KR101907799B1 - Fuse and firing device using side jet and firing method thereof - Google Patents

Abstract

The present invention relates to a fuse having a rotation detecting sensor therein. The fuse comprises: an electronic control unit measuring the flight distance and rotational direction of a bullet by using the rotation detecting sensor; a side thrust device generating a side thrust in the bullet; and a safety loading device loaded when the bullet is beyond a safe area. More specifically, the present invention relates to a vertical ignition fuse and an aircraft having the vertical ignition fuse in a warhead of the aircraft, wherein the vertical ignition fuse applies the side thrust to the bullet so as to induce the bullet in the direction perpendicular to the ground and ignites when the bullet is perpendicular to the ground. Accordingly, the vertical ignition aircraft can be induced in the direction perpendicular to the ground through the side thrust device and ignited when the same is perpendicular to the ground.

Description

TECHNICAL FIELD [0001] The present invention relates to a vertically detonating aircraft including a vertically detonated fuse and a vertically detonated fuse using lateral force,

[0001] The present invention relates to a vertical aerodynamic body including a vertical aerodynamic explosion tube and a vertical aerodynamic explosion tube, and a method of exploiting the same. More specifically, a lateral thrust system is disposed on the side of the aerodynamic body, And a vertical detonating aircraft including a vertical detonating fuse and a vertical detonating fuse which maximize the effective debris dispersed in the direction of the ground by exploding in a vertical state, and a detonating method thereof.

The present invention is a technique applied to a new pipe of a flying aerial explosion which mainly rotates. In the conventional case, when the aerial explosion of the aerial explosion occurs over the target, fragments disposed on the outer periphery of the round body are scattered in all directions at 360 °. However, most of the enemies are hiding in the ground at the point where the air explosion occurs, so that only 50% of the fragments due to the air explosion can attack the enemy, and the remaining 50% Only about 50% of the debris they have has been used as a means of attacking the enemy.

In order to solve the above-mentioned problem, a lateral thrust device is arranged on the outer side of a flying body so that the fuselage and the flying object are swung 90 ° when seen from the lateral direction with respect to the flight path at the time of aerial explosion, So that almost all the fragments possessed by the flying object are dispersed in the direction of the ground to be used as effective fragments.

An electronic control unit for measuring the flying distance and rotation direction of a bullet using a rotation sensor, a lateral thrust device for generating a lateral thrust on the bullet, and a safety load for loading the bullet outside the safety zone Wherein the air is guided when the side impact force is applied to the bullet to induce the bullet in a direction perpendicular to the ground surface and when the bullet is perpendicular to the ground surface, the air is flared, and in the air vehicle including the warhead and the vertical explosion fuse It is a vertical aerodynamic body that induces a flight body vertically through the side thrust device and is disengaged when the plane and the ground are in a vertical state.

When the vertical explosion-proof pipe and the vertical aerobatic body according to the present invention are applied, it is possible to concentrate and disperse the fragments scattered in the air, rather than the place where the target is present, on the floor where the target is flocculated.

In addition, since effective fragments can be drawn to the maximum value, the fragments of the bullet can be efficiently used, and it is applicable to all the bullets using the rotary bulb, and the application field is also wide.

1 is an operation flowchart and operation conceptual diagram of a vertical explosion-proof flight vehicle according to the present invention.
FIG. 2 is a block diagram of an electronic control unit of a vertical explosion-proof flying body according to the present invention and a state diagram in which a rotation signal is converted into a digital signal.
3 is an internal structural view of a vertical arcing aircraft according to the present invention.
FIG. 4 is a state view showing fragments generated in the aerial explosion of a conventional aerial explosion as viewed from the side (a) and the front (b) of the flight direction.
FIG. 5 is a view of a fragment generated when the vertical detonating aircraft is detonated according to the present invention, viewed from the side (a) and the front (b) of the flight direction.
FIG. 6 is a view showing an output pattern of a rotation signal according to a positional change of a rotation detection sensor of a vertical rocket engine according to the present invention. FIG.
FIG. 7 is a state diagram illustrating a process in which pitching is progressed by lateral force on the basis of the lateral direction of the vertical aerodynamic flight according to the present invention.
FIG. 8 is a conceptual diagram illustrating rolling caused by a lateral thrust on the basis of the frontal direction of the vertical arcing aircraft according to the present invention.
FIG. 9 is a state diagram illustrating a process in which rolling and pitching are progressed together with the lateral thrust on the basis of the frontal direction of the vertical explosive flying vehicle according to the present invention.
10 is a flow chart of a method of detonating a vertical detonating vehicle according to the present invention.

