JP2021063616A - Capture net extension airframe device - Google Patents

Abstract

To provide a capture net extension airframe device having a long effective range capable of being ejected by a gas cylinder launcher for capturing a small unmanned aircraft flying in the sky.SOLUTION: The capture net extension airframe device according to the invention has: a case in a cylinder shape having one closed end; a capture net; a plurality of weights mounted to an outer peripheral edge part of the capture net; a discharge device for discharging gas for ejection for being ejected from the case and gas for dispersion for dispersing the plurality of weights in a radial direction, delayed by a predefined time from a generation of the gas for ejection; and a packaging body for enclosing an outer periphery of the plurality of weights and the capture net in the state where the plurality of weights and the capture net are arranged in the order of the plurality of weights and the capture net from the discharge device side, wherein the discharge device comprises a missile being stored in the case in the state where the discharge device is positioned at the closed end side of the case, and a flying stabilization member fixed to the missile at the end side where the capture net is arranged, extending backward in a flying direction of the missile when the missile is ejected from the case and stabilizing a flying attitude of the missile ejected from the case.SELECTED DRAWING: Figure 2

Description

The present invention relates to a capture network deployment flight device that is used for capturing an unmanned aerial vehicle (including an unmanned floating aircraft such as a multicopter) flying over the sky and can be ejected by a gas cylinder launcher.

Unmanned aerial vehicles that fly by remote control or automatic control using wireless communication are generally provided. Unmanned aerial vehicles are used for play purposes and for aerial photography with on-board digital cameras (including digital video cameras). In addition, unmanned aerial vehicles are used, for example, for the purpose of inspecting places where it is difficult for humans to enter and grasping the situation. On the other hand, the flight of unmanned aerial vehicles in no-fly zones such as important facilities and attacks by unmanned aerial vehicles carrying substances and explosives that damage public safety have been regarded as problems, and these incidents have occurred. ing.

Unmanned aerial vehicles with such dangers are required to be dealt with from outside the range of influence on substances and explosives that damage public safety. Therefore, for example, an unmanned aerial vehicle is flown, and a capture net attached to the lower part of the unmanned aerial vehicle is entwined with the unmanned aerial vehicle to be captured to make the unmanned aerial vehicle unflyable, or a capture net installed on the unmanned aerial vehicle A method has been devised, such as injecting the aircraft toward the unmanned aerial vehicle to be captured, deploying the ejected capture network, entwining it with the unmanned aerial vehicle to be captured, and making it impossible to fly. In addition, as a method of capturing the criminal on the ground, there is a method of releasing a combination consisting of a weight and a net package from a gun, deploying a net while flying the released combination, and capturing the criminal by the deployed net. Proposed (see Patent Document 1).

Special Table 2000-513089

In the restraint net system disclosed in Patent Document 1, the effective capture range of the criminal is, for example, 1.5 m or less, and the effective capture range is narrow. Therefore, when such a restraint net system is used when capturing an unmanned aerial vehicle, it is necessary to fly the combination body from outside the above-mentioned range of influence, and therefore it is necessary to increase the flight distance. For example, in order to increase the flight distance of the combination, it is necessary to increase the amount of ammunition released. Generally, a moment (hereinafter referred to as a tipping moment) acts on the center of gravity of an object. Since the overturning moment destabilizes the flight attitude of the object when it flies, simply increasing the amount of ammunition released does not stabilize the flight attitude of the combination, and the flight attitude of the combination is not stable. It is difficult to increase the flight distance.

The present invention has been made to meet such a problem, and in order to capture a small unmanned aerial vehicle flying over the sky, it is determined to provide a capture network deployment flight device having a long effective range that can be ejected by a gas cylinder launcher. is there.

The present invention has been invented to solve the above problems, and the capture net deployment flight device of the present invention includes a tubular case with one end closed, a capture net, and an outer peripheral edge portion of the capture net. A plurality of weights attached to the case, an injection gas to be ejected from the case, and a discharge device for discharging the scattering gas for scattering the plurality of weights in the radial direction with a predetermined time delay from the generation of the injection gas. The plurality of weights and the catching net are arranged in the order of the plurality of weights and the catching net from the discharge device side, and the plurality of weights and the packaging body surrounding the outer periphery of the catching net are provided. Then, the projectile housed in the case with the release device located on the closed end side of the case and the projectile fixed to the projectile on the end side where the capture net is arranged, and fly. It is characterized by including a flight stabilizing member that extends rearward in the flight direction of the projectile when the body is ejected from the case and stabilizes the flight attitude of the projectile ejected from the case.

Further, it includes a protective member which is arranged at an end portion opposite to one end side on which the release device is arranged to protect the catching net packaged in the package and to which the flight stabilizing member is fixed. The package is characterized by surrounding the outer periphery of the protective member in addition to the plurality of weights and the catch net.

Further, the flight stabilizing member is characterized in that the overturning moment acting on the flying flying object is canceled by a moment based on the drag force of the flying stabilizing member acting on the flying flying object.

