Solid rocket engine ignition device and solid rocket engine

Abstract

The invention provides a solid rocket engine ignition device and a solid rocket engine. The solid rocket engine ignition device comprises a shell, an end combustion propellant and an ignition powder box, an inner cavity of the shell is divided into a combustion chamber and a spray pipe cavity, the end combustion propellant and the ignition powder box are installed in the combustion chamber, and a boss is arranged at the end, facing the spray pipe cavity, of the end combustion propellant; the ignition powder box is arranged at the end, close to the spray pipe cavity, of the combustion chamber, a communicating hole is formed in the middle of the ignition powder box, the boss partially enters the communicating hole, the space, not filled with the end combustion propellant, in the combustion chamber forms a heat exchange cavity, the space, not filled with the end combustion propellant, between the end face of the boss and the spray pipe cavity forms a heat exchange slit, and the heat exchange cavity, the heat exchange slit and the spray pipe cavity are communicated. Through the design of the heat exchange cavity and the heat exchange slits, the heat transfer direction of high-temperature fuel gas can be determined, it is ensured that the end face of the end combustion propellant can be successfully ignited, and the advantages of being easy to operate, safe, efficient, high in ignition success rate and the like are achieved.

Description

Technical Field

[0001] The invention relates to the field of solid rocket engines, and in particular to a solid rocket engine ignition device and a solid rocket engine. Background Art

[0002] For small-diameter solid rocket engines that work for a long time, their caliber is small and the space for charging is very limited. On the premise of meeting technical indicators such as thrust, total impulse and working time, the end-burning charging method has the advantages of maximum loading density (full filling), simple structure, and stable thrust in the balance section. With the substantial improvement of the propellant technology level, the end-burning charging method is increasingly favored by designers.

[0003] However, the ignition of low burning rate propellant in solid rocket engines using end-face combustion has the following problems: end-face combustion propellant is generally ignited at the rear, and the gas in the ignition cartridge may spray onto the solid propellant burning surface or toward the nozzle. The flow and heat transfer of the ignition gas is random, which may cause the engine ignition failure. Even if the ignition gas is sprayed onto the burning surface, the ignition delay may occur due to the large randomness of the heat transfer flow. The use of end-face combustion surface grooves improves the ignition success rate to a certain extent, but there is still a possibility of ignition failure when reducing the amount of propellant, and the possibility of failure is greater for low burning rate end-face propellant. In order to ensure the stable ignition of low burning rate end-face combustion propellant charges, a new ignition method must be developed.

[0004] Prior art CN115142985A discloses a solid rocket engine ignition device, including a cartridge shell, pyrotechnics, a plugging piece, a double-base propellant, an electric ignition head, a cartridge cover and a connector. The pyrotechnics is ignited by the electric ignition head, and then the double-base propellant is ignited by the pyrotechnics. However, the pyrotechnics and the double-base propellant have only one contact surface. When the pyrotechnics is ignited, the spraying direction of the combustion gas may be the top of the cartridge shell, the plugging piece or the electric ignition head, and does not necessarily flow to the double-base propellant. Only when the connection between the pyrotechnics and the double-base propellant is ignited can it be determined that the double-base propellant is ignited. In addition, the combustion gas airflow in the device first rushes to the top of the cartridge shell, and then diverts to the plugging piece to open the plugging piece. Due to the loss of a certain pressure when the airflow is diverted, the end face ignition of the double-base propellant produces a certain ignition delay, which may lead to ignition failure. Summary of the invention

[0005] The purpose of the present invention is to provide a solid rocket engine ignition device and a solid rocket engine, so as to improve the problems of uncertain spraying direction of high-temperature fuel gas of the ignition box of the traditional ignition device, uncontrollable flow and heat transfer of fuel gas of the ignition box, and low ignition success rate.

[0006] The present invention provides a solid rocket engine ignition device, which includes a housing, end-burning propellant, and an ignition cartridge. The inner cavity of the housing is divided into a combustion chamber and a nozzle cavity. The end-burning propellant and the ignition cartridge are installed in the combustion chamber. A boss is provided at one end of the end-burning propellant facing the nozzle cavity. The ignition cartridge is arranged at one end of the combustion chamber close to the nozzle cavity. A communication hole is provided in the middle of the ignition cartridge. Part of the boss enters the communication hole. The space in the combustion chamber not filled with the end-burning propellant forms a heat exchange cavity. The space not filled between the end face of the boss and the nozzle cavity forms a heat exchange slit. The heat exchange cavity, the heat exchange slit, and the nozzle cavity are connected.

