JP2002115998A - Propeller of projectile and side jet unit - Google Patents

Abstract

PROBLEM TO BE SOLVED: To solve such a problem that an article processed with heat and used in a guided projectile has a warhead and a propeller and effective operation is required because separation thereof may become useless. SOLUTION: A detonator is fixed to the solid state fuel of a propeller such that the function of a warhead can also be provided by triggering it, thus utilizing a charged powder effectively.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a propulsion device for applying a propulsive force to a flying object.

[0002]

2. Description of the Related Art FIG. 15 is a view showing a conventional guided flying object, in which 2 is a propulsion device, 3 is an igniter, 4 is a propellant, 5 is a primer, 7 is a nozzle of the propulsion device,
8 is a guidance device, 40 is a control device, 45 is a warhead, 46 is a safety detonator of a warhead, 47 is a charge of a warhead, and 48 is a wing of a flying object.

In a conventional flying object, an igniter 3 provided in a propulsion device 7 is operated by a signal from the outside, a propellant 4 starts burning, and a combustion gas is discharged from a nozzle 7 to the outside. Propell forward. Guidance device 3 while flying
When the control device 40 operates according to the command of 8, a part or all of the wing 48 is steered, and takes a predetermined flight route to approach the target. When approaching the target, the proximity fuze in the guidance device recognizes the approach of the target and the safety detonator 46
The primer 5 is actuated via. Then, the explosive charge 47 of the warhead 45 detonates and destroys the target.

[0004]

In a conventional flying object, components that generate energy using a reaction of a chemical substance are arranged separately in a warhead and a propulsion device.
In situations where the residual propellant remains and the target is reached, the residual propellant is not used effectively, and in situations where the kinetic energy to fly to the target is insufficient, the explosive of the warhead is completely lost. Missions could be disabled if not used.

An object of the present invention is to reduce the weight of a flying object and improve the function of meeting a target by effectively utilizing chemical substances of a warhead and a propulsion device mounted on the flying object.

[0006]

According to a first aspect of the present invention, there is provided a flying object propulsion apparatus which includes a propellant for performing internal combustion, a container for accommodating the propellant, a nozzle for ejecting the burned propellant, and a propulsion. An igniter for burning a medicine, a squib for detonating a propellant, and a propulsion device ignition control device for controlling ignition of the igniter and the squib.

A propelling device for a flying object according to a second aspect of the present invention is a propellant for burning an end face, a container for containing the propellant, a nozzle for ejecting the burned propellant, and a propellant disposed outside the propellant. The igniter includes a igniter for burning a medicine, a squib disposed inside the propellant to detonate the propellant, and an ignition control device for controlling ignition of the igniter and the squib.

[0008] A flying object propulsion device according to a third aspect of the present invention is the first aspect of the invention, wherein the ram fuel gas generating agent, a container accommodating the ram fuel gas generating agent, and a second device for burning the ram fuel. An igniter, a second primer for detonating ram fuel, an air inlet, and a gas supply port for jetting ram fuel gas to mix with air taken in from the air inlet; The ignition control device controls the ignition of the second igniter and the second primer.

A fourth aspect of the invention provides a flying object propulsion apparatus according to the third aspect, further comprising a separation nozzle that widens an opening of the nozzle according to ignition of the second igniter. is there.

A fifth aspect of the invention provides a flying object propulsion apparatus according to the third aspect, further comprising a nozzleless booster that widens an opening of the nozzle after ignition of the igniter and before ignition of the second igniter. Things.

A flying object propulsion device according to a sixth aspect of the present invention is the flying object propulsion device according to the first aspect, wherein the second propellant, the second container for accommodating the second propellant, and the second propellant. 2 igniter, a second primer for the second propellant, and a check valve for passing the propellant gas from the second container without passing the propellant gas from the container. .

According to a seventh aspect of the present invention, there is provided a flying object side jet apparatus, comprising: a side jet fuel; a container for storing the side jet fuel; a flow control valve for adjusting a flow rate of gas generated by combustion of the side jet; A nozzle that discharges the discharged gas flow to the outside, an igniter that burns the side jet fuel, a primer that detonates the side jet fuel, and a side jet ignition control device that controls ignition of the igniter and the primer. is there.

