JP6239724B1 - Flying object - Google Patents

Abstract

An object of the present invention is to protect a flying object flying at high speed from aerodynamic heating and to burst the flying object at the time of collision. A liquid filling unit is provided inside an outer shell and filled with a liquid. The discharge valve 5 is connected to the liquid filling unit 11 and opens when the pressure of the liquid 10 is equal to or higher than a predetermined value. The discharge nozzle 4 discharges the discharge from the discharge valve 5 in the direction opposite to the flight direction. The metal storage unit 21 is provided in contact with the liquid filling unit 11 and is configured as a sealed container in which the metal 20 is enclosed. [Selection] Figure 1

Description

  The present invention relates to a flying object.

  It is known that a flying object flying at high speed in the air is heated by aerodynamic heating, that is, the surface of the flying object is heated by frictional heat with air. Therefore, in order to prevent malfunction and damage of the flying object due to the temperature rise, a method for suppressing the temperature rise has been proposed.

  For example, the structure which suppresses the temperature rise of a front-end | tip dome by circulating a cooling fluid to the front-end | tip dome of a flying body is proposed. FIG. 7 shows a configuration example of a flying body that can suppress the temperature rise of the tip dome (Patent Document 1).

  In the flying body main body 510, an infrared sensor 521 is disposed corresponding to the tip dome 511. The infrared sensor 521 is connected to the guidance control unit 522, detects infrared rays from a target (not shown), and outputs a detection signal to the guidance control unit 522. The guidance control unit 522 is connected to the steering blade 523 constituting the propulsion device, generates a guidance signal based on the detection signal input via the infrared sensor 521, controls the steering blade 523, and controls the flying body main body 510. Guide in the target direction.

  In this flying body, a coolant accommodating portion 512 is provided between the first dome 511A and the second dome 511B of the tip dome 511. When the acceleration of the flying body 510 is increased, the coolant stored in the coolant storage unit 517 is circulated and supplied to the coolant storage unit 512 of the tip dome 511 through the second pipe 515 using the change in acceleration. Is done. Then, after the cooling liquid has taken away the amount of heat by the aerodynamic heating of the tip dome 511, the cooling liquid is led to the cooler 516 through the first pipe 514 to be cooled, and again through the third pipe 518 to the cooling liquid storage unit 517. Be contained. When the acceleration decreases as the flying speed of the flying body 510 decreases, the liquid supply path is reversed, and the coolant stored in the coolant storage unit 517 cools the tip dome 511 via the cooler 516. The tip dome 511 is cooled by being supplied to the liquid container 512.

  In the coolant storage unit 517, the piston 519 is housed and disposed so as to be movable in the directions of arrows A and B so that the coolant is filled inside. As a result, the piston 519 is urged to move in the direction of the arrow A or B in the coolant storage unit 517 according to the direction in which the acceleration is applied, and the coolant in the coolant storage unit 517 is discharged according to the direction of movement. It discharges to one of the second pipe 515 or the third pipe 518. The piston 519 is latched and positioned at a predetermined position of the coolant storage unit 517 until reaching a desired acceleration via the latch mechanism 520.

JP 2002-277199 A

However, the flying object described above has the following problems. In order to apply the above-described cooling mechanism for a flying object to a small flying object that flies at a speed exceeding the hypersonic region, for example, Mach 5, the cooling mechanism itself must be miniaturized. However, it is known that the aerodynamic heating in the hypersonic region is 100 MW / m ² or more, which is an order of magnitude larger than the supersonic region (Mach 1.2 or more and less than 5). The temperature at the tip of the flying object in the middle exceeds 1000 ° C., and exceeds 2500 ° C. during the flight. Therefore, such a small circulation type cooling mechanism has a problem that the operation cannot follow the temperature rise and the cooling becomes insufficient.

  Also, if the acceleration at the time of launching the flying object is large, such as an electromagnetic injection device called a railgun, if the acceleration at the time of launching is extremely high, such as tens of thousands of G or more, the inside of the flying object is to withstand the acceleration. It is desirable to simplify the structure as much as possible. For this reason, it is not preferable to mount a complicated mechanism such as a coolant circulation mechanism or a mechanical part such as a piston on the flying object. In addition, there is a problem that things that may be ignited by an acceleration impact such as glaze cannot be mounted on the flying object.

  The present invention has been made in view of the above circumstances, and an object of the present invention is to cool a flying object flying at high speed to protect it from aerodynamic heating and to burst the flying object at the time of collision.

