Projectile, launch system and launch device

Abstract

To provide a missile to be ejected from an ejection device by electromagnetic force having a mechanism allowing an activation after ejection in a simple structure.SOLUTION: A missile 10 is inserted into a space enclosed by a conductive rail and an insulation rail, is accelerated in an X direction by receiving force from an armature accelerated by an electric current flowing from the conductive rail and is ejected from an ejection port at an ejection device 1. The missile 10 includes a body 10A, electrodes EA1 and EA2, a capacitor Cm connected between the electrodes EA1 and EA2 and a load circuit 14. A pair of external electrodes are provided at a position opposite to the missile 10 in the insulation rail. The capacitor Cm is charged by the electrodes EA1 and EA2 contacting with the pair of external electrodes respectively and a power source being supplied when the missile 10 is inserted.SELECTED DRAWING: Figure 6

Description

[Technical Field]

[0001] The present invention relates to a projectile, a launch system, and a launch device. [Background technology]

[0002] An electromagnetic railgun is known as an electromagnetic accelerator that accelerates a projectile using electromagnetic force (Patent Document 1). In general, in a railgun, a current is passed through an armature made of a conductive material inserted between two conductive rails, and the armature is accelerated by the electromagnetic force (Lorentz force) that acts at this time. The projectile, which is the object to be launched, is held by the armature, and is launched from the electromagnetic accelerator by accelerating the armature.

[0003] Furthermore, when a projectile is launched, a mechanism mounted on the projectile may be activated after launch to perform a desired operation. Examples of such mechanisms include a fuse for a shell and a mechanism associated with the fuse, and proposed mechanisms include an electric fuse that operates using electricity generated by the rotation of a windmill after launch (Patent Document 2) and a fuse power supply that automatically activates after launch (Patent Documents 2 and 4). [Prior art documents] [Patent documents]

[0004] [Patent Document 1] Japanese Patent Application Publication No. 10-206090 [Patent Document 2] Japanese Patent Application Publication No. 57-104099 [Patent Document 3] Japanese Patent Application Publication No. 8-124581 [Patent Document 4] Japanese Patent Application Publication No. 9-113199 Summary of the Invention [Problem to be solved by the invention]

[0005] However, it is expected that projectiles launched from electromagnetic railguns will be launched at high speeds, such as hypersonic speeds. Therefore, the air resistance of the projectile must be reduced as much as possible, making it impossible to use a power generation mechanism that utilizes airflow, such as that described in Patent Document 2. Furthermore, since the acceleration acting on the projectile at the time of launch can reach 100,000 G or more, equipping the mechanism with a power source as described in Patent Documents 3 and 4 requires a robust structure, which inevitably increases the size and weight. Therefore, it is difficult to use the above-mentioned general mechanisms for projectiles launched from electromagnetic railguns.

[0006] Other objects and novel features will become apparent from the description of this specification and the accompanying drawings. [Means for solving the problem]

[0007] A projectile according to one embodiment is inserted into a space surrounded by a pair of opposing conductive rails and a pair of opposing insulating rails in an injection device, and is accelerated in a first direction, which is the extension direction of the conductive rails, by receiving a force from a conductive member that is accelerated by a current flowing from the conductive rails, and is then injected from an injection outlet of the injection device at the end of the conductive rails. The projectile comprises a main body, a pair of first electrodes provided on the outer surface of the main body, a capacitor provided within the main body and connected between the pair of first electrodes, and a load circuit that receives power from the capacitor. A pair of second electrodes are provided on the pair of insulating rails at positions opposite the projectile, and when the projectile is inserted into the space, the pair of first electrodes come into contact with the pair of second electrodes, respectively, and power is supplied, thereby charging the capacitor.

[0008] The ejection system according to one embodiment includes a ejection device that ejects an object held by a conductive member by accelerating the conductive member using electromagnetic force, and a flying object that is accelerated in a first direction by the conductive member and ejected from an ejection port of the ejection device. The ejection device includes a pair of conductive rails that are arranged opposite each other and extend in the first direction, a pair of insulating rails that are arranged opposite each other and extend in the first direction, and a pair of second electrodes that are provided on the pair of insulating rails at positions facing the flying object. The flying object includes a main body, a pair of first electrodes that are provided on an outer surface of the main body, a capacitor that is provided within the main body and connected between the pair of first electrodes, and a load circuit that receives power from the capacitor. When the flying object is inserted into a space surrounded by the pair of conductive rails and the pair of insulating rails, the pair of first electrodes come into contact with the pair of second electrodes, respectively, and power is supplied, thereby charging the capacitor.

