JP7415512B2 - Ignition system for end-fired rocket motors - Google Patents

Description

The present invention relates to an ignition device for an edge-burning rocket motor.

A rocket motor is a rocket propulsion engine that uses a propellant made of solid fuel (hereinafter referred to as "solid propellant") that is a mixture of solid fuel and oxidizer. Rocket motors are widely used as propulsion engines for defense rockets, missiles, rockets for launching artificial satellites, observation rockets, attitude control rockets, artificial rain rockets, and the like.

A rocket motor mainly consists of a motor case, nozzle, solid propellant, and ignition device (initiator). The motor case of a rocket motor is hollow, and solid propellant is loaded inside. Further, a nozzle is provided at the rear end of the motor case. Then, the solid propellant loaded in the motor case is ignited and combusted by the ignition device, generating high-temperature, high-pressure combustion gas inside the motor case. The propulsive force of the rocket motor can be obtained by this combustion gas flowing out from the nozzle at high speed.

The ignition system for a rocket motor requires an initiator (squib or ignition ball) that ignites by passing an electric current, an ignition charge that ignites and burns with the initiator's flame, and an ignition charge that increases the combustion time and combustion energy of the ignition system. It is housed in the ignition device according to the When the ignition device is ignited, the ignition powder or ignition charge burns inside, and the combustion flame of the ignition powder or ignition charge ejects from a flame outlet provided in the case of the ignition device, igniting the propellant.

In the case of internal combustion propellants, which have a cavity (inner hole) in the center of the propellant in the axial direction, the ignition device is installed at the front of the motor opposite to the nozzle, and when the ignition device burns, the combustion flame is propelled. The propellant flows through the internal hole toward the nozzle and ignites the propellant.

For example, Patent Document 1 discloses an ignition device for an internal combustion rocket motor in which a cavity is provided in the propellant and the ignition powder is directly loaded into the cavity, or the ignition powder is filled in a combustible container. . The structure is such that a cavity is provided in the propellant of the rocket motor to house the ignition device. Ignition of the solid propellant occurs from the front side of the motor near the ignition device, but the combustion flame of the ignited propellant also flows through the inner hole towards the nozzle side, so if the propellant on the upstream side of the inner hole ignites, the combustion flame of the ignited propellant also flows through the inner hole toward the nozzle. The propellant ignites quickly. For this reason, internal combustion propellants can quickly ignite the entire surface with a relatively small amount of ignition charge.

Further, Patent Document 2 discloses an ignition device in which a methacrylate resin container having burnout property is filled with an igniter.

Further, Patent Document 3 discloses an ignition device that uses an igniter container reinforced with carbon fiber cloth or the like made of a plastic material in order to provide burnout property, and the container burns out during motor combustion. is disclosed.

Publication No. 48-96304 Japanese Unexamined Patent Publication No. 2-116387 Japanese Patent Application Publication No. 3-130566

On the other hand, in the case of an end-burning propellant that burns forward from the nozzle-side end surface of the propellant, the ignition device is installed on the nozzle-side wall surface and ignites the propellant by spraying the flame of the ignition charge onto the propellant surface.
Even if the propellant is ignited by the flame of the ignition device, the combustion flame of the propellant flows to the nozzle side and is discharged, so a larger amount of ignition powder is required compared to internal combustion propellant, and the ignition device is large. There is a tendency to become

Furthermore, since the ignition device of an edge-burning rocket motor is installed near the nozzle, the ignition device is exposed to high-temperature propellant flame when the propellant is combusted. Since end-combustion motors generally burn for a long time, the ignition device is exposed to high-temperature flame for a long time. During this time, it is necessary to install heat insulating material around the igniter to prevent it from burning out, so that the igniter does not melt down and parts block the nozzle. For this reason, there are problems in that the ignition device becomes larger, the number of parts increases, and the price becomes expensive.