  A flying object according to one aspect of the present invention is provided with an outer shell, a liquid filling portion provided inside the outer shell, filled with liquid, and the liquid filling portion, and the pressure of the liquid is predetermined. A first valve that opens when the value is equal to or greater than the first valve; a first nozzle that discharges the discharge from the first valve in a direction opposite to the flight direction; and the liquid filling unit. And a metal storage portion configured as a sealed container in which metal is enclosed. As a result, the tip of the outer shell is heated by aerodynamic heating during flight, and when the pressure of the liquid exceeds a predetermined pressure, the first valve opens and the liquid is vaporized from the first nozzle. Gas is discharged from the flying object. As a result, since the liquid is cooled by the heat of vaporization, the tip of the outer shell can be protected from excessive temperature rise. When the flying object collides with an external object after flying, the metal storage unit is damaged and the liquid and the metal are mixed. At this time, a high-temperature liquid or a high-temperature gas generated by vaporizing the liquid and a metal chemically react with each other, and a gas is preferably generated by the reaction, which can cause a crack.

  A flying object according to one aspect of the present invention is the above-described flying object, and performs an exothermic reaction when the liquid or a gas generated by vaporizing the liquid and the metal are mixed at a predetermined temperature or higher. It preferably occurs. As a result, when the flying object collides with an external object after flying, the high-temperature liquid or the high-temperature gas generated by vaporizing the liquid and the metal undergoes an exothermic reaction, and as a result, a crack can be generated. .

  The flying object which is one aspect of the present invention is the above-described flying object, and the liquid is preferably mixed with the metal in a supercritical state. Thereby, in the supercritical state, there is no distinction between the liquid phase and the gas phase, and thus it is possible to cause a reaction with the metal more suitably.

  A flying object according to an aspect of the present invention is the above-described flying object, wherein the outer shell is provided with a tip dome having a tip facing the flying direction, and the tip dome is directed toward the metal storage portion. It is preferable to further have a projecting rod extending. Thereby, when the front-end | tip of a flying body collides with an external object, a metal storage part can be damaged reliably and the mixture of a liquid and a metal can be more easily burst.

  The flying object which is one aspect of the present invention is the above-described flying object, and it is preferable that the thrust bar is provided so as to extend in the flying direction. Thereby, when the tip of the flying object collides with an external object, the metal accommodating part can be more easily damaged by more efficiently applying the impact force at the time of collision to the metal accommodating part.

  The flying object which is one aspect of the present invention is the above-described flying object, and one end of the thrust bar on the metal housing part side preferably has a tapered shape that becomes narrower toward the metal housing part. . Thereby, when the tip of the flying object collides with an external object, the metal housing part can be more easily damaged by reducing the area of the part to which the impact force is applied in the metal housing part.

  A flying object according to an aspect of the present invention is the above-described flying object, further including a pipe provided inside the metal storage portion so as to extend in the flying direction, and one end of the pipe is The abutting against the inner wall of the metal storage part at a position facing the thrust bar, the liquid introduced from the liquid filling part or the liquid is evacuated to the tube by the thrust bar breaking through the metal storage part. It is desirable that a plurality of ejection holes for ejecting the gas generated by the conversion toward the metal is provided. Thereby, the liquid or the gas which the liquid vaporized can be ejected simultaneously and uniformly through the ejection hole provided in the pipe | tube with respect to the some site | part of a metal. As a result, the metal can be cracked more rapidly and uniformly.

  The flying object which is one aspect of the present invention is the above-described flying object, and the thickness of the metal storage part at a position facing the thrust bar is that of the metal storage part at a position not facing the thrust bar. It is desirable that it is thinner than the thickness. Thereby, by reducing the mechanical strength of the metal storage portion at the position facing the thrust bar, the metal storage portion can be more easily damaged when the tip of the flying object collides with an external object.

  The flying object that is one embodiment of the present invention is the above-described flying object, and preferably includes a plurality of sets of the first valve and the first nozzle. Thereby, the flow rate of the discharge | emission material from each nozzle can be adjusted with the number of the groups which consist of a 1st valve | bulb and a 1st nozzle.

  A flying object according to an aspect of the present invention is the flying object described above, wherein one or a plurality of second objects are provided in the metal storage part so that the liquid filling part and the inside of the metal storage part can be connected. A valve, a signal receiving unit provided on a surface of the outer shell facing in the opposite direction and configured to receive a control signal, and the one or more according to the control signal received by the signal receiving unit And a valve control unit for opening the second valve. Thereby, according to the control signal, the flying object can be exploded in the vicinity of the target object before colliding with the target object or even when the target object is not flying on the collision course.

  The flying object which is one aspect of the present invention is the above-described flying object, wherein a third valve connected to the liquid filling unit, and discharge from the third valve are directed to the opposite direction. A second nozzle that discharges to the rear of the flying object at a predetermined angle, and the valve control unit detects the attitude of the flying object and determines the position of the third valve according to the detection result. It is desirable to control the opening and closing. Thus, by discharging the gas from the third valve, it is possible to control the attitude of the flying object and guide the flying object to a desired target.

  The flying object which is one embodiment of the present invention is the above-described flying object, and preferably includes a plurality of sets of the third valve and the second nozzle. Thereby, the attitude control of the flying object can be performed more precisely.