For a better understanding of the present invention, a preferred embodiment of the present invention will be described with reference to the accompanying drawings. The embodiments of the present invention can be modified in various forms, and the scope of the present invention should not be construed as being limited to the embodiments described in detail below. The present embodiments are provided to enable those skilled in the art to more fully understand the present invention. Therefore, the shapes and the like of the elements in the drawings can be exaggeratedly expressed to emphasize a clearer description. It should be noted that the same components are denoted by the same reference numerals in the drawings. Detailed descriptions of well-known functions and constructions which may be unnecessarily obscured by the gist of the present invention are omitted.

2 is a block diagram of an electronic control unit of a vertical detonation vehicle according to the present invention and a state diagram in which a rotation signal is converted into a digital signal, Figure 1 shows the internal structure of a vertical explosion aircraft according to Fig.

1 to 3, the present invention is a fuse having a built-in rotation detection sensor 10, which includes an electronic control unit 210 for measuring a flying distance and a rotation direction of a bullet using a rotation detection sensor, And a safety loading device (240) for loading the bullet when the bullet is out of a safe area. The bullet thrust is applied to the bullet to guide the bullet in a direction perpendicular to the ground, (Hereinafter referred to as a new fuselage) characterized in that the fuselage is fired when the ground surface is in a vertical state, and a flying object (hereinafter referred to as a flying object) including the fuselage 200 on the warhead, Wherein the airplane is guided in a vertical direction with respect to the airplane, and when the airplane and the ground are perpendicular to each other, the airplane is detonated.

In the fuse (200), the vertical state indicates a state in which the bullet is perpendicular to the front side of the direction of flight of the bullet by pitching, and the bullet is perpendicular to the side of the bullet by the rolling.

The electronic control unit 210 converts the rotation signal 50 acquired from the rotation sensor 10 into a digital signal 70 and sets the generation time of the side thrust by measuring the rotation direction with the digital signal. The electronic controller 210 includes the rotation sensor 10 for generating the rotation signal 50 based on a geomagnetic field, an amplifier 20 for amplifying the rotation signal 50, And a CPU 40 for calculating the flying distance of the bullet by using the digital signal. The loading distance of the safety loading device 240 Set the viewpoint.

Next, in the air vehicle, the vertical state refers to a state in which the air vehicle is perpendicular to a front side of the air vehicle in relation to the air vehicle direction by pitching, and the air vehicle is perpendicular to the flight side of the air vehicle by rolling.

The flying object includes the bullet 200 and the bullet 100. The bullet 110 includes a bulge 110 and a high explosive 130. The center of gravity G of the bullet, Lt; / RTI >

The side thrust device 230 is fastened at a position having a minimum separation distance in the axial direction from the center of gravity G of the air vehicle and a maximum separation distance in the radial direction.

FIG. 4 is a state view of fragments generated in the aerial explosion of a conventional aerial explosion as viewed from the side (a) and the front (b) of the flight direction, FIG. 5 is a view (A) and a front view (b).

As shown in FIG. 4 (a), the scattering direction of the fragments viewed from the side of the flying direction of the aerial explosion of the conventional aerial explosion is about 50% of the total fragments of the effective fragments 150 toward the ground on which the target is disposed And the remaining invalid fragments 160 were scattered in the air.

Also, as shown in FIG. 4 (b), the scattering direction of the fragment viewed from the front of the flying direction is also about 50% As shown in FIG.

FIG. 3 is an internal structural view of a vertical articulated vehicle according to the present invention. In order to solve the conventional problem as shown in FIG. 4, the body 100, which exhibits a kill power, is placed on the tummy of the air vehicle, And a high explosive 130 for dispersing the shaped debris. The rotation sensing sensor 10 for allotting the new pipe 200 to the warhead of the airplane and the rotation angle sensor 10, The safety loading device 240 including the electronic control unit 210 capable of precisely controlling the system, the safety of the soldiers and the lateral thrust system, the side thrust device 230 capable of generating side thrust of the thrust, A connecting gunpowder 240a for a torpedo, a swivel ball 120, and the like.

