordinary skill in the art that the present invention may be practiced without these specific details. In other instances, well-known methods, procedures, components, and circuits have not been described in detail so as not to unnecessarily obscure aspects of the present invention.

[0042] Within the scope of the present description, the reference to an embodiment or the embodiment or some embodiments means that a particular feature, structure, or element described with reference to an embodiment is comprised in at least one embodiment of the described object. The sentences in an embodiment or in the embodiment or in some embodiments in the description do not therefore necessarily refer to the same embodiment or embodiments. The feature, structures or elements can be furthermore combined in any adequate way in one or more embodiments.

[0043] Within the scope of the present description, the word drones include different forms of unmanned flying targets including unmanned aerial vehicles, drones, multicopters with propellers affixed at different locations on the drones.

[0044] Within the scope of the present description, the words coupling, connecting, coupled, coupling, connections, coupler, bolted, laid, connected positioned, attached, attaching, affixed, affixing are used to mean attaching between two described members using hardware such as screws, nails, tongs, prongs, clips, spikes, staples, pins, male and female nuts, buttons, sleeves, lugs, pivots, cams, handles, bars, fasteners, connectors, ball-bearing latches, 3D gimbals, or the likes that meet the MIL-STD commercial off the shelf (COTS).

[0045] Within the scope of the present description, the word remote control, remote controlling is used to mean wired and/or wireless controlling. Wired connections include electrically conducting wires, cables, lines, coaxial cables, strips, or the likes that meet the MIL-STD. Conducting wires are made of conductors such as coppers, aluminum, gold, or the likes that meet the MIL-STD. Wireless connections include electromagnetic waves and long-range wireless communication channels include UHF/VHF radio frequencies 900 MHz and 2.4 Ghz.

[0046] Within the scope of the present description, the word rotation, rotating, rotate includes clockwise and/or counterclockwise direction.

[0047] Within the scope of the present description, the limitation rigid used in the present invention includes non-inflatable materials such as light steel, carbon composite, polymer, epoxy based resins, etc.

[0048] Within the scope of the present invention, the Cartesian XYZ coordinate (x,y,z) also includes equivalent spherical coordinate (r, , ), and/or cylindrical coordinate (r, , z) that can determine the directions of movements or coordinates of the enemy targets including GPS coordinates.

[0049] Within the scope of the present description, the word motors refer to the rotors that drive the propellers, tilt rotors, electric rotors, hybrid rotors, AC brushless motors (BLAC), DC brushless motors (BLDC), also known as permanent magnet synchronous motors (PMSM).

[0050] Within the scope of the present description, the word targets refer to the enemy's tanks, armored vehicles, military transportation means, trucks, ships, troops, bunkers, buildings, tents, airports, and aircrafts on the ground, the enemy's ground missile launchers, or the likes.

[0051] Referring now to the drawings and specifically to FIG. 1, a flow chart of a method 100 for destroying enemy targets using a multicopter drone capable of being carried by a soldier in a backpack and deployed therefrom in accordance with an exemplary embodiment of the present invention is illustrated. Method 100 provides a novel method for both detecting and destroying the enemy targets using a multicopter drone capable of carrying heavy duty weapon and at the same time being carried by a single soldier. That is, the multicopter drone is invented such that the volume reduction ratio between a folded (stowed) state and fully extended (operational) state is significantly large (in the range of more than 90%) so that a soldier can carry it in his/her backpack. In the operational state, the multicopter drone is extended out to carry heavy weapon in accordance with the law of physics: the weight of the payload is proportional to the wingspan of the carrier UVAs or drones.