Further, in the case of an ignition device in which a methacrylate resin container is filled with ignition powder as in Patent Document 2, it is assumed that sufficient ignition performance cannot be obtained for end-burning propellants with low ignitability. Furthermore, a container reinforced with carbon fiber or the like as disclosed in Patent Document 3 is expensive, and even though it is burnt-out, it does not burn out completely and generates small flexible fragments and particles. It has been shown that As a result, there is a possibility that the nozzle may be damaged or debris may be scattered behind the rocket motor.

SUMMARY OF THE INVENTION Therefore, an object of the present invention is to provide an ignition device for an edge-burning rocket motor that is small and can be manufactured at low cost.

As a result of intensive studies to address the above-mentioned problems, the inventors of the present invention discovered that the case of the ignition device houses the ignition charge inside, and at the time of ignition, the combustion flame of the ignition charge performs the function of igniting the propellant. However, they focused on the fact that the case for the ignition device was unnecessary after the propellant was ignited.

In other words, if the case disappears when the ignition device burns, parts such as a heat insulator for protection from the combustion flame of the propellant become unnecessary. Therefore, by manufacturing the case of the ignition device from a gunpowder component and making it integral with the ignition powder so that it has burnout properties, it is possible to reduce the size and cost of the ignition device, while also ensuring reliable ignition performance. The present invention was completed based on the discovery that it is possible to provide a device.
That is, the present invention is the following ignition device for an edge-burning rocket motor.

The ignition device of the present invention for solving the above problems includes an initiator fixed to a head plate on the opposite side to the propulsion direction, a gunpowder container fixed to the head plate around the initiator, and a gunpowder container loaded in the gunpowder container. ignition powder, and the explosive container is characterized in that it has burnout property.
According to this ignition device, the igniter in contact with the initiator is loaded into an ignition powder container made of explosive components, and by imparting burnout properties to the entire ignition device, the ignition device container, which is required during propellant combustion, is constructed. There is no need to provide heat-resistant strength to the material. As a result, the ignition system no longer requires insulation, making it lighter and cheaper, and at the same time, it can supply the high temperature flame and pressure necessary to ignite the end-burning propellant for a sufficient period of time. It can demonstrate reliable ignition performance.

Furthermore, according to one embodiment of the ignition device of the present invention, ignition powder is stored in a combustible film, and the ignition powder stored in the combustible film is loaded into a container made of explosives.
According to this feature, by loading the ignition powder stored in the flammable film into a gunpowder container, the flammable film can be made into various shapes, and functional designs such as higher ignition performance and sustainability can be achieved. This makes it possible to achieve the effects of the present invention in that it achieves weight reduction and cost reduction while at the same time ensuring reliable ignition performance.

Furthermore, according to one embodiment of the ignition device of the present invention, the ignition device is fixed on a mirror plate between the end of the nozzle opening of the rocket motor on the main body side and the outer peripheral wall surface.
According to this feature, when the igniter is fixed on the end plate between the end of the nozzle opening on the main body side and the outer peripheral wall surface, for example, when the igniter is fixed inside the nozzle or on the opening on the main body side of the nozzle. Compared to the ignition system, no device is required to secure the ignition system, and it is possible to avoid direct hit by the combustion flame after the solid propellant ignites, making it possible to make the ignition system smaller and lower costs. The effects of the present invention can be further exhibited. Note that the "outer peripheral wall surface" here refers to the inner side wall of the motor case.

Furthermore, according to an embodiment of the ignition device of the present invention, in a rocket motor having a plurality of nozzles, the ignition device is fixed on a mirror plate between the ends of the openings of the plurality of nozzles on the main body side. It is characterized by
According to this feature, when the ignition device is applied to a rocket motor having multiple nozzles, solid propulsion The present invention has the effect of making it possible to reduce the size and cost of the ignition device, since it is possible to ensure uniform and reliable ignition performance of the drug, and at the same time avoid direct hit by the combustion flame after ignition of the solid propellant. You can demonstrate your abilities even more.