The flying object side jet apparatus according to an eighth aspect of the present invention is the seventh aspect of the invention, further comprising a condition determining circuit for determining whether to use as a side jet or as a warhead.

A ninth invention provides a flying object propulsion device according to any one of the first to sixth inventions, wherein the optical fiber for transmitting an ignition command to the primer and the primer which receives and operates an optical signal are provided. It is provided.

A flying object propulsion device according to a tenth aspect of the present invention is the flying object propulsion device according to any one of the first to sixth aspects, wherein the outer wall of the storage container is formed of fragment fragments.

A flying object propulsion device according to an eleventh aspect of the present invention is the flying object propulsion device according to any one of the first to sixth aspects, wherein a continuous rod is attached to an outer wall of the storage container.

A flying object propulsion device according to a twelfth aspect of the present invention is the airplane propulsion device according to the first or second aspect, wherein the proximity fuze, the arrival and departure tube, a forced detonation command, and each of these fuze and detonation commands are provided. A detonation signal generation circuit for generating a detonation signal for the primer.

According to a thirteenth aspect of the present invention, there is provided a flying object propulsion apparatus according to any one of the first to twelfth aspects, wherein a primer is disposed on an outer wall in contact with a propellant storage container.

[0019]

DESCRIPTION OF THE PREFERRED EMBODIMENTS Embodiment 1 FIG. 1 is a sectional view of an internal combustion propulsion device according to Embodiment 1 of the present invention,
In the figure, 1 is a propulsion device ignition control device, 2 is a propulsion device, 3 is an igniter, 4 is a propellant, 5 is a primer, 6 is a detonation signal path, and 7 is a nozzle. FIG. 2 is a block diagram showing the operation of this propulsion device. 8 is an external igniter ignition command, 9 is a proximity fuze, 10 is an incoming and outgoing pipe, 11 is a forced detonation command, 12 is an explosion signal generation circuit, and 13 is a propulsion signal. 1 shows a device safety detonator.

Next, the operation will be described. When the propulsion device mounted on the flying object is fired from the base unit, an ignition command is issued from the base unit, which becomes an external igniter ignition command 8 and transmitted to the igniter 3. In the case of launching from the ground, an external igniter ignition command 8 is transmitted through a launcher equipped with a flying object. The igniter 3 receives the ignition command and
The explosive inside the fuel burns, and the resulting high-temperature gas starts burning the propellant 4. The propulsion device 2 accelerates the flying object equipped with the propulsion device by a reaction when the generated gas is pushed backward through the nozzle 7. Here, when the combustion is not completed, the ignition signal generation circuit 12
, A detonation command is issued and transmitted to the detonator 5 through the detonation signal path 6 through the propulsion device safety detonator 13. When a command is transmitted to the primer 5, the primer 5 operates and its energy is rapidly transmitted to the propellant 4. As a result, the propellant 4 explodes. The detonation signal generation circuit 12 outputs a signal of the arrival / departure tube 10 for detecting that the target has been hit, a signal of the proximity fuze 9 for detecting that the vehicle has passed the vicinity of the target, or an external command when an abnormality occurs. A detonation signal is generated by a signal of a compulsory detonation command 11 for forcibly detonating the battery according to the above or by own judgment.

The explosion signal path 6 is an explosive path in the case of a normal primer, but means such as an optical fiber is used when a laser primer is used. The laser detonator itself has explosives for causing detonation, but uses light energy instead of filaments or explosives in which ignition means of the explosives is operated by electricity. The ignition control circuit has a laser light generator, and generates high-energy laser light in response to an ignition command. The generated laser light is guided to the primer 5 through an optical fiber. The primer 5 converts the guided laser light into thermal energy, and finally the explosive in the primer reacts. In this laser detonator, the use of optical fibers between the ignition control circuit and the laser detonator increases the degree of freedom in arranging the detonator, and furthermore, there is no excitation of energy along the way due to external electromagnetic noise, and it is resistant to external noise. An ignition system configuration is possible.