[0052] More particularly, at step 101, a multicopter drone is carried inside a backpack of a soldier. To implement step 101, the multicopter drone must be sufficiently light and compact to be inserted inside the soldier's backpack. Yet the multicopter drone has great lift capacity to carry heavy duty weapon when fully extended. In various embodiments of the present invention, step 101 is realized by a multicopter drone having a dimension of 200 cm200 cm50 cm and weighs 56 kg (including a missile weighing 33 kg) in operational state. In the folded state, the multicopter drone has a dimension 60 cm38 cm25 cm and weighs 23 kg. Thus, the volume reduction ratio is 97%. This multicopter drone can lift a missile that weighs up to 33 kg. With this reduction ratio, this multicopter drone is capable of being carried by a single soldier who may advance toward the enemy targets in adversary environment such as deserts, mountains, swamps, and dense jungles.

[0053] At step 102, at a chosen location, the multicopter drone is removed from the backpack and unfolded. In many aspects of the present invention, second soldiers carry the missile and its launcher, both to be carried by the multicopter drone. Once the multicopter drone is fully extended, the missile and its launcher can be coupled to the multicopter drone using different types of couplers known in the art such as gimbal connectors or other types of well-known connectors. In many preferred embodiments, the missile and its launcher are coupled to the multicopter drone at the center of gravity of the missile and its launcher. Please refer to FIG. 7A (a)-FIG. 7A (d) below. As alluded above, the multicopter drone when fully extended has a wingspan of at least 1.2 meters.

[0054] At step 103, the multicopter drone carrying the missile and its launcher is remotely controlled to fly out to detect the enemy targets. In many aspects of the present invention, the flying range of the multicopter drone is 6 km sufficient to stay out of the enemy's detection range. In many aspects of the present invention, the multicopter drone is equipped with cameras operable to transmit a wide angle of view of the enemies and their positions back to the soldiers and the base camps.

[0055] At step 104, the missile is launched from the multicopter drone via a remote control when the enemy targets are detected. The detection of the enemy targets is achieved by either visual or thermal images transmitted from the multicopter drone back to the operating soldier. In other aspects, GPS coordinates are also transmitted back to the operating soldier. When the soldier decides to destroy the enemy targets, he or she presses a button on the remote control, the missile is launched from the launcher. The missile is automatically heading toward the enemy targets because the missile can be an automatically self-guided missile. In different aspects of the present invention, step 104 can be implemented with air-to-ground missiles, ground-to-ground missiles, surface to air such as the FIM-92 Stinger, shoulder operated air-to-air missiles, various types of bombs such as laser guided bombs, and automatic Gatling guns such as the M134. In other words, the rigid multicopter drone of the present invention is used as an effective heavy weapon system. All of this is possible because of the large wingspan in the operational state that allows the rigid multicopter drone of the present invention to carry heavy weapon. On the other hands, in the folded state, the rigid multicopter drone of the present invention is compact the light that it can be carried in the backpack of a soldier.

[0056] Finally, at step 105, after destroying the enemy's target such asbut not limited toa tank, the multicopter drone is returned safely to the operating soldier far away from the enemy's position. The multicopter drone is then disconnected from the launcher, folded up, and stored in the backpack, ready for the next mission. As alluded above, the multicopter drone when folded has a dimension of 60 cm38 cm25 cm, small and compact enough to be stowed in the soldier's backpack. It will be noted that in some aspects of the present invention, other weapons can be carried by the multicopter drone such asbut not limited tobombs, machine guns, air to ground missiles, etc.

[0057] Now, referring to FIG. 2, a perspective diagram 200 demonstrating the portability of the multicopter drone in accordance with an exemplary embodiment of the present invention is illustrated. A first soldier 201 carries a multicopter drone 600 which is neatly folded in his or her backpack 211. The dimension of the multicopter drone when stowed by first soldier 201 is 60 cm38 cm25 cm. One or more second soldiers 202 is designated to carry at least one missile stored in their launchers 212. In many aspects of the present invention, the missiles are the FGM-148 Javelin missile which weighs 22.3 kg. However, other types of aerial deployment missiles with heavier weights can be used. Furthermore, other weapon or devices can be carried in the same fashion as described in method 100 above. In other situations, a third soldier (not shown) can be designed to carry auxiliary equipment to support the operations and maintenance multicopter drone 600. The auxiliary equipment includes batteries, replacement propellers, couplers, cables, parts, couplers, IC boards, command launch unit (CLU), etc.