Advantageous Effects of Invention According to the present invention, it is possible to provide an ignition device for an end-burning rocket motor that is small and can be realized at low cost in an ignition device that ignites solid propellant.

1 is a schematic vertical sectional view showing an example of a rocket motor according to an embodiment of the present invention. 1 is a schematic longitudinal sectional view showing an example of an ignition device according to an embodiment of the present invention. 1 is a schematic longitudinal sectional view showing an example of an ignition device according to an embodiment of the present invention. 1 is a schematic vertical sectional view showing an example of a rocket motor according to an embodiment of the present invention.

DESCRIPTION OF EMBODIMENTS Hereinafter, embodiments of an ignition device according to the present invention will be described in detail with reference to the drawings. It should be noted that the structure, shape, and other specific aspects of each member such as the ignition device and rocket motor described in the embodiments are merely exemplified to explain the ignition device according to the present invention, and are not limited thereto. It is not something that will be done.

[Rocket motor]
The rocket motor of the present invention will be explained using FIG. 1. FIG. 1 is a schematic vertical sectional view showing an example of a rocket motor according to an embodiment of the present invention.

As shown in FIG. 1, the rocket motor 1 includes a main body part 14 and a nozzle part 13. The main body portion 14 further includes a motor case 12 and a mirror plate 16. Further, the nozzle section 13 is composed of a nozzle main body 3 and a spout 32.

The nozzle portion 13 has a shape in which the inside diameter of the nozzle body 3 decreases from the spout 32 side toward the main body portion 14 side. The nozzle section 13 is inserted into the main body section 14 with the spout 32 facing outward. Further, an O-ring (not shown) is provided on the outer circumferential surface of the nozzle section 13 on the main body section 14 side, and the outer circumferential surface of the nozzle section 13 on the main body section 14 side and the inner circumferential surface of the main body section 14 are in a sealed state. is fixed.

An ignition device 2 is fixed on the end plate 16 between the opening start point of the nozzle body 3 inside the motor case 12 and the outer cylindrical part of the motor case 12, and the solid propellant 18 is filled in the main body part 14. ing. Further, as shown in FIG. 2, the end plate 16 to which the ignition device 2 is fixed is connected to the main body portion 14 so that combustion flame is ejected from the ignition device 2 toward the inside of the motor case 12. Thereby, when the ignition device 2 is ignited, the ignition powder 26 and the explosive container 22 are combusted, and the solid propellant 18 is blown with combustion flame. Incidentally, when fixing the ignition device 2 and the end plate 16, a sealing means such as an O-ring may be interposed between them. As a result, the outer circumferential surface of the mirror plate 16 on the main body 14 side and the inner circumferential surface of the main body 14 are fixed in a sealed state. With this configuration, the compressed gas generated by combustion of the solid propellant 18 can be ejected only from the ejection port 32 of the nozzle portion 13.

Each configuration will be explained in detail below.
<Nozzle part>
The nozzle portion 13 is a portion that discharges high-temperature, high-pressure gas generated within the rocket motor 1 to the outside of the rocket motor 1, and is a portion that generates propulsive force in the rocket motor 1 using the high-temperature, high-pressure gas.
The nozzle section 13 includes a nozzle body 3 and a jet nozzle 32, and is inserted into the end plate 16 with the jet nozzle 32 facing outward. Further, an O-ring (not shown) is provided on the outer peripheral surface of the nozzle 3 on the end plate 16 side, and the outer peripheral surface of the nozzle 3 on the end plate 16 side and the inner peripheral surface of the end plate 16 are fixed in a sealed state. .

The nozzle body 3 is provided at the outermost end of the rocket motor 1 and is a part that discharges high-temperature, high-pressure gas to the outside. The shape of the nozzle body 3 is not particularly limited, but it needs to have a hollow structure inside in order to release high temperature and high pressure gas, and it may have a structure where the diameter decreases toward the tip (tapering structure). It may also be a structure that expands. For accelerating high-temperature, high-pressure gas to supersonic speed, a structure that expands toward the exit is preferable. The material is not particularly limited, but a heat-resistant material is preferable, and graphite is particularly preferable.
Further, the length of the nozzle body 3 is not particularly limited, but can be appropriately set to a length that allows the rocket motor 1 to obtain a propulsive force.