In general, when conducting a test operation or an evaluation test of a flying object, the test may be carried out without a warhead, but after the flying object passes near the target,
Propeller fuel may remain. At that moment,
There is a possibility that the flying object that has lost the target by passing the target will make an unstable flight, but if the propulsion device of the present invention is used, all the remaining explosives can be consumed at the desired stage, As a result, there is also an effect that a safe flying object can be constructed.

In this embodiment, the fuel is burned at a speed of several centimeters per second when burned as a propulsion device while the same gunpowder is used, and when fired as a warhead, the fire is about 4000 m or more per second. It is assumed that it will show a detonation reaction that reaches the burning rate. The underlying commonality of gunpowder and propellant charge is described in "Physical and Engineering Design of Ordinary Warhead Systems", published by the American Society of Aeronautics and Astronautics, Richard M. Lloyd, p. 278. In general, RD is used as the main component of ammunition in the explosive composition of a warhead.
X and HMX are used and are described in "Tactical Missile Propulsion System", edited by Gordon E. Jensen et al.
X and HMX are described as being used as components of high-energy propellants.Furthermore, "Explosives", published by the Nikkan Kogyo Shimbun, written by Naminosuke Kubota, p. 22 states that "propellants burn. Does not mean that the propellant will detonate, if at all, will detonate gracefully. " Even if the ignition device is ignited by burning the propulsion device, it will burn as a propulsion device, and will explode as a warhead when detonated by applying a shock with a detonator.

Embodiment 2 FIG. FIG. 3 is a cross-sectional view of the end combustion propulsion device according to the second embodiment, in which the configuration of the first embodiment and the shape of the propellant and the arrangement of the igniter 3 and the primer 5 are different. After filling, the igniter 3 is arranged near the inlet of the nozzle 7 and the primer 5 is arranged on the end face filled with the propellant 4 in the propulsion device, so that the center of the propulsion device is not hollow as shown in FIG. This is a propulsion device that adopts a form that burns from the end face.

Next, the operation will be described. This propulsion device has a propellant shape used for anti-ship missiles and the like, and burns from an open portion of the propulsion device, so that the remaining propellant concentrates near the detonator 5 until near the end of combustion. With this method, for example, if the propellant 4 remains after hitting a target ship, it can be exploded as a warhead. Normally, not only the propulsion device but also the warhead are present in the projectile, but by detonating the remaining propellant 4 when approaching the target, the effect is added in coping with the target. Become.

Embodiment 3 FIG. FIG. 4 is a diagram showing a third embodiment in which the present invention is applied to a flow control type ducted propulsion device, in which 14 is a ram fuel gas generator,
15 is a ram fuel gas generating agent, 16 is a ram fuel igniter, 17 is a ram fuel primer, 18 is an air intake,
9 is a flow control device, 20 is a gas supply port, and 21 is a ram combustion compatible nozzle. FIG. 5 is a block diagram showing the operation of the third embodiment. In FIG. 5, reference numeral 22 denotes an internal igniter ignition command.

Next, the operation will be described. In the initial stage, the propellant 4 of the propulsion device 2 starts combustion by ignition by the operation of the igniter 3 and operates as the propulsion device 2.
After a lapse of a predetermined time, an igniter ignition command 22 is generated from the inside of the flying object, and a command is issued to the ram fuel igniter 16 to cause the ram fuel gas generating agent 15 to start decomposition at a high temperature to generate ram fuel gas. I do. The generated gas passes through the flow control device 19 and a required amount of gas is released from the gas supply port 20. The released gas is a combustible gas, reacts with oxygen in the ram compressed air that has flowed in from the air intake port 18, and is released to the outside from the ram combustion corresponding nozzle 21 to be a propulsive force. In addition, with the end of combustion of the propellant 4, the nozzle 7 moves to the ram combustion nozzle 21.
The method of transfer includes a method using nozzle combustion (nozzleless booster), a method using nozzle separation (separation nozzle), and the like. The nozzleless booster is characterized in that the open end of the propellant 4 functions as a nozzle during combustion of the propellant 4, and there is no airborne matter. On the other hand, the separation nozzle has a feature that the ideal nozzle shape can be maintained while the propellant 4 is burning, although there are airborne substances.

