KR20210086776A - Drone with parachute and method of drone release thereof - Google Patents

Abstract

The present invention relates to a drone equipped with a parachute and a method for releasing a drone of a projectile. The drone equipped with a parachute comprises: a drone main body that can fly; and a parachute pack unit that is detachably mounted on the upper part of the drone main body and has a built-in parachute unfolded after being released from the projectile. After the drone is released from the projectile, and after the posture is stabilized with the parachute, the drone flies and conducts wartime operations such as reconnaissance at the relevant point, thereby allowing drones to be used as a variety of weapon systems and greatly improving efficiency when using the drones.

Description

DRONE WITH PARACHUTE AND METHOD OF DRONE RELEASE THEREOF

The present invention relates to a drone equipped with a parachute and a drone ejection method of a projectile, and more particularly, a drone in which a plurality of drones emitted to the outside after boarding a projectile are stably maintained in their postures with a parachute and then fly The invention relates to a projectile and a method for discharging a projectile from a drone.

A drone that is remotely controlled through a wireless communication method was initially developed for military use as an unmanned aerial vehicle and used for simple shooting practice. However, with the continuous development of electronic communication technology, it is being expanded and distributed not only for military use, but also for shooting and transportation purposes.

In general, a drone may include a plurality of fans for outputting lift, a battery for supplying power to the fans, and a control unit. Here, the fan may include a motor that generates rotational force by electric power supplied from a battery, and a propeller connected to a drive shaft of the motor.

Drones are small aircraft, and their use is increasing in future wartime situations, and various methods of directly putting them into battle are being proposed.

Currently, drones are widely used for reconnaissance on the battlefield, but due to the short flight time, there was a problem that the efficiency of reconnaissance work was decreased.

Therefore, the development of surveillance and reconnaissance of the enemy by attaching a reconnaissance device to the shells is being carried out.

However, one reconnaissance device per shell is inefficient, and there is a disadvantage that the device is damaged due to the impact when the shell is fired.

In addition, when a drone is released from a shell or missile in flight, the drone is not positioned in a flying position and crashes frequently occur. Therefore, the use of the drone to actually mount the drone on a shell or missile and then release it to the outside There was a problem that the efficiency was very low.

0001) Korean Patent Registration No. 1924011 "Fire suppression system including reconnaissance drone and fire suppression drone" (registered on November 26, 2018)

An object of the present invention is to embed a plurality of drones in a projectile, move the drone to a target point with the projectile, and then safely release the drone to perform efficient exhibition work through a plurality of drones. is to provide

In order to achieve the above object of the present invention, an embodiment of a drone equipped with a parachute according to the present invention has a built-in parachute that is detachably mounted on a drone body capable of flying, and is detachably mounted on the upper part of the drone body, and is spread out after being released from the projectile body. It is characterized in that it includes a parachute pack part.

In the present invention, the drone body includes a base body in which a rechargeable battery and a flight controller are located, and a wing arm in which a propeller rotated by a motor is rotatably located in the base body and positioned at an end side, the The wing arm portion may be folded and inserted into the base body portion to be positioned.

An embodiment of the drone equipped with a parachute according to the present invention may further include a parachute mounting unit for detachably mounting the parachute pack unit and the drone body.

In the present invention, the parachute mounting unit may include a mechanical locking unit for releasing the restraint of the parachute pack unit by rotation of the wing arm unit while the wing arm unit is rotated.

In the present invention, the parachute mounting unit includes an electromagnet located on the upper surface of the parachute pack unit or the drone body, and an electromagnetic locking unit for restraining the parachute pack unit to the upper surface of the drone body by the magnetic force of the electromagnet unit.

In the present invention, the parachute mounting part includes a mechanical locking part for releasing the restraint of the parachute pack part by rotation of the wing arm part while the wing arm part is rotated, and an electromagnet part located on the upper surface of the parachute pack part or the drone body. It may include an electronic locking part for restraining the parachute pack part to the upper surface of the drone body by the magnetic force of the stone part.

In the present invention, the parachute mounting unit including the mechanical locking part and the electronic locking part rotates the wing arm part in an unfolded state of the parachute to release the lock of the mechanical locking part and it was confirmed that the drone was stabilized in a flying posture. After that, the electronic locking unit may be released to finally separate the parachute pack unit from the drone body.

In the present invention, the mechanical locking part is located to protrude from the lower part of the parachute pack part and is located on the locking protrusion member and the drone body with the locking jaw protruding outwardly on the lower end side, and hangs and fixes the locking protrusion member, and the wing arm rotates It may include a lock chuck for releasing the jammed state when unfolded.

In the present invention, the lock chuck part is positioned to be movable up and down in the base body part, and the lower end side of the locking protrusion member is inserted into the collet chuck to hang and fix the locking jaw, and between the collet chuck and the base body part. It includes a chuck supporting spring member for supporting the position of the collet chuck, and the collet chuck is lifted by the rotation of the wing arm portion to release the locking state of the locking jaw.

In the present invention, a chuck-through part through which the collet chuck passes is located in the base body, and a spring seating part hooked on the chuck-through part and seated with the spring member for supporting the chuck protrudes from the lower end of the collet chuck.

