CN115263610A - Safety ignition device of solid rocket engine - Google Patents
Safety ignition device of solid rocket engine Download PDFInfo
- Publication number
- CN115263610A CN115263610A CN202210891840.6A CN202210891840A CN115263610A CN 115263610 A CN115263610 A CN 115263610A CN 202210891840 A CN202210891840 A CN 202210891840A CN 115263610 A CN115263610 A CN 115263610A
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- ignition
- piston
- ignition device
- gas channel
- rocket engine
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/95—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by starting or ignition means or arrangements
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Toys (AREA)
Abstract
The invention is suitable for the technical field of solid rocket engine ignition devices, and provides a safe ignition device of a solid rocket engine, which comprises: a housing; the ignition powder box is internally provided with ignition powder and is provided with a first gas channel communicated with the ignition powder; the electric ignition device is arranged on one side of the ignition medicine box and is provided with a second gas channel; and the piston assembly comprises a piston movably arranged in the shell and a driving mechanism connected with the piston, and the driving mechanism can drive the piston to move back and forth along the axis direction of the shell so as to enable the first fuel gas channel and the second fuel gas channel to be communicated or disconnected. The safety ignition device of the solid rocket engine provided by the invention has the advantages that the second gas channel of the electric ignition device is physically separated from the first gas channel of the ignition medicine box by using the piston when ignition is not needed, and ignition cannot be finished even if the electric ignition device is ignited by mistake, so that the ignition device is prevented from being ignited by mistake, and the safety performance is improved.
Description
Technical Field
The invention relates to the technical field of ignition devices of solid rocket engines, in particular to a safe ignition device of a solid rocket engine.
Background
With the use mode of the solid rocket engine becoming more and more complex, the requirements on the ignition time and the sequence accuracy of the solid rocket engine ignition device become higher and higher. In the working process of the engine, the flight path of the aircraft is out of control due to the mis-ignition of the ignition device, the aircraft can be disassembled seriously and even fall into a non-predetermined area, and the life and property of people are damaged; in the process of storing and transporting the engine, the storage warehouse can explode due to the mistaken ignition of the ignition device, and the consequence is serious. Therefore, the solid rocket engine ignition device needs to have the characteristics of reliable ignition and no accidental ignition, and meets the safety requirements of the solid rocket engine in the processes of use, storage, transportation and the like.
In the prior art, a mechanism special for preventing the ignition device of the solid rocket engine from being ignited by mistake is not usually arranged on the ignition device of the solid rocket engine, and the ignition device of the solid rocket engine is very easy to ignite by mistake due to the misfiring in the using, storing, transporting and other processes of the solid rocket engine, so that the safety performance is poor.
Disclosure of Invention
The invention provides a safe ignition device of a solid rocket engine, and aims to solve the problems that the ignition device of the solid rocket engine in the prior art is easy to ignite by mistake and has poor safety performance.
The present invention is achieved in this way, and provides a safety ignition device for a solid rocket engine, comprising:
a housing;
the ignition medicine box is arranged in the shell, ignition powder is arranged in the ignition medicine box, and the ignition medicine box is provided with a first gas channel communicated with the ignition powder;
the electric ignition device is arranged on one side of the ignition medicine box and is provided with a second gas channel communicated with the first gas channel of the ignition medicine box; and
the piston assembly comprises a piston movably arranged in the shell and a driving mechanism connected with the piston, and the driving mechanism can drive the piston to move back and forth along the axis direction of the shell so as to enable the first fuel gas channel to be communicated or disconnected with the second fuel gas channel.
Preferably, the first gas channel and the shell are arranged coaxially, the piston is arranged on one side of the ignition medicine box close to the electric ignition device, and the piston can move back and forth along the axial direction of the shell to open or close the first gas channel.
Preferably, the method further comprises the following steps:
the main ignition powder is arranged in the shell and is positioned on one side of the ignition medicine box, which is far away from the electric ignition device.
Preferably, the drive mechanism includes:
a motor;
the worm gear is in transmission connection with the motor; and
and the worm is in meshing transmission with the worm wheel and is connected with the piston, and the worm can drive the piston to move along the axis direction of the shell.
Preferably, the driving mechanism comprises an electromagnet, the piston is connected with a movable iron core of the electromagnet, and the movable iron core can drive the piston to move along the axis direction of the shell.