[0007] Compared with the prior art, when the solid rocket engine ignition device provided by the present invention starts ignition, high-temperature gas forms a local high-pressure airflow in the heat exchange cavity of the combustion chamber. And the boss part of the end-burning propellant is arranged at one end of the combustion chamber close to the nozzle cavity. After the ignition cartridge works, the ignition gas must flow through the heat exchange slit, which improves the contact between the ignition gas and the surface of the end-burning propellant from the traditional random low-intensity contact to deterministic high-intensity contact. The housing can also prevent heat energy loss and control the high-pressure high-temperature gas from transferring heat to the boss of the end-burning propellant. Moreover, the heat exchange slit reduces the flow cross-sectional area of the ignition gas, increases the density of the ignition gas, and speeds up the flow velocity. The high-pressure high-temperature gas completes deterministic strong convective heat transfer with the boss in the heat exchange slit, ensuring efficient heat transfer to the end-burning propellant, enabling the end face of the end-burning propellant to be successfully and quickly ignited, and avoiding the ignition delay phenomenon caused by the slow heating of the propellant surface. The present invention improves the determinacy of the heat transfer direction of the high-temperature gas and further improves the ignition success rate of the ignition device and the reliability of the solid rocket.

[0008] Preferably, the volume ratio of the heat exchange cavity to the combustion chamber is 1:(15 - 70). Controlling the volume ratio of the heat exchange cavity to the combustion chamber within a reasonable range enables the heat exchange cavity to be sufficient to accommodate the high-temperature gas generated by the ignition cartridge and form high-pressure gas. If the volume of the heat exchange cavity is too large, high-pressure high-temperature gas cannot be formed. If the volume is too small, local strong high pressure may be formed, which may cause an explosion.

[0009] Preferably, the distance between the inner wall of the ignition cartridge and the outer wall of the boss is 0.5 - 10 cm, and the distance between the end face of the boss and the nozzle cavity is 3 - 8 cm. A suitable distance gap is left between the inner wall of the ignition cartridge and the outer wall of the boss for connecting the heat exchange cavity and the heat exchange slit, and it is also convenient for the high-temperature gas after the ignition cartridge is ignited to fully expand the flow, expand the diffusion area of the high-temperature gas, and form high-pressure high-temperature gas faster. By controlling the distance between the end face of the boss and the nozzle cavity to set the appropriate width of the heat exchange slit, it can ensure that the high-temperature gas can maintain a high speed of sweeping the boss, form forced convection, and ensure successful ignition.

[0010] Preferably, it is characterized in that the thickness between the inner wall and the outer wall of the ignition cartridge is 0.8 - 1.5 cm, and the length of the boss entering the communication hole is 0.1 - 1.3 cm. Controlling the thickness of the ignition cartridge within a reasonable range can leave a suitable volume for the heat exchange chamber, provide sufficient initial high-temperature gas for ignition while enhancing the ignition effect. Setting the length of the boss entering the communication hole can ensure the spatial size of the heat exchange slit, so as to control the high-temperature and high-pressure gas flowing out from the heat exchange slit to forcibly contact the boss and ignite the boss, improving the ignition success rate.

[0011] Preferably, the end-burning propellant is one or more of hydroxyl-terminated polybutadiene, carboxyl-terminated polybutadiene, double-base propellant, polyvinyl chloride, ammonium nitrate, polyurethane, acrylonitrile-butadiene copolymer, and butadiene-acrylic acid copolymer.

[0012] Preferably, the nozzle cavity includes a convergent section, a throat section, and a divergent section connected in sequence. The convergent section is connected to the combustion chamber. Along the direction away from the combustion chamber, the opening of the convergent section gradually shrinks, the opening size of the throat section remains unchanged, and the opening of the divergent section gradually increases. The gradually decreasing inner diameter of the convergent section and the small inner diameter of the throat section can increase the airflow velocity, and the gradually increasing inner diameter of the divergent section facilitates the ejection of high-speed airflow, generating a strong thrust and enhancing the propulsion effect of the ignition device.

