CN115467763A - Simple and reliable solid rocket engine ignition device - Google Patents
Simple and reliable solid rocket engine ignition device Download PDFInfo
- Publication number
- CN115467763A CN115467763A CN202210896378.9A CN202210896378A CN115467763A CN 115467763 A CN115467763 A CN 115467763A CN 202210896378 A CN202210896378 A CN 202210896378A CN 115467763 A CN115467763 A CN 115467763A
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- ignition
- gas channel
- rocket engine
- solid rocket
- gas
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- 239000007787 solid Substances 0.000 title claims abstract description 46
- 239000000843 powder Substances 0.000 claims abstract description 58
- 239000000463 material Substances 0.000 claims abstract description 39
- 239000003380 propellant Substances 0.000 claims abstract description 28
- 238000002485 combustion reaction Methods 0.000 claims abstract description 23
- 230000002093 peripheral effect Effects 0.000 claims abstract description 19
- 238000004880 explosion Methods 0.000 claims abstract description 5
- 239000007789 gas Substances 0.000 claims description 94
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims description 10
- 229910000838 Al alloy Inorganic materials 0.000 claims description 5
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 5
- 239000004917 carbon fiber Substances 0.000 claims description 5
- 239000000835 fiber Substances 0.000 claims description 5
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 5
- 239000000377 silicon dioxide Substances 0.000 claims description 5
- 238000002844 melting Methods 0.000 claims description 4
- 230000008018 melting Effects 0.000 claims description 4
- 239000003292 glue Substances 0.000 claims description 3
- 239000000567 combustion gas Substances 0.000 claims description 2
- 239000011819 refractory material Substances 0.000 claims 1
- 239000003814 drug Substances 0.000 description 6
- 101100495256 Caenorhabditis elegans mat-3 gene Proteins 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 238000004804 winding Methods 0.000 description 4
- 238000002679 ablation Methods 0.000 description 3
- 230000000903 blocking effect Effects 0.000 description 2
- 230000007423 decrease Effects 0.000 description 2
- 238000009792 diffusion process Methods 0.000 description 2
- 239000006185 dispersion Substances 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 229910052751 metal Inorganic materials 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 238000007789 sealing Methods 0.000 description 2
- 239000007921 spray Substances 0.000 description 2
- 238000004026 adhesive bonding Methods 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 238000005336 cracking Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 239000006260 foam Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 229910052755 nonmetal Inorganic materials 0.000 description 1
- 238000004806 packaging method and process Methods 0.000 description 1
- 239000004449 solid propellant Substances 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
Images
Classifications
-
- 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)
- Air Bags (AREA)
Abstract
The invention is suitable for the technical field of solid rocket engine ignition devices, and provides a simple and reliable solid rocket engine ignition device, which comprises: the gas burner comprises a shell made of high-temperature-resistant materials, wherein a gas channel is arranged in the shell, and a plurality of gas holes are formed in the peripheral surface of the shell; ignition powder arranged in the gas channel; the electric explosion tube is arranged in the gas channel; the air guide sleeve is connected with one end of the gas channel and is provided with a plurality of air guide holes communicated with the gas channel. The simple and reliable solid rocket engine ignition device provided by the invention utilizes the shell made of high-temperature resistant materials to encapsulate the ignition powder, the ignition powder which is not ignited can be continuously ignited in the gas channel for full combustion, and the utilization rate of the energy of the ignition powder is improved; meanwhile, ignition gas is guided to the combustion surface of the propellant through the plurality of gas holes and the plurality of flow guide holes, so that the energy loss of the ignition gas is reduced, the ignition reliability of the solid rocket engine is improved, and the structure is simple and reliable.
Description
Technical Field
The invention relates to the technical field of solid rocket engine ignition devices, in particular to a simple and reliable solid rocket engine ignition device.