Preferably, the method further comprises the following steps:
the piston is fixed on the connecting rod, and the driving mechanism drives the piston to move along the axis direction of the shell through the connecting rod.
Preferably, the number of the electric ignition devices is two, the second fuel gas channels of the two electric ignition devices form an included angle with each other, the second fuel gas channels of the two electric ignition devices extend to the first fuel gas channel respectively, and the piston can move between the two second fuel gas channels.
Preferably, the piston is movable along an inner wall surface of the first gas passage into the first gas passage to close the first gas passage, and the piston is movable out of the first gas passage along the inner wall surface of the first gas passage to open the first gas passage.
Preferably, the surface of the piston, which is matched with the inner wall surface of the first gas channel, is provided with a first sealing element for sealing a gap between the inner wall surface of the first gas channel and the piston.
Preferably, an opening is formed in one end of the shell, the end, provided with the opening, of the shell is connected with a top cover, the electric ignition device is installed on the top cover, the ignition medicine box is installed inside the top cover, and a second sealing element is arranged on a matching surface between the ignition medicine box and the top cover.
The invention provides a safety ignition device of a solid rocket engine, which is characterized in that a piston assembly is arranged, the piston assembly comprises a piston movably arranged in a shell and a driving mechanism connected with the piston, the driving mechanism can drive the piston to move along the axial direction of the shell so as to connect or disconnect a first gas channel and a second gas channel, when the safety ignition device of the solid rocket engine does not need ignition, the second gas channel of an electric ignition device and the first gas channel of an ignition medicine box are physically separated by the piston, so that the first gas channel is disconnected with the second gas channel, even if the electric ignition device is subjected to accidental ignition, the gas of the electric ignition device cannot be contacted with ignition medicine of the ignition medicine box, the purpose that the ignition device cannot ignite is achieved, the solid rocket engine is prevented from being ignited by mistake, a safety function is achieved, the safety performance of the ignition device is improved, and the ignition device is safe and reliable; furthermore, the flow area of the gas can be controlled by the piston movement, thereby controlling the accurate ignition time and ignition timing of the ignition device.
Drawings
FIG. 1 is a schematic sectional view of a safety ignition device of a solid rocket engine according to an embodiment of the present invention, wherein a first gas passage is disconnected from a second gas passage;
FIG. 2 is an enlarged view of portion A of FIG. 1;
FIG. 3 is a schematic sectional view of a safety ignition device of a solid rocket engine according to an embodiment of the present invention, wherein a first fuel gas passage is communicated with a second fuel gas passage;
fig. 4 is an enlarged view of a portion B in fig. 3.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and do not limit the invention.
According to the safe ignition device of the solid rocket engine, the piston assembly is arranged, the piston assembly comprises the piston movably arranged in the shell and the driving mechanism connected with the piston, the driving mechanism can drive the piston to move along the axial direction of the shell so as to enable the first gas channel and the second gas channel to be communicated or disconnected, when the safe ignition device of the solid rocket engine does not need to ignite, the piston is used for physically isolating the second gas channel of the electric ignition device from the first gas channel of the ignition medicine box, even if the electric ignition device ignites by mistake, the gas of the electric ignition device cannot be contacted with the ignition medicine of the ignition medicine box, the purpose that the ignition device cannot ignite is achieved, the solid rocket engine is prevented from being ignited by mistake, a safety function is achieved, and the safety performance of the ignition device is improved; furthermore, the flow area of the gas can be controlled by the piston movement, thereby controlling the accurate ignition time and ignition timing of the ignition device.
Referring to fig. 1 to 4, an embodiment of the present invention provides a safety ignition device for a solid rocket engine, including:
a housing 1;
the ignition medicine box 2 is arranged in the shell 1, ignition medicine 20 is arranged in the ignition medicine box 2, and the ignition medicine box 2 is provided with a first gas channel 21 communicated with the ignition medicine 20;
the electric ignition device 3 is arranged on one side of the ignition medicine box 2, and the electric ignition device 3 is provided with a second gas channel 31 which is used for being communicated with the first gas channel 21 of the ignition medicine box 2; and
the piston assembly comprises a piston 41 movably arranged in the shell 1 and a driving mechanism 42 connected with the piston 41, and the driving mechanism 42 can drive the piston 41 to move back and forth along the axial direction of the shell 1 so as to enable the first gas channel 21 to be communicated with or disconnected from the second gas channel 31.