In the present invention, the collet chuck includes a plurality of locking pieces spaced apart in the circumferential direction, and the locking pieces protrude inward to the upper end side and a chuck protrusion for hanging and restraining the locking jaw is located, and is bent obliquely to the upper end side and an inclined pressing part for closing the chuck protrusion of the chuck, and the inclined pressing part may be pressed at the entrance of the chuck penetrating part to close the upper end of the collet chuck so that the chuck protrusion is positioned inward.

In the present invention, the chuck groove portion into which the lower end of the collet chuck is inserted is located in the blade arm portion, and an elevation guide surface for guiding the elevation of the collet chuck in the rotational direction is located, and the elevation guide surface is uphill in the rotation direction of the blade arm portion. When the wing arm part rotates with the inclined surface, the collet chuck may be raised and lowered while pushing up the lower end of the collet chuck.

In the present invention, the lock chuck part includes a locking rotary plate member in which an unlocking opening through which the locking jaw passes is located and rotated together with a rotation shaft of the wing arm, wherein the locking rotary plate member is rotated and unfolded when the wing arm is rotated. It is rotated together with the rotation shaft of the wing arm portion to release the restraint by being positioned so that the locking release opening coincides with the locking jaw.

In addition, in order to achieve the above object of the present invention, an embodiment of the method for emitting a drone of a projectile according to the present invention is a projectile moving step in which the projectile is moved by flying to a predetermined position with the projectile, and the projectile is moved to a predetermined position in the moving step. A drone release step of emitting a plurality of drones from the existing projectile, and a drone posture correction step of stabilizing the posture of the drone emitted to the outside of the projectile through the drone release step by spreading a parachute.

In the present invention, the drone posture correction step includes a parachute deployment process in which a parachute is deployed while the drone is released to the outside of the projectile, a drone posture confirmation process to check a possible flight posture of the drone after the parachute deployment process, and a drone in the drone posture confirmation process When it is confirmed that the flight is possible, it may include a parachute separation process of separating the parachute pack unit and a flight process in which the propeller is rotated after the parachute separation process to activate the flight of the drone.

In the present invention, the parachute separation process reconfirms the flightable posture of the drone after releasing the mechanical lock while the wing arm of the folded drone is unfolded, and finally, when the flightable posture of the drone is confirmed in the drone posture reconfirmation process, the magnetic force of the electronic part A drone release method of a projectile, characterized in that the parachute pack part is finally separated from the drone by releasing it.

In the present invention, the drone ejecting step includes a projectile cutting process in which a linear skin cutout is operated to separate the projectile into a plurality of pieces, and a gas generating unit is operated to inflate an airbag located at the center of the projectile, and after the projectile cutting process, the drone A storage box release process in which a plurality of release storage boxes stored inside are released to the outside of the projectile by the expansion force of the airbag, and a drone release process in which a drone is released while being stored inside as the storage box for release released in the storage box release process is separated may include.

In the present invention, the storage box release process releases at least one release storage box that stores the wireless repeater inside, and the drone release process releases the drone from the release storage box together with the wireless repeater stored therein. You can release a radio repeater from your storage box.

The present invention allows the drone to be used as a variety of weapon systems by flying after being released from a projectile, after the posture is stabilized with a parachute, and then performing wartime operations such as reconnaissance at the relevant point, and greatly improves the efficiency when using the drone there is

In addition, the present invention can utilize projectile weapons such as missiles in a more diverse way, preempting reconnaissance technology using drones, greatly improving the efficiency of drone reconnaissance work, and greatly increasing the utility of drones.

1 is a schematic diagram showing an embodiment of a projectile on which a drone equipped with a parachute according to the present invention is mounted.
2 is a cross-sectional view showing an embodiment of a projectile on which a drone equipped with a parachute according to the present invention is mounted.
Figure 3 is a view showing an embodiment of the release box from the projectile is equipped with a drone equipped with a parachute according to the present invention.
4 is a view showing an example in which a drone is emitted from a projectile on which a drone equipped with a parachute according to the present invention is mounted.
5 is a cross-sectional view showing another embodiment of a projectile on which a drone equipped with a parachute according to the present invention is mounted.
6 is a flowchart illustrating an embodiment of a method for releasing a drone of a projectile according to the present invention.
7 and 8 are views showing an embodiment of a drone equipped with a parachute according to the present invention.
9 and 10 are diagrams illustrating an embodiment of a mechanical lock applied to a drone in a drone equipped with a parachute according to the present invention.
11 is a view showing another embodiment of a mechanical lock applied to a drone equipped with a parachute according to the present invention.
12 is a flowchart illustrating a drone posture stabilization step in the drone ejection method of the projectile according to the present invention.

The present invention will be described in more detail.

A preferred embodiment of the present invention will be described in detail with reference to the accompanying drawings as follows. Prior to the detailed description of the present invention, the terms or words used in the present specification and claims described below should not be construed as being limited to conventional or dictionary meanings. Therefore, the configuration shown in the embodiments and drawings described in the present specification is only the most preferred embodiment of the present invention and does not represent all the technical spirit of the present invention, so at the time of the present application, various It should be understood that there may be equivalents and variations.