Background
The solid rocket engine is used as a power device of an aircraft, and thrust control must be carried out according to different requirements of the aircraft. The solid rocket engine uses solid propellant to burn in the combustion chamber after being ignited, and chemical energy is converted into heat energy to produce high-temperature and high-pressure combustion products. The combustion products flow through the nozzle where they expand and accelerate, and the thermal energy is converted to kinetic energy, which is expelled from the nozzle at high velocity to produce thrust. Wherein, the solid rocket engine can select low-burning-rate propellant and high-burning-rate propellant according to the use working condition.
In the prior art, when the solid rocket engine using the low-burning-rate propellant is ignited by using the traditional ignition device, because the ignition medicine box of the traditional simple and reliable solid rocket engine ignition device adopts the explosive-cracking material (such as plastic) to package the ignition medicine, at the moment of ignition work, the ignition medicine box can crack to cause the uncertainty of the movement direction of the ignition medicine filled in the ignition medicine box, the ignition energy is dispersed, the energy for igniting the propellant is reduced, the difficulty of successful ignition of the solid rocket engine using the low-burning-rate propellant is increased, and the ignition reliability of the solid rocket engine is poor.
Disclosure of Invention
The invention provides a simple and reliable solid rocket engine ignition device, and aims to solve the problems of high ignition difficulty and poor ignition reliability of the solid rocket engine in the prior art.
The invention is thus achieved, providing a simple and reliable solid rocket engine ignition device comprising:
the ignition device comprises a shell made of high-temperature-resistant materials, wherein a gas channel for placing ignition powder is arranged in the shell, a plurality of gas holes distributed in an array mode are formed in the peripheral surface of the shell, and the gas holes are respectively communicated with the gas channel;
ignition powder arranged in the gas channel;
the electric explosion tube is arranged in the gas channel; and
the air guide sleeve is connected with one end of the gas channel and is provided with a plurality of air guide holes communicated with the gas channel.
Preferably, the high-temperature resistant material is a carbon fiber winding material or a high silica fiber winding material.
Preferably, the air guide sleeve is made of aluminum alloy.
Preferably, the diameter of the diversion hole in the central area of the diversion cover is larger than that of the diversion hole in the peripheral area.
Preferably, the air guide sleeve is made of a functional gradient material, and the melting point of the material of the central area of the air guide sleeve is lower than that of the material of the peripheral area of the air guide sleeve.
Preferably, the central axis of each said deflector hole is arranged perpendicular to the combustion face of the propellant outside the housing.
Preferably, the ignition powder is ignition powder or ignition tablets, and the ignition powder or the ignition tablets are wrapped by a wrapping layer and placed in the gas channel.
Preferably, two ends in the gas channel are respectively and fixedly provided with two plugging blocks, and the ignition charge is fixedly arranged between the two plugging blocks in the gas channel.
Preferably, one end of the air guide sleeve extends into the gas channel, and one end of the air guide sleeve extending into the gas channel is in threaded connection with the shell or is bonded by high-temperature-resistant inorganic glue.
The simple and reliable solid rocket engine ignition device provided by the invention is characterized in that the shell made of high-temperature-resistant materials is arranged, the shell is internally provided with a gas channel and a flow guide cover connected with one end of the gas channel, the outer peripheral surface of the shell is provided with a plurality of gas holes which are communicated with the gas channel and distributed in an array manner, the flow guide cover is provided with a plurality of flow guide holes, and ignition powder is packaged in the gas channel. When the ignition powder is ignited by the electric detonator, because the shell made of the high-temperature resistant material cannot be burst, the ignition powder which is not ignited is wrapped in the gas channel, the ignition powder which is not ignited is prevented from randomly diffusing, so that the ignition powder which is not ignited has sufficient space and time to be ignited, the ignition powder part which is not ignited can be continuously ignited and fully combusted in the gas channel, and the utilization rate of the energy of the ignition powder is improved; meanwhile, ignition gas generated by ignition powder is guided to the combustion surface of the propellant through the plurality of gas holes in the outer peripheral surface of the shell and the plurality of guide holes in the guide cover, so that the energy loss of the ignition gas is reduced, the ignition reliability is improved, and the difficulty of successful ignition is greatly reduced. Moreover, the whole simple and reliable solid rocket engine ignition device is free of moving parts, simple and reliable in structure, low in implementation cost and high in reliability.