In this case, the total area of the flight stabilizer is set so that the moment based on the drag force of the flight stabilizer acting on the flying object is equal to or greater than the overturning moment acting on the flying object during flight. And.

Further, the flight stabilizing member is a ribbon, and the width of the ribbon is preferably set to be equal to or less than a value obtained by dividing the outer peripheral length of the flying object by the number of ribbons fixed to the flying object. The width of the ribbon is preferably 5 mm or more and 40 mm or less. Further, the number of the ribbons is preferably 3 or more and 24 or less, and the ribbons are preferably arranged on the projectile at predetermined angular intervals. Further, the width of the ribbon is preferably 80 mm or more and 500 mm or less.

The release device includes a first tubular member that stores a release agent that generates the injection gas, a second tubular member that stores the developing agent that generates the scattering gas, and combustion of the release agent. It is characterized by including a third tubular member that stores a delaying drug that ignites the developing drug stored in the second tubular member after the elapse of the predetermined time.

Here, it is preferable that the second tubular member is attached to the third tubular member housed in the first tubular member.

Further, the plurality of weights are fixed to the discharge device in a state of being arranged along the outer circumference of the second tubular member.

In this case, it is provided in a space formed by arranging the plurality of weights along the outer circumference of the second tubular member, and has a damage prevention member for preventing damage to the capture net due to combustion of the developing agent. Is preferable.

The case is characterized by having a detonator containing an explosive that ignites the release agent at a closed end.

Further, the case preferably includes a case body having a tubular shape with both ends opened, and a holder fixed to one end of the case body while holding the detonator.

According to the present invention, in order to capture a small unmanned aerial vehicle flying over the sky, it is possible to provide a capture network deployment projectile having a long effective range that can be ejected by a gas cylinder launcher.

It is sectional drawing which shows an example of the capture net deployment flight apparatus of this invention. It is a perspective view which shows by disassembling the capture net deployment flight apparatus shown in FIG. It is sectional drawing which illustrates the structure inside the case body. (A) is a diagram when a square-shaped capture net is deployed, and (b) is a diagram when an octagon-shaped capture net is deployed. It is sectional drawing which shows an example of a discharge device. It is a figure explaining the moment acting on a flying flying object. It is a figure which shows the movement from the injection of a flying object to the capture of the unmanned aerial vehicle to be captured. (A) The combustion flow from the detonator being hit by the hammer to the ignition of the release agent, and (b) is the combustion flow from the ignition of the release agent to the ignition of the deploying agent. It is a figure explaining the content of the verification test of the flight attitude of a flying object. It is a figure which shows the specification of the ribbon used for a flying object. It is a graph which shows the time transition of the flight attitude (pitch angle).

Hereinafter, the capture net deployment flight apparatus of the present invention will be described with reference to the drawings.

FIG. 1 is a cross-sectional view showing an example of a capture net deployment flight device, FIG. 2 is a perspective view showing an exploded view of the capture net deployment flight device, and FIG. 3 is a cross-sectional view showing a configuration of a case body. The capture net deployment flight device 10 includes a case 15, a protective cap 16, and a flying object 17. The case 15 has a case body 21 and a case holder 22.

In the present embodiment, the case 15 in which the case body 21 and the case holder 22 are made of separate members will be described as an example, but the case may be a case in which the case body and the case holder are integrally provided.

The case body 21 is, for example, a cylindrical member with both ends open. The material of the case body 21 is, for example, a metal such as steel, copper alloy, aluminum alloy, magnesium alloy, or titanium. The case body 21 holds a case holder 22 at one end in the axial direction (C1 direction in FIG. 1) and a protective cap 16 at the other end. The case body 21 has a flying object storage unit 21a for storing the flying object 17 and a holder storage unit 21b for storing the case holder 22. The inner diameter D1 of the flying object storage portion 21a is larger than the inner diameter D2 of the holder storage portion 21b. Therefore, a stepped surface 21c based on the difference in inner diameter is formed between the flying object storage portion 21a and the holder storage portion 21b. A release device 31 constituting the flying object 17, which will be described later, is abutted against the stepped surface 21c.

Further, in the holder storage portion 21b, the inner diameter D3 is larger than the inner diameter D2 of the holder storage portion 21b in a predetermined range A1 from the end surface 21d of the case main body 21. In the predetermined range A1 from the end surface 21d of the case body 21, the packing 25 attached to the case holder 22 enters the space 21e having an inner diameter D3 larger than the inner diameter D2 of the holder storage portion 21b.

The case holder 22 is a member attached to the end surface 21d side of the case body 21. The material of the case holder 22 is, for example, a metal such as steel, copper alloy, aluminum alloy, magnesium alloy, or titanium. The case holder 22 has a flange portion 22a protruding from the outer peripheral surface of the case holder 22 at one end in the axial direction. Further, the case holder 22 has a groove portion 22b over the entire circumference of the outer peripheral surface at a position close to the flange portion 22a. The groove portion 22b stores and holds the annular packing 25.