Here, in the stage where fuel is present, the propellant 4 or the ram fuel gas generating agent 15 is detonated by operating the primer 5 or the ram fuel detonator 17 to operate as a warhead. In Embodiments 1 and 3 of the invention, the existence of a normal warhead is not described. In general,
In order to cope with the target after the propulsion device burns, it is desirable that the warhead is mounted on the projectile, and it is customary that the projectile possesses a warhead. In this case, the description is omitted for the propelling device that is used only for the propulsion device that may also serve as a warhead.

Embodiment 4 FIG. 6 is a fourth embodiment showing an example in which the present invention is applied to a two-pulse rocket including two solid propulsion devices. In FIG. 6, reference numeral 23 denotes a second propulsion device, 24 denotes a second propellant, and 25 denotes a propulsion. Gas check valve, 26
Indicates a second igniter, and 27 indicates a second primer. FIG. 7 is a block diagram illustrating the operation. 8 and 9 are diagrams showing the relationship between the target and the flying object. FIG. 8 shows a state in which the flying object has passed near the target, and FIG. 9 shows a state in which the flying object has failed to pass near the target. Indicates the status. In the figure, reference numeral 28 denotes a target, and 29 denotes a flying object.

Next, the operation will be described. The operation of the propulsion device 2 is the same as in the first and third embodiments. The propulsion gas check valve 25 is provided so that the combustion gas generated by the propulsion device 2 that burns first does not flow to the second propulsion device 23 side, and the second propulsion device 23 is used as a propulsion device. When burning, the combustion gas is discharged in the direction of the propulsion device 2 without being disturbed by the check valve 25. Here, a case is considered in which the second propulsion device 23 is used instead of the warhead whose description has been omitted in Embodiments 1 to 3. In this case, if the kinetic energy of the flying object is sufficient with only the propulsion device 2, the second propulsion device 23 is used as a warhead to operate the second detonator 27 by approaching and hitting the target. As a result, the flying object 2 as shown in FIG.
9 can defeat target 28. However, when the flight distance to the target is long, the kinetic energy may be insufficient as shown in FIG. 9 when the propulsion device 2 alone is used near the target meeting, and the meeting to the target may not be achieved. In such a case, the ignition of the second propulsion device should be performed even if the function of the second propulsion device 23 as a warhead is abandoned, because the meeting of the target is the first mission of the projectile. By further accelerating, you can aim for a meeting to the goal. Even in that case, projectile 29 and target 3
If zero air collision can be realized, target coping can be performed to some extent even in a situation where there is no warhead. For a target at a short distance, the target can be more effectively defeated by using both the first propulsion device 2 and the second propulsion device 23 as warheads. The second propulsion device 23 transmits an igniter ignition command 22 from the inside of the flying object based on the speed of the flying object.
Is generated, and the igniter 26 is ignited by the igniter ignition command 22, whereby the second propellant 24 is ignited and operates.

FIG. 10 shows an embodiment of the invention in which the surface of the propulsion device is fragmented to further increase the effect as a warhead. In the figure, reference numeral 30 denotes a propulsion device container used as a bullet. By making the propulsion device container 30 a collection of bullets, not only the destruction effect due to the shock wave of the blast but also the destruction by the bullets becomes possible. Here, the fourth embodiment of the invention is described as an example, but the fragmentation structure here may be applied to the first to third embodiments of the invention. Although fragment fragments are described as fragments, the same applies to other methods such as a continuous rod made of a rod-shaped metal. Fragment munitions are usually made into notches in a steel plate on the outer wall of the warhead storage container in a grid pattern to make it easier to break at the time of the explosion, and the outer wall of the storage container becomes small fragments (fragment shards) due to the explosion of the warhead It will fly. In a continuous rod, a metal rod is arranged outside the warhead, and the ends are alternately joined, so that the explosion of the warhead causes a large metal rod to fly. Alternatively, a cut is made in the cylindrical portion of the warhead in parallel to the axis to make it easier to break, and when the explosion occurs, it is made into a rod-like member and scattered to destroy the target. In addition, although a diagram is shown in which bullets are added to the first propulsion device and the second propulsion device, a procedure for adding bullets only to the second propulsion device that is likely to operate as a warhead is described. You may.