Drawings
Fig. 1 is a schematic diagram of a simple and reliable solid rocket engine ignition device provided by an embodiment of the invention.
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 are not intended to limit the invention.
The simple and reliable solid rocket engine ignition device provided by the embodiment of the invention is characterized in that the shell made of high-temperature-resistant materials is arranged, the shell is internally provided with a gas channel, the peripheral surface of the shell is provided with a plurality of gas holes which are communicated with the gas channel and are distributed in an array manner, and ignition powder is packaged in the gas channel; and the air guide cover is connected with the gas channel and is provided with a plurality of air guide holes. When ignition powder is ignited by the electric detonator, the ignition powder which is not ignited is wrapped in the gas channel, so that the ignition powder which is not ignited can be continuously ignited and fully combusted in the gas channel, the utilization rate of the energy of the ignition powder is improved, the ignition gas generated by the ignition powder simultaneously flows to the combustion surface of the propellant through a plurality of gas holes on the outer peripheral surface of the shell and a plurality of flow guide holes on the flow guide cover so as to ignite the propellant, the loss of the energy of the ignition gas is reduced, the ignition reliability of the solid rocket engine is further improved, the difficulty of successful ignition is greatly reduced, the ignition device of the rocket engine is simple and reliable in structure, the realization cost is low, the reliability is high
Referring to fig. 1, an embodiment of the present invention provides a simple and reliable solid rocket engine ignition device, including:
the ignition device comprises a shell 1 made of high-temperature-resistant materials, wherein a gas channel (not numbered) for placing ignition powder 2 is arranged in the shell 1, a plurality of gas holes 12 distributed in an array mode are formed in the peripheral surface of the shell 1, and the plurality of gas holes 12 are respectively communicated with the gas channel;
ignition powder 2 arranged in the gas channel;
the electric explosion tube 3 is arranged in the gas channel; and
the air guide sleeve 4 is connected with one end of the gas channel, and a plurality of air guide holes 41 communicated with the gas channel are formed in the air guide sleeve 4.
In the embodiment of the invention, the simple and reliable solid rocket engine ignition device is particularly used for a solid rocket engine with low-burning-rate propellant. In practical application, the simple and reliable solid rocket engine ignition device can be arranged in a propellant grain of a solid rocket engine, when the simple and reliable solid rocket engine ignition device ignites, the electric squib 3 ignites the ignition powder 2, ignition gas generated by combustion of the ignition powder 2 is guided to a combustion surface of the propellant through the plurality of gas holes 12 on the outer peripheral surface of the shell 1 and the plurality of guide holes 41 on the guide cover 4 so as to ignite the propellant, and the solid rocket engine can be successfully ignited.
In the embodiment of the invention, the gas channels are distributed in the shell 1 along the length direction of the shell 1. Wherein, the casing 1 shown in fig. 1 is a cylindrical pipe structure, and the gas channel is a cylindrical inner hole arranged inside the casing 1. In addition, the housing 1 may be provided in other shapes.
In the embodiment of the invention, the ignition powder 2 is placed in the gas channel, and the ignition powder 2 can be selected from but not limited to black powder, ignition tablets and the like. The gas channel can reduce escape of unburned ignition powder 2, and simultaneously plays a guiding role in gas flow of the ignition powder 2, and energy loss is reduced.
In the embodiment of the invention, the number and the direction of the gas holes 12 can be designed according to specific working conditions, the air guide sleeve 4 is of a porous structure provided with a plurality of air guide holes 41, the air guide sleeve 4 can be made of materials such as but not limited to aluminum alloy, functionally gradient alloy and the like, and the selection of materials, the number of holes and the diameter are carried out according to the working conditions in the combustion chamber of the solid rocket engine.