1 is a schematic diagram showing an embodiment of a projectile equipped with a drone equipped with a parachute according to the present invention, and FIG. 2 is a cross-sectional view showing an embodiment of a projectile equipped with a drone equipped with a parachute according to the present invention 3 is a view showing an embodiment of a release box from a projectile mounted with a drone equipped with a parachute according to the present invention, and FIG. 3 (a) is a discharge box from a projectile equipped with a drone according to the present invention. It is a cross-sectional view showing an embodiment of, Figure 3 (b) is a perspective view showing an embodiment of the release storage box from the projectile is equipped with a drone equipped with a parachute according to the present invention.

An embodiment of a projectile on which a drone equipped with a parachute according to the present invention is mounted will be described in detail below with reference to FIGS. 1 to 3 .

A projectile equipped with a drone equipped with a parachute according to the present invention is a projectile 100 flying to a target point, a plurality of drones 200 positioned inside the projectile 100 and emitted to the outside of the projectile 100 during flight. includes

The drone 200 is a known configuration capable of flying and controlling by induction of radio waves, and a more detailed description thereof will be omitted.

A projectile equipped with a drone equipped with a parachute according to the present invention may be a guided missile or a shell that has a propulsion engine and flies to a target point, or may be a type of various known bullets flying toward a target.

A projectile equipped with a drone equipped with a parachute according to the present invention will be described as an example of a guided missile including a guidance unit 110 , a warhead unit 120 , a fuse unit 130 , and a propulsion unit 140 .

The induction unit 110 is located on the head of the projectile 100 and has a built-in electronic equipment for guiding the projectile 100 to the target point, and the warhead unit 120 and the fuse unit 130 are the body of the projectile 100 . The propulsion unit 140 is a propulsion engine that is located at the rear of the bullet body 100 to generate propulsion force.

The fuse unit 130 may be freely arranged on the front or rear side of the warhead unit 120, and it is disclosed that it is a configuration that can be freely positioned according to the design of the bullet.

The guidance unit 110, the warhead unit 120, the fuse unit 130, and the propulsion unit 140 are known configurations in rockets such as guided missiles, and a more detailed description will be omitted.

For example, the plurality of drones 200 are located in the warhead unit 120 , and a plurality of release storage boxes 400 in which the drones 200 are stored are located in the warhead unit 120 .

The release storage box 400 is made of an elastic material having a certain rigidity or higher, such as urethane and synthetic rubber, and serves to protect the drone 200 stored therein from the release pressure.

The release storage box 400 has a rigidity that minimizes deformation when the projectile 100 is released to the outside of the projectile 100 while cutting the projectile 100 by the deployment of the airbag 310, which will be described later, and is stored inside the drone 200. It should be noted that it can be made of a variety of known materials capable of protecting against discharge pressure.

The release storage box 400 is opened by the force emitted while being released to the outside of the projectile 100 and serves to finally discharge the drone 200 stored therein.

In the interior of the projectile 100 , that is, the warhead 120 , the release storage box 400 is released to the outside of the projectile 100 , and the discharge storage box 400 is opened to finally release the drone 200 to the outside. That is, the drone emitting unit 300 for emitting into the atmosphere is located.

The drone discharge unit 300 includes an airbag 310 positioned at the center of the projectile 100 , and a gas generator 320 that fills the airbag 310 with gas to inflate the airbag 310 .

And, the projectile on which the drone equipped with Mt. Nakhak according to the present invention is mounted is composed of a plurality of storage boxes 400 for release and includes a ring-shaped storage module 400a in which a hollow part is located in the center, and storage module 400a ) has a structure in which a plurality of layers are stacked in the longitudinal direction of the projectile 100 , that is, in the longitudinal direction of the warhead unit 120 .

As an example, the storage box 400 for release has a sector shape in which a donut-shaped box including a hollow part is divided into a plurality, and a donut-shaped box body including a hollow part has a form divided into four.

The projectile on which the drone equipped with a parachute according to the present invention is mounted has a structure in which a storage module 400a including a plurality of release storage boxes 400 is stacked in a plurality in the longitudinal direction of the projectile 100, and a plurality of drones ( 200) can be stored efficiently.

In the hollow of the storage module 400a, the drone emitting unit 300, that is, the gas generating unit 320 and the airbag 310 are positioned, and a plurality of the airbags 310 may be provided.

The gas generator 320 and the airbag 310 are positioned in the longitudinal direction in the bullet 100 to push each storage module 400a stacked in the longitudinal direction from the inside to the outside, respectively, to be released to the outside of the bullet 100. make it possible

The gas generator 320 may be variously modified and implemented using a known gas generator that inflates the airbag 310 by injecting gas into the airbag 310 , and a detailed description thereof will be omitted.

The plurality of airbags 310 are positioned at the boundary of each release storage box 400 to push and release the two release storage boxes 400 in which one airbag 310 is placed facing each other to the outside.

As an example, the storage box 400 for release is formed in a sector shape that is connected to each other and forms a hollow in the center.

The release storage box 400 includes a first storage box member 410 having one side open, and a second storage box member 420 having at least a part open on the other side and inserted into the first storage box member 410, and an airbag 310. It has a structure in which the first storage box member 410 and the second storage box member 420 are separated from each other by the release pressure due to the expansion of the .