The O-ring (not shown) is a member for ensuring airtightness inside the rocket motor 1. The material of the O-ring (not shown) is not particularly limited, but it is preferably a heat-resistant material. Further, in order to ensure airtightness inside the rocket motor 1, it is preferably made of an elastic material, and more preferably a rubber-like substance.
The inner diameter and cross-sectional area of the O-ring (not shown) are not particularly limited, but can be set as appropriate depending on the size of the rocket motor 1.

<Motor case>
The motor case 12 is a part that burns the solid propellant 18 inside and sends high-temperature, high-pressure gas to the nozzle section 13 .
The main body portion 14 includes a cylindrical motor case 12 and a mirror plate 16 fixed to one side of the motor case 12.

The main body portion 14 of the motor case 12 is a portion that burns the solid propellant 18 to generate high temperature and high pressure gas.
A solid propellant 18 is loaded in a portion of the main body 14 other than the empty portion. Further, the shape of the main body portion 14 may be a hollow shape, and the external shape is not particularly limited. For example, it may have a cylindrical shape as shown in FIG. 1, or it may have a substantially spherical shape. In addition, since high-temperature, high-pressure gas is generated by combustion of the solid propellant 18 filled inside the main body 14, from the viewpoint of pressure resistance, the shape of the main body 14 should be a structure with corners such as a rectangular parallelepiped or a cube. A cylindrical or spherical structure is more preferable.

The solid propellant 18 loaded into the main body 14 includes, for example, a double-base propellant mainly composed of nitrocellulose and nitroglycerin, ammonium perchlorate as an oxidizing agent, and HTPB (hydroxyl-terminated polybutadiene) as a fuel and binder. A composite propellant made of aluminum powder or the like can be used as a system binder and metal fuel. In order to increase the combustion rate of the solid propellant 18, for example, atomized ammonium perchlorate may be used, or iron oxide or the like may be used as a combustion catalyst. may also be blended.
The shape of the solid propellant 18 is not particularly limited as long as it can be loaded into the main body 14, and can be appropriately designed to allow the rocket motor 1 to obtain a predetermined propulsive force for a predetermined time. .
Moreover, as a method of burning the solid propellant 18, it is burned using a flame generated from an ignition device 2, which will be described later.

The end plate 16 of the motor case 12 is a part that is configured to generate a flame for burning the solid propellant 18. While the solid propellant 18 can generally be stored at room temperature, a high heat flow rate is required for combustion. Therefore, the solid propellant 18 is instantly ignited and combusted using a device that generates a high heat flow such as a combustion flame.

As shown in FIG. 1, an ignition device 2 is fixed on a mirror plate 16 between the end of the opening of the nozzle body 3 of the rocket motor 1 on the main body 14 side and the outer peripheral wall surface of the rocket motor 1. . With this configuration, a device for fixing the ignition device 2 is not required, compared to, for example, a case where the ignition device 2 is fixed inside the nozzle body 3 or on the main body side opening of the nozzle body 3, and Since the direct hit of the combustion flame after the solid propellant 18 is ignited can be avoided, the ignition device 2 can be made smaller and lower in cost. The end plate 16 is inserted into the main body 14 so that flame is ejected from the ignition device 2 toward the inside of the motor case 12.
Further, the end plate 16 includes an O-ring (not shown) that ensures airtightness inside the rocket motor 1.