[0058] Next, referring to FIG. 3, a flow chart of a method 300 that enables the reduction ratio of 97% from its extended (operational) state to its folded (stowed) state so that method 100 can be implemented in accordance with an aspect of the present invention is illustrated.

[0059] At step 301, a multicopter drone having a hub, an rigid main body that supports the hub, a plurality of rigid flight arms extending outward from the rigid main body, and a plurality of stands extending downward from the rigid main body is provided. Please refer to FIG. 4 for the complete illustration of the described multicopter drone. More particularly, a rigid main body 410 supports a hub 11. In various embodiments of the present invention, hub 11 can be removably connected to rigid main body 410 at any angle on the plane of the Z-axis of a Cartesian coordinate 499. That is, hub 11 can be rotatably connected to rigid main body 410 at any angle relative to the Z-axis depending on the type of payloads and the mission objective.

[0060] Hub 11 divides rigid main body 410 into a first rigid segment 411a and a second rigid segment 411b. First rigid segment 411a is connected to a first main body folding joint 411c positioned near a bottom side of hub 11. Second rigid segment 411b is connected to a second main body folding joint 411d positioned near a bottom side and in opposite of first main body folding joint 411c. With this arrangement, first rigid segment 411a is folded adjacent to hub 11 by first main body folding joint 411c, leaving no empty spaces therebetween. Second rigid segment 411b is folded adjacent to hub 11 by second main body folding joint 411d, leaving no empty spaces therebetween.

[0061] Continuing with step 301 and FIG. 4, a first rigid flight arm 420 is connected to first rigid segment 411a at a first flight arm folding joint 423. A second flight arm 430 is connected to second rigid segment 411b at a second rigid flight arm folding joint 433. First rigid flight arm 420 comprised a first rigid cross arm 421 and a second rigid cross arm 422 which are configured to be folded into first rigid segment 411a, leaving no empty spaces therebetween. Second rigid flight arm 430 comprised a third rigid cross arm 431 and a fourth rigid cross arm 432 which are configured to be folded into second rigid segment 411b, leaving no empty spaces therebetween. First rigid cross arm 421 is connected to a first motor 421m, and second rigid cross arm 422 is connected to a second motor 422m. Third rigid cross arm 431 is connected to a third motor 431m, and fourth rigid cross arm 432 is connected to a fourth motor 432m. First motor 421m to fourth motor 431m are either fixed pitch or variable pitch rotors.

[0062] At step 302, the elongate main body is folded or extended at two main body folding joints located on two opposite sides that are substantially adjacent to the hub. In other words, the two main body folding joints are located substantially in flush with the opposite sides of the hub in the Z direction so that the rigid main body does not yield any wasteful empty spaces between the hub and itself. FIG. 4 illustrates an implementation of step 302. First and second main body folding joints 411c and 411d are located almost in flush with the two opposite sides of a hub 11 in the Z direction of a Cartesian coordinate system 499. In the folded (stowed) state, a first rigid segment 411a and a second rigid segment 411b of rigid main body 410 almost touch and parallel to the respective opposite lateral sides of hub 11 along an axis 441z, leaving zero or very little empty spaces therebetween. In various embodiments of the present invention, axis 411z of hub 11 can be parallel to or formed an angle with the Z-axis.

[0063] At step 303, rigid flight arms that supports the propellers are folded into the rigid main body. Referring again to FIG. 4, because of a first rigid flight arm folding joint 423 and a second rigid flight arm folding joint 433 located at the distal ends of rigid main body 410, flight arms 420 and 430 are folded to become a unitary unit with rigid main body 410, leaving zero or very little empty spaces therebetween.