FIG. 5 is a side view (a) and a front view (b) of a flying debris generated when the vertical detonating aircraft is detonated according to the present invention. In the present invention, the flying object is detonated vertically with respect to the ground Almost all of the debris is dispersed toward the ground to be used as the effective debris 150.

 FIG. 10 is a flowchart of a detonating method of a vertical detonating vehicle including the fuse 200 according to the present invention. 10, the detonating method includes a flight information collecting step (S10) of measuring a flight distance and a turning direction of the air vehicle, a side force generating step (S30) of generating side force based on the rotation direction, A loading step (S20) for loading the flying object on the basis of the flying distance, and a determining step (S40) for checking whether the flying object is perpendicular to the ground. If the determination step is satisfied, And if the determination is unsatisfactory, the side force generation step is executed again.

1, 2, and 10, the flight information collection step S10 includes a rotation signal sensing step S11 for sensing the rotation signal 50 generated by the rotation sensor 10, An amplification step S12 of amplifying the rotation signal by the amplifier 20, a digital signal generation step S13 of converting the amplified rotation signal 60 into the digital signal 70, (S14) of analyzing the slope of the flying object with respect to the ground in the rotating direction, and a flying distance obtaining step (S14) of obtaining the flying distance of the flying object with the digital signal, And sets the loading time of the air vehicle at the flying distance obtaining step.

FIG. 6 is a view illustrating an output pattern of a rotation signal according to a change in position of a rotation sensor of a vertical rocket flying vehicle according to the present invention. FIG. FIG. 8 is a conceptual view illustrating rolling caused by lateral thrust on the basis of the frontal direction of the vertical arcing flight according to the present invention, and FIG. 9 is a view showing the frontal direction of the vertical arcing flight according to the present invention Fig. 5 is a state diagram showing a process in which rolling and pitching are progressed together by a lateral force as a reference. Fig.

As shown in FIG. 7, the center of gravity (G) of the whole flying object (char) is formed on the body 100 when viewed from the side direction of the flying body. When the side force is generated 90 in the speculative force device 230, the flying object rotates about the center of gravity G. On the basis of this principle, pitching of the fuse 200 is caused to occur do. The position of the flying object (bullet) during the flight is raised from P5 to P6 in the vertical direction as in the final P7 due to the lateral thrust. However, at this time, since pitching and rolling occur in the flying object, the center of the flying object (bullet) is fixed and can not be rotated from P5 to P6 to the position of P7 as shown in FIG. , Rolling and pitching are simultaneously performed as shown in FIG. 9, and the final vertical position is reached.

The operation sequence of the present invention will be described in detail with reference to FIGS. 1, 2, 6, and 10. FIG.

2, when the flying object (shot) is fired, a fine rotation signal 50 based on the earth's magnetic field is generated by the rotation sensor 10 in the fuse 100, The microcomputer 30 amplifies the rotation signal (fine signal) 60 using the amplification circuit of the microcomputer 20 and generates the digital signal 70 that can be processed by the CPU 40 via the comparator 30. The electronic control unit 210 in the fuse box measures the rotation of the flying object to obtain the flying distance information. When the safety control unit 240 moves out of the safety zone of the group, And the accurate rotation position of the flying object (shot) is confirmed through the rotation angle analysis at the final destination. As shown in FIG. 6, the rotation detecting sensor 10 rotates at an interval of 90 ° from the position of P1 and rotates one rotation at a time of 360 ° through P2, P3 and P4. During this rotation, the rotation signal 50 is output by the rotation sensor 10 in the form of a sinusoidal wave of one cycle, and the rotation direction of the rotation relative to the ground surface is measured by precisely measuring one cycle of the sinusoidal wave with respect to time Based on this information, the lateral thrust device 230 calculates a position to be fired, and controls the pitching occurring in the lateral direction with respect to the flying direction of the flying object and the rolling occurring in the frontal direction, And the lateral force is generated to eventually cause the airplane to be vertically detonated.

It will be apparent to those skilled in the art that various modifications and equivalent arrangements may be made therein without departing from the spirit and scope of the invention as defined by the appended claims. Therefore, it is to be understood that the present invention is not limited to the above-described embodiments. Accordingly, the true scope of the present invention should be determined by the technical idea of the appended claims. It is also to be understood that the invention includes all modifications, equivalents, and alternatives falling within the spirit and scope of the invention as defined by the appended claims.