[0013] Preferably, a plug is provided in the divergent section. The plug makes a closed space formed between the nozzle cavity and the combustion chamber, which is beneficial to the formation of high-temperature and high-pressure gas by high-temperature airflow in this closed space. When the gas in the nozzle cavity reaches a certain pressure, the plug is forced out of the nozzle cavity, and the high-pressure jet also sprays out accordingly.

[0014] Preferably, the housing includes an outer housing and a housing insulation layer, and the housing insulation layer is laid on the inner wall of the outer housing.

[0015] Preferably, a barrel-shaped flame retardant layer is further provided in the combustion chamber, with its opening facing the nozzle cavity, and the flame retardant layer is laid on the inner wall of the housing insulation layer.

[0016] Setting the housing insulation layer and the flame retardant layer can effectively prevent the heat energy loss in the combustion chamber and the nozzle cavity, ensure that the internal temperature of the ignition device remains above the ignition temperature of the end-burning propellant, guarantee the ignition success rate, and the flame retardant layer can make the end-burning propellant maintain end-face combustion, preventing the outer wall and the end face of the end-burning propellant from burning simultaneously, which may lead to the disorder of the heat transfer direction and affect the ignition success rate.

[0017] The present invention also provides a solid rocket engine equipped with the above-mentioned solid rocket engine ignition device. The ignition success rate of this solid rocket engine reaches more than 99.9%.

[0018] The beneficial effects of the present invention are as follows: First, the end-burning propellant designed in the present invention has a boss structure, and the ignition cartridge is located upstream of the boss structure. The ignition gas can only flow out to the nozzle cavity through the heat exchange slit, making the gas necessarily flow and sweep the surface of the propellant, increasing the certainty of the flow direction. Second, the heat exchange slit reduces the flow cross-sectional area of the ignition gas, increases the pressure of the ignition gas, and speeds up the flow velocity. Furthermore, it improves the forced heat transfer effect on the surface of the end-burning propellant and increases the heating intensity of the ignition gas on the propellant. The present invention ensures that the end face of the end-burning propellant can be successfully ignited by determining the heat transfer direction of the high-temperature gas, and the ignition device can successfully ignite, further improving the ignition success rate and safety performance of the solid rocket engine, and having broad application prospects. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 It is a sectional view of the ignition device of the solid rocket engine used in Embodiment 1 of the specific embodiment of the present invention;

[0020] Figure 2 It is a sectional view of the end-burning propellant used in Embodiment 1 of the specific embodiment of the present invention.

[0021] Description of the reference numerals:

[0022] 1 - housing; 2 - end-burning propellant; 3 - flame retardant layer; 4 - combustion chamber; 5 - nozzle cavity; 6 - heat exchange cavity; 7 - ignition cartridge; 8 - heat exchange slit; 9 - throat section; 10 - plug; 11 - outer housing; 12 - housing insulation layer; 21 - boss; 22 - propellant body. SPECIFIC EMBODIMENTS

[0023] In order to make the above objects, features, and advantages of the present invention more obvious and understandable, the following will describe the specific embodiments of the present invention in detail with reference to the accompanying drawings.

[0024] In order to make the objects, technical solutions, and advantages of the embodiments of the present invention clearer, the following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are some, but not all, of the embodiments of the present invention. Usually, the components of the embodiments of the present invention described and shown in the accompanying drawings here can be arranged and designed in various different configurations.

[0025] It should be noted that: Similar reference numerals and letters denote similar items in the following drawings. Therefore, once an item is defined in one drawing, it does not need to be further defined and explained in subsequent drawings.

[0026] In the description of the present invention, it should be noted that the orientation or positional relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings. It is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, it should not be construed as a limitation to the present invention.