The case holder 22 has a storage space 22c into which one end of the discharge device 31, which will be described later, is inserted into an end portion on the side opposite to the one end side on which the flange portion 22a is formed in the axial direction. Further, the case holder 22 has a detonator storage space (not shown) for accommodating the detonator 26 on one end side where the flange portion 22a is formed. Reference numeral 22d in FIG. 1 is provided between the detonator storage space and the storage space 22c, and is a fire transmission hole (flash) through which sparks and combustion gas generated when the explosive provided inside the detonator 26 burns. Hall).

The packing 25 is an annular member having a circular cross-sectional shape. The material of the packing 25 is, for example, rubber such as nitrile rubber and urethane rubber, and synthetic resin such as ABS resin, polyethylene, polyacetal, polycarbonate and polyurethane. The packing 25 is inserted and held in the groove portion 22b of the case holder 22. A part of the packing 25 is exposed from the groove 22b of the case holder 22 in a state where the packing 25 is inserted and held in the groove 22b of the case holder 22. When the case holder 22 is attached to the case body 21 in this state, the packing 25 is in a state of being pressed against the inner peripheral surface 21f of the case body 21 and the bottom surface of the groove portion 22b of the case holder 22.

The protective cap 16 is attached to the other end of the case body 21 opposite to one end to which the case holder 22 is attached. By attaching the protective cap 16 to the case body 21, the protective cap 16 protects the flying object 17 housed inside the case 15 when the capture net deployment flying device 10 is stored. The protective cap 16 is removed when the capture net deployment flight device 10 is loaded into the gas cylinder launcher 70 described later. The material of the protective cap 16 is, for example, a metal such as steel, copper alloy, aluminum alloy, magnesium alloy, or titanium, or a synthetic resin such as ABS resin, polyethylene, polyacetal, polycarbonate, or polyurethane.

The projectile 17 includes a catch net 28, a weight 29, a release device 31, a protective plate (corresponding to the damage prevention member according to claim) 32, a protective lid (corresponding to the protective member according to claim) 33, and a packaging body 34. Etc.

The capture net 28 is developed by radially scattering weights 29 attached to the outer peripheral edge of the capture net 28 via a string member. The material of the catch net 28 is a thread such as kepler, vectran, polyester, nylon, cotton, or silk. Further, as shown in FIG. 4A or FIG. 4B, the catching net 28 may be, for example, a catching net 28'having a square outer shape, or a catching net 28 having an octagonal outer shape. The outer shape of the capture net 28 may be a polygon other than a square shape or an octagonal shape, as long as it can be entangled with the unmanned aerial vehicle to be captured after the capture net 28 is deployed. It may have a shape or another outer shape. The capture net 28 is folded in a state where a plurality of weights attached to the outer peripheral edge are put together, and is incorporated into the projectile 17 in the folded state. Is done.

A plurality of weights 29 are attached to the outer peripheral edge of the capture net 28 via string members (not shown). Examples of the position of the capture net 28 to which the weight 29 is attached include the midpoint of the line connecting the vertices of the capture net 28 and the adjacent vertices. The material of the weight 29 is, for example, a metal such as steel, copper alloy, aluminum alloy, magnesium alloy, or titanium. Although FIG. 2 shows a case where eight weights 29 are used, the number of weights 29 is set according to the outer shape of the capture net 28.

Here, in the state of forming the flying object 17, the weight 29 is arranged along the outer circumference of the deployable medicine case 43 of the release device 31. The weight 29 is fixed to the outer cylinder 41 of the discharge device 31 with double-sided tape or the like in a state of being arranged along the outer circumference of the deployable drug case 43 of the release device 31.

The release device 31 is a device for ejecting the projectile 17 from the case 15 and for deploying the capture net 28 by radially scattering the weight 29 while the projectile 17 is flying. As shown in FIG. 5, the release device 31 includes an outer cylinder (corresponding to the first tubular member according to claim) 41, an inner cylinder (corresponding to the third tubular member according to claim) 42, and a developing agent. It has a case (corresponding to the second tubular member according to claim) 43.

The outer cylinder 41 is a member having a shape in which cylinders having different outer diameters are combined so as to be coaxial in the axial direction (C2 direction in FIG. 5). The material of the outer cylinder 41 is a synthetic resin such as ABS resin, polyethylene, polyacetal, polycarbonate, and polyurethane. As an example, the shape of the outer cylinder is a combination of cylinders having different outer diameters so as to be coaxial in the axial direction, but the shape of the outer cylinder is not limited to this embodiment. An appropriate shape can be used.