[0064] Next at step 304, a plurality of landing gears is folded upward into the rigid main body. Referring to FIG. 4, in a four coaxial propeller embodiment 400, landing gear 14 is located at the distal ends of rigid main body 410. More specifically, landing gear 14 is comprised a first rigid landing gear 14a and a second rigid landing gear 14b. First rigid landing gear 14a and second rigid landing gear 14b are either V-shaped or inverted T-shaped. First rigid landing gear 14a is folded into and parallel to first rigid segment 411a of rigid main body 410. Second rigid landing gear 14b is folded into and parallel to second rigid segment 411b of rigid main body 410. In various embodiments of the present invention, rigid landing gears 14a and 14b are located at first flight arm folding joint 423 and second flight arm folding joint 433 respectively. In some embodiments of the present invention, rigid landing gears 14a and 14b are located at first main body folding joint 411c and second main body folding joint 411d respectively

[0065] It is noted that multicopter drone 400 designed using method 300 is not limited to 4 propellers (or two flight arms 420 and 430), a plurality of rigid flight arms 122 and a plurality of rigid landing gears are also within the scope of the present invention. For example, method 100 and method 300 are applicable to four non-coaxial propeller (four flight arms), twelve coaxial propeller (or six flight arms), and sixteen coaxial propeller (or eight flight arms) multicopter drones. It is noted again that the limitation rigid used in the present invention includes non-inflatable materials such as light steel, carbon composite, polymer, epoxy based resins, etc.

[0066] Because of method 300 of the present invention implemented by multicopter drone 400 described above, a multicopter drone having a dimension of 200 cm200 cm50 cm and weighs 56 kg (including a missile weighing 33 kg) in operational state can be reduced to a dimension of 60 cm38 cm25 cm and weighs 23 kg. Thus, the reduction ratio is 97%. This multicopter drone can lift a missile that weighs up to 60 kg in the operational state of at least 1.2 meters wingspan. With this reduction ratio, this multicopter drone is capable of being carried by a single soldier who may move toward the enemy in adversary environment such as deserts, mountains, swamps, and dense jungles.

[0067] Next, referring to FIG. 4, four coaxial propeller multicopter drone 400 in a fully extended (operational) state that employs the method 300 of the present invention is illustrated. In some exemplary embodiments of the present invention, four propeller multicopter drone 400 includes rigid main body 410 configured to support a hub 11 located at the center of rigid main body 410. Hub 11 divides rigid main body 410 into first rigid segment 411a and second rigid segment 411b. Four coaxial propeller multicopter drone 400 is an implementation of step 301. As seen in FIG. 4, rigid main body 410 is extended and folded perpendicular to a longitudinal axis 441x parallel with X-axis of a Cartesian coordinate system 499. This folding/extending operation is realized by first and second main body folding joints 411c and 411d located sufficiently adjacent to and in flush with lateral surfaces of hub 11. In many preferred embodiments of the present invention, hub 11 is a polyhedron with many lateral sides (surfaces). Hub 11 is supported by rigid main body 410 so that its main axis 441z is parallel to the Z axis of Cartesian coordinate system 499. With this novel arrangement, rigid main body 410 is folded toward the Z-axis or main axis 441z to hug closely along opposite surfaces of hub 11, yielding no wasteful empty spaces. Hub 11 is electrically connected to video cameras 163 and other sensors 165. Video cameras 163 may be RGB, thermal, infrared cameras. Sensors 165 include GPS, position magnetic sensors, optics, LIDAR. This disclosure is the implementation of step 302. First and second main body folding joints 411c and 411d may be 90 self-locking hinges.

[0068] Next, rigid landing gear 14, comprised of first rigid landing gear 14a and second rigid landing gear 14b, are located either at first and second flight arm folding joints 423 and 433 respectively. First and second rigid landing gears 14a and 14b are folded upward long the Z-axis into rigid main body 410. This is an implementation of step 304. First and second rigid flight arms 420 and 430 are also folded into rigid main body 410 along the X-axis. First and second flight arms 420 and 430 are extended along the Y-axis. This is an implementation of step 303.