[0027] Embodiment 1

[0028] Combined with Figure 1 、 Figure 2 As shown, a solid rocket engine ignition device is provided in a specific embodiment of the present invention, including: a housing 1, an ignition cartridge 7, and a end-burning propellant 2;

[0029] The housing 1, the inner cavity of the housing 1 is divided into a combustion chamber 4 and a nozzle cavity 5; the housing 1 includes an outer housing 11 and a housing insulation layer 12, and the housing insulation layer 12 is laid on the inner wall of the outer housing 11. The combustion chamber 4 and the nozzle cavity 5 are both formed within the housing insulation layer 12; the volume of the combustion chamber 4 is 15L, which can fully accommodate a large dose of the end-burning propellant 2; the nozzle cavity 5 includes a convergent section, a throat section 9, and a divergent section connected in sequence. The convergent section is connected to the combustion chamber 4. Along the direction away from the combustion chamber 4, the inner diameter of the convergent section gradually decreases, the inner diameter of the throat section 9 remains unchanged, and the inner diameter of the divergent section gradually increases. The convergent section can converge the ejected high-temperature gas, and the gradually decreasing inner diameter can increase the flow rate of the high-temperature gas in the convergent section. The gradually increasing inner diameter of the divergent section can allow the high-speed and high-temperature gas to be ejected quickly, thereby improving the ignition effect of the ignition device and generating a huge thrust; the convergent section, the throat section 9, and the divergent section of the nozzle cavity 5 are all formed by the housing insulation layer 12, and the housing insulation layer 12 can effectively reduce the heat energy loss of the ignition device, keep the temperature inside the device up to the ignition point of the propellant, and improve the ignition success rate.

[0030] Combined with Figure 2As shown, the end-burning propellant 2 includes a boss 21 and a propellant body 22. First, the end-burning propellant 2 is poured into a mold for shaping, and after curing and cooling, an integrally formed end-burning propellant 2 with a boss 21 is obtained; the material of the end-burning propellant 2 is selected from one or more of hydroxyl-terminated polybutadiene, carboxyl-terminated polybutadiene, double-base propellant, polyvinyl chloride, ammonium nitrate, polyurethane, polybutadiene acrylonitrile, and butadiene acrylate copolymer; the end-burning propellant 2 is fixedly arranged in the combustion chamber 4 by bonding. The boss 21 of the end-burning propellant 2 is close to the nozzle cavity 5. The space in the combustion chamber 4 not filled by the boss 21 forms a heat exchange cavity 6. The volume of the heat exchange cavity 6 is 300 mL, and the volume ratio of the heat exchange cavity 6 to the combustion chamber 4 is 1:50. The high-temperature gas expands and boosts pressure in the heat exchange cavity 6, contacts the end-burning propellant 2 for heat transfer, and then ignites the end-burning propellant 2. A barrel-shaped flame retardant layer 3 is provided in the combustion chamber 4, which is laid on the inner wall of the shell insulation layer 12, and the opening of the flame retardant layer 3 faces the nozzle cavity 5. This can further prevent the heat loss of the end-burning propellant 2, reduce the internal temperature of the cavity, and prevent the outer wall of the propellant body 22 and the end face of the end-burning propellant 2 from burning simultaneously, resulting in heat transfer disorder and affecting the ignition effect.

[0031] The ignition cartridge 7 is bonded to one end of the combustion chamber 4 close to the nozzle cavity 5. A communication hole is provided in the center of the ignition cartridge 7, and the boss 21 of the end-burning propellant 2 enters this communication hole to Figure 1 The length direction of the boss 21 entering the communication hole is the left-right direction. The length of the boss 21 entering the communication hole is 0.5 cm. The thickness of the ignition cartridge 7 is 1.5 cm. The distance between the inner wall of the ignition cartridge 7 and the outer wall of the boss 21 is 0.5 cm. The unfilled space between the end face of the boss 21 and the nozzle cavity 5 forms a heat exchange slit 8. The gap formed by the distance between the outer wall of the boss 21 and the inner wall of the ignition cartridge 7 connects the heat exchange cavity 6 with the heat exchange slit 8. The heat exchange slit 8 communicates with the nozzle cavity 5. Therefore, the heat exchange cavity 6, the heat exchange slit 8, and the nozzle cavity 5 are connected. This facilitates the high-temperature gas generated after the ignition cartridge 7 is ignited to form high-pressure and high-temperature gas in the heat exchange cavity 6, contact the end-burning propellant 2 to ignite it, and then flow out of the nozzle cavity 5 at high speed from the heat exchange slit 8. And in the heat exchange slit 8, the high-pressure and high-temperature gas forms forced convection contact with the boss 21, further igniting the boss 21 of the end-burning propellant 2 to achieve successful ignition.