In the embodiment of the invention, the electric ignition device 3 is an electric squib, an electric ignition tube or an electric ignition head, and can be arranged according to actual requirements.
As an embodiment of the present invention, the first gas passage 21 is disposed coaxially with the housing 1, the piston 41 is disposed on a side of the ignition medicine box 2 close to the electric ignition device 3, and the piston 41 can move back and forth along the axial direction of the housing 1 to open or close the first gas passage 21. Specifically, the axis is a central axis of the housing 1, the first gas channel 21 is the same as the central axis of the housing 1, and the driving mechanism 42 drives the piston 41 to move back and forth along the central axis of the housing 1 to open or close the first gas channel 21.
In the embodiment, the driving mechanism 42 drives the piston 41 to move back and forth along the axial direction of the housing 1 to open or close the first gas channel 21, so that the first gas channel 21 is communicated with or disconnected from the second gas channel 31, the implementation structure is simple, the piston 41 moves along the axial direction of the housing 1, the installation space is small, and the environmental adaptability is strong; when the electric ignition device is ignited by mistake to generate gas, the piston 41 is under the action force of the electric ignition device 3 to generate gas, the end face of the piston 41 can be uniformly applied with rightward action force to press and close the piston 41 to the first gas channel 21, so that the piston 41 can more reliably separate the first gas channel 21 from the second gas channel 31, and the mistaken ignition of the ignition device is blocked. In addition, in other embodiments, the driving mechanism 42 may also drive the piston 41 to open or close the second gas passage 31, and when ignition is not needed, the second gas passage 31 is closed by the piston 41, so as to prevent the solid rocket engine from misfiring.
In the embodiment of the invention, when the safety ignition device of the solid rocket engine does not need to ignite, the piston 41 physically isolates the first gas channel 21 of the ignition medicine box 2 from the second gas channel 31 of the electric ignition device 3 (as shown in fig. 1 and fig. 2), even if the electric ignition device 3 ignites by mistake, the gas generated by the electric ignition device 3 cannot contact with the ignition powder 20 of the ignition medicine box 2, so that the purpose that the solid rocket engine cannot ignite is achieved, the solid rocket engine is prevented from being ignited by mistake, a safety protection function is achieved, and the safety performance of the safety ignition device of the solid rocket engine is improved; when the safety ignition device of the solid rocket engine needs ignition, after an ignition instruction is sent, the driving mechanism 42 drives the piston 41 to move in the direction away from the second gas channel 31 along the axis of the housing 1, so as to open the second gas channel 31, and realize the communication between the first gas channel 21 and the second gas channel 31 (as shown in fig. 3 and fig. 4), at this time, the gas of the electric ignition device 3 enters the ignition cartridge 2 through the second gas channel 31 and the first gas channel 21, so that the ignition charge of the ignition cartridge 2 is ignited, and the successful ignition is realized.
In the embodiment of the invention, due to the arrangement of the piston assembly, the piston 41 can be driven by the driving mechanism 42 to move to control the flowing area of the fuel gas, the flow rate of the fuel gas of the electric ignition device 3 entering the ignition medicine box 2 can be controlled by the piston 41, and the accurate ignition time and the ignition time sequence of the ignition device are further controlled.
As an embodiment of the present invention, the method further includes:
the main ignition powder 7 is arranged in the shell 1, and the main ignition powder 7 is positioned on one side of the ignition medicine box 2 far away from the electric ignition device 3.
In this embodiment, when the safety ignition device of the solid rocket engine ignites, the gas generated by the electric ignition of the electric ignition device 3 enters the first gas channel 21 from the second gas channel 31, so as to ignite the ignition charge 20 in the ignition charge box 2, and the ignition charge 20 then ignites the main ignition charge 7, thereby realizing the successful ignition of the solid rocket engine; the ignition energy of the solid rocket engine is increased by using the main ignition powder 7, and the reliability of successful ignition of the solid rocket engine is greatly improved.
As an embodiment of the present invention, the drive mechanism 42 includes:
a motor (not shown);
a worm gear (not shown) in transmission connection with the motor; and
and a worm (not shown) in meshing transmission with the worm wheel, wherein the worm is connected with the piston 41, and the worm can drive the piston 41 to move along the axial direction of the shell 1.