In the embodiment of the invention, one end of the shell 1 is fixed on the solid rocket engine through the fixing component 5, so that the simple and reliable solid rocket engine ignition device is fixed, the other end of the shell is provided with the air guide sleeve 4, and the air guide sleeve 4 guides ignition gas passing through the end surface of the gas channel to the combustion surface of the propellant, so that the energy dispersion is reduced, and the ignition reliability is improved.
In the embodiment of the invention, the shell 1 made of high-temperature resistant material is arranged to encapsulate the ignition powder 2, and the gas channel is designed on the shell 1 as the placing space of the ignition powder 2 according to the position relation between the flow direction of ignition gas and the combustion surface of propellant, so that at the moment that the ignition powder 2 is ignited by the electric explosion tube 3, the shell 1 made of high-temperature resistant material cannot be burst, and the shell 1 wraps the ignition powder 2 which is not ignited, so that the ignition powder 2 which is not ignited can be continuously ignited and fully combusted in the gas channel, and the utilization rate of the energy of the ignition powder 2 is improved; meanwhile, ignition gas generated by combustion of the ignition powder 2 is guided to the combustion surface of the propellant through the plurality of gas holes 12 on the outer peripheral surface of the shell 1 and the plurality of guide holes 41 on the guide cover 4 to ignite the propellant, so that the energy loss of the ignition gas is reduced, and the reliability of successful ignition of the propellant is improved; moreover, the whole simple and reliable solid rocket engine ignition device has no moving part, simple structure, low realization cost and high reliability.
In the embodiment of the invention, in the working process of the ignition device, after the ignition powder 2 is ignited, the ignition gas generated by the ignition powder 2 is guided to the propellant combustion surface through the gas hole 12 on the cylindrical surface of the ignition gas channel and the gas hole 12 on the air guide sleeve 4, and meanwhile, the gas channel can reduce the random diffusion of the powder or tablet of the ignition powder 2 which is not ignited, so that the ignition powder 2 is ignited in sufficient space and time, the measures are taken, the energy dispersion of the ignition powder 2 is reduced, and the ignition reliability is improved. Compared with the traditional ignition medicine box, the simple and reliable solid rocket engine ignition device has the advantages that the energy utilization efficiency of the ignition gas is higher, and the ignition process is more reliable; compared with the traditional basket-type ignition device, the basket-type ignition device has the advantages of simpler structure, small installation space, lower cost and improved reliability. In practical application, the connection mode of all components of the ignition device, the number, the diameter, the direction and the like of the gas holes 12 can be designed, so that the ignition device is wide in application range and high in designability.
In practical application, the gas hole 12 may be a cylindrical hole, or may be a tapered hole to accelerate the gas diffusion speed. The shape, number and diameter of the gas holes 12 and the diversion holes 41 can be set according to actual working conditions. For example, the ratio of the sum of the cross-sectional areas of all the gas holes 12 and all the diversion holes 41 to the combustion surface of the propellant is 5-30%, so that a good ignition effect can be realized. In practical application, the sum of the cross-sectional areas of all the gas holes 12 and all the diversion holes 41 and the combustion surface ratio of the propellant can be flexibly adjusted according to actual needs.
As an embodiment of the present invention, the high temperature resistant material is a carbon fiber wound material or a high silica fiber wound material, i.e. the shell 1 is made of a carbon fiber wound material or a high silica fiber wound material. The characteristics that the carbon fiber winding material or the high silica fiber winding material has strong bearing capacity and high temperature resistance are utilized, so that the whole bearing capacity of the shell 1 is strong, the shell 1 cannot be cracked or melted when the ignition powder 2 is ignited by the electric detonator 3, and the packaging reliability of the ignition powder 2 is good. Besides, the high-temperature resistant material can also be other non-metal high-temperature resistant materials or high-temperature resistant metal materials.