  The flying object which is one aspect of the present invention is the above-described flying object, wherein the outer shell around the liquid filling portion has a fragmented portion made of a material having a density higher than that of the outer shell. Is desirable. Thereby, when the crack by a liquid and a metal arises, a fragment with a high density is scattered around, and the destruction effect by a fragment can be increased.

  The flying object which is one aspect of the present invention is the above-described flying object, and it is preferable that a plurality of kerfs are provided on the side of the fragmented part facing the liquid filling part. Thereby, fragments can be easily generated at the time of the fracture, and fragments having a desired size can be obtained depending on the position of the kerf.

  The flying object which is one aspect of the present invention is the above-described flying object, and further includes a secondary bullet storage unit provided between the metal and the outer shell and storing a plurality of secondary bullets. Is preferred. Thereby, the destruction effect can be increased by spraying the bullets having a desired size and shape at the time of the burst.

  The flying object which is one embodiment of the present invention is the above-described flying object, wherein the liquid is water, and the metal is any one of aluminum, magnesium, zinc and boron, or a part or all of the metal. It is preferably a mixture. Thereby, when the liquid or the gas in which the liquid is vaporized and the metal are mixed, an exothermic reaction occurs, and hydrogen gas can be generated. As a result, the flying object can be exploded. In addition, since liquid and metal do not cause a chemical reaction at room temperature, it can be safely stored and transported, and a flying object with high durability against the force applied by acceleration when injected is realized. Can do.

  The flying object according to one aspect of the present invention is the above-described flying object, and the metal is preferably enclosed in the metal storage part as a powder, a member having a hollow part, or a porous member. . As a result, the contact area between the liquid or the gas in which the liquid is vaporized and the metal can be increased, and an exothermic reaction can be caused quickly and efficiently.

  According to the present invention, a flying object flying at high speed can be cooled and protected from aerodynamic heating, and the flying object can be exploded at the time of collision.

It is a figure which shows typically the cross-sectional structure of the flying body concerning Embodiment 1. FIG. It is a figure which shows typically the cross-sectional structure of the flying body concerning Embodiment 2. FIG. It is a figure which shows typically the cross-sectional structure of the modification of the flying body concerning Embodiment 2. FIG. It is a figure which shows typically the cross-sectional structure of the flying body concerning Embodiment 3. FIG. It is a figure which shows typically the cross-sectional structure of the modification of the flying body concerning Embodiment 3. FIG. It is a figure which shows typically the cross-sectional structure of the flying body concerning Embodiment 4. FIG. It is a figure which shows the structural example of the flying body which can suppress the temperature rise of a front-end | tip dome.

    Embodiments of the present invention will be described below with reference to the drawings. In the drawings, the same elements are denoted by the same reference numerals, and redundant description is omitted as necessary.

Embodiment 1
A flying object according to the first embodiment will be described. FIG. 1 schematically shows a cross-sectional configuration of a flying object 100 according to the first embodiment. In FIG. 1, the flying object 100 is displayed as a flying object whose traveling direction is the positive direction of the X axis parallel to the horizontal direction of the paper (the right direction of the paper). The flying object 100 in the present embodiment will be described as being ejected from a device that emits a high acceleration to an object, such as a gun or an electromagnetic ejection device.

  In the present embodiment, the flying object 100 is ejected at a high acceleration, and the temperature of the tip or front surface of the flying object 100 is heated to about 1000 ° C. within a few milliseconds after the start of acceleration. Therefore, in order to protect from damage due to heating, the flying object 100 is provided with a mechanism for cooling the outer shell of the tip or front part of the flying object 100. Hereinafter, the configuration of the flying object 100 will be specifically described.

  The flying body 100 has an outer shell composed of a flying body main body 1, a tip dome 2, and a bottom portion 3, which are made of, for example, a metal member. The flying body main body 1 and the tip dome 2 are configured as members having a cylindrical portion whose central axis is the X-axis direction. The cylindrical portion has, for example, a circular cross section in a plane to which a Y axis that is a direction perpendicular to the X axis in the paper plane and a Z axis that is parallel to the normal direction of the paper plane belong. The tip dome 2 has, for example, a conical shape with the tip 2C as a vertex in order to suppress air resistance during flight.

  In the space inside the flying body 1 and the tip dome 2, a liquid filling unit 11 filled with the liquid 10 is provided. In addition, inside the liquid filling unit 11, a metal storage unit 21, which is a sealed container in which the metal 20 is stored, is provided in contact with the liquid 10 in the liquid filling unit 11.