Embodiment 5 In air-to-air guided missiles,
In the case where an aircraft is attacked and has to be evacuated immediately, dumping of guided missiles may be performed.
By detonating all unused propulsion devices after dumping, it is possible to damage the attacking aircraft as an aerial scattered object in the event of being attacked from behind. FIG. 11 shows the situation of the mother aircraft and the attacking aircraft when they become airborne objects due to the explosion. In the figure, reference numeral 31 denotes a base machine on which a flying object is mounted, and reference numeral 32 denotes a flying object in the air. The flying object 29 on which the propulsion device of this embodiment is mounted is dumped from the base machine 31 without the ignition of the propulsion device. At this time, the flying object 29 falls to the rear of the base unit due to air resistance, but all the propulsion devices of the flying unit 29 are detonated within a distance that can secure the safety of the base unit. Then, an area where the airborne objects 32 float is generated,
When the attacking aircraft 28 enters there, there is a possibility that airborne flying objects will be sucked into the engine and the like, making flight impossible. As a result, the attacking aircraft 28 is damaged, and the parent machine 31 can safely evade.

Embodiment 6 FIG. FIG. 12 shows a sixth embodiment in which the present invention is applied to a side jet device. In the figure, 33 is a side jet device, 34 is a side jet ignition control circuit, 35 is a side jet fuel (solid), 36 is a side jet flow control valve, and 37 is a side jet nozzle. FIG. 13 is a block diagram showing the operation of this embodiment, in which 38 is a guidance device, 39 is a condition determination circuit, 40 is a control device, and 41 is a side jet safety detonator. FIG. 14 is a diagram showing the operation when this embodiment is applied to a flying object, where 42 is a launcher for launching a flying object, 43 is a gas of a side jet emitted from the flying object, and 44 is a high altitude. Indicate your goals.

Next, the operation will be described. Altitude goal 4
The flying object 29 heading for 4 takes an association route to the target 44 at a high altitude while changing the attitude of the flying object with the control device 40 based on the guidance signal from the guidance device 38. When coping with the high altitude target 44, since the air density becomes lower at higher altitudes, the effective aerodynamic steering device does not show effective control force at low altitude, but the internally generated gas independent of the air density is generated. By using the used side jet device 33, an effective control force can be secured. This is because the side jet fuel 35 is ignited by the igniter 3 and controlled by the flow control valve 36 to discharge the generated gas at a required flow rate from the nozzle 37, so that the reaction at the time of the gas discharge can be used for the flying object. It changes the route. As described above, the side jet device 33 is used for a high altitude target, and its use is determined by the condition determination circuit 39 based on target information from the guidance device 38. When the altitude of the flying object is increased and the target is recognized as the high altitude target 44, the condition determination circuit 39 issues an activation command for the side jet safety detonator 41 and a igniter ignition command 22 for the igniter ignition command 22. Indicates an ignition command, and an inactive command is issued to the proximity fuse. If no command is issued from the condition determination circuit, the side jet safety detonator 41 and the igniter ignition command 22 from the inside are in a safe / inactive state.

When the igniter command 22 from the inside is transmitted to the igniter 3, the side jet fuel 35 starts burning, and the flow control valve 36 is controlled based on the command of the control device 40. As a result, the gas 43 emitted from the nozzle 37
As a result, the flying object 29 changes the route, and finally hits the target 44 at a high altitude. Since the altitude target 44 is high-speed but hardly changes the route, it can be destroyed by the direct hit of the flying object 29. Arrival tube 10 when hitting the target
A detonation command is generated from the detonation signal generation circuit 12 by the signal of
The signal is transmitted to. When the primer 5 is activated, the remaining side jet fuel 35 detonates and the outer shell 3 of the side jet 33
A bullet at zero will destroy the target more effectively.