[0009] According to one embodiment, the launching device launches a projectile held by a conductive member by accelerating the conductive member using electromagnetic force. The launching device comprises a pair of conductive rails arranged opposite each other and extending in a first direction, a pair of insulating rails arranged opposite each other and extending in the first direction, and a pair of second electrodes arranged on the pair of insulating rails at positions opposite the projectile. The projectile has a main body, a pair of first electrodes arranged on the outer surface of the main body, a capacitor arranged within the main body and connected between the pair of first electrodes, and a load circuit that receives power from the capacitor. The pair of second electrodes are arranged so that when the projectile is inserted into a space surrounded by the pair of conductive rails and the pair of insulating rails, the pair of first electrodes come into contact with the pair of second electrodes, respectively, and power is supplied to charge the capacitor. [Effects of the Invention]

[0010] According to one embodiment, it is possible to realize a flying object that is launched by electromagnetic force from a launching device and has a mechanism that allows activation after launch with a simple configuration. [Brief explanation of the drawings]

[0011] [Figure 1] FIG. 1 is a diagram schematically illustrating a configuration of a launch system that launches a flying object according to a first embodiment. [Figure 2] FIG. 1 is a side view schematically showing the configuration of an injection device according to a first embodiment. [Figure 3] FIG. 1 is a top view schematically showing the configuration of an injection device according to a first embodiment. [Figure 4] FIG. 3 is a diagram schematically illustrating the connection relationship between external electrodes and a power supply circuit. [Figure 5] FIG. 2 is a diagram illustrating a configuration of a power supply circuit. [Figure 6] FIG. 2 is a diagram illustrating a configuration of a flying object according to the first embodiment. [Figure 7] FIG. 10 is a side view schematically showing the configuration of an injection device according to a second embodiment. [Figure 8] FIG. 10 is a side view schematically showing the configuration of an injection device according to a third embodiment. [Figure 9] FIG. 10 is a diagram schematically illustrating a configuration of a flying object according to a third embodiment. [Figure 10] 10A and 10B are diagrams showing the induced current flowing in the magnetic field detection coil before and after the magnetic field detection coil passes through the magnetic field generating coil. DETAILED DESCRIPTION OF THE INVENTION

[0012] Specific embodiments will be described in detail below with reference to the drawings. However, the present invention is not limited to the following embodiments. For clarity of explanation, the following description and drawings have been simplified as appropriate. The same elements are given the same reference numerals, and duplicate explanations will be omitted.

[0013] Embodiment 1 The launching device according to this embodiment will be described. Fig. 1 shows a schematic configuration of a launching system 100 that launches a flying object 10 according to this embodiment. The launching system 100 includes a launching device 1, a power supply device 101, a switch 102, and a control device 103.

[0014] The launch device 1 is configured as a so-called railgun, which accelerates an armature AM made of a conductor by an electromagnetic force (Lorentz force) caused by a magnetic field generated by passing a pulse current Id through the armature AM. A projectile 10, which is an object to be launched, is accelerated by being pushed by the armature AM, and as a result, is launched from the launch port EX.

[0015] The power supply device 101 is an injection power supply device connected to the injection device 1, and is configured to be able to supply a pulse current Id to the injection device 1.

[0016] The switch 102 is configured to open and close the power supply path from the power supply device 101 to the injection device 1. As the switch 102, various types of switches, relays, etc. can be used as long as they can safely open and close the path through which a relatively large current supplied to the injection device 1 flows.

[0017] The control device 103 is configured by, for example, a computer, and can control the operation of the power supply device 101 by providing a control signal CON. For example, the control device 103 can control the timing and duration at which the power supply device 101 supplies the pulse current Id to the injection device 1, the current value of the pulse current Id, and the like, by controlling the switch 102. This allows the control device 103 to control the timing at which the flying object 10 is injected from the injection device 1 and the injection speed of the flying object 10.