[0069] The full description of multicopter drone 400 is disclosed in a co-pending US2021250980, entitled A Multicopter, filed on 15 Oct. 2021 in Australia. This patent application is incorporated in its entirety herewith.

[0070] Next referring to FIG. 5, a perspective diagram 500 further illustrating the folding joint locations and the folding process of multicopter drone of the present invention is illustrated. First main body folding joint 411c and second main body folding joint 411d are located at the opposite bottom surfaces of hub 11. First and second rigid flight arms 420 and 430 are located at respective distal ends of rigid main body 410 at first rigid flight arm folding joints 423 and second rigid flight arm folding joint 433, extending outward along the Y-axis of a Cartesian coordinate system 499. Rigid landing gears 14 are also located at first flight arm folding joints 423 and second flight arm folding joint 433. Hub 11 is supported by rigid main body 410 and stands in the Z-direction. In other embodiments of the present invention, hub 11 can be removably coupled to rigid main body 410 at any angles formed between axis 441z of hub and longitudinal axis 441x of rigid main body 410 in the Z-plane. First flight arm folding joints 423 and second flight arm folding joint 433 may be duplex 90 self-locking folding hinges.

[0071] From the fully extended (operational) state as shown in FIG. 4, first landing gear 14a is folded merging into first rigid segment 411a as shown in a direction arrow 501. This operation is achieved by first landing gear folding joint 14c. Second landing gear 14b is folded merging into second rigid segment 411b as shown in a direction arrow 501. This operation is achieved by second landing gear folding joint 14d.

[0072] Next, first rigid cross arm 421 is folded merging into first rigid segment 411a of rigid elongate main body 410 along arrows 503 by the virtue of first flight arm folding joint 423. Second rigid cross arm 422 is folded merging into first rigid segment 411a of rigid main body 410 along arrows 503 by the virtue of first flight arm folding joint 423. First rigid cross arm 431 is folded merging into second rigid segment 411b of rigid main body 410 along arrows 504 by the virtue of second flight arm folding joint 433. Fourth rigid cross arm 432 is folded merging into second rigid segment 411b of rigid main body 410 along arrows 504 by the virtue of second flight arm folding joint 433.

[0073] Finally, first rigid segment 411a is folded in the Z-direction merging into hub 11 along direction 505 by virtue of first main body folding joint 411c. Second rigid segment 411b is folded in the Z-direction merging into hub 11 along direction 506 by virtue of second main body folding joint 411d. The completion of the above steps leads to the folded or stowed state in FIG. 6 below.

[0074] Next, referring to FIG. 6, a perspective diagram of multicopter drone 600 in the folded (stowed) after the folding process 300 and that in FIG. 5 is illustrated. As shown, in the fully folded state, multicopter drone 600 has almost zero waste empty spaces between the elements described above, i.e., hub 11, rigid main body 411, and first and second rigid flight arms 420 and 430 respectively. Again, the reduction ratio between the fully extended state 400 in FIG. 4 and the fully folded state 600 in FIG. 6 is 97%. This allows method 100 to be realized. The dimension of multicopter drone 600 in the folded (stowed) status is 60 cm38 cm25 cm. This is sufficiently compact to be stowed in backpack 211. In the fully extended state of multicopter drone 400 as shown in FIG. 4, the dimension of multicopter drone 400 is 200 cm200 cm50 cm. That is the wingspan of multicopter drone 400 is 2.2 meters. With the following technical specifications: [0075] Volume reduction ratio: 97% [0076] Propeller size: 3619 [0077] The width and length of the hub is 66 [0078] Folded status dimension: 60 cm38 cm25 cm [0079] Fully extended (operational) status: 200 m200 m50 cm [0080] Battery: 58.8V, 45000 mA [0081] Maximum Take-off Weight (including a missile weighed 12 kg to 60 kg): [0082] Maximum flight time without payload: 50 minutes

[0083] With the wingspan of more than 1.2 m, multicopter drone 400 can carry weapon such as the anti-tank missile Javelin, other high explosive anti-tank (HEAT) missiles, air to surface missiles, bombs, and artillery, etc. With the reduction of 97%, multicopter drone 600 is carried inside a soldier's backpack 211. With these features, multicopter drone 400 of the present invention is an effective weapon system.