However, when the side jet fuel 35 remains when the vehicle directly hits the target 44, it explodes.
When it is used as a control means and does not remain, no explosion occurs, but in that case, the target is destroyed by the kinetic energy when hitting the target directly.

On the other hand, when the target altitude of the flying target 28 is low as shown in FIG. 14, the flying object can turn by the aerodynamic steering force, but the target 28 may also avoid turning. There is. In this case, even if the side jet is used, it is difficult for the flying object 29 to directly hit the target 28. In this case, if the condition determination circuit 39 determines from the signal of the guidance device 38 that the altitude of the target 28 is low and the target can be dealt with by aerodynamic steering, the igniter ignition command 22 from the inside is inactivated, An activation command is sent to the fuse 9 and an activation command is sent to the side jet safety detonator 41. As a result, the side jet device 33 operates as a warhead having the bullet 30. That is,
The side jet fuel 3
5 is detonated. The bullet 30 may be not only a fragment bullet as described in the fourth embodiment but also a continuous rod.

According to this embodiment, when the side jet device has to be used as the flight control means, the target can be destroyed even if there is no warhead due to the direct hit effect, while it is necessary to use the side jet device as the flight control means. However, if a direct hit cannot be expected due to the target's avoidance behavior, efficient operation can be achieved by using a close fuse and acting as a warhead.

[0039]

As described above, according to the first to sixth and ninth to twelfth aspects of the present invention, the fuel portion of the propulsion device is operated as a warhead depending on the conditions, thereby making it possible to efficiently use a pyrotechnic mounted on a flying object. The use of pyrotechnics, which previously had a dedicated role as a warhead, for the propulsion device can reduce the weight of the flying vehicle Become.

According to the seventh and eighth aspects of the present invention, since the side jet device is also used as a warhead, it is necessary to control the flying object by the original operation of the side jet device and to hit the target directly. In this situation, when the control device operates as a control device and does not need the control force of the side jet and needs a function as a warhead to a target, there is an effect that efficient operation can be realized by operating as a warhead.

According to the thirteenth aspect, all the primers are arranged on the outer wall in contact with the propellant storage container.
There is an effect that the combustion of the propulsion device and the side jet fuel is not hindered, the gas generation and the gas flow inside the propulsion device are not impaired, and the original function is not reduced.

[Brief description of the drawings]

FIG. 1 is a cross-sectional view of an internal combustion propulsion device showing an example of Embodiment 1 of the present invention.

FIG. 2 is a block diagram showing the operation of the first embodiment of the present invention;

FIG. 3 is a cross-sectional view of an end-face combustion propulsion device in which the configuration of the second embodiment and the shape of the propellant are different.

FIG. 4 is a diagram showing an example of a third embodiment in which the present invention is applied to a flow control type ducted propulsion device.

FIG. 5 is a block diagram showing the operation of the third embodiment.

FIG. 6 is a diagram showing an example of a fourth embodiment in which the present invention is applied to a two-pulse rocket including two solid propulsion devices.

FIG. 7 is a block diagram showing the operation of the fourth embodiment.

FIG. 8 is a diagram showing a state in which the flying object has passed the vicinity of the target.

FIG. 9 is a diagram showing a state where a flying object cannot pass near a target.

FIG. 10 is a diagram showing a state in which the surface of the propulsion device is fragmented.

FIG. 11 is a diagram showing the situation of the mother aircraft and the attacking aircraft when they become scattered objects in the air due to the explosion.

FIG. 12 is a diagram showing a sixth embodiment in which the present invention is applied to a side jet device.

FIG. 13 is a block diagram showing the operation of the sixth embodiment.

FIG. 14 is a diagram showing an operation when the sixth embodiment is applied to a flying object;

FIG. 15 shows a conventional flying object.