(Ignition device)
The ignition device 2 is fixed inside the end plate 16 in a sealed state. As a means for fixing the ignition device 2, it may be buried using a gasket or the like, or it may be connected to the inside of the end plate 16 by welding, screw connection, or a method using an adhesive. From the viewpoint of ensuring the burnout property of the igniter 2, adhesion using an adhesive is preferable. The adhesive is not particularly limited, but for example, a heat-resistant adhesive is preferable, such as an epoxy adhesive, a silicone adhesive, and the like. Incidentally, when fixing the ignition device 2 and the end plate 16, a sealing means such as an O-ring may be interposed between them.
The arrangement of the ignition device 2 is not particularly limited, but it may be arranged at a position where combustion into the solid propellant 18 is ensured.

The ignition device 2 of the present invention will be explained in detail using FIG. 2. FIG. 2 is a schematic vertical sectional view showing an example of an ignition device according to an embodiment of the present invention.
The ignition device 2 is a part that generates a combustion flame for burning the solid propellant 18. The ignition device 2 includes an initiator 28, a combustible film 24 fixed to the top surface of the initiator 28, and a gunpowder container 22.
An igniter 26 is stored inside the combustible film 24. The initiator 28 is in contact with the ignition powder 26 inside the explosive container 22, and is connected to a power source outside the explosive container 22 (not shown). An explosive container 22 made of an explosive component is fixed on the end plate 16 so as to surround the initiator 28 and the combustible film 24.

The initiator 28 is a pyrotechnic device that ignites a small amount of gunpowder and generates a small flame by applying an ignition current supplied from an electric wire (not shown), and is called a squib or ignition ball. , a member for igniting the ignition powder 26 filled in the explosive container 22 of the present invention. As the initiator 28, an electric bridge wire that becomes red-hot when a current is applied can be used. Examples of the conductive wire material for the bridge wire include platinum wire and nichrome wire.

The ignition powder 26 filled in the combustible film 24 is a member that ignites the explosive container 22. Examples of the ignition powder 26 include BP (black powder), BK (boron/potassium nitrate), AL/KP (aluminum/potassium perchlorate), or MTV (magnesium/Teflon (registered trademark)/Viton (registered trademark)). General ignition powder can be used.Also, it may contain metal particles, non-ferrous metal particles, conductive oxide particles, etc.As the metal particles and non-ferrous metal particles, for example, aluminum , magnesium, zirconium, boron, etc. As the conductive oxide particles, oxides such as titanium oxide and manganese oxide are preferred.

The ignition powder 26 may be in the form of powder, granules, or pellets. From the viewpoint of ease of ignition from the initiator 28 and ease of ignition from the ignition powder 26 to the explosive container 22, it is preferable that the powder be in the form of a fluid powder or granules. Since the ignition charge 26 can be arranged according to the shape of the combustible film 24, which will be described later, desired ignition performance can be achieved. Furthermore, since the ignited flame propagates evenly, the explosive container 22 can be ignited without difficulty. Further, it is preferable that the particle size of the granules is large and the porosity is high because the propagation speed of the applied combustion flame becomes large.
Furthermore, by loading the ignition powder 26 into the explosive container 22 that has burnout properties, even when using fluid ignition powder 26 that has relatively high ignition performance, the ignition powder 26 can be ignited by the explosive container 22. The gunpowder 26 can be gripped, and the effect of the present invention that the ignition powder 26 and the gunpowder container 22 together exhibit reliable ignition performance can be further exhibited.

The combustible film 24 is a member for storing the ignition powder 26 and loading it into the explosive container 22. The combustible film 24 is made of an combustible material, such as a non-heat resistant resin, cloth, paper, or an easily combustible metal such as aluminum or magnesium. Here, "having burnout property" means that the solid propellant 18 is burnt out by being exposed to the combustion flame generated by combustion, and no burnout residue is produced. Even if burnout residue is generated, it is sufficient that the burnout residue is so fine that it does not clog or damage the nozzle and does not affect the combustion of the solid propellant 18. Note that if the igniter 26 is in a molded shape such as a pellet, the combustible film 24 is not essential.