[0018] Next, the injection device 1 will be described in more detail. FIG. 2 is a side view schematically illustrating the configuration of the injection device 1 according to the first embodiment, and FIG. 3 is a top view schematically illustrating the configuration of the injection device 1 according to the first embodiment. The horizontal direction from left to right on the paper surfaces of FIGS. 2 and 3 is the X direction (also referred to as the first direction). The normal direction from the front to the back on the paper surface of FIG. 2 and the vertical direction from the bottom to the top on the paper surface of FIG. 3 are the Y direction (also referred to as the second direction). The vertical direction from the bottom to the top on the paper surface of FIG. 2 and the normal direction from the back to the front on the paper surface of FIG. 3 are the Z direction (also referred to as the third direction). Note that in FIG. 3, the conductive rail A1 is indicated by a dashed line for simplification of the drawing.

[0019] The injection device 1 is configured to include conductive rails A1 and A2 and insulating rails B1 and B2. The conductive rails A1 and A2 are a pair of conductive members that are spaced apart in the direction perpendicular to the plane of the paper (Z direction) of FIG. 2 and extend in the injection direction (X direction). The conductive rail A1 is connected to the positive electrode of a power supply device 101 via a switch 102, and the conductive rail A2 is connected to the negative electrode of the power supply device 101. The insulating rails B1 and B2 are a pair of insulating members that are spaced apart in the direction normal to the plane of the paper (Y direction) of FIG. 2 and in the direction perpendicular to the plane of the paper of FIG. 3 and extend in the injection direction (X direction).

[0020] The armature AM and flying object 10 are inserted into a space surrounded by conductive rails A1 and A2 and insulating rails B1 and B2. The armature AM is composed of a conductor that contacts the conductive rails A1 and A2 and is positioned on the -X direction side of the flying object 10. By passing a pulse current Id through the conductive rails A1 and A2 and the armature AM, an electromagnetic force F in the ejection direction (+X direction) is generated in the armature AM, and the armature AM is accelerated in the ejection direction. As a result, the flying object 10 is pushed by the armature AM, and the flying object 10, guided by the conductive rails A1 and A2 and insulating rails B1 and B2, is accelerated and ejected from the end (ejection port EX) on the +X direction side of the conductive rails A1 and A2.

[0021] On the insulating rails B1 and B2, a plurality of electrodes are arranged in the longitudinal direction on the surfaces facing the flying object 10. Here, from the initial position of the flying object 10 toward the ejection port EX, external electrodes EB1_0 to EB1_n are arranged on the insulating rail B1, and external electrodes EB2_0 to EB2_n (n is an integer of 2 or more) are arranged on the insulating rail B2. If k is an integer of 0 to n, external electrode EB1_k and external electrode EB2_k (also referred to as the second electrode) constitute an external electrode pair PBk. The two external electrodes EB1_k and EB2_k that constitute the external electrode pair PBk are provided at positions spaced the same distance from the initial position of the flying object 10. In addition, the distance in the X direction between the external electrode pair is W1 in this example.

[0022] Power is supplied to the external electrodes from a power supply circuit. Fig. 4 shows a schematic diagram of the connection between the external electrodes and the power supply circuit. A power supply circuit Sk is connected to the external electrode EB1_k and the external electrode EB2_k (external electrode pair PBk).

[0023] 5 shows the configuration of the power supply circuit Sk. The power supply circuit Sk has diodes DAk and DBk, a resistor Rk, an inductor Lk, and a capacitor Ck. The diode DAk, the inductor Lk, and the capacitor Ck are connected in series in this order between the external electrode EB1_k and the external electrode EB2_k. The cathode of the diode DAk is connected to the external electrode EB1_k, and the anode is connected to the inductor Lk. The diode DBk and the resistor Rk are connected in series in this order between the node between the diode DAk and the inductor Lk and the node between the external electrode EB2_k and the capacitor Ck. The cathode of the diode DBk is connected to the node between the diode DAk and the inductor Lk, and the anode of the diode DBk is connected to the resistor Rk.