[0032] A plug 10 is also provided in the enlarged section of the nozzle cavity 5. The plug 10 is bonded to the shell insulation layer 12 of the enlarged section. The high-temperature and high-pressure gas flow generated by the ignition of the end-burning propellant 2 enters the nozzle cavity 5. Due to the blocking effect of the plug 10, the pressure in the ignition device rises. The converging section and the throat section 9 further increase the air flow pressure. Finally, after reaching a certain high pressure, the air flow breaks through the plug 10 in the enlarged section and sprays out of the nozzle cavity 5, and the ignition device successfully ignites and generates a huge driving force.

[0033] Example 2

[0034] In this embodiment, a solid rocket engine equipped with the solid rocket engine ignition device provided in Embodiment 1 above is used for further ignition experiments.

[0035] Using the solid rocket engine ignition device of Embodiment 1, first, the hydroxyl-terminated polybutadiene propellant is loaded into a mold with a boss 21 structure. The boss 21 is cylindrical, with a height of 30 mm and a diameter of 70 mm. Then, the ignition cartridge 7 is made into an annular shape, with an inner diameter of 75 mm, an outer diameter of 95 mm, and a cartridge thickness of 20 mm. 7.5 g of potassium borate nitrate powder is used to fill the ignition cartridge 7, and the excess space in the ignition cartridge 7 is filled with flammable materials such as cotton. The end-burning propellant 2 with the boss 21 structure is loaded into the ignition device, and the boss 21 of the end-burning propellant 2 faces the nozzle cavity 5 end. Prepare 10 solid rocket engines equipped with the above solid rocket engine ignition device for synchronous ignition, and the ignition success rate is 100%.

[0036] Embodiment 3

[0037] In this embodiment, a solid rocket engine equipped with the solid rocket engine ignition device provided in Embodiment 1 above is used for further ignition experiments.

[0038] Using the solid rocket engine ignition device of Embodiment 1, first, the carboxyl-terminated polybutadiene propellant is loaded into a mold with a boss 21 structure. The boss 21 is cylindrical, with a height of 30 mm and a diameter of 70 mm. Then, the ignition cartridge 7 is made into an annular shape, with an inner diameter of 75 mm, an outer diameter of 95 mm, and a cartridge thickness of 20 mm. 7.5 g of potassium borate nitrate powder is used to fill the ignition cartridge 7, and the excess space in the ignition cartridge 7 is filled with flammable materials such as cotton. The end-burning propellant 2 with the boss 21 structure is loaded into the ignition device, and the boss 21 of the end-burning propellant 2 faces the nozzle cavity 5 end. Prepare 10 solid rocket engine ignition devices under the above conditions for synchronous ignition, and the ignition success rate is 100%.

[0039] Comparative Example 1

[0040] First, the hydroxyl-terminated polybutadiene propellant is loaded into a mold without the boss 21 structure and otherwise the same as in Embodiment 1 for curing and shaping. Then, the ignition cartridge 7 is made into a cylindrical shape and placed at the end face of the end-burning propellant 2. The ignition cartridge 7 has a height of 10 mm and a diameter of 31 mm, and contains 7.5 g of potassium borate nitrate ignition powder. The excess space in the ignition cartridge 7 is filled with flammable materials such as cotton. After loading, the end face of the end-burning propellant 2 faces the nozzle cavity 5 end, and the ignition cartridge 7 is placed between the end face of the end-burning propellant 2 and the nozzle cavity 5. Otherwise, the conditions are the same as in Embodiment 2. Prepare 10 solid rocket engine ignition devices under the above conditions for synchronous ignition, and the ignition success rate is 70%.

[0041] Comparative Example 2

[0042] First, load the carboxyl-terminated polybutadiene propellant into a mold without a boss 21 structure and the rest is the same as that in Example 1, and cure and shape it. Then, make the ignition cartridge 7 into a cylindrical shape and place it at the end face of the end-burning propellant 2. The height of the ignition cartridge 7 is 10 mm, the diameter is 31 mm, and it contains 7.5 g of boron potassium nitrate ignition powder. Fill the extra space of the ignition cartridge 7 with flammable materials such as cotton. After filling, the end face of the end-burning propellant 2 faces the nozzle cavity 5 end, and place the ignition cartridge 7 between the end face of the end-burning propellant 2 and the nozzle cavity 5. The rest is the same as the conditions in Example 3. Prepare 10 solid rocket engine ignition devices under the above conditions and conduct synchronous ignition. The ignition success rate is 60%.