The outer cylinder 41 has a release agent storage portion 41c for storing the release charge 45 and an inner cylinder storage portion 41d for storing the inner cylinder 42 from one end surface 41a having a small outer diameter to the other end surface 41b having a large outer diameter. , The release drug storage section 41c, and the inner cylinder storage section 41d in this order. Here, the inner diameter of the release drug storage portion 41c is smaller than the inner diameter of the inner cylinder storage portion 41d. Therefore, a stepped surface 41e due to the difference in inner diameter is provided between the release agent storage portion 41c and the inner cylinder storage portion 41d. The inner cylinder 42 is abutted against the stepped surface 41e. Further, the outer cylinder 41 has a groove portion 41f on the outer peripheral surface over the entire circumference. The packing 46 is stored and held in the groove portion 41f.

The packing 46 is an annular member having a rectangular or circular cross section. The material of the packing 46 is, for example, rubber such as nitrile rubber and urethane rubber, and synthetic resin such as ABS resin, polyethylene, polyacetal, polycarbonate and polyurethane.

The release agent 45 is provided to eject the projectile 17 housed inside the case 15 from the inside of the case 15 by the combustion gas generated at the time of combustion (corresponding to the injection gas according to the claim). The release agent 45 is, for example, black powder, smokeless powder, or the like. The release agent 45 is ignited by a fire type based on the combustion of the explosive in the detonator 26 propagated from the fire transmission hole 22d to the storage space 22c. The combustion of the explosive in the detonator 26 is caused by the striking of the gas cylinder launcher 70, which will be described later.

The ignited release agent 45 burns from one end surface 41a toward the other end surface 41b. At that time, combustion gas is generated. The combustion gas is filled in the region between the inner peripheral surface of the storage space 22c and the discharge device 31. When the pressure of the combustion gas filled in this region becomes equal to or higher than a predetermined value, the flying object 17 housed inside the case 15 is pushed out toward the outside of the case.

The release agent storage portion 41c described above is sealed by attaching a holding seal 47 to one end surface 41a with the release agent 45 loaded. The holding seal 47 is, for example, an aluminum seal. The material of the holding seal 47 may be any material that is easily destroyed by the kind of fire or combustion gas caused by the burning of the explosive inside the detonator 26.

The packing 46 is stored and held in the groove portion 41f of the outer cylinder 41. A part of the packing 46 is exposed from the groove 41f of the outer cylinder 41 in a state of being inserted and held in the groove 41f of the outer cylinder 41. For example, when the flying object 17 is housed in the case body 21, the packing 46 is in a state of being pressed against the bottom surface of the groove 41f of the outer cylinder 41 and the inner peripheral surface 21g of the case body 21. As described above, the packing 25 is pressed against the inner peripheral surface 21f of the case body 21 and the bottom surface of the groove portion 22b of the case holder 22. Therefore, when the projectile 17 is housed inside the case 15, the internal space (not shown) of the case 15 between the packing 25 and the packing 46 is hermetically maintained.

The inner cylinder 42 is stored in the inner cylinder storage portion 41d of the outer cylinder 41. The material of the inner cylinder 42 is, for example, a metal such as steel, copper alloy, aluminum alloy, magnesium alloy, or titanium, or a synthetic resin such as ABS resin, polyethylene, polyacetal, polycarbonate, or polyurethane.

The inner cylinder 42 has a Nobutoki medicine storage portion 42a on one end side in the axial direction (C2 direction in FIG. 5) and a locking portion 42c protruding from the end surface 42b on an end surface 42b opposite to the one end side in the axial direction. Have. An insertion hole 42d that communicates with the Nobutoki medicine storage portion 42a is provided at the center of the locking portion 42c provided on the inner cylinder 42. When the Nobutoki medicine cylinder 48 is stored in the Nobutoki medicine storage portion 42a, the fast-firing wire 48a protruding from the Nobutoki medicine cylinder 48 is inserted into the insertion hole 42d. In the state where the Nobutoki medicine cylinder 48 is housed in the inner cylinder 42, the fast-fire wire 48a is in a state of protruding outward from the locking portion 42c.

The Nobutoki medicine cylinder 48 stores and holds the Nobutoki medicine 49. The deferring agent 49 is an agent for delaying the ignition of the developing agent 51 (or the burning of the developing agent 51) described later with respect to the ignition of the releasing agent 45 (or the burning of the releasing agent 45). The Nobutoki 49 is an explosive such as a boron-based Nobutoki or a manganese-based Nobutoki. The delay time from the ignition of the releasing agent 45 to the ignition of the developing agent 51 can be adjusted by adjusting the doses of the releasing agent 45 and the deferring agent 49.

The fast-fire line 48a stores black powder as an example inside. In the flash point 48a, the internal explosive ignites and burns when a predetermined time elapses after the deferring agent 49 burns. The fast-fire line 48a burns from the root side of the Nobutoki medicine cylinder 48 toward the tip of the fast-fire line 48a. At the time of this combustion, the developing agent 51, which will be described later, ignites, and the developing agent 51 starts burning.

The developing drug case 43 is a tubular member with one end closed. The material of the developing agent case 43 is paper or the like, as well as synthetic resins such as ABS resin, polyethylene, polyacetal, polycarbonate, and polyurethane. That is, the developing agent case 43 may be made of a material that is easily crushed by the combustion of the developing agent 51 or the combustion gas generated by the combustion of the developing agent 51.