  In the following, the liquid 10 and the metal 20 are selected so that a chemical reaction accompanied by heat generation occurs when the high-temperature liquid 10 or a high-temperature gas of the liquid 10 is in contact with the metal 20. In order to chemically react the liquid 10 or the high-temperature gas of the liquid 10 and the metal 20 at high speed and high efficiency, it is preferable that the contact area between the liquid 10 or the high-temperature gas of the liquid 10 and the metal 20 can be increased. Therefore, the metal 20 is a metal container 21 as a powder, for example, as a member having a large number of hollow parts such as a honeycomb structure, or as a porous member having fine holes into which the liquid 10 or the high-temperature gas of the liquid 10 can be introduced. It is preferable to be enclosed inside.

  In the present embodiment, the tip dome 2 has a dome portion 2A and a stick 2B. As described above, the dome portion 2A is configured as a member having a dome shape with the tip 2C as a vertex. The thrust bar 2B connects the inner wall of the tip dome 2 near the tip 2C and the metal storage portion 21.

  A discharge nozzle 4 penetrating through the bottom 3 is provided at the bottom 3 of the flying object 100. The discharge nozzle 4 is connected to the liquid filling unit 11 through a discharge valve 5 and a gas discharge pipe 6. Thereby, when the discharge valve 5 is opened when the liquid 10 inside the liquid filling unit 11 becomes high temperature and high pressure, high temperature gas can be discharged from the discharge nozzle 4 in the direction opposite to the traveling direction. Hereinafter, the discharge nozzle 4 is also referred to as a first nozzle, and the discharge valve 5 is also referred to as a first valve.

  Hereinafter, the operation of the flying object 100 when the flying object 100 is ejected and flying in the air at high speed will be described. During the flight of the flying object 100, the temperature of the tip dome 2 rises due to friction with air. For example, when the flying object 100 flies at a supersonic speed, the tip dome 2 generates a quantity of heat that can raise the temperature to about 3000 [K]. At this time, the liquid 10 inside the liquid filling unit 11 acts as a cooling liquid for cooling the tip dome 2, thereby preventing damage to the tip dome 2 due to heat. Further, when the tip dome 2 is continuously heated, heat is conducted from the tip dome 2 to the liquid 10, thereby increasing the temperature and pressure of the liquid 10.

  In this configuration, when the pressure in the liquid filling unit 11 rises to a predetermined value, for example, about 1000 atmospheres, the discharge valve 5 opens autonomously. When the discharge valve 5 is opened, the high-temperature and high-pressure liquid 10 is vaporized, and high-temperature gas is discharged from the discharge nozzle 4 to the rear of the flying object 100 through the gas discharge pipe 6 and the discharge valve 5. Thereby, the pressure inside the liquid filling part 11 is maintained below a certain level, and the flying object 100 can be prevented from being damaged. At this time, depending on the gas discharge amount and discharge speed, it is possible to apply an auxiliary propulsive force to the flying object 100.

  Moreover, it is also possible to suppress generation | occurrence | production of the turbulent flow in the rear part of the flying body 100 by discharging | emitting high temperature gas back. Thereby, since the flow in the vicinity of the flying object 100 can be adjusted and the air resistance can be reduced, the flying posture of the flying object 100 can be stabilized.

  In addition, although demonstrated as what has one set of the discharge nozzle 4 and the discharge valve 5 here, this is only an illustration. A plurality of discharge nozzles 4 and discharge valves 5 may be provided, that is, a plurality of pairs of discharge nozzles 4 and discharge valves 5 may be provided. In this case, the flow rate of the gas discharged from the discharge valve 5 or the distribution of the gas discharged backward from the bottom 3 can be adjusted by the number of the discharge valves 5.

  Thereafter, when the tip dome 2 collides with an arbitrary object, for example, a target, the thrust bar 2B destroys the metal storage portion 21. As a result, the metal 20 in the metal storage part 21 is contacted or mixed with the high-temperature gas which the liquid 10 vaporized. In the present embodiment, as described above, the liquid 10 and the metal 20 are selected so as to cause an explosive chemical reaction, in other words, to explode. In other words, it can be understood that the liquid 10 and the metal 20 cause the same chemical reaction as the glaze when the flying object 100 collides with the object.

In the present embodiment, as an example, a case where the liquid 10 is water and the metal 20 is aluminum will be described. For example, aluminum is encapsulated in the metal storage portion 21 in a powdered state. Aluminum and high-temperature steam cause the reaction shown in the following reaction formula (1).

2Al + 3H ₂ O = Al ₂ O ₃ + 3H ₂ +818.21 [kJ / mol] (1)

  In particular, when the temperature is 374 ° and the pressure is 218 atm, water becomes a supercritical state and there is no distinction between the liquid phase and the gas phase, so that the state suitable for the reaction with the metal 20 is obtained. Therefore, here, it is assumed that the exothermic reaction and gas generation occur when the liquid 10 or the gas 10 generated by vaporizing the liquid 10 and the metal 20 are brought into contact with and mixed with each other.