There are no particular limitations on the method of fixing the combustible film 24. It may be adhered to the initiator 28 with an adhesive, or it may be gripped inside the explosive container 22 by providing an extinguishable lid 23, which will be described later.

The shape of the combustible film 24 is not particularly limited as long as the ignition power generated from the ignition powder 26 is evenly transmitted to the explosive container 22. It may be rectangular parallelepiped, cylindrical, or spherical.

The thickness of the combustible film 24 is not particularly limited. Although it depends on the material used, it is preferably 10 μm to 300 μm. If it is 10 μm or more, it is possible to increase the pressure when the combustion gas is crushed and spouted due to the increase in the pressure of the combustion gas, and the combustion gas and combustion flame will be spouted out with strong force. On the other hand, if the thickness is 300 μm or less, the burnout property of the combustible film 24 can be easily ensured.

Further, it is preferable to provide a desired space between the combustible film 24 and the explosive container 22 by adjusting the shape and size of the combustible film 24. With this configuration, a passage is created for the combustion flame and combustion gas of the ignition powder 26 applied by the initiator 28, and the spread of the ignition powder 26 and the ignition of the explosive container 22 can be rapidly promoted. The width of the space can be changed depending on the size of the rocket motor 1 and the duration of propulsion, and is preferably 0.5 mm to 10 mm, although it is not particularly limited. By being 0.5 mm or more, combustion flame and combustion gas can easily move. Moreover, by being 10 mm or less, uniform and reliable ignition performance for the explosive container 22 can be ensured. Note that the width of the space can be calculated as the average value of the distance from an arbitrary position on the inner side surface of the explosive container 22 to the combustible film 24 in the normal direction.

An explosive container 22 (also referred to as ignition charge) is fixed on a mirror plate around the initiator 28 and the combustible film 24. This gunpowder container 22 is made of a gunpowder component, and has the function of generating high-temperature combustion gas during combustion to ignite the propellant. Furthermore, it is preferable to use an easily moldable explosive component as the container. As the explosive component, a composite propellant or a double base propellant can be used. As the composite propellant, for example, a general composite propellant composition containing ammonium perchlorate as an oxidizing agent, a synthetic rubber binder as a fuel and binder, and a small amount of aluminum powder as a metal fuel can be used. Alternatively, if it is desired to reduce smoke during combustion of the igniter, a common smokeless double base propellant containing nitrocellulose and nitroglycerin as main components may be used. Further, it is preferable to use a cut product in order to easily form the container. The shape of the explosive container 22 may be cylindrical, ring-shaped, spherical, or square, as appropriate, in order to load the combustible film 24 containing the initiator 28 and the igniter 26 therein.

Next, FIG. 3 is a schematic longitudinal sectional view showing an example of another embodiment of the ignition device 2 of the present invention. In FIG. 3, instead of storing the igniter 26 in the combustible film 24 as in the embodiment shown in FIG. A burnable lid 23 made of burnable material is adhered to the burnable material to seal it. As the material of the burnable lid 23, burnable materials such as resin film, thin plastic plate, paper, and metal foil can be used. In the structure of FIG. 3, the amount of ignition powder 26 can be increased compared to that in FIG. can be ignited more efficiently in a shorter time. In Fig. 3, a flat extinguishable lid 23 is attached on top of the explosive container 22, but if you want to further increase the amount of ignition powder, the extinguishable lid 23 can be made into a dome shape or a cylindrical cap shape. You can also.

The thickness of the burnable lid 23 is not limited as long as the effects of the present invention are achieved, but it is preferably 10 μm to 500 μm. If it is 10 μm or more, the pressure caused by the combustion flame and combustion gas generated from the explosive container 22 and the ignition powder 26 can be increased, and the ignition performance of the solid propellant 18 can be improved. If it is 500 μm or less, the burnability of the burnable lid 23 can be easily ensured.