The deployable medicine case 43 is attached to the locking portion 42c of the inner cylinder 42 with the deployable medicine 51 stored inside. Reference numeral 43a is an engaging portion that is engaged with the locking portion 42c of the inner cylinder 42. When the engaging portion 43a of the deploying medicine case 43 was engaged with the locking portion 42c of the inner cylinder 42 (the deploying medicine case 43 was attached to the inner cylinder 42), it was inserted into the insertion hole 42d of the locking portion 42c. The fast-firing wire 48a is held in a state of being inserted inside the deploying agent 51 housed in the deploying agent case 43.

A groove 43b is provided on the outer peripheral surface of the deployable medicine case 43 over the entire circumference. The groove portion 43b facilitates the destruction of the developing agent case 43 by the combustion gas generated when the developing agent 51 is burned. In FIG. 5, the groove 43b is illustrated at one location on the outer peripheral surface of the deployable medicine case 43 with respect to the axial direction of the deployable medicine case 43, but the groove portions 43b are provided at a plurality of locations. Can be provided in.

The developing agent 51 ignites due to the combustion of the flash point 48a and starts combustion, and at the time of the combustion, a combustion gas (corresponding to the scattering gas according to the claim) is generated. The developing agent 51 is, for example, black powder, smokeless powder, or the like. The developing medicine case 43 is destroyed by the combustion gas generated by the combustion of the developing medicine 51, and the weight 29 arranged on the outer periphery of the developing medicine case 43 is scattered in the radial direction.

Returning to FIG. 2, in the protective plate 32, when the deploying agent 51 included in the release device 31 described above burns and the deploying agent case 43 is destroyed, the capture net 28 burns when the deploying agent 51 burns. , Prevents the capture net 28 from being damaged. The protective plate 32 is arranged in a space formed by arranging a plurality of weights 29 along the outer circumference of the deployable medicine case 43.

The protective lid 33 is a member that protects the capture net 28 when the flying object 17 is ejected. The material of the protective lid 33 is ABS resin, polyethylene, polyacetal, polycarbonate, polyurethane or other synthetic resin, or thick paper (cardboard).

The package 34 is a member that integrally holds the catch net 28, the weight 29, and the protective lid 33 in a state where the weight 29, the catch net 28, and the protective lid 33 are arranged in this order from the release device 31 side. The packaging body 34 is, for example, a member formed into a cylindrical shape by fixing both ends of a curved film. The material of the package 34 may be any material that can be easily torn when the weight 29 is scattered in the radial direction and the catch net 28 is deployed due to the scattering of the weight 29.

A ribbon (corresponding to the flight stabilizing member according to claim) 55 is attached to the protective lid 33 described above. The ribbon 55 is a member that stabilizes the flight of the flying object 17 ejected from the case 15. The material of the ribbon 55 is, for example, cloth or nylon. The ribbon 55 is folded and stored when the flying object 17 is stored in the case 15, is released from the folded state when the flying object 17 is flying, and is rearward with respect to the flight direction of the flying object 17. It will be in a stretched state. Therefore, the material of the ribbon 55 is not particularly limited as long as it is a material that does not easily crease when folded in a completely stretched state. Note that FIG. 2 shows a case where the two ribbons 55 are fixed to the protective lid 33 in a state of being orthogonal to each other at the midpoint of each ribbon. Although FIG. 2 shows a case where the two ribbons 55 are fixed to the protective lid 33, it is also possible to fix three or more ribbons to the protective lid. In this case, each ribbon may be arranged and fixed to the protective lid so that the angles formed by the adjacent ribbons are the same.

Next, the specifications of the ribbon 55 provided on the flying object 17 will be described. When the flying object 17 flies, the flying object 17 is affected by a _{moment (hereinafter, overturning moment) M m.} Therefore, the flying object 17 flies while rotating due to the action of the _{overturning moment M m.} As a result, the flight distance of the projectile 17 is shortened. Further, when the flying object 17 flies while rotating, the capture net 28 may not be deployed on a surface that intersects the flight direction of the flying object 17 within a range of a predetermined angle. The orientation of the net 28 is not stable.

On the other hand, as shown in FIG. 6, when the ribbon 55 is provided on the projectile 17, the projectile 17, in addition to acting overturning moment M _m, in the opposite direction to the said overturning moment M _m, according to the drag of the ribbon subjected to the action of the moment _{M R.} As a result, the overturning moment M _{m and the moment M R} due to the drag force of the ribbon are canceled out, the flight attitude of the projectile 17 is stabilized, and the flight distance is lengthened. Further, since the flight attitude of the flying object is stabilized, the capturing net 28 is deployed on the surface intersecting the flight direction of the flying object 17 within a range of a predetermined angle, so that the captured net 28 is deployed. The orientation is stable.