  As can be seen from Equation (1), the chemical reaction between the high-temperature water vapor and aluminum generates heat and the accompanying generation of high-temperature hydrogen gas. That is, the flying object 100 is ruptured by an explosive reaction inside the flying object 100, and a plurality of pieces are scattered around the flying object 100 at high speed. As a result, the destruction effect on the target or its surroundings can be increased by the cracking and debris effects.

  In this configuration, as the liquid 10 and the metal 20, a combination such as water and aluminum in which a chemical reaction does not proceed at room temperature is selected. For this reason, when the flying object 100 is not flying, even if an impact is applied to the flying object 100 or a malfunction occurs and the liquid 10 and the metal 20 are mixed, no explosion occurs. Further, even when the flying object 100 is ejected at a high acceleration of several tens of thousands G, for example, 30,000 G or more as in a rail gun, the liquid 10 is at room temperature at the time of injection, so that the situation where the flying object 100 may accidentally burst due to the high acceleration. It can be surely prevented. Moreover, since it does not explode at room temperature, the flying object 100 is advantageous from the viewpoint of ensuring safety during storage and transportation.

  Moreover, in this structure, since the glaze with a normal combustion reaction is not used, the carbon dioxide by a chemical reaction does not arise. Therefore, the flying object 100 can contribute to prevention of global warming. And since the flying object 100 does not use a glaze, the fuze which detonates a glaze is not required. Therefore, it is not necessary to attach or detach the fuze, so that the flying object 100 can be stored and ejected more easily.

Embodiment 2
Next, a flying object according to the second embodiment will be described. A flying object 200 according to the second embodiment is a modification of the flying object 100 according to the first embodiment. FIG. 2 schematically shows a cross-sectional configuration of the flying object 200 according to the second embodiment. The flying object 200 has a configuration in which the metal storage part 21 of the flying object 100 according to the first embodiment is replaced with a metal storage part 22.

  In the flying body 200, a high temperature gas introduction pipe 23 having the propulsion direction, that is, the X axis as the central axis direction is provided inside the metal housing portion 22. The high temperature gas introduction pipe 23 is provided with a plurality of gas ejection holes 24. In this configuration, the metal 20 is stored in a portion surrounded by the inner wall of the metal storage portion 22 and the hot gas introduction pipe 23.

  Between the inner wall of the distal end 2C of the distal end dome 2 and the metal storage portion 22, a thrust bar 2B having the traveling direction, that is, the X axis as the longitudinal direction is provided. In the present configuration, a rupture desk 25 is provided in the metal storage portion 22 at a position facing the thrust bar 2B. The rupture desk 25 is formed so as to be thinner than other portions of the metal storage portion 22. Thereby, the rupture desk 25 can be easily broken by the stick 2B. Note that the tip of the thrust bar 2B may be separated from the rupture desk 25 or may be in contact therewith. In addition, it is desirable that the tip of the thrust bar 2B has a tapered shape that becomes narrower toward the rupture desk 25.

  Further, the flying body main body 1 around the metal storage portion 22 is provided with a fragmentation portion 1A. In the present embodiment, the fragmented portion 1A is a part of the flying body main body 1. For example, by providing a kerf on the inner wall of the fragmented portion 1A, the liquid 10 and the metal 20 can be easily reacted. Configured to be multiple pieces. Thereby, the destruction effect by the debris with respect to the target object or the periphery of the target object can be increased. Moreover, you may comprise the fragmentation part 1A with a material with a density larger than parts other than the fragmentation part 1A of the flying body main body 1. FIG. In this case, the fragment effect can be further increased.

  In the present embodiment, when the flying object 200 collides with the target, the liquid 10 vaporized by the thrust bar 2B breaking through the rupture desk 25 is introduced into the high-temperature gas introduction pipe 23. Thereafter, the hot gas is ejected toward the metal 20 through the gas ejection holes 24. Thereby, as in the first embodiment, an exothermic reaction and generation of hydrogen gas occur. Therefore, the same effect as that of the flying object 100 can be obtained.

  Moreover, according to the flying object 200 concerning this Embodiment, a high temperature gas can be ejected more uniformly with respect to each site | part of the metal 20. FIG. That is, exothermic reaction and generation of hydrogen gas can be performed uniformly and at high speed. As a result, the destructive effect on the target or its surroundings can be further increased.

  In the present embodiment, the example in which the fragmented portion 1A is provided has been described, but this is merely an example. For example, instead of the fragmentation part 1A, a part for storing a bullet formed of a previously separated metal piece may be provided. FIG. 3 schematically shows a cross-sectional configuration of a flying object 201 which is a modified example of the flying object 200 according to the second embodiment. In this example, the metal storage part 22 in the flying body 200 is replaced with a metal storage part 26, and the fragmented part 1A is removed. In the metal storage part 26, a bullet storage part 27 in which a bullet 28 made of metal, for example, is stored is provided around the metal 20. Other configurations of the metal storage unit 26 are the same as those of the metal storage unit 22.