[0084] Now referring to FIG. 7A, a series of diagrams 700A illustrating the assembling of multicopter drone 600 in accordance with an exemplary embodiment of the present invention are shown.

[0085] In FIG. 7A (a), a fully folded multicopter drone 600 as shown in FIG. 6 is neatly stored in backpack 211 of a soldier. Additional blades and parts of multicopter drone 600 are also stored inside backpack 211. Upon reaching the predetermined destination, first soldier 201 starts to open his/her backpack 211 and extend multicopter drone 600. Please also refer to FIG. 6 above.

[0086] Next, in FIG. 7A (b), multicopter drone 700 is unfolded by first flipping down first rigid land gear 14a from first segment 411a in a direction 701. Next, second rigid landing gear 14b is unfolded from second rigid segment 411b in a direction 702. Following, rigid first segment 411a is flipped down from hub 11 in a direction 704. Similarly, on the other side of hub 11, second rigid segment 411b is flipped down from hub 11 in a direction 705.

[0087] Next, in FIG. 7A (c), first rigid cross arm 421 is extended from first rigid segment 411a in a direction 706. Then second rigid cross arm 422 is extended from first rigid segment 411a in a direction 707. Next, third rigid cross arm 431 is extended from second rigid segment 411b in a direction 708. Following, fourth rigid cross arm 432 is extended from second rigid segment 411b in a direction 709.

[0088] Finally, in FIG. 7A (d), a first coaxial propeller 441 connected to first motor 421m is extended in a direction 711. A second coaxial propeller 442 connected to second motor 422m is extended in a direction 712. A third coaxial propeller 451 connected to third motor 431m is extended in a direction 713. A fourth coaxial propeller 452 connected to fourth motor 432m is extended in a direction 714. Second soldier 202 couples missile and its launcher 212 to multicopter drone 710 at a coupler 16 in a direction 715. In many aspects of the present invention, coupler 16 is activated to release missile 212 by command launch unit (CLU) operated by first soldier 201. This control/release mechanism of coupler 16 is well-known in the art and needs not to be described in detail here. Missile 212 armed to multicopter drone 700 is a fire and forget missile.

[0089] Hub 11 is firmly mounted on top of rigid main body 410. Hub 11 contains integrated circuit (IC) boards (not shown) for remotely controlling multicopter drone 700, transmitter/receiver board, GPS, etc. The IC boards are well-known in the art and need not to be described herein. A battery 15 is coupled to provide the necessary power supplies to hub 11. Coupler 16 can be gimbaled connectors or other types of connectors. Electric motors 321m to 332m are mounted at the tips of first rigid cross arm 421 to fourth rigid cross arm 432 respectively. Each electric motor or servo 431m to 432m has a maximum thrust of 29 kg. Electric motors 421m to 432m with more thrust can also be used. Together four of them can carry a weapon of 12 kg to 60 kg while the weight of a Javelin missile including its launcher is 22.3 kg.