For example, the overturning moment M _m can be expressed by the following equation (1). In the equation (1), the symbol ρ is the air density, the symbol V is the flight speed of the flying object 17, the symbol A is the cross-sectional area of the flying object 17, the symbol d is the diameter of the flying object 17, and the symbol C _mα is the flying object 17. The overturning moment coefficient of, the symbol α _t, is the angle of attack.

Further, the moment M _R by drag ribbon 55 can be expressed by the following equation (2). In equation (2), the symbol _FDR is the drag force of the ribbon 55, the symbol _LCG is the distance from the center of gravity G of the flying object 17 to the ribbon 55 (hereinafter, the distance between the ribbon and the center of gravity), and the symbol _CR is the ribbon 55. The drag coefficient symbol S is the total area of the ribbon 55.

In order to increase the flying distance of the flying body 17, moments M _R by the drag F _DR of the ribbon 55 may if offsetting overturning moment M _m of the projectile 17. Therefore, the following equation (3) holds.

_{M R ≧ M m ··· (3} )

The above equation (3), the total area of Substituting equations (1) and (2), the ribbon 55 which overturning moment _{M m} of the projectile 17 is offset by the moment _{M R} by the drag _{F DR} of the ribbon 55 S Is obtained from the following equation (4).

Here, 40 mm diameter d of the projectile 17, the ribbon - distance between centers of gravity of 78mm, overturning moment coefficient _{C m.alpha} 0.85 projectile 17 and the drag coefficient _{C R} of the ribbon 55 and 0.1, projectile overturning moment _{M m} of 17 the total area S of the ribbon 55 which is offset by the moment _{M R} by drag ribbon 55 becomes S ≧ 5500 (mm ^2).

Therefore, when the diameter d of the flying object 17 is 40 mm, the flying attitude of the flying object 17 becomes stable when ^{the total area of the ribbon is 5500 mm 2 or more.}

The width of the ribbon 55 should be set to be equal to or less than the value obtained by dividing the outer peripheral length of the projectile 17 by the number of ribbons 55, considering that the ribbon 55 is stored inside the case 15 in a folded state. Is preferable. For example, when the diameter d of the flying object 17 is 40 mm, the width of the ribbon 55 is preferably 5 mm or more and 40 mm or less. The number of ribbons 55 is preferably, for example, 3 to 24. Further, the length of the ribbon 55 is preferably 80 mm or more and 500 mm or less. The number and length of the ribbons 55 are set to values in consideration of preventing the ribbons 55 from being entangled with each other when the flying object 17 flies.

Next, the operation of the projectile and the flow of combustion inside the release device from the injection of the projectile to the capture of the unmanned aerial vehicle to be captured will be described with reference to FIGS. 7 and 8. Note that FIG. 7 is a diagram for explaining the operation of the projectile until the unmanned aerial vehicle to be captured is captured, and FIGS. 8 (a) and 8 (b) are diagrams for explaining the flow of combustion inside the release device. Is.

The capture net deployment flight device 10 is loaded into the gas cylinder launcher 70. At this time, the protective cap 16 is removed. When the trigger of the gas cylinder launcher 70 is operated with the capture net deployment flight device 10 loaded in the gas cylinder launcher 70, the hammer (hammer) of the gas cylinder launcher 70 moves, and the hammer (hammer) of the gas cylinder launcher 70 moves. The detonator 26 attached to the case 15 of the capture net deployment flight device 10 loaded in the gas cylinder launcher 70 is hit. When the detonator 26 is hit by a hammer, the explosive stored inside the detonator 26 is ignited and the explosive is burned. The flame or combustion gas generated by this combustion reaches the holding seal 47 attached to the discharge device 31 through the fire transmission hole 22d. The flame transmitted through the fire transmission hole 22d destroys the holding seal 47. Then, the release agent 45 stored in the release agent storage portion 41c of the outer cylinder 41 ignites. As a result, the release agent 45 burns to generate combustion gas. Here, the space between the case body 21 and the case holder 22 is airtightly held by the packing 25. At the same time, the space between the release device 31 of the projectile 17 and the case body 21 is airtightly held by the packing 46. Therefore, the combustion gas generated by the combustion of the release agent 45 is filled in the space (not shown) between the storage space 22c of the case holder 22 and the release device 31 of the flying object 17, and is filled in the space. The projectile 17 is ejected from the case 15 in response to the pressure of the combustion gas becoming equal to or higher than a predetermined value. The projectile 17 ejected from the case 15 moves inside the barrel of the gas cylinder launcher 70, and then is ejected diagonally upward from the tip of the barrel (see FIG. 7A).

The projectile 17 ejected from the gas cylinder launcher 70 is ejected diagonally upward, and the projectile 17 rotates in the direction E in FIG. 7B due to the action of the overturning moment. Due to the rotation of the flying object 17, the folded ribbon 55 gradually extends backward with respect to the flying direction of the flying object 17. As the ribbon 55 stretches, not only the overturning moment but also the moment due to the drag force of the ribbon 55 begins to act on the projectile 17.