  According to the flying object 201, when the liquid 10 and the metal 20 react, a bullet is sprayed. As a result, the same effect can be obtained as if the fragments are scattered in the flying object 200. Therefore, it is possible to increase the destruction effect of the target bullet or the surroundings of the target by the bullet. In FIG. 3, the example in which the secondary bullet storage unit 27 is provided inside the metal storage unit 26 has been described. However, the secondary bullet storage unit 27 may be provided outside the metal storage unit 26.

Embodiment 3
Next, a flying object according to the third embodiment will be described. FIG. 4 schematically shows a cross-sectional configuration of the flying object 300 according to the third embodiment. The flying object 300 has a configuration in which the tip dome 2 and the rupture desk 25 of the flying object 200 are replaced with a tip dome 7 and a gas introduction control valve 29, respectively, and a valve control unit 30 and a signal receiving unit 33 are added. Hereinafter, the gas introduction control valve 29 is also referred to as a second valve.

  As shown in FIG. 4, opening and closing of the gas introduction control valve 29 is controlled by the valve control unit 30. The tip dome 7 has a configuration in which the stick 2B of the tip dome 2 is removed.

  The valve control unit 30 includes, for example, a battery 31 and a control circuit 32. The control circuit 32 is configured to be operable by receiving power supply from the battery 31. The control circuit 32 can receive the control signal CON from the outside of the flying object 300, for example, the injection device of the flying object 300 via the signal receiving unit 33. In this example, the signal receiving unit 33 is configured as an antenna capable of receiving a control signal CON that is a radio signal. For example, the signal receiving unit 33 can be provided as a ring-shaped antenna provided on the bottom 3. The control circuit 32 opens the gas introduction control valve 29 according to the received control signal CON, thereby introducing a high temperature gas into the high temperature gas introduction pipe 23 to cause an exothermic reaction and generation of hydrogen gas. As a result, the same effects as those of the first and second embodiments can be obtained.

  Here, the signal receiving unit 33 is provided on the bottom 3, and the reason will be described. Since the flying object 300 flies at hypersonic speed, for example, the surface temperature of the tip dome 7 may rise to several thousand degrees Celsius. In such a high temperature environment, ionization occurs in the material of the surface of the tip dome 7, so a transmitter that transmits radio waves and light and a receiver that receives radio waves and light are installed at the front or front of the flying object. However, it is difficult to perform communication using radio waves or light and sensing objects during flight. Therefore, in the present embodiment, the signal receiving unit 33 is provided on the bottom 3 that is not affected by the ionization of the material as described above, and the control signal CON for controlling the operation of the flying object 300 is received. It is said. Thereby, for example, the position of the target is tracked on the side of the injection device of the flying object 300, and the flying object 300 can be guided to the target object by giving the flying object 300 a control signal CON according to the tracking result. It becomes.

  In the first and second embodiments, an exothermic reaction and generation of hydrogen gas are performed when a flying object collides with a target object, as in a detonation operation using a so-called landing tube. On the other hand, in this configuration, as in the case of the detonation operation by the so-called timed fuse, the desired time can be taken even before the flying object collides with the target object or even when the flying object does not fly the collision course against the target object. Can be subjected to exothermic reaction and hydrogen gas generation. Thereby, it becomes possible to arbitrarily control the burst timing in accordance with the characteristics of the target and the desired destruction effect. This is advantageous in that, when the flying object 300 does not directly collide with the target object, the target object can be destroyed by the blast and debris by bursting the flying object 300 in the vicinity of the target object. .

  Further, even when the gas introduction control valve 29 is opened by mistake when the flying object 300 is not flying, the liquid 10 and the metal 20 are at room temperature, so that no explosion occurs due to a chemical reaction. Therefore, a highly safe flying object can be realized as in the first and second embodiments.

  In the present embodiment, the signal receiving unit 33 has been described as an antenna, but this is merely an example. For example, instead of the antenna, a signal receiving unit 34 including an optical sensor may be provided. FIG. 5 schematically shows a cross-sectional configuration of a flying object 301 that is a modification of the flying object 300 according to the third embodiment. In this example, the signal receiving unit 33 in the flying object 300 is replaced with a signal receiving unit 34. The signal receiving unit 34 receives the control signal CON that is an optical signal, photoelectrically converts the received signal, and outputs it to the valve control unit 30. Thereby, the flying body 301 can open the gas introduction control valve 29 according to the received control signal CON, similarly to the flying body 300. As a result, the same effects as those of the first and second embodiments can be obtained.

  Although the present embodiment has been described as having one gas introduction control valve 29, this is merely an example. A plurality of gas introduction control valves 29 may be provided. By providing a plurality of gas introduction control valves 29 not only in the vicinity of the tip 2C but also on the side surface of the metal housing portion 22, a high-temperature gas can be ejected to the metal 20 more uniformly and simultaneously. Thereby, the mixture of the high temperature gas and the metal 20 can be more uniformly and rapidly exploded.