[Explanation of symbols]

REFERENCE SIGNS LIST 1 propulsion device ignition control device 2 propulsion device 3 igniter 4 propellant 5 detonator 6 detonation signal passage 7 nozzle 8 external igniter ignition command 9 proximity fuze 10 arrival transmission tube 11 forced detonation command 12 detonation signal generation device 13 transmission device safe detonation Device 14 Ram fuel gas generator 15 Ram fuel gas generating agent 16 Ram fuel igniter 17 Ram fuel detonator 18 Air intake port 19 Flow control device 20 Gas supply port 21 Nozzle for ram combustion 22 Igniter ignition command from inside 23 Second Propelling device 24 second propellant 25 propelling gas check valve 26 second igniter 27 second detonator 28 target 29 projectile 30 propelling device container used as a projectile 31 mother machine 32 airborne objects 33 side jet device 34 Side jet ignition control circuit 35 Side jet fuel 6 Flow control valve for side jet 37 Side nozzle for nozzle 38 Guidance device 39 Condition judging circuit 40 Controller 41 Side jet safety detonator 42 Launcher for launching projectile 43 Gas of side jet released from projectile 44 Altitude goal

Claims (13)

[Claims] 1. A propellant for performing internal combustion, a container for storing the propellant, a nozzle for ejecting the burned propellant, an igniter for burning the propellant, a primer for detonating the propellant, and the igniter. And a propulsion device ignition control device for controlling ignition of a primer. 2. A propellant that performs end-face combustion, a container that stores the propellant, a nozzle that ejects the burned propellant, and an igniter that is disposed outside the propellant and burns the propellant.
A projectile propulsion device comprising: a detonator disposed inside a propellant for detonating a propellant; and an ignition control device for controlling ignition of the igniter and the detonator. 3. A ram fuel gas generating agent, a container for storing the ram fuel gas generating agent, a second igniter for burning the ram fuel, a second primer for detonating the ram fuel, and air A propulsion device ignition control device for igniting the second igniter and the second detonator; and a gas supply port for jetting ram fuel gas to mix with air taken in from the air intake. 2. The flying object propulsion device according to claim 1, wherein the propulsion device is controlled. 4. The flying object propulsion device according to claim 3, further comprising a separation nozzle that widens an opening of the nozzle according to ignition of the second igniter. 5. The flying object propulsion device according to claim 3, further comprising a nozzleless booster that widens an opening of the nozzle after ignition of the igniter and before ignition of the second igniter. . 6. A second propellant, a second container containing the second propellant, a second igniter for the second propellant, a second primer for the second propellant, 2. The flying object propulsion device according to claim 1, further comprising: a check valve that allows the propulsion gas from the second container to pass without passing the propulsion gas from the container. 7. A side jet fuel, a container for storing the side jet fuel, a flow control valve for adjusting a gas flow rate generated by combustion of the side jet fuel, a nozzle for discharging a gas flow whose flow rate is controlled to the outside, A side jet device for a flying object, comprising: an igniter for burning the side jet fuel; a primer for detonating the side jet fuel; and a side jet ignition controller for controlling the ignition of the igniter and the primer. 8. The side jet apparatus according to claim 7, further comprising a condition determination circuit for determining whether the side jet is to be used as a side jet or a warhead. 9. The propulsion of a flying object according to claim 1, further comprising an optical fiber for transmitting an ignition command to the primer and a primer for receiving and operating an optical signal. apparatus. 10. The flying object propulsion device according to claim 1, wherein the outer wall of the storage container is formed of fragment fragments. 11. The flying object propulsion device according to claim 1, wherein a continuous rod is attached to an outer wall of the storage container. 12. A fuze, a fuze, a forcible detonation command, and a detonation signal generating circuit for generating a detonation signal for the primer based on each of the detonation and detonation commands. The flying object propulsion device according to claim 1 or 2, wherein: 13. The flying object propulsion device according to claim 1, wherein the primer is disposed on an outer wall in contact with the propellant storage container.