Then, when the projectile 17 rotates to the state where the release device 31 is positioned forward, the ribbon 55 is in a completely extended state, so that the moment due to the drag force of the ribbon 55 is larger than the overturning moment due to the air resistance of the projectile 17. Become. As a result, the rotation of the projectile 17 is stopped. That is, the projectile 17 flies in a state where the release device 31 is located in the front and the ribbon 55 is fluttering in the rear (see FIG. 7C).

Here, when the projectile 17 is ejected from the case 15, the release agent 45 is burned. Combustion of the release agent 45 causes the deferral agent 49 to ignite. In the process of igniting the Nobutoki drug 49 and starting combustion, the flash point 48a is ignited and the flash point 48a is burned. The burning of the fast-fire line 48a causes the burning of the deploying agent 51. When the developing agent 51 is burned, combustion gas is filled between the inner cylinder 42 of the discharging device 31 and the developing agent case. When the pressure of the combustion gas filled inside the developing agent case 43 exceeds the proof stress of the developing agent case 43, the developing agent case 43 is destroyed and the combustion gas is released to the outside. The combustion gas released to the outside presses the weight 29 arranged on the outer periphery of the deployable medicine case 43 in the radial direction. Here, the outer peripheral surface of the flying object 17 is covered with the packaging body 34. The force that the weight 29 presses in the radial direction is larger than, for example, the adhesive force of the double-sided tape that fixes the weight 29 to the discharge device 31, and is larger than the proof stress of the package 34. Therefore, the weight 29 pressed by the combustion gas discharged to the outside is disengaged from the discharge device 31, and at the same time, breaks the package 34 and scatters in the radial direction of the projectile 17. The weight 29 scatters in the radial direction of the projectile 17. Since the weight 29 is attached to the capture net 28, the outer peripheral edge of the capture net 28 is pulled by the scattering of the weight 29 in the radial direction of the flying object, and the capture net 28 expands (see FIG. 7 (d)). ).

Further, while the capture net 28 is deployed by the weight 29 scattering in the radial direction of the flying object 17, the protective lid 33 to which the ribbon 55 is fixed and the release device 31 from which the weight 29 is removed fall to the ground. (See FIG. 7 (e)).

For example, when the flying object 17 is flying stably and the unmanned aerial vehicle to be captured is flying (floating) in the flying direction of the flying object 17, the capture net 28 is based on the flying direction of the flying object 17. Since it is stably deployed on the intersecting surfaces within a predetermined angle range, the deployed capture net 28 is surely entangled with the unmanned aerial vehicle 80 (FIG. 8 (f)). As a result, the unmanned aerial vehicle 80 to be captured cannot fly (float), and the unmanned aerial vehicle 80 entwined with the capture net 28 falls.

By providing the ribbon 55 on the flying object 17 in this way, the flying attitude of the flying object 17 is stabilized, the flying distance of the flying object 17 can be obtained, and the flying object 17 is predetermined with respect to the flight direction. It can be stably deployed on intersecting surfaces within a range of angles.

Hereinafter, a verification test of the flight attitude of the flying object in the present embodiment was conducted.

<Flying attitude verification test>
The flight attitude verification test of the projectile was conducted by changing the length of the ribbon attached to the projectile. Here, as the flight attitude of the flying object, for example, the pitch angle of the flying object with respect to the horizontal plane can be mentioned.

As shown in FIG. 9, a plurality of cameras shoot a projectile from a launch tube arranged 25 ° upward with respect to the horizontal plane, and fly a projectile in a range of 30 m to 50 m in which the flight attitude of the projectile is stable. This was done by verifying the flight attitude of the photographed flying object.

As shown in FIG. 10, Example 1 is an embodiment of a flying object in which the number of ribbons is 4, the width of the ribbon is 24 mm, and the length is 50 mm. Further, Example 2 is an embodiment of a flying object in which the number of ribbons is 4, the width of the ribbon is 24 mm, and the length is 100 mm. Further, Example 3 is an embodiment of a flying object in which the number of ribbons is 4, the width of the ribbon is 24 mm, and the length is 150 mm.

The total area of the ribbon used for the projectile shown in Example 1 is 4800 mm ² . The total area of the ribbon used for the projectile shown in Example 2 is 9600 mm ² . The total area of the ribbon used for the projectile shown in Example 3 is 14400 mm ² . In the projectiles shown in Examples 1 to 3, black powder was used as the release agent (1.2 g), B / KNO ₃ : 0.33 g was used as the delay agent, and black powder: 1.5 g was used as the developing agent. There is.

As shown in FIG. 11, in the case of the flying object shown in the first embodiment, the pitch angle of the flying object changes in the range of 120 ° to −180 °. On the other hand, in the case of the flying object shown in Example 2, the pitch angle of the flying object changes in the range of 60 ° to −30 °. Further, in the case of the flying object shown in the third embodiment, the pitch angle of the flying object changes in the range of 60 ° to −30 ° as in the case of the flying object shown in the second embodiment. Here, assuming that the range of the pitch angle of the projectile when the projectile flies and the capture net is normally deployed is in the range of + 90 ° to −90 °, the capture net is the projectile shown in the first embodiment. It can be judged that it cannot be deployed normally. On the other hand, it can be determined that the capture net can be normally deployed in the projectiles shown in Examples 2 and 3.