Embodiment 4
Next, a flying object according to the fourth embodiment will be described. FIG. 6 schematically shows a cross-sectional configuration of the flying object 400 according to the fourth embodiment. The flying object 400 has a configuration in which the valve control unit 30 of the flying object 300 is replaced with a valve control unit 40, and an attitude control gas discharge nozzle 51, an attitude control gas discharge valve 52, and a gas discharge pipe 53 are added. . FIG. 6 shows an example in which two posture control gas discharge nozzles 51, two posture control gas discharge valves 52 and two gas discharge pipes 53 are provided. Hereinafter, the attitude control gas discharge nozzle 51 is also referred to as a second nozzle, and the attitude control gas discharge valve 52 is also referred to as a third valve.

  The valve control unit 40 has a configuration in which an attitude detection unit 43 is added to the valve control unit 30. The battery 41 and the control circuit 42 of the valve control unit 40 correspond to the battery 31 and the control circuit 32 of the valve control unit 30, respectively. The posture detection unit 43 detects the posture of the flying object 400 during flight and outputs the detection result to the control circuit 42. The control circuit 42 can control the opening and closing of the gas introduction control valve 29 similarly to the flying object 300 and can control the attitude control gas discharge valve 52 according to the detection result received from the attitude detection unit 43.

  The attitude control gas discharge valve 52 is connected to the liquid filling unit 11 via a gas discharge pipe 53. The opening / closing of the attitude control gas discharge valve 52 is controlled by the valve control unit 40. When the attitude control gas discharge valve 52 is opened, the high temperature gas is ejected to the rear of the flying object 400 through the attitude control gas discharge nozzle 51. The attitude control gas discharge nozzle 51 is provided to be inclined with respect to the center axis of the flying object 400, and discharges the high temperature gas in a direction away from the center axis of the flying object 400. Thus, by controlling the opening / closing of the plurality of posture control gas discharge valves 52, a force can be applied in the yaw direction of the flying object 400. As a result, the flying object 400 can be accurately guided with respect to the target.

  Further, the flying object 400 may perform attitude control according to the control signal CON received via the signal receiving unit 33 as well as the result of attitude detection by the control circuit 42. Further, the flying object 400 may perform attitude control according to both the result of attitude detection by the control circuit 42 and the control signal CON received via the signal receiving unit 33.

  In addition, although demonstrated as what has two sets of attitude | position control gas discharge | emission nozzles 51 and attitude | position control gas discharge | emission valves 52, this is only an illustration. One or more of the attitude control gas discharge nozzle 51 and the attitude control gas discharge valve 52 may be provided, that is, one set of the attitude control gas discharge nozzle 51 and the attitude control gas discharge valve 52 is one. You may have 3 or more sets. When one set of the posture control gas discharge nozzle 51 and the posture control gas discharge valve 52 is provided, the posture of the flying object can be controlled although the posture control direction is limited. Further, when there are three or more sets of posture control gas discharge nozzles 51 and posture control gas discharge valves 52, it becomes possible to control the posture of the flying object more precisely.

Other Embodiments The present invention is not limited to the above-described embodiments, and can be appropriately changed without departing from the spirit of the present invention. For example, in the above-described embodiment, the case where water is used as the liquid 10 and aluminum is used as the metal 20 has been described. However, other materials can be used.

For example, water may be used as the liquid 10 and magnesium may be used as the metal 20. High-temperature steam and magnesium cause the reaction shown in the following reaction formula (2).
Mg + H ₂ O = MgO + H ₂ +315.87 [kJ / mol] (2)

For example, water may be used as the liquid 10 and zinc may be used as the metal 20. High temperature steam and zinc cause the reaction shown in the following reaction formula (3).
Zn + H ₂ O = ZnO + H ₂ +62.17 [kJ / mol] (3)

For example, water may be used as the liquid 10 and boron may be used as the metal 20. High-temperature steam and boron cause the reaction shown in the following reaction formula (4).
2B + 3H ₂ O = B ₂ O ₃ + 3H ₂ +416.01 [kJ / mol] (4)
Boron is generally classified as a semi-metal that exhibits intermediate properties between metal elements and non-metal elements, but here we focus on the properties of boron as a metal element and enclose it in a metal housing. Treated boron as a metal.

  Although it has been described above that any of aluminum, magnesium, zinc, and boron can be used as the material used as the metal 20, a plurality of these may be mixed and used. That is, as the metal 20, a mixture of any two powders, a mixture of any three powders, and a mixture of four powders of aluminum, magnesium, zinc, and boron may be used as the metal 20.

  In the second embodiment, the flying object 200 having the fragmentation part 1A and the flying object 201 having the slave bullet storage part 27 have been described, but the flying object having both the fragmentation part 1A and the bullet storage part 27 is configured. May be. Also in the third and fourth embodiments, only the bullet storage unit 27 may be provided in the flying body, or both the fragmentation unit 1A and the bullet storage unit 27 may be provided.