[0043] In summary, using the solid rocket engine of the solid rocket engine ignition device provided by the present invention Figure 1 as shown can completely determine the spraying direction of the high-temperature gas after the ignition cartridge 7 is ignited, ensure that the high-temperature gas is in high-speed convective contact with the end-burning propellant 2, greatly improve the possibility of ignition success, and the heat exchange slit 8 restricts the jet direction of the high-temperature and high-pressure gas to surely pass through the boss 21 of the end-burning propellant 2, so that the high-temperature and high-pressure gas can sweep the boss 21 at high speed, further ignite the boss 21, ensure the ignition success of the end-burning propellant 2, enhance the initial driving force of the engine ignition, and have an extremely high ignition success rate compared with the prior art, thereby improving the safety performance of the solid rocket engine device.

[0044] Although the present disclosure is disclosed as above, the protection scope of the present disclosure is not limited thereto. Those skilled in the art can make various changes and modifications without departing from the spirit and scope of the present disclosure, and these changes and modifications will all fall within the protection scope of the present invention.

Claims

1. A solid rocket engine ignition device, characterized in that, It includes a housing (1), end-burning propellant (2), and an ignition cartridge (7). The inner cavity of the housing (1) is divided into a combustion chamber (4) and a nozzle cavity (5). The end-burning propellant (2) and the ignition cartridge (7) are installed in the combustion chamber (4). A boss (21) is provided at one end of the end-burning propellant (2) facing the nozzle cavity (5). The ignition cartridge (7) is arranged at one end of the combustion chamber (4) close to the nozzle cavity (5). A communication hole is provided in the middle of the ignition cartridge (7), and part of the boss (21) enters the communication hole. The space in the combustion chamber (4) not filled with the end-burning propellant (2) forms a heat exchange chamber (6). The unfilled space between the end face of the boss (21) and the nozzle cavity (5) forms a heat exchange slit (8). The heat exchange chamber (6), the heat exchange slit (8), and the nozzle cavity (5) are in communication.

2. The ignition device for a solid rocket motor according to claim 1, characterized in that, The volume ratio of the heat exchange chamber (6) to the combustion chamber (4) is 1:(15 - 70).

3. The ignition device for a solid rocket motor according to claim 2, wherein The distance between the inner wall of the ignition cartridge (7) and the outer wall of the boss (21) is 0.5 - 10 cm, and the distance between the end face of the boss (21) and the nozzle cavity (5) is 3 - 8 cm.

4. The ignition device for a solid rocket motor according to claim 3, characterized in that, The thickness between the inner wall and the outer wall of the ignition cartridge (7) is 0.8 - 1.5 cm, and the length of the part of the boss (21) entering the communication hole is 0.1 - 1.3 cm.

5. The ignition device for a solid rocket motor according to claim 1, wherein, The material of the end-burning propellant (2) is selected from one or more of hydroxyl-terminated polybutadiene, carboxyl-terminated polybutadiene, double-base propellant, polyvinyl chloride, ammonium nitrate, polyurethane, polybutadiene acrylonitrile, and butadiene acrylate copolymer.

6. The ignition device for a solid rocket motor according to any one of claims 1-5, characterized in that The nozzle cavity (5) includes a convergent section, a throat section (9), and a divergent section connected in sequence. The convergent section is connected to the combustion chamber (4). Along the direction away from the combustion chamber (4), the opening of the convergent section gradually decreases. The opening size of the throat section (9) remains unchanged, and the opening of the divergent section gradually increases.

7. The ignition device for a solid rocket motor according to claim 6, characterized in that, A plug (10) is provided in the divergent section.

8. The ignition device for a solid rocket motor according to any one of claims 1-5, characterized in that, The housing (1) includes an outer housing (11) and a housing insulation layer (12). The housing insulation layer (12) is laid on the inner wall of the outer housing (11).

9. The ignition device for a solid rocket motor according to claim 8, wherein A barrel-shaped flame retardant layer (3) is further provided in the combustion chamber (4), with its opening facing the nozzle cavity (5). The flame retardant layer (3) is laid on the inner wall of the housing insulation layer (12).

10. A solid rocket motor, characterized in that, It includes the solid rocket engine ignition device according to any one of claims 1 - 9.

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