In this embodiment, when the safety ignition device of the solid rocket engine does not need to ignite, the piston 41 blocks the communication between the first gas passage 21 and the second gas passage 31 on both sides thereof, even if the ignition device is fired by mistake, the gas of the electric ignition device 3 cannot ignite the ignition charge 20 of the ignition charge case 2, so that the ignition charge 20 of the ignition charge case 2 is not ignited in the case of the ignition by mistake of the electric ignition device 3, thereby preventing the mis-ignition.
When the safety ignition device of the solid rocket engine needs ignition, after an ignition instruction is sent, the motor works to drive the worm wheel to rotate, the worm wheel drives the worm to move towards the direction far away from the second gas channel 31, the worm drives the piston 41 to move towards the direction far away from the second gas channel 31 along the axis of the shell 1, so that the second gas channel 31 is opened, and the first gas channels 21 on the two sides of the piston 41 are communicated with the second gas channel 31, thereby ensuring the successful ignition. Moreover, the worm gear structure has a self-locking function, so that the piston 41 can be stably kept at a certain position. When ignition is needed, the self-locking of the worm and gear structure can ensure that the first fuel gas channel 21 and the second fuel gas channel 31 are communicated, and the successful ignition is ensured; when ignition is not needed, the self-locking of the worm and gear structure can ensure that the first gas channel 21 and the second gas channel 31 are kept disconnected, the piston 41 is prevented from shifting, the reliability of mis-ignition is ensured, a locking mechanism is not needed to be additionally arranged, and the gas-fuel injector is simple in structure and low in implementation cost.
The motor can be subjected to model selection based on the layout space according to voltage, current and power density of the motor.
As another embodiment of the present invention, the driving mechanism 42 includes an electromagnet (not shown), and the piston 41 is connected to a plunger (not shown) of the electromagnet, and the plunger can drive the piston 41 to move along the axial direction of the housing 1.
In this embodiment, when the safety ignition device of the solid rocket engine needs to ignite, the electromagnet is powered on, and the movable iron core of the electromagnet moves towards the direction away from the first gas channel 21, so that the piston 41 opens the first gas channel 21, and the first gas channels 21 on the two sides of the piston 41 are communicated with the second gas channel 31, thereby ensuring successful ignition; when the safety ignition device of the solid rocket engine does not need to ignite, the electromagnet is kept powered off, the movable iron core of the electromagnet is under the action of the spring of the electromagnet, and the spring drives the movable iron core to move towards the direction close to the first fuel gas channel 21, so that the piston 41 is driven to close the first fuel gas channel 21, the piston 41 is enabled to separate the first fuel gas channel 21 from the second fuel gas channel 31, and therefore the accidental ignition of the ignition device is prevented.
In other embodiments of the present invention, the driving mechanism 42 may also be a combination of a motor and a rack-and-pinion mechanism, the piston 41 is fixed on the rack, the motor drives the rack to rotate, the rack is driven by the gear to move, and the piston 41 can be driven to open or close the first gas channel 21.
As an embodiment of the present invention, the piston assembly further includes:
the piston 41 is fixed to a connecting rod 43 connected to the driving mechanism 42, and the driving mechanism 42 drives the piston 41 to move along the axial direction of the housing 1 through the connecting rod 43.
In this embodiment, the piston 41 and the connecting rod 43 may be connected by a screw thread, so that the piston 41 and the connecting rod 43 are locked and fixed more stably. In addition, the piston 41 and the connecting rod 43 may be fixedly connected in other manners. The piston 41 and the driving mechanism 42 are connected by the connecting rod 43, so that the piston 41 and the driving mechanism 42 are conveniently assembled and fixed.
When the driving mechanism 42 includes a motor, a worm wheel drivingly connected to the motor, and a worm meshing with the worm wheel, the worm may be directly connected to the piston 41, or may be connected to the piston 41 by a connecting rod 43. When the driving mechanism 42 includes an electromagnet, the movable core of the electromagnet may be directly connected to the piston 41, or the movable core of the electromagnet may be connected to the piston 41 by a connecting rod 43.
As an embodiment of the present invention, the number of the electric ignition devices 3 is two, the second gas passages 31 of the two electric ignition devices 3 are disposed at an angle to each other, the second gas passages 31 of the two electric ignition devices 3 extend toward the first gas passage 21, respectively, and the piston 41 is movable between the two second gas passages 31. The angle between the second gas channels 31 of the two electric ignition devices 3 can be set according to practical requirements.