100:
200: Fuse
10: Rotation sensor
20: Amplifier
30: comparator
40: CPU
50: rotation signal
60: Amplified rotation signal
70: Digital signal
80: Rolling direction
90: Explosive
110: molded debris
120: Rotating balls
130: High explosive gunpowder
140: Ground
150: effective fragment
160: Invalid fragment
210:
230: side thrust device
240: Safety Loading Device
240a: Connection gunpowder
G: Center of gravity

Claims (14)

In a new pipe with a built-in rotation sensor,
An electronic control unit for measuring a flying distance and a rotating direction of the bullet using the rotation detecting sensor;
A side thrust device for generating a lateral thrust force on said barrel;
A safety loading device that is loaded when the shot is out of a safe area; Including the
Wherein a lateral thrust is applied to the bullet to induce the bullet in a direction perpendicular to the ground, and when the bullet and the ground are in a vertical state, the bulwark is excited. The method according to claim 1,
Wherein the vertical state is a state in which the bullet is perpendicular to a front face of the bullet with respect to a flying direction of the bullet by pitching and the bullet is perpendicular to a side of the bullet with respect to a flying direction of the bullet by rolling. The method according to claim 1,
Wherein the electronic control unit converts the rotation signal acquired from the rotation sensor into a digital signal and sets the generation time of the side thrust by measuring the rotation direction with the digital signal. The method of claim 3,
The electronic control unit
A rotation sensor for generating the rotation signal based on a geomagnetic field;
An amplifier for amplifying the rotation signal;
A comparator for converting the amplified rotation signal into the digital signal;
A CPU for calculating the flying distance of the shot with the digital signal; And it includes a
And setting the loading time of the safety loading device at the flying distance. In a vehicle including a new pipe having a rotation sensor incorporated in the warhead,
An electronic control unit for measuring a flying distance and a rotating direction of a flying object using a rotation detecting sensor;
A side thrust device for generating lateral thrust force on the air vehicle;
A safety loading device for loading the airplane when the airplane is out of the safe area; Including the
Wherein the vertical force is induced when the airplane and the ground surface are perpendicular to each other by guiding the airplane in a vertical direction with respect to the ground surface through the side thrust device. 6. The method of claim 5,
Wherein the vertical state is a state in which the airplane is vertical to a front side of the flying direction of the airplane due to pitching, and the airplane is perpendicular to a side of the airplane in a flying direction by rolling. 6. The method of claim 5,
Wherein the electronic control unit converts the rotation signal acquired from the rotation sensor to a digital signal and sets the generation time of the side thrust by measuring the rotation direction of the air vehicle with the digital signal. 8. The method of claim 7,
The electronic control unit
A rotation sensor for generating the rotation signal based on a geomagnetic field;
An amplifier for amplifying the rotation signal;
A comparator for converting the amplified rotation signal into the digital signal;
A CPU for calculating the flying distance of the air vehicle with the digital signal; And it includes a
And setting the loading time of the safety loading device at the flying distance. 6. The method of claim 5,
The airplane includes a body on the tummy
Wherein said body is a molded piece; And high explosives; It includes
Wherein the center of gravity of the airplane is located in the tampon. 6. The method of claim 5,
The side thrust device
And a maximum separation distance in the radial direction is a minimum separation distance in the axial direction from the center of gravity of the flying object. 11. A method of detonating a vertical explosion vehicle according to any one of claims 5 to 10,
A flight information collecting step of measuring the flying distance and the rotating direction of the flight vehicle;
A side force generating step of causing the side thrust device to generate side force based on the rotation direction;
A loading step of loading the airplane when the airplane is out of the safe area based on the flying distance; And it includes a
Wherein the lateral force is induced in the vertical direction with respect to the ground by the lateral thrust generated in the lateral force generating step, and when the ground and the air are perpendicular to each other, the air is woken up. 12. The method of claim 11,
The flight information collecting step
A rotation signal sensing step of sensing a rotation signal generated by the rotation detection sensor;
An amplifying step of amplifying the rotation signal;
A digital signal generation step of converting the amplified rotation signal into a digital signal;
A rotation angle analyzing step of analyzing the inclination of the flying object with respect to the ground in the direction of the digital signal and the rotation direction;
Acquiring a flight distance of the air vehicle with the digital signal; Wherein the airbag comprises an airbag. 13. The method of claim 12,
And the generation timing of the lateral thrust is set in the rotation angle analysis step. 13. The method of claim 12,
And setting the time point of the loading step of the flying object in the flying distance obtaining step.

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