The burnout lid 23 may have a thickness of a certain level or more (for example, 0.1 mm or more), and may have a through hole of a predetermined diameter as a flame ejection hole (not shown). The diameter of the flame outlet is not particularly limited, and is approximately 0.1 to 20 mm, preferably 0.5 to 10 mm, and more preferably 1 to 5 mm. It can be appropriately designed according to the distance to the solid propellant 18 in the rocket motor 1, the diameter of the end face of the solid propellant 18, etc. The flame ejection holes may be provided in a plurality of two or more, and may be provided perpendicularly to the end surface of the solid propellant 18 on the ignition device 2 side, or may be provided obliquely. As a result, the trajectories of the flames ejected from the respective flame ejection holes overlap, and the flames are ejected as a flame having a high heat flow rate. This makes it possible to uniformly spray a flame having a larger area than the flame ejection hole and having a high heat flow rate onto the end face of the solid propellant 18.

Next, FIG. 4 is a schematic vertical sectional view showing an example of another embodiment of the rocket motor 1 of the present invention. In FIG. 4, a plurality of nozzle bodies 3 are arranged not at the center of the end plate 16 but around the end plate 16. In such a rocket motor 1, the thrust is generated in the direction of the resultant force of the thrust vectors generated in each nozzle part 13, so that thrust can be generated in the forward direction of the machine axis even if the nozzle part 13 is not at the machine axis position. In this case, it is preferable that the ignition device 2 is located at a position that does not overlap the opening starting point of the nozzle body 3, and is installed on the mirror plate 16 between the body-side ends of the openings of the plurality of nozzle bodies 3. . With this configuration, the solid propellant 18 can be reliably and uniformly ignited by the combustion flame of the ignition powder 26 and the gunpowder container 22, and no igniter 2 remains after combustion, giving it burnout properties. be able to. In addition, when the arrangement|positioning of the several nozzle part 13 has symmetry, it is preferable that the ignition device 2 is arrange|positioned on the mirror plate 16 near this center.

In addition, the embodiment mentioned above shows an example of an ignition device and a rocket motor. The ignition device and rocket motor according to the present invention are not limited to the embodiments described above, and the ignition device and rocket motor according to the embodiments described above may be modified without changing the gist of the claims. good.

The ignition device of the present invention has a configuration in which the ignition powder in contact with the initiator is loaded into an ignition powder container made of gunpowder components, and by imparting burnout property to the entire ignition device, the ignition device container required during propellant combustion is provided. There is no need to provide heat-resistant strength to the material. As a result, the ignition device does not require any insulation material, making it lighter and lower in cost, so it can be used not only for rocket motors but also for gas generators, defense equipment, etc. .

DESCRIPTION OF SYMBOLS 1... Rocket motor, 12... Motor case, 13... Nozzle part, 14... Main body part, 16... End plate, 18... Solid propellant, 2... Ignition device, 22 ... Gunpowder container, 23 ... Burnable lid, 24 ... Flammable film, 26 ... Ignition powder, 28 ... Initiator, 3 ... Nozzle body, 32 ... Spout nozzle

Claims (4)

An initiator fixed to a mirror plate on the side opposite to the propulsion direction, a gunpowder container made of a gunpowder component fixed to a mirror plate surrounding the initiator, and an ignition powder loaded in the gunpowder container, An ignition device for an end-burning rocket motor , characterized in that the explosive container has burnout properties, and the explosive component is a composite propellant or a double base propellant . 2. The ignition device for an edge-burning rocket motor according to claim 1, wherein the ignition powder is housed in a flammable film, and the ignition powder housed in the flammable film is loaded into a gunpowder container. 3. The ignition device for an edge-burning rocket motor according to claim 1, wherein the ignition device is fixed on an end plate between the end of the nozzle opening on the main body side of the rocket motor and the outer peripheral wall surface. In a rocket motor having a plurality of nozzles, the end face according to claim 1 or 2, wherein the end face is fixed on a mirror plate between ends on the main body side of the openings of the plurality of nozzles. Ignition system for combustion type rocket motors.