In the embodiment, the two electric ignition devices 3 are arranged, and the ignition powder of the ignition powder box is ignited by the two electric ignition devices 3 at the same time, so that the ignition success reliability is greatly improved; moreover, the second gas passages 31 of the two electric ignition devices 3 are arranged at an included angle, and the second gas passages 31 of the two electric ignition devices 3 extend towards the first gas passage 21 respectively, so that the gas in the second gas passages 31 can fully enter the first gas passage 21, and the piston 41 and the two second gas passages 31 are arranged in a staggered manner, so that the piston 41 can smoothly enter and exit the first gas passage 21, and the interference of the second gas passages 31 on the movement of the piston 41 is avoided.
As an embodiment of the present invention, the piston 41 may be moved into the first gas passage 21 along the inner wall surface of the first gas passage 21 to close the first gas passage 21, and the piston 41 may be moved out of the first gas passage 21 along the inner wall surface of the first gas passage 21 to open the first gas passage 21.
In this embodiment, the outer diameter of the piston 41 is matched with the aperture of the first gas passage 21, when the piston 41 enters and exits the first gas passage 21, the inner wall surfaces of the piston 41 and the first gas passage 21 are in mutual matching contact, and the inner wall surface of the first gas passage 21 guides the movement of the piston 41, so that the piston 41 enters and exits the first gas passage 21 more stably.
As an embodiment of the present invention, a surface of the piston 41 that is fitted to the inner wall surface of the first gas passage 21 is provided with a first sealing member 9 for sealing a gap between the inner wall surface of the first gas passage 21 and the piston 41. Wherein, the first sealing element 9 may be a rubber sealing ring sleeved on the outer surface of the piston 41, and the specific number of the first sealing elements 9 is not limited.
In the embodiment, the first sealing element 9 is used for sealing the gap between the inner wall surface of the first gas channel 21 and the piston 41, so that the sealing performance of the first gas channel 21 when being closed by the piston 41 is enhanced, and the reliability of mis-ignition is further improved; moreover, the first sealing element 9 is in fit contact with the inner wall surface of the first gas channel 21, so that the movement of the piston 41 can be guided, and the piston 41 can smoothly enter and exit the first gas channel 21.
As an embodiment of the present invention, one end of the housing 1 is provided with an opening, the end of the housing 1 provided with the opening is connected with a top cover 5, the electric ignition device 3 is mounted on the top cover 5, the ignition medicine box 2 is mounted in the top cover 5, and the mating surface between the ignition medicine box 2 and the top cover 5 is provided with a second sealing element 10.
In this embodiment, the second sealing element 10 is used to prevent the gas from escaping from the mating surface between the ignition medicine box 2 and the top cover 5, so as to further improve the reliability of the mis-ignition. The second sealing element 10 may be a rubber sealing ring sleeved on the outer surface of the ignition medicine box 2, and the specific number of the second sealing elements 10 is not limited.
As an embodiment of the present invention, the method further includes:
the swivel nut 6, 6 spiro union of swivel nut one end and top cap 5, the other end is equipped with open-ended one end spiro union with casing 1, and ignition medicine box 2 is fixed between swivel nut 6 and top cap 5, the fixed equipment of the ignition medicine box 2 of being convenient for.
The present invention further comprises a heat insulating layer 8 disposed between the top cover 5 and the housing 1, wherein the heat insulating layer 8 is used for insulating and reducing heat transfer between the top cover 5 and the housing 1.
According to the safety ignition device of the solid rocket engine, when ignition is not needed, the second gas channel of the electric ignition device is physically separated from the first gas channel of the ignition medicine box by the piston, even if the electric ignition device is ignited by mistake, the gas of the electric ignition device cannot contact with the ignition medicine of the ignition medicine box, so that the purpose that the solid rocket engine cannot ignite is achieved, a safety insurance function is achieved, and the safety performance of the safety ignition device of the solid rocket engine is improved; furthermore, the flow area of the gas can be controlled by the piston movement, thereby controlling the accurate ignition time and ignition timing of the ignition device.