3, the storage box 400 for release is shown as having a structure in which the first storage box member 410 and the second storage box member 420 are detachably coupled to each other in the left and right directions, but the first storage box member 410 The coupling direction of the and the second storage box member 420 is not limited thereto, and it is noted that various modifications may be made in the up, down, and diagonal directions.

It is revealed that the release storage box 400 can be variously modified and implemented into a structure having a detachable coupling state when it is released to the outside of the projectile 100 by the release pressure caused by the expansion of the airbag 310 .

A notch groove 100a is positioned on the inner peripheral surface of the warhead 120 to allow the projectile 100 to be incised by the release pressure caused by the expansion of the airbag 310 .

The notch grooves 100a are formed in the longitudinal direction of the projectile 100, and are located in a plurality of spaced apart from the center of the projectile 100 in the circumferential direction so that the projectile 100 is formed by the pressure caused by the expansion of the plurality of airbags 310. While being separated into a plurality of pieces, it is possible to discharge the plurality of storage boxes 400 for discharging to the outside of the bullet body 100 .

The notch groove 100a is located at the boundary between the two release storage boxes 400 on the inner circumferential surface of the projectile 100 so that the two release storage boxes 400 are centered on the notch groove 100a on both sides of the notch groove 100a. is located in the notch so that the notch groove (100a) can be cut more smoothly by the pressure released by the airbag (310).

A projectile on which a drone equipped with a parachute according to the present invention is mounted is positioned to be spaced apart in the circumferential direction on the inner circumferential surface of the projectile 100 and cut the projectile 100 in the longitudinal direction to separate the projectile 100 into a plurality of pieces. It further includes a skin incision 600 .

The linear sheath cutout 600 is a tube initiator 610 for linear incision in which a high explosive 612 is inserted in the metal tube 611, a tube initiator for linear incision 610 is inserted into the initiator insertion groove 621 ) includes a linear cut-out support member 620, a support fixing member 630 for fixing one side of the shaping cut-out support member to the bullet 300.

The support fixing member 630 is an example of a high-tensile bolt for fixing one side of the linear cut-out support member 620 to the bullet by fastening the bolt, and is linear only on one side of the notch groove 100a based on the notch groove 100a. The cut-out support member 620 is fixed to the inner circumferential surface of the bullet body 100 .

For example, the tube detonation unit 610 for linear incision is MDF (Mild-detonating Fuse) stored in the RDX (Research Department Explosive, cyclonite), HNS (Hexanitrostilbene) high explosive 612 in the metal tube 611. do.

The linear sheath cutout 600 is positioned so that the tube initiator 610 for the linear cutout is positioned at a position corresponding to the notch groove 100a, so that the energy of the gunpowder is concentrated in the notch groove 100a so that the bullet can be smoothly cut do.

The initiator insertion groove 621 is opened toward the notch groove 100a so that the gunpowder energy generated after detonation is directed toward the notch groove 100a.

The linear sheath cutout 600 concentrates the energy of the gunpowder generated while the tube detonator 610 for linear incision is detonated in the notch groove to smoothly and linearly cut the projectile and separate it into a plurality of pieces.

In addition to the linear skin cutout 600, an incision device using a flexible linear shaped charge (FLSC) may be used, and an expansion tube-based linear separation device that suppresses the generation of debris and gas and reduces the pyro impact It should be noted that various modifications can be made using a known linear separation device, etc.

The gas generator 320 and the linear skin cutout 600 are operated when the projectile 100 flies and reaches a preset position, may be set using a timer, or set using GPS to confirm the position It should be noted that it can also be controlled from the main control room through wireless communication.

In addition, it is pointed out that the initiating structure for initiating the tube initiator 610 for linear incision can be variously modified and implemented using a known initiating structure.

That is, when the projectile 100 flies and reaches a preset position, the linear shell cutout 600 is operated to separate the projectile 100 into a plurality of pieces through the notch groove 100a, and at the same time the gas generating unit As the gas is supplied to the airbag 310 by the 320 and the airbag 310 rapidly inflates, each release storage box 400 of the storage box module 400a in the hollow portion is pushed to the outside of the bullet body 100 in a plurality of the release storage box 400 is released to the outside of the projectile 100 by the inflation force of the air bag 310 .

And, when the release storage box 400 is released to the outside of the projectile 100 by the expansion force of the airbag 310 as shown in FIG. 4 , the first storage box member 410 and the second storage box member 420 are separated. The drone 200 positioned inside is finally released.

After the drone 200 is released, it automatically flies along a preset flight path to perform operational tasks such as reconnaissance around the environment.

5 is a cross-sectional view showing another embodiment of a projectile on which a drone equipped with a parachute according to the present invention is mounted, and with reference to FIG. 5 , at least one of a plurality of release storage boxes 400 has a radio of the drone 200 A wireless repeater 500 that increases the communication distance may be located.

That is, the projectile on which the drone equipped with a parachute according to the present invention is mounted is located in the bullet body 100, is emitted together with the drone 200, and may further include a wireless repeater 500 for wireless communication of the drone 200. have.

The wireless repeater 500 is a repeater for wireless communication with the drone 200 and a control center that receives information from the drone 200 or controls the operation of the drone 200, and is a known repeater for wireless communication. It should be noted that detailed description is omitted.