[0090] FIG. 7B shows a top view diagram 700B of multicopter drone 700 after being fully extended and assembled and ready to be deployed. Top view diagram 700B shows folding joints 411c, 411d, 423, and 433 aligned on rigid main body 410. Rigid main body 410 includes first main body folding joint 411c and second main body folding joint 411d for unfolding rigid main body 410. The locations of first main body folding joint 411c and second main body folding joint 711db are in flush with opposite sides of hub 11 as described above in FIG. 4 to FIG. 6. First flight arm folding joint 423 and a fourth flight arm folding joint 433 are designed for unfolding first rigid cross arm 421 to fourth arm 433 respectively. In some embodiments of the present invention, rigid main body 410 may be telescopic tube so that the length of rigid main body 410 can be adjusted according to the type of missile 212

[0091] From the disclosure of FIG. 1 to FIG. 7A and FIG. 7B above, the following targets of the present invention are achieved: [0092] (a) a method for destroying an enemy's target using a missile launched from a multicopter drone. [0093] (b) a method for destroying the enemy targets without exposing the soldiers to the enemy. [0094] (c) a method for better detecting the enemy's position and targets, e.g., having a better angle of view. [0095] (d) a method for destroying an enemy's target that is efficient, cost-effective, and capable of returning the multicopter drones to safety. These objectives are illustrated in FIG. 8 below.

[0096] Now referring to FIG. 8, a diagram 800 illustrating a deployment of a multitude of multicopter drones 700B.sub.1, 700B.sub.2, 700B.sub.3, to 700B.sub.N in accordance with method 100 of the present invention is illustrated. A group of soldiers 801a, 802a, 803a to 801b, 802b, to 803b, to 801N, 802N, to 403N who control and support the operations to the multitudes of multicopter drones 700B.sub.1, 700B.sub.2, 700B.sub.3, to 700B.sub.N using separate remote controllers 810a, 810b, and 810N respectively. An end of line of sight 811 separates the enemies from group of soldiers 801a, 802a, 803a to 801b, 802b, to 803b, to 801N, 802N, to 803N. It is noted that beyond line of sight 811 to the left of FIG. 8, the enemies cannot see the group of soldiers 801a, 802a, 803a to 801b, 802b, to 803b, and 801N, 802N, to 803N. On the other side of line 811, there are a first enemy tank 831, a second enemy tank 832, a third enemy tank 833, a caravan of military trucks 835, and ground troops 834.

[0097] Continuing with FIG. 8, as shown, first multicopter drone 700B.sub.1 carrying an anti-tank missile 212B.sub.1 as described in FIG. 7A to FIG. 7B and method 100 is still not launch its missile 212B.sub.1. Second multicopter drone 700B.sub.2 is launching its missile 212B.sub.2 toward enemy tank 832. In the meantime, third multicopter drone 700B.sub.3 is launching its missile 212B.sub.3 toward first enemy tank 831. On the other hand, multicopter drone 700B.sub.N drops its bomb 212 to destroy caravan of military trucks carrying ammunition.

[0098] As illustrated in FIG. 8, FIG. 1 to FIG. 7A and FIG. 7B are applicable to situations where multiple multicopter drones as described above can be deployed at the same time. Furthermore, multicopter drone 700B.sub.N can carry different weapons such as bombs from missiles 212. Thus, the number of multicopter drones, their types of weapons, their geometrical shapes, and their operations if read on method 100 and assembling steps in FIG. 7A to FIG. 7B are all within the scope of the present invention.

[0099] Because of the present invention, a team of multicopter drones 700B.sub.1 to 700B.sub.N as described above in FIG. 1 to FIG. 7A, FIG. 7B can be deployed into an attacking force that is fast, evasive, agile, and effective.

[0100] The foregoing description details certain embodiments of the invention. It will be appreciated, however, that no matter how detailed the foregoing appears in text, the invention can be practiced in many ways. As is also stated above, it should be noted that the use of terminology when describing certain features or aspects of the invention should not be taken to imply that the terminology is being re-defined herein to be restricted to including any specific characteristics of the features or aspects of the invention with which that terminology is associated. The scope of the invention should therefore be construed in accordance with the appended claims and any equivalents thereof.

[0101] After the foregoing description of the novel features and the details of certain embodiments of the invention above, it will be appreciated that the mechanical parts, the propeller driving motors, and electrical parts, sensors, controller boards, radars, transceivers, and the process to assemble them together to build multicopter drones 400, 600, and 700, a person of ordinary skills in the related arts can build the multicopter drones of the present invention without undue experiment. Therefore, they need not to be described in detail herein.