Here, the total area of the ribbon used for the projectile shown in Example 1 is 4800 mm ² . The total area of the ribbon used for the projectile shown in Example 2 is 9600 mm ² , and the total area of the ribbon used for the projectile shown in Example 3 is 14400 mm ² . That is, in the flight attitude verification test, it was possible to obtain the result that ^{the theoretical value S ≧ 5500 (mm 2} ) of the total area of the ribbon in which the flight attitude of the flying object is stable is satisfied.

10 ... capture net deployment flying device, 15 ... case, 16 ... protective cap, 17 ... flying object, 21 ... case body, 22 ... case holder, 26 ... detonator, 28 ... capture net, 29 ... weight, 31 ... release device, 32 ... Protective plate, 33 ... Protective lid, 34 ... Package, 41 ... Outer cylinder, 42 ... Inner cylinder, 43 ... Expanding medicine case

Claims (14)

A tubular case with one end closed and
The catching net, a plurality of weights attached to the outer peripheral edge of the catching net, and the injection gas to be ejected from the case and the plurality of weights scattered in the radial direction with a predetermined time delay from the generation of the injection gas. The plurality of weights and the capture net are arranged in the order of the plurality of weights and the capture net from the release device side. A flying object having a packaging body surrounding the outer periphery of the net and being housed in the case with the discharging device located on the closed end side of the case.
The flight is fixed to the projectile on the end side where the capture net is arranged, extends rearward in the flight direction of the projectile when the projectile is ejected from the case, and the flight ejected from the case. A flight stabilizer that stabilizes the flight attitude of the body,
A capture net deployment flight device characterized by including. In the capture net deployment flight apparatus according to claim 1,
A protective member which is arranged at an end opposite to one end on which the release device is arranged to protect the catch net packaged in the package and to which the flight stabilizer is fixed is included.
The package is a catching net deploying flying device, which surrounds the outer periphery of the protective member in addition to the plurality of weights and the catching net. In the capture net deployment flight apparatus according to claim 1 or 2.
The flight stabilizer is a capture net deployment flying device, characterized in that a moment based on the drag force of the flight stabilizer acting on the flying flying object cancels the overturning moment acting on the flying flying object. In the capture net deployment flight apparatus according to claim 3,
The total area of the flight stabilizer is set so that the moment based on the drag force of the flight stabilizer acting on the flying object is equal to or greater than the overturning moment acting on the flying object during flight. Net deployment flight device. In the capture net deployment flight apparatus according to claim 3 or 4.
The flight stabilizing member is a ribbon.
The width of the ribbon is set to be equal to or less than a value obtained by dividing the outer peripheral length of the flying object by the number of the ribbons fixed to the flying object. In the capture net deployment flight apparatus according to claim 5,
A catch net deployment flight device characterized in that the width of the ribbon is 5 mm or more and 40 mm or less. In the capture net deployment flight apparatus according to claim 5 or 6.
A capture net deployment flying device characterized in that the number of ribbons is 3 or more and 24 or less, and the ribbons are arranged on the flying object at predetermined angular intervals. In the capture net deployment flight apparatus according to any one of claims 5 to 7.
A catch net deployment flight device characterized in that the width of the ribbon is 80 mm or more and 500 mm or less. In the capture net deployment flight apparatus according to any one of claims 1 to 8.
The release device is
A first tubular member for accommodating the release agent that generates the injection gas, and
A second tubular member for storing the developing agent that generates the scattering gas, and
A third tubular member that houses a delaying drug that ignites the developing drug that is ignited by the combustion of the released drug and ignites the deploying drug that is stored in the second tubular member after the lapse of a predetermined time.
A capture net deployment flight device characterized by including. In the capture net deployment flight apparatus according to claim 9,
The catch net deployment flight device, wherein the second tubular member is attached to the third tubular member housed in the first tubular member. In the capture net deployment flight apparatus according to claim 9 or 10.
A capture net deployment flight device, wherein the plurality of weights are fixed to the release device in a state of being arranged along the outer circumference of the second tubular member. In the capture net deployment flight apparatus according to claim 11,
It is provided in a space formed by arranging the plurality of weights along the outer circumference of the second tubular member, and is characterized by having a damage prevention member that prevents damage to the catching net due to combustion of the developing agent. A capture net deployment flight device. In the capture net deployment flight apparatus according to any one of claims 9 to 12.
The case is a capture net deployment flight device characterized by having a detonator containing an explosive that ignites the release agent at a closed end. In the capture net deployment flight apparatus according to claim 13,
The case is
A tubular case body with both ends open,
A holder fixed to one end of the case body while holding the detonator,
A capture net deployment flight device characterized by including.

Images