A wireless repeater 500 may be located in any one of the storage module 400a of the plurality of storage module 400a stacked in the longitudinal direction of the projectile 100, respectively, in the storage box 400 for release.

The wireless repeater 500 uses the same principle as the drone 200, that is, according to the expansion of the airbag 310, the release storage box 400 is released to the outside of the projectile 100, and then is released from the release storage box 400. It falls to the ground so that the drone 200 can stably wirelessly communicate with the control center so that reconnaissance information photographed from the drone 200 can be smoothly transmitted to the control center.

6 is a process diagram illustrating an embodiment of a method for releasing a drone of a projectile according to the present invention. Referring to FIGS. 2, 5, and 6, an embodiment of a method for discharging a drone of a projectile according to the present invention is a projectile ( A drone ejecting step (S200) of emitting a plurality of drones from the projectile 100 moved to a preset position in the projectile moving step (S100) and moving the projectile by flying to a preset position as 100) (S100) (S200) ) is included.

And, in the drone ejection step (S200), the linear skin cutout 600 is operated to separate the projectile 100 into a plurality of pieces, and the gas generating unit 320 is operated to operate the airbag located in the center of the projectile 100 . After the projectile cutting process (S210) of inflating the 310, the projectile cutting process (S210), the drone 200 is stored inside the plurality of release storage boxes 400 by the inflation force of the airbag 310 of the projectile 100. It includes a drone release process (S230) in which the drone 200 being stored inside is released while the storage box 400 for release emitted in the storage box release process (S220) and the storage box release process (S220) is separated.

In addition, the storage box release process (S220) releases the at least one release storage box 400 that stores the wireless repeater 500 inside, and the drone release process (S230) releases the drone 200 into the release storage box ( The wireless repeater 500 emits the wireless repeater from the storage box 400 for release that is stored inside the wireless repeater 500 with the release box in 400).

That is, in the storage box discharging process (S220), the plurality of discharge storage boxes 400 emitted to the outside of the projectile 100 are separated into a first storage box member 410 and a second storage box member 420, and the drone is stored inside. (200) or the repeater 500 is finally released.

In the drone release method of the projectile according to the present invention, the linear shell cutout 600 is operated to separate the projectile into a plurality of pieces, and the drone 200 is stored inside the drone 200 using the expansion of the airbag 310. (400) is primarily emitted, and the drones 200 are secondarily released from the released storage box 400, so that a plurality of drones 200 are separated from each other and released to a plurality of drones 200. It makes it possible to reliably carry out operations over a wider area.

The drone release method of the projectile according to the present invention uses the expansion of the airbag 310 to primarily release the release storage box 400 while the drone 200 is stored therein, and from the released storage box 400 for the drone. By secondary emitting 200, the drone 200 can be stably released without damage.

Meanwhile, FIGS. 7 and 8 are diagrams illustrating an embodiment of a drone 200 equipped with a parachute according to the present invention, and referring to FIGS. 7 and 8 , a drone 200 equipped with a parachute according to the present invention. The drone body 210 capable of flying, is detachably mounted on the upper part of the drone body 210, and may include a parachute pack unit 220 having a built-in parachute 220a that is spread out after being released from the projectile 100. .

The drone body 210 is rotatably located in the base body 211, the base body 211, in which the rechargeable battery and the flight control unit are located, and the wing arm part in which the propeller rotated by the motor is located at the end side ( 212), and the wing arm portion 212 is folded and inserted into the base body portion 211 to be a foldable drone 200 that can be positioned as an example.

The drone body 210 can be inserted into the interior of the storage box 400 for release in a compact size by being folded and positioned so that the wing arm part 212 is folded and inserted into the base body part 211, thereby increasing the size of the base body part 211. It can be designed as large as possible, thereby increasing the capacity of the rechargeable battery and embedding wireless equipment for stable wireless communication.

The base body part 211 has an arm insertion part 211a that can be stored by folding the wing arm part 212 around the outer surface, and the wing arm part 212 is rotated by the arm rotation part to be folded and stored and unfolded during flight. can be used

The parachute pack unit 220 expands the parachute 220a while the drone 200 is released from within the projectile so that the drone 200 that is released by the inflation force of the airbag 310 can be stabilized to a flightable position.

The parachute pack unit 220 is operated so that the parachute 220a is unfolded when the drone 200 is finally released while the release storage box 400 is separated into the first storage box member 410 and the second storage box member 420. .

The parachute pack unit 220 allows the parachute 220a to automatically unfold after a preset time from the time when the airbag 310 is deployed, so that the drone 200 is finally released from the release storage box 400 and then the parachute 220a Let it unfold automatically.

In addition, the parachute pack unit 220 and the drone main body 210 communicate wirelessly, and the drone main body 210 is emitted by the acceleration force generated while the drone main body 210 is emitted from an acceleration sensor located in the drone main body 210 . It detects that and when the emission signal is sensed, it is transmitted to the parachute pack unit 220 so that the parachute pack unit 220 can operate to open the parachute 220a.

In addition, the parachute pack unit 220 may receive a separate deployment signal from the induction unit 110 of the projectile 100 to deploy the parachute 220a, and in addition, the drone 200 can be deployed using a known parachute deployment system. It is noted that in the state released to the outside of (100), the parachute (220a) can be spread out.