The present invention is not limited to the above preferred embodiments, and any modifications, equivalent substitutions and improvements made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. A safety ignition device for a solid rocket engine, comprising:
a housing;
the ignition medicine box is arranged in the shell, ignition powder is arranged in the ignition medicine box, and the ignition medicine box is provided with a first gas channel communicated with the ignition powder;
the electric ignition device is arranged on one side of the ignition medicine box and is provided with a second gas channel communicated with the first gas channel of the ignition medicine box; and
the piston assembly comprises a piston movably arranged in the shell and a driving mechanism connected with the piston, and the driving mechanism can drive the piston to move back and forth along the axis direction of the shell so as to enable the first fuel gas channel to be communicated or disconnected with the second fuel gas channel.
2. The safe ignition device for solid rocket engines according to claim 1, wherein said first gas channel is coaxially disposed with said housing, said piston is disposed on the side of said ignition cartridge near said electric igniter, said piston can move back and forth along the axial direction of said housing to open or close said first gas channel.
3. A safe ignition device for a solid-rocket engine according to claim 1, further comprising:
the main ignition powder is arranged in the shell and is positioned on one side of the ignition medicine box, which is far away from the electric ignition device.
4. A solid rocket engine safety ignition device as recited in claim 1, wherein said drive mechanism comprises:
a motor;
the worm gear is in transmission connection with the motor; and
and the worm is in meshing transmission with the worm wheel and is connected with the piston, and the worm can drive the piston to move along the axis direction of the shell.
5. A solid rocket engine safety ignition device as recited in claim 1, wherein said actuating mechanism comprises an electromagnet, said piston is connected to a plunger of said electromagnet, and said plunger is driven by said plunger in the axial direction of said housing.
6. A safe ignition device for a solid-rocket engine according to claim 1, further comprising:
the piston is fixed on the connecting rod, and the driving mechanism drives the piston to move along the axis direction of the shell through the connecting rod.
7. A solid rocket engine safety ignition device as defined in claim 1, wherein said number of said electric ignition devices is two, said second gas passages of two of said electric ignition devices are disposed at an angle to each other, said second gas passages of two of said electric ignition devices extend toward said first gas passage, respectively, and said piston is movable between said two second gas passages.
8. A solid rocket engine safety ignition device as defined in claim 1, wherein said piston is movable along an inner wall surface of said first gas passage into said first gas passage to close said first gas passage, and said piston is movable along an inner wall surface of said first gas passage out of said first gas passage to open said first gas passage.
9. A solid rocket engine safety ignition device as defined in claim 1, wherein the surface of said piston mating with the inner wall surface of said first gas passage is provided with a first sealing element for sealing the gap between the inner wall surface of said first gas passage and said piston.
10. A safety ignition device for a solid rocket engine as claimed in claim 1, wherein said housing is provided with an opening at one end thereof, said housing is connected to a top cover at the end thereof provided with said opening, said electric ignition device is mounted to said top cover, said ignition cartridge is mounted inside said top cover, and a second sealing member is provided at a mating surface between said ignition cartridge and said top cover.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210891840.6A CN115263610A (en) | 2022-07-27 | 2022-07-27 | Safety ignition device of solid rocket engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210891840.6A CN115263610A (en) | 2022-07-27 | 2022-07-27 | Safety ignition device of solid rocket engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115263610A true CN115263610A (en) | 2022-11-01 |
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ID=83771977
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210891840.6A Pending CN115263610A (en) | 2022-07-27 | 2022-07-27 | Safety ignition device of solid rocket engine |
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| CN (1) | CN115263610A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116044607A (en) * | 2022-12-29 | 2023-05-02 | 湖北三江航天红林探控有限公司 | Engine safety device |
| CN117552893A (en) * | 2023-04-03 | 2024-02-13 | 陕西普利美材料科技有限公司 | Composite winding shell ignition device |
-
2022
- 2022-07-27 CN CN202210891840.6A patent/CN115263610A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116044607A (en) * | 2022-12-29 | 2023-05-02 | 湖北三江航天红林探控有限公司 | Engine safety device |
| CN117552893A (en) * | 2023-04-03 | 2024-02-13 | 陕西普利美材料科技有限公司 | Composite winding shell ignition device |
| CN117552893B (en) * | 2023-04-03 | 2024-03-19 | 陕西普利美材料科技有限公司 | Composite winding shell ignition device |
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