[0102] After the foregoing description details certain embodiments of the invention above, it will be appreciated that remote controlling and the operations of multicopter drones 400, and 700, a person of ordinary skills in the related arts and trained how to operate multicopter drones or the likes would know how to fly the multicopter drones of the present invention. Therefore, the controls and operations of the multicopter drones of the present invention need not to be described in detail herein.

[0103] Within the scope of the present description, the reference to an embodiment or the embodiment or some embodiments means that a particular feature, structure or element described with reference to an embodiment is comprised in at least one embodiment of the described object. The sentences in an embodiment or in the embodiment or in some embodiments in the description do not therefore necessarily refer to the same embodiment or embodiments. The particular feature, structures or elements can be furthermore combined in any adequate way in one or more embodiments.

DESCRIPTION OF NUMERALS

[0104] 11 hub [0105] 14 rigid landing gears [0106] 14a first rigid landing gear [0107] 14b second rigid landing gear [0108] 14c first landing gear folding joint [0109] 14d second landing gear folding joint [0110] 15 battery [0111] 16 coupler [0112] 121 folding joint of rigid stand [0113] 122 rigid flight arms [0114] 141 folding joint of the right flight arms [0115] 163 video cameras [0116] 165 sensors [0117] 201 a first soldier who carries the drone in his/her backpack [0118] 202 a second soldier who carries the missiles [0119] 203 a third soldier who carries auxiliary devices [0120] 211 backpack containing the folded multicopter drone [0121] 212 missile and missile launcher [0122] 212B.sub.1 missile carried by first multicopter drone [0123] 212B.sub.2 missile carried by second multicopter drone [0124] 212B.sub.3 missile carried by third multicopter drone [0125] 212B.sub.N air-to-ground bomb [0126] 400 multicopter drone in the fully extended state [0127] 410 rigid main body [0128] 411a first segment of rigid main body [0129] 411b second segment of rigid main body [0130] 411c first main body folding joint [0131] 411d second main body folding joint [0132] 420 first rigid flight arm [0133] 421 first rigid cross arm [0134] 421m first motor [0135] 422 second rigid cross arm [0136] 422m second motor [0137] 423 first flight arm folding joint [0138] 430 second rigid flight arm [0139] 431 third rigid cross arm [0140] 431m third motor [0141] 432 fourth rigid cross arm [0142] 432m fourth motor [0143] 423 second flight arm folding joint [0144] 441 first propeller [0145] 442 second propeller [0146] 451 third propeller [0147] 452 fourth propeller [0148] 499 Cartesian coordinate system [0149] 600 multicopter drone in folded state [0150] 700 multicopter drone in operational state [0151] 700B.sub.1 first multicopter drone controlled by the first group [0152] 700B.sub.2 second multicopter drone controlled by the second group [0153] 700B.sub.3 third multicopter drone controlled by the third group [0154] 700B.sub.N N.sup.th multicopter drone controlled by the N.sup.th group [0155] 801a multicopter drone carrying soldier in the first group [0156] 802a missile carrying soldier in the first group [0157] 803a auxiliary devices carrying soldier in the second group [0158] 801b multicopter drone carrying soldier in the second group [0159] 802b missile carrying soldier in the second group [0160] 803b auxiliary devices carrying soldier in the first group [0161] 801N multicopter drone carrying soldier in the Nth group [0162] 802N missile carrying soldier in the Nth group [0163] 803N auxiliary devices carrying soldier in the Nth group [0164] 811 Enemy's end of line of sight [0165] 831 Enemy's first tank [0166] 832 Enemy's second tank [0167] 833 Enemy's third tank [0168] 834 Enemy's ground troops [0169] 835 Enemy's trucks carrying logistics and/or troops