Meanwhile, the drone 200 equipped with a parachute according to the present invention may further include a parachute mounting unit 230 for detachably mounting the parachute pack unit 220 from the drone body.

The parachute mounting unit 230 may include a mechanical locking unit 231 for releasing the restraint of the parachute pack unit 220 by the rotation of the wing arm unit 212 while the wing arm unit 212 is rotated.

The mechanical locking part 231 is located to protrude to the lower part of the parachute pack part 220 and is located on the locking protrusion member 232 with the locking jaw protruding to the outside on the lower end side, the drone body 210, and the locking protrusion member 232 It may include a lock chuck part 233 for locking and fixing the wing arm part 212 and releasing the jammed state when the wing arm part 212 is rotated and unfolded.

In addition, the parachute mounting unit 230 includes an electromagnet unit 237a positioned on the upper surface of the parachute pack unit 220 or the drone main body 210 by the magnetic force of the electromagnet unit 237a to attach the parachute pack unit 220 to the drone body 210 . ) may include an electronic locking part 237 for restraining the upper surface.

The parachute mounting unit 230 includes a mechanical locking unit 231 that releases the restraint of the parachute pack unit 220 by the rotation of the wing arm unit 212 while the wing arm unit 212 is rotated and the parachute pack unit 220 or the drone body 210 ) including an electromagnet unit 237a located on the upper surface of the electromagnet unit 237a magnetic force to bind the parachute pack unit 220 to the upper surface of the drone body 210 It may include an electromagnetic locking unit 237 .

The parachute mounting part 230 includes a mechanical locking part 231 and an electronic locking part 237 and rotating the wing arm part 212 in the state in which the parachute 220a is unfolded to primarily lock the mechanical locking part 231. Release and check whether the drone 200 is stabilized in the flightable posture, and when the drone 200 is positioned in the flightable posture, the electronic locking unit 237 is released and the parachute pack unit 220 is finally installed in the drone body 210 ) is separated and removed.

In a state in which the drone 200 is released to the outside of the projectile 100 and the parachute pack unit 220 is unfolded, the flight control unit of the drone 200 uses a gyro sensor in the drone 200 to check whether the drone 200 is in a flying position. And the wing arm 212 is rotated to position it in the operating position, and at this time, the mechanical locking part 231 is operated by the rotation of the wing arm 212 to release the restraint of the parachute pack part 220 .

And, in the state in which the wing arm unit 212 is unfolded, the flight control unit of the drone 200 uses a gyro sensor in the drone 200 to finally check whether the drone 200 is in a flying position and stops the operation of the electromagnet unit 237a. to release the restraint of the electronic locking unit 237 to separate and remove the parachute pack unit 220 from the drone main body 210, and immediately operate the propeller so that the drone main body 210 flies in a preset flight path to perform operational tasks make it possible

9 and 10 are diagrams illustrating an embodiment of a mechanical locking unit 231 applied to the drone 200 in a projectile on which a drone equipped with a parachute according to the present invention is mounted, see FIGS. 9 and 10 The lower lock chuck part 233 is located on the base body part 211 so as to be movable up and down, and the lower end side of the locking protrusion member 232 is inserted into the collet chuck 234, collet chuck for hooking and fixing the locking jaw. and a chuck supporting spring member 235 for supporting the position of the collet chuck 234 between the 234 and the base body 211 , and the collet chuck 234 is formed by the rotation of the wing arm 212 . It lifts and clears the jammed state of the jamming jaw

In addition, the chuck piercing portion 211b through which the collet chuck 234 passes is located in the base body portion 211, and is caught by the chuck piercing portion 211b at the lower end of the collet chuck 234 and a spring member 235 for supporting the chuck. The spring seating portion 234d on which is seated is positioned to protrude.

The collet chuck 234 includes a plurality of engaging pieces 234a spaced apart from each other in the circumferential direction in the structure shown in FIG. The chuck protrusion 234b is positioned, and it is provided with an inclined pressing part 234c that is bent to close the chuck protrusion 234b of the upper end side.

The inclined pressing portion 234c is pressed at the entrance of the chuck penetrating portion 211b to close the upper end of the collet chuck 234 so that the chuck protrusion 234b is positioned inward.

A chuck groove 212a into which the lower end of the collet chuck 234 is inserted is positioned in the wing arm 212 , and an elevation guide surface for guiding the elevation of the collet chuck 234 in the rotational direction is positioned.

The elevating guide surface is an inclined surface inclined upward in the rotational direction of the wing arm 212 so that the collet chuck 234 is elevated while pushing and lifting the lower end of the collet chuck 234 when the wing arm is rotated.

The collet chuck 234 is raised and lowered while the wing arm part 212 is rotated while compressing the spring member 235 for supporting the chuck, and the upper end side is widened while the chuck protrusion 234b releases the locking state of the locking jaw. The restraint of the parachute pack unit 220 is released.

The collet chuck 234 has a known collet chuck structure in which the lock is released while the end side is widened when pushed up, and a more detailed description thereof will be omitted.