[0024] FIG. 6 shows the configuration of the flying object 10. In the flying object 10, a time-delay operation circuit 11, a power supply detector 12, and a capacitor Cm are provided inside the main body 10A of the flying object, and electrodes EA1 and EA2 (also referred to as first electrodes) are provided so as to be exposed on the outer surface of the cylindrical main body 10A of the flying object. The electrodes EA1 and EA2 form an electrode pair PA. The capacitor Cm is connected between the electrodes EA1 and EA2. The current detector 12 is configured to detect the current flowing through the electrodes EA1, the capacitor Cm, and the electrode EA2. In this example, the current detector 12 is provided to detect the current between the electrode EA1 and the capacitor Cm.

[0025] The time-limit operation circuit 11 has an activation signal generation circuit 13 and a load circuit 14. The current detected by the current detector 12 is monitored by the activation signal generation circuit 13. As will be described later, after the flying object 10 is launched, a pulse current flows through the capacitor Cm, and the activation signal generation circuit 13 is configured to detect the timing at which this current pulse flows.

[0026] Based on the detection result of the current pulse, the start-up signal generation circuit 13 generates a start-up signal ST for starting the load circuit 14 and outputs it to the load circuit 14. When the load circuit 14 receives the start-up signal ST, it starts up and can perform a predetermined operation.

[0027] That is, the activation signal generating circuit 13 can activate the load circuit 14 at a desired timing after the projectile 10 is launched, based on the activation signal generated based on the detection result of the current pulse after the projectile 10 is launched.

[0028] The projectile 10 may be, for example, a cannonball, and the load circuit 14 may be, for example, a fuse provided on the cannonball.

[0029] Next, the operation of the flying object 10 will be described in detail. [Activation stage] First, the flying object 10 is placed at an initial position before being launched from the launch device 1. The initial position is set as a position spaced apart from the launch port EX along the longitudinal direction (X direction) of the launch device 1 so that the flying object 10 is sufficiently accelerated by electromagnetic force.

[0030] The power supply circuits S0 to Sn are charged in advance to a predetermined voltage by connecting the capacitors C0 to Cn to an external power supply. At this time, the capacitors C0 to Cn are charged so that the charging voltages increase in order. In other words, the charging voltage of the capacitor C0 of the power supply circuit S0 is the lowest, and the charging voltages of the capacitors C1 to Cn-1 of the power supply circuits S1 to Sn-1 increase stepwise, with the charging voltage of the capacitor Cn of the power supply circuit Sn being the highest. Here, the charging voltages of the capacitors C0 to Cn are designated V0 to Vn, respectively.

[0031] In the initial position, the electrode EA1 of the flying object 10 contacts the external electrode EB1_0 of the insulating rail B1, and the electrode EA2 of the flying object 10 contacts the external electrode EB2_0 of the insulating rail B2. Therefore, the charging voltage V0 of the capacitor C0 of the power supply circuit S0 is supplied as a power supply voltage to the flying object 10. As a result, the capacitor Cm of the flying object 10 is charged, and power is supplied to the time-limit operation circuit 11, which starts operation (i.e., turns on).

[0032] In this way, with this configuration, the capacitor Cm charged when the flying object 10 is placed in the initial position is used as the power source for the time-limit operation circuit 11, making it possible to activate the time-limit operation circuit 11 mounted on the flying object 10 with a simple configuration. This eliminates the need for a complex power source mechanism or a mechanism that generates electricity using airflow, making it possible to reduce the size of the flying object.

[0033] [Injection stage] When the conductive rails A1 and A2 and the armature AM are energized to launch the flying object 10, the flying object 10 begins to move in the launch direction (+X direction) due to electromagnetic force. When the movement starts, the electrode pair PA (electrodes EA1 and EA2) of the flying object 10 moves away from the external electrode pair PB0 (external electrodes EB1_0 and EB2_0) and then contacts the next external electrode pair PB1 (external electrodes EB1_1 and EB2_1). Because the charging voltage V1 of capacitor C1 is higher than the charging voltage V0 of capacitor C0, current flows through capacitor Cm of the flying object 10, further charging it. The charging current flowing at this time is detected by current detector 12 as a pulsed current flowing when the electrodes come into contact.

[0034] From this point onwards, the current detector 12 will detect a pulse-like current whenever the electrode pair PA of the flying object 10 comes into contact with each of the outer electrode pairs PB2 to PBn of the insulating rail.