In the embodiment of the invention, when the simple and reliable solid rocket engine ignition device is ignited, the ignition gas on one end surface of the gas channel is guided to the combustion surface of the propellant through the guide holes 41 on the guide cover 4, and the energy divergence of the ignition gas is reduced by utilizing the guide effect of the guide holes 41 on the guide cover 4, so that the successful ignition reliability of the propellant can be improved.
As an embodiment of the invention, the air guide sleeve 4 is made of aluminum alloy, so that the air guide sleeve 4 can be completely ablated and melted after ignition is finished, and the air guide sleeve 4 is prevented from falling off and blocking an engine spray pipe.
As an embodiment of the present invention, the diameter of the guide holes 41 of the center area of the pod 4 is larger than the diameter of the guide holes 41 of the peripheral area. By making the diameter of the diversion hole 41 in the central area of the diversion cover 4 larger than the diameter of the diversion hole 41 in the peripheral area, the design can ensure that the diversion cover 4 starts to be ablated from the central area in the ablation process and gradually diffuses to the periphery, thereby avoiding the dropping of large metal blocks and the blockage of an engine spray pipe. Specifically, the diameter of the diversion hole 41 on the diversion cover 4 gradually decreases from the central area to the edge position, so that the characteristic that the diversion hole 41 of the diversion cover 4 gradually decreases from the central area to the edge position is realized.
As another embodiment of the invention, the air guide sleeve 4 is made of a functional gradient material, the melting point of the material of the central area of the air guide sleeve 4 is lower than that of the material of the peripheral area, namely the ablation rate of the material at the central position of the air guide sleeve 4 is higher, the melting point is lower, the air guide sleeve 4 starts to be ablated from the central position in the ablation process and gradually diffuses to the periphery, and the phenomenon that the engine jet pipe is blocked due to the fact that large metal blocks fall off is avoided. For example, the material of the central area of the pod 4 may be plastic, and the material of the peripheral area of the pod 4 may be an aluminum alloy.
As an embodiment of the invention, the central axis of each deflector hole 41 is arranged perpendicular to the combustion surface of the propellant outside the housing 1.
In practical application, when the simple and reliable solid rocket engine ignition device ignites, the air guide sleeve 4 vertically guides ignition gas passing through the end face of the gas channel to the combustion face of the propellant through the guide holes 41, so that the utilization rate of gas energy is further improved, and the ignition reliability is improved. In other embodiments, the diversion holes 41 may also be disposed non-perpendicular to the combustion surface of the propellant, for example, the diversion holes 41 may be inclined holes, and may be flexibly adjusted according to actual needs.
As an embodiment of the present invention, the ignition charge 2 is ignition charge powder or ignition tablets, and the ignition charge 2 powder or ignition tablets are wrapped by a wrapping layer (not shown) and placed in the combustion gas channel. The wrapping layer can be silk cloth or other wrapping films, so that ignition powder or ignition tablets cannot leak out of the gas holes 12 on the outer peripheral surface of the shell 1, and the ignition powder or the ignition tablets can be stably placed in the gas channel.
As an embodiment of the invention, two sealing blocks 6 are respectively and fixedly arranged at two ends in the gas channel, and the ignition powder 2 is fixedly arranged between the two sealing blocks 6 in the gas channel. The ignition powder 2 is sealed by the two plugging blocks 6, so that the ignition powder 2 is prevented from leaking from two ends in the gas channel, and the safety performance is improved. Wherein, the blocking block 6 can be a foam block or other easily-ablated materials.
As an embodiment of the invention, one end of the air guide sleeve 4 extends into the gas channel, and one end of the air guide sleeve 4 extending into the gas channel is in threaded connection or is bonded with the shell 1 by high-temperature-resistant inorganic glue.
In this embodiment, the housing 1 and the air guide sleeve 4 are separately arranged, and the air guide sleeve 4 and the housing 1 are connected in a threaded connection manner or a high-temperature-resistant inorganic adhesive bonding manner, so that the housing 1 and the air guide sleeve 4 can be conveniently