Meanwhile, FIG. 10 is a view showing another embodiment of the mechanical locking unit 231 applied to the drone 200 in the projectile on which the drone equipped with a parachute according to the present invention is mounted. Referring to FIG. 10, the lock chuck unit ( 233 may include a locking rotation plate member that is positioned with the locking release opening 236a through which the locking jaw passes and is rotated along with the rotation shaft of the wing arm 212 .

The locking rotation plate member is rotated together with the rotation shaft of the blade arm part 212 when the blade arm part 212 is rotated and unfolded so that the lock release opening 236a is positioned to coincide with the locking jaw to release the restraint, and the parachute pack part 220 to be separated from the drone body 210 .

On the other hand, FIG. 11 is a flowchart illustrating the drone posture correction step (S300) in the method for discharging a drone of a projectile according to the present invention, and referring to FIGS. 6 and 11 , the method of discharging a drone of a projectile according to the present invention is performed It further includes a drone posture correction step (S300) for stabilizing the flight of the drone 200, and the drone posture correction step (S300) is a parachute deployment process in which a parachute is deployed while the drone 200 is released to the outside of the bullet body 100 (S310), after the parachute deployment process (S310), the drone posture confirmation process (S320), the drone posture confirmation process (S320) to confirm the flightable posture of the drone 200 It includes a parachute separation process (S330) of separating the parachute pack unit 220, a flight process (S340) in which the flight of the drone 200 is activated by rotating the propeller after the parachute separation process (S330).

In the parachute separation process (S330), the wing arm part 212 of the folded drone 200 is unfolded and the mechanical lock is released, and then the flightable posture of the drone 200 is reconfirmed, and finally, in the drone 200 posture reconfirmation process, the drone When the flight posture of 200 is confirmed, the magnetic force of the electronic unit is released to finally separate the parachute pack unit 220 from the drone 200 .

The flight posture of the drone 200 may be confirmed by the flight controller that controls the flight of the drone 200 by a gyro sensor located in the drone 200, and the drone posture correction step (S300) of the drone 200 By separating the parachute pack unit 220 in a state in which the flight posture is completely made, the drone 200 is prevented from falling due to the shock emitted, and the drone 200 is stably reconnaissance work through the flight process (S340). to be able to carry out its operational tasks.

In addition, in the drone posture correction step (S300), in a state in which the flight posture of the drone 200 is completely made, the parachute pack unit 220 is separated and the propeller is operated to make the drone 200 fly stably. By increasing the flight time and increasing the execution time for the operational task of the drone 200, the operational efficiency of the drone 200, such as reconnaissance, is improved.

The present invention allows the drone to be used as a variety of weapon systems by allowing the drone to be used as a variety of weapon systems by performing wartime operations such as reconnaissance at the relevant point by flying after the posture is stabilized with a parachute after being released from the projectile, and greatly improving the efficiency when using the drone have.

In addition, the present invention can utilize projectile weapons such as missiles more diversely, preoccupy reconnaissance technology using drones, greatly improve the efficiency of drone reconnaissance work, and greatly increase the utilization of drones.

It should be noted that the present invention is not limited to the above-described embodiments, and can be implemented with various modifications without departing from the gist of the present invention, which is included in the configuration of the present invention.

100: bullet body 100a: notch groove
110: induction part 120: warhead part
130: fuse section 140: propulsion section
200: drone 210: drone body
211: base body part 211a: female insertion part
211b: Chuck through part 212: Wing arm part
212a: chuck groove 220: parachute pack part
220a: parachute 230: parachute mounting part
231: mechanical lock 232: locking protrusion member
233: lock chuck 234: collet chuck
234a: jamming side 234b: chuck
234c: inclined pressing part 234d: spring seating part
235: spring member for chuck support 236: rotating plate member
236a: jam release opening 237: electronic locking part
237a: electromagnet 300: drone emitter
310: air bag 320: gas generating unit
400: storage box for release 400a: storage box module
410: first storage box member 420: second storage box member
500: wireless repeater 600: linear skin cutout
610: tube initiator for linear incision 611: metal tube
612: high explosives 620: linear cut support member
630: support fixing member
S100: projectile movement step S200: drone release step
S210: shell cutting process S220: storage box release process
S230: Drone release process S240: Repeater release process
S300: drone posture correction step S310: parachute deployment process
S320: Drone posture check process S330: Parachute separation process
S340: Flight process

Claims (18)