[0035] In this embodiment, the width d of the electrodes EA1 and EA2 of the flying object 10 in the acceleration direction (X direction) A The width d of the outer electrode EB1_k of the insulating rail B1 and the outer electrode EB2_k of the insulating rail B2 in the acceleration direction (X direction) B smaller than (d1 <d B ) Furthermore, the velocity of the flying object 10 is v, and τ f =d B / v. Under these conditions, when the capacitor Cm of the flying object 10 is charged from the capacitor Ck of the power supply circuit Sk by LC resonance, a pulsed current is obtained regardless of the electrode width. The time width τ of the pulse current at this time is expressed by the following equation:

number

[0036] In this way, a current pulse is obtained when the electrode of the flying object and the external electrode first come into contact, regardless of the electrode width. Therefore, it is desirable to position the two external electrodes constituting each of the external electrode pairs PB2 to PBn so that they come into contact with the two electrodes of the accelerating flying object at the same time.

[0037] In this way, by detecting the pulse current as the flying object 10 moves, it is possible to obtain the acceleration characteristics of the flying object 10. It is also possible to calculate the initial velocity of the flying object 10 when it is launched from the launching device 1. This allows the load circuit 14 to be started at a desired timing after launch based on the calculated initial velocity, so that the load circuit 14 can be started when the flying object 10 reaches a desired position.

[0038] Furthermore, when the projectile 10 is a cannonball and the load circuit 14 is its fuse, it can be understood that this configuration makes it possible to realize a time fuse with a simple configuration.

[0039] Furthermore, since it is only necessary to provide an external electrode on the insulating rail that is originally provided on the injection device, the mechanism provided on the projectile can be activated and the load circuit can be started at the desired timing without affecting the basic configuration of the injection device.

[0040] Embodiment 2 In the first embodiment, the configuration in which an external electrode is provided on each of the insulating rails B1 and B2 has been described, but in the present embodiment, the configuration in which an external electrode is provided on one of the insulating rails B1 and B2 will be described.

[0041] Fig. 7 is a side view schematically showing the configuration of the injection device 2 according to the second embodiment. In the example of Fig. 7, an external electrode is provided only on the insulating rail B1.

[0042] The external electrodes EB1_k and EB2_k constituting the external electrode pair PBk are arranged spaced apart vertically, i.e., in the Z direction, at positions spaced apart the same distance from the initial position of the flying object 20. In this example, the external electrode EB1_k is arranged on the upper side (+Z direction), and the external electrode EB2_k is arranged on the lower side (-Z direction).

[0043] In the flying object 20, the electrodes EA1 and EA2 that make up the electrode pair PA are arranged spaced apart vertically, i.e., in the Z direction. In this example, the electrode EA1 is arranged on the upper side (+Z direction) and the electrode EA2 is arranged on the lower side (-Z direction). Needless to say, the flying object 20 is inserted into the initial position of the ejection device 2 so that the electrode pair PA faces the external electrode pair PBk.

[0044] Other configurations of the injection device 2 and the flying object 20 are the same as those of the injection device 1 and the flying object 10 according to the first embodiment, and therefore description thereof will be omitted.

[0045] As described above, according to this configuration, as in embodiment 1, by detecting the pulse current as the flying object 20 moves, the initial velocity of the flying object 20 can be calculated, and the load circuit 14 can be started when the flying object 20 reaches the desired position.

[0046] Embodiment 3 In the first and second embodiments, the flying object 10 calculates its speed by detecting a pulse current supplied through electrodes provided on an insulating rail. However, it may be difficult to provide electrodes on an insulating rail. Therefore, in the third embodiment, a flying object whose speed can be calculated without supplying a pulse current through electrodes will be described.

[0047] 8 is a side view schematically illustrating the configuration of an injection device 3 according to a third embodiment. The injection device 3 has a configuration in which magnetic field generating coils LB1 and LB2 are added compared to the injection device 1. In this embodiment, only the external electrodes EB1_0 and EB2_0 are provided on the insulating rails B1 and B2, respectively.

[0048] The magnetic field generating coils LB1 and LB2 are annular coils with their axis in the emission direction (+X direction) and are provided closer to the emission direction than the emission outlet EX. The magnetic field generating coil LB1 is provided on the side of the emission outlet EX, and the magnetic field generating coil LB2 is provided at a position spaced a distance W2 from the magnetic field generating coil LB1 in the emission direction (+X direction).

[0049] The magnetic field generating coils LB1 and LB2 are connected in series between the conductive rails A1 and A2, so that they can generate a magnetic field in conjunction with the supply of current to the conductive rails A1 and A2. This allows a large current to flow for a short time only when the projectile is launched, without the need for a separate power supply to supply power to the magnetic field generating coils LB1 and LB2, making it easy to generate a relatively large magnetic field.

[0050] In this embodiment, currents I1 and I2 flow in the clockwise direction in the magnetic field generating coils LB1 and LB2, respectively, when viewed along the X direction (i.e., from left to right on the paper surface of FIG. 8). As a result, magnetic fields H1 and H2 in the +X direction are generated in the hollow portions of the magnetic field generating coils LB1 and LB2. Note that in FIG. 8, for convenience of illustration, currents I1 and I2 are shown near the magnetic field generating coils LB1 and LB2, respectively.

[0051] FIG. 9 shows a schematic diagram of a flying object 30 according to a third embodiment. The flying object 30 includes a main body 30A, which is provided with a time-delay circuit 31, a current detector 12, a capacitor Cm, and a magnetic field detection coil Lm. Electrodes EA1 and EA2 are provided so as to be exposed on the outer surface of the cylindrical main body 30A. The magnetic field detection coil Lm is provided near the outer surface of the cylindrical main body 30A. For example, the magnetic field detection coil Lm may be fitted into a groove provided on the outer surface of the cylindrical main body 30A. Furthermore, the magnetic field detection coil Lm may be exposed from the outer surface of the cylindrical main body 30A, or may be covered with a cover made of a material that transmits magnetic fields.

[0052] In this embodiment, the time-limit operation circuit 31 has a configuration in which a zero-cross detection unit 35 is added to the time-limit operation circuit 11 according to the first embodiment. Also, in the time-limit operation circuit 31, the current detector 12 is provided to detect the induced current I flowing through the magnetic field detection coil Lm.

[0053] Next, the operation of the time limit operation circuit 31 according to the third embodiment will be described in detail. [Activation stage] At this stage, similar to the first embodiment, the flying object 30 is placed in an initial position when it is launched from the launch device 3. The capacitor C0 of the power supply circuit S0 is connected to an external power source and charged to a charging voltage V0. At the initial position, the electrode EA1 of the flying object 30 contacts the external electrode EB1_0 of the insulating rail B1, and the electrode EA2 of the flying object 30 contacts the external electrode EB2_0 of the insulating rail B2. As a result, similar to the first embodiment, the capacitor Cm is charged, power is supplied to the time-limited operation circuit 31, and the time-limited operation circuit 31 starts operating (i.e., it is turned on).

[0054] [Injection stage] When current is applied to the conductive rails A1 and A2 and the armature AM, the flying object 30 is launched from the launch port EX, as in the first embodiment. The launched flying object 30 first passes through the magnetic field generating coil LB1, which is close to the launch port. At this time, an induced current I is generated in the magnetic field detection coil Lm by the magnetic field H1 generated by the magnetic field generating coil LB1.

[0055] 10 shows the induced current flowing in the magnetic field detection coil Lm before and after it passes through the magnetic field generation coil LB1. Before the magnetic field detection coil Lm passes through the magnetic field generation coil LB1, when the magnetic field detection coil Lm approaches the magnetic field generation coil LB1, the magnetic field H1 causes an induced current I to flow counterclockwise in the magnetic field detection coil Lm when viewed along the X direction (the direction from left to right on the paper in FIG. 10).

[0056] After that, when the magnetic field detection coil Lm passes through the magnetic field generating coil LB1 and moves away from the magnetic field generating coil LB1, the magnetic field H1 causes an induced current I to flow in the magnetic field detection coil Lm in a clockwise direction when viewed along the X direction.

[0057] In other words, the direction of the induced current I flowing through the magnetic field detection coil Lm is opposite before and after passing through the magnetic field generating coil LB1. If the directions of the induced current I before and after passing through the magnetic field generating coil LB1 are positive and negative, respectively, the current value of the induced current I changes from positive to negative (zero crossing). Therefore, by detecting the zero crossing point of this induced current I, it is possible to detect the timing when the magnetic field detection coil Lm passes through the magnetic field generating coil LB1.

[0058] Similarly, when the magnetic field detection coil Lm passes through the magnetic field generation coil LB2, the induced current I changes from positive to negative (zero crossing), but since the principle is the same, the explanation will be omitted.

[0059] The direction of the current flowing through the magnetic field detection coil may be opposite. In this case, the direction of the magnetic field generated by the magnetic field detection coil is opposite, but the current value of the induced current I flowing through the magnetic field detection coil Lm changes from negative to positive (zero crossing), and the zero crossing point can be detected in the same way.

[0060] In this configuration, the zero-cross detector 35 detects the zero-cross point of the induced current I and outputs a detection signal DET to the activation signal generating circuit 13. The activation signal generating circuit 13 can calculate the speed of the flying object 30 immediately after launch by dividing the time difference Δt between the detection signals DET received each time the flying object 30 passes through two magnetic field generating coils by the distance W2. The activation signal generating circuit 13 can then output a maneuver signal ST to the load circuit 14 at an appropriate timing based on the calculated speed, thereby activating the load circuit 14 at the desired timing.

[0061] Other embodiments The present invention is not limited to the above-described embodiment, and can be modified as appropriate without departing from the spirit of the invention. For example, the railgun configuration of the launching device described above is merely an example, and it goes without saying that the present invention can be applied to cases where a projectile is launched by a railgun of various other configurations.

[0062] In the above embodiment, an example in which a pair of insulating rails is provided in the injection device has been described, but the number of insulating rails may be three or more depending on the application.

[0063] In the second embodiment, the description has been given assuming that the external electrode pair is provided on the insulating rail B1, but it goes without saying that the external electrode pair may also be provided on the insulating rail B2.

[0064] In the third embodiment, a configuration in which two magnetic field generating coils are provided has been described, but this is merely an example, and three or more magnetic field generating coils may be provided to detect three or more zero crossing points, and the speed of the flying object may be calculated based on the detection results.

[0065] In the third embodiment, similarly to the first embodiment, the electrodes EA1 and EA2 of the flying object may be arranged, and an external electrode pair may be arranged on one of the insulating rails. [Explanation of symbols]

[0066] 1~3 Injection device 10, 20, 30 projectiles 10A, 30A main unit 11, 31 Timed operation circuit 12 Current detector 13 Start signal generation circuit 14 Load circuit 35 Zero cross detector 100 Injection System 101 Power supply 102 Switch 103 Control device A1, A2 Conductive rails AM armature B1, B2 insulating rails C0~Cn, Cm capacitors CON control signal DAk, DBk diodes DET detection signal EA1, EA2 electrode EB1_0~ External electrode EB1_0~EB1_n, EB2_0~EB2_n external electrode EX injection port Lk inductor LB1, LB2 magnetic field generating coils Lm magnetic field detection coil PA electrode pair PB0~PBn External electrode pairs Rk resistance S0~Sn Power supply circuit

Claims

1. a projectile inserted into a space surrounded by a pair of conductive rails and a pair of insulating rails arranged opposite to each other in an injection device, the projectile being accelerated in a first direction, which is the extension direction of the conductive rails, by receiving a force from a conductive member that is accelerated by a current flowing from the conductive rails, and being injected from an injection port of the injection device at an end of the conductive rails, The main body and a pair of first electrodes provided on an outer surface of the body; a capacitor provided within the body and connected between the pair of first electrodes; a current detector for detecting a charging current of the capacitor; an activation signal generating unit that calculates the velocity of the flying object based on the timing at which the charging current flows and outputs an activation signal based on the calculated velocity; a load circuit that receives power from the capacitor and is activated in response to the activation signal, a plurality of electrode pairs, each consisting of a pair of second electrodes arranged at positions facing the flying object, are arranged in the first direction on the pair of insulating rails; the flying object is inserted into the space, and after the flying object starts accelerating from the inserted position, a pulse current flows as the charging current through the capacitor each time the pair of first electrodes contacts each electrode pair, thereby charging the capacitor; the plurality of electrode pairs include a first electrode pair and a second electrode pair; the activation signal generating unit calculates the velocity of the flying object based on a time width between a pulse current flowing in the capacitor when the pair of first electrodes contacts the first electrode pair and a pulse current flowing in the capacitor when the pair of first electrodes contacts the second electrode pair, and outputs the activation signal to the load circuit based on the calculated velocity. Flying object.

2. the pair of first electrodes are provided on the outer surface of the main body at positions facing each other in a second direction perpendicular to the first direction, one of the pair of second electrodes in each electrode pair is provided on one of the pair of insulating rails, and the other of the pair of second electrodes is provided on the other of the pair of insulating rails; The flying object according to claim 1 .

3. the pair of first electrodes are arranged side by side on the outer surface of the main body in a third direction that is perpendicular to the first direction and parallel to surfaces of the pair of insulating rails that face the pair of first electrodes; the pair of second electrodes in each electrode pair are arranged side by side in the third direction; The flying object according to claim 1 .

4. The activation signal generation unit outputs the activation signal at a timing when the flying object reaches a desired position. The flying object according to any one of claims 1 to 3.

5. the projectile is a cannonball, the load circuit is a fuse; The flying object according to any one of claims 1 to 4.

6. an ejection device that ejects an object held by a conductive member by accelerating the conductive member using an electromagnetic force; a projectile that is accelerated in a first direction by the conductive member and ejected from an ejection port of the ejection device, The injection device a pair of conductive rails disposed opposite each other and extending in a first direction; a pair of insulating rails arranged opposite to each other and extending in the first direction; a plurality of electrode pairs arranged in the first direction, each of which includes a pair of second electrodes arranged in positions facing the flying object on the pair of insulating rails; The flying object is The main body and a pair of first electrodes provided on an outer surface of the body; a capacitor provided within the body and connected between the pair of first electrodes; a current detector for detecting a charging current of the capacitor; an activation signal generating unit that calculates the velocity of the flying object based on the timing at which the charging current flows and outputs an activation signal based on the calculated velocity; a load circuit that receives power from the capacitor and is activated in response to the activation signal, the flying object is inserted into a space surrounded by the pair of conductive rails and the pair of insulating rails, and after the flying object starts accelerating from the inserted position, a pulse current flows as the charging current through the capacitor each time the pair of first electrodes contact each electrode pair, thereby charging the capacitor; the plurality of electrode pairs include a first electrode pair and a second electrode pair; the activation signal generating unit calculates the velocity of the flying object based on a time width between a pulse current flowing in the capacitor when the pair of first electrodes contacts the first electrode pair and a pulse current flowing in the capacitor when the pair of first electrodes contacts the second electrode pair, and outputs the activation signal to the load circuit based on the calculated velocity. Injection system.

7. 1. A launching device that launches a projectile held by a conductive member by accelerating the conductive member using an electromagnetic force, a pair of conductive rails disposed opposite each other and extending in a first direction; a pair of insulating rails arranged opposite to each other and extending in the first direction; a plurality of electrode pairs arranged in the first direction, each of which includes a pair of second electrodes arranged in positions facing the flying object on the pair of insulating rails; The flying object is The main body and a pair of first electrodes provided on an outer surface of the body; a capacitor provided within the body and connected between the pair of first electrodes; a current detector for detecting a charging current of the capacitor; an activation signal generating unit that calculates the velocity of the flying object based on the timing at which the charging current flows and outputs an activation signal based on the calculated velocity; a load circuit that receives power from the capacitor and is activated in response to the activation signal, the flying object is inserted into a space surrounded by the pair of conductive rails and the pair of insulating rails, and after the flying object starts accelerating from the inserted position, a pulse current flows as the charging current through the capacitor each time the pair of first electrodes contact each electrode pair, thereby charging the capacitor; the plurality of electrode pairs include a first electrode pair and a second electrode pair; the activation signal generating unit calculates the velocity of the flying object based on a time width between a pulse current flowing in the capacitor when the pair of first electrodes contacts the first electrode pair and a pulse current flowing in the capacitor when the pair of first electrodes contacts the second electrode pair, and outputs the activation signal to the load circuit based on the calculated velocity. Injection device.

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