  In the third and fourth embodiments, the flying object that does not have the thrust bar 2B has been described. However, the thrust bar 2B may be provided at a position that does not interfere with the gas introduction control valve 29, as in the first and second embodiments. Needless to say.

  Also in the fourth embodiment, a signal receiving unit 34 may be provided instead of the signal receiving unit 33.

DESCRIPTION OF SYMBOLS 1 Flying body main body 1A Fragmentation part 2,7 Tip dome 2A Dome part 2B Tip 2C Tip 3 Bottom part 4 Discharge nozzle 5 Discharge valve 6, 53 Gas discharge pipe 10 Liquid 11 Liquid filling part 20 Metal 21, 22, 26 Metal accommodation Unit 23 High-temperature gas introduction pipe 24 Gas ejection hole 25 Rupture desk 27 Ream bullet storage unit 28 Ream bullet 29 Gas introduction control valve 30, 40 Valve control unit 31, 41 Battery 32, 42 Control circuit 33, 34 Signal receiving unit 43 Attitude detection Part 51 Attitude control gas discharge nozzle 52 Attitude control gas discharge valve 100, 200, 201, 300, 301, 400 Flying object 510 Flying object body 511 Tip dome 511A First dome 511B Second dome 512 Cooling liquid storage part 514 First piping 515 Second piping 516 Cooler 517 Coolant storage unit 518 Third piping 519 Piston 520 Latch mechanism 521 Infrared sensor 522 Guidance control unit 523 Steering blade CON Control signal

Claims (17)

The outer shell,
A liquid filling portion provided inside the outer shell and filled with liquid;
A first valve connected to the liquid filling unit and opened when a pressure of the liquid is equal to or higher than a predetermined value;
A first nozzle that discharges the discharge from the first valve in a direction opposite to the flight direction;
Provided in contact with the liquid filling unit, and a metal storage unit configured as a sealed container in which metal is enclosed, and
Flying object. An exothermic reaction occurs when the liquid or a gas generated by vaporizing the liquid and the metal are mixed at a predetermined temperature or higher.
The flying object according to claim 1. The liquid is mixed with the metal in a supercritical state;
The flying object according to claim 2. The outer shell is provided with a tip dome having a tip facing the flight direction,
Further comprising a thrust bar extending from the tip dome toward the metal storage portion;
The flying object according to any one of claims 1 to 3. The thrust bar is provided so as to extend in the flight direction.
The flying object according to claim 4. One end of the thrust bar on the metal storage part side has a tapered shape that narrows toward the metal storage part,
The flying object according to claim 4 or 5. Further comprising a tube provided inside the metal storage portion so as to extend in the flight direction;
One end of the tube abuts on the inner wall of the metal storage portion at a position facing the thrust bar,
The tube has a plurality of ejection holes for ejecting the liquid introduced from the liquid filling section or the gas generated by vaporization of the liquid toward the metal by the thrust bar breaking through the metal storage section. Provided,
The flying object according to any one of claims 4 to 6. The thickness of the metal storage part at the position facing the thrust bar is thinner than the thickness of the metal storage part at a position not facing the thrust bar,
The flying object according to any one of claims 4 to 7. A plurality of sets of the first valve and the first nozzle;
The flying object according to any one of claims 1 to 8. One or a plurality of second valves provided in the metal storage portion so as to be connectable between the liquid filling portion and the inside of the metal storage portion;
A signal receiving unit provided on the surface of the outer shell facing in the opposite direction and configured to receive a control signal;
A valve control unit that opens the one or more second valves in response to the control signal received by the signal receiving unit;
The flying object according to any one of claims 1 to 9. A third valve connected to the liquid filling unit;
A second nozzle for discharging the discharge from the third valve to the rear of the flying object at a predetermined angle with respect to the reverse direction;
The valve control unit detects an attitude of the flying object, and controls opening and closing of the third valve according to a detection result;
The flying object according to claim 10. A plurality of sets of the third valve and the second nozzle;
The flying object according to claim 11. The outer shell around the liquid filling portion has a fragmented portion made of a material having a higher density than the outer shell.
The flying object according to any one of claims 1 to 12. On the side facing the liquid filling part of the fragmentation part, a plurality of kerfs are provided,
The flying object according to claim 13. Further comprising a secondary bullet storage section provided between the metal and the outer shell and containing a plurality of secondary bullets;
The flying object according to any one of claims 1 to 14. The liquid is water;
The metal is any one of aluminum, magnesium, zinc and boron, or a part or all of a mixture thereof.
The flying object according to any one of claims 1 to 15. The metal is encapsulated in the metal storage part as a powder, a member having a hollow part, or a porous member.
The flying object according to claim 16.

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