drone body capable of flying; and
Drone equipped with a parachute, characterized in that it is detachably mounted on the upper portion of the drone body and includes a parachute pack unit having a built-in parachute that unfolds after being released from the bullet.
The method according to claim 1,
The drone body is
a base body in which a rechargeable battery and a flight controller are located; and
It is rotatably located in the base body portion and includes a wing arm portion in which a propeller rotated by a motor is located on the end side,
A drone equipped with a parachute, characterized in that the wing arm is folded and inserted into the base body to be positioned.
3. The method according to claim 2,
Drone equipped with a parachute, characterized in that it further comprises a parachute mounting unit for detachably mounting the parachute pack unit and the drone body.
4. The method according to claim 3,
The parachute mounting unit,
Drone equipped with a parachute, characterized in that it comprises a mechanical locking part for releasing the restraint of the parachute pack part by the rotation of the wing arm part while the wing arm part is rotated.
4. The method according to claim 3,
The parachute mounting unit,
A drone equipped with a parachute, comprising an electromagnetic locking part for restraining the parachute pack part to the upper surface of the drone body by the magnetic force of the electromagnet, including the parachute pack part or an electromagnet part located on the upper surface of the drone body
4. The method according to claim 3,
The parachute mounting unit,
a mechanical locking part for releasing the restraint of the parachute pack part by rotation of the wing arm part while the wing arm part is rotated; and
A drone equipped with a parachute, comprising an electromagnetic locking part for restraining the parachute pack part to the upper surface of the drone body by the magnetic force of the electromagnet part, including an electromagnet part located on the upper surface of the parachute pack part or the drone body.
7. The method of claim 6,
The parachute mounting unit,
First, by rotating the wing arm in a state in which the parachute is unfolded, including the mechanical locking part and the electronic locking part, the mechanical locking part is unlocked and it is confirmed that the drone is stabilized in a flying posture A drone equipped with a parachute, characterized in that the parachute pack part is finally separated from the drone body.
5. The method according to claim 4,
The mechanical lock is
a locking protrusion member positioned to protrude from the lower part of the parachute pack part and having a locking jaw protruding outward from the lower end side; and
The drone is equipped with a parachute, characterized in that it comprises a locking chuck located in the drone main body to hang the locking protrusion member and to release the locking state when the wing arm is rotated and unfolded.
9. The method of claim 8,
The lock chuck unit,
a collet chuck positioned so as to be movable up and down in the base body part, the lower end side of the locking protrusion member being inserted thereinto, and fixing the locking jaw; and
and a chuck supporting spring member for supporting the position of the collet chuck between the collet chuck and the base body,
The collet chuck is raised and lowered by the rotation of the wing arm, the drone equipped with a parachute, characterized in that the locking state of the locking jaw is released.
10. The method of claim 9,
A chuck penetrating portion through which the collet chuck passes is located in the base body portion,
A drone equipped with a parachute, characterized in that the lower end of the collet chuck is positioned to protrude a spring seat portion caught on the chuck through portion and on which the spring member for supporting the chuck is seated.
11. The method of claim 10,
The collet chuck includes a plurality of engaging pieces positioned to be spaced apart in the circumferential direction,
The locking piece has a chuck protrusion that protrudes inward to the upper end side and hangs and constrains the locking jaw, is bent obliquely and has an inclined pressing part for closing the chuck protrusion on the upper end side,
Drone equipped with a parachute, characterized in that the inclined pressing part is pressed at the entrance of the chuck penetrating part to close the upper end of the collet chuck so that the chuck protrusion is located inward.
10. The method of claim 9,
A chuck groove portion into which the lower end of the collet chuck is inserted is located in the wing arm portion, and an elevation guide surface for guiding the elevation of the collet chuck in the rotational direction is located;
The elevating guide surface is an inclined surface inclined upward in the rotational direction of the wing arm, and when the wing arm rotates, the lower end of the collet chuck is pushed up and the collet chuck is raised and lowered.
9. The method of claim 8,
The lock chuck unit,
and a locking rotation plate member in which an unlocking opening through which the locking jaw passes is located and rotated together with the rotation shaft of the wing arm,
The locking rotation plate member is rotated together with the rotation shaft of the blade arm when the blade arm is rotated and unfolded to release the restraint by positioning the locking opening to coincide with the locking jaw.
A projectile moving step of moving by flying to a predetermined position with the projectile;
a drone emitting step of emitting a plurality of drones from the projectile moved to a predetermined position in the projectile moving step; and
and a drone posture correction step of stabilizing the posture of the drone emitted to the outside of the projectile through the drone ejection step by unfolding a parachute.
15. The method of claim 14,
The drone posture correction step is,
Parachute deployment process in which the parachute is deployed as the drone is released to the outside of the projectile;
After the parachute deployment process, the drone posture check process for confirming the flying posture of the drone;
Parachute separation process of separating the parachute pack unit when it is confirmed that the flight of the drone is possible in the drone posture confirmation process; and
After the parachute separation process, the propeller is rotated to activate the flight of the drone.
16. The method of claim 15,
In the parachute separation process, the wing arm of the folded drone is unfolded, the mechanical lock is released, the drone's flightable posture is reconfirmed, and the drone's flightable posture is finally confirmed in the drone posture reconfirmation process. A drone ejection method of a projectile, characterized in that the pack part is finally separated from the drone.
15. The method of claim 14,
The drone release step is,
a shell cutting process in which the linear skin cutout is operated to separate the projectile into a plurality of pieces, and the gas generator is operated to inflate the airbag located at the center of the projectile;
a storage box discharging process of discharging a plurality of discharge storage boxes stored inside the drone to the outside of the projectile by the expansion force of the airbag after the ammunition cutting procedure; and
A drone ejection method of a projectile comprising a drone ejection process in which a drone being stored therein is released as the release storage box released in the storage box release process is separated.
18. The method of claim 17,
The storage box release process releases at least one storage box for release that holds the wireless repeater inside,
The drone ejection process is a drone ejection method of a projectile, characterized in that the radio repeater is released from the release storage box stored inside the drone together with the release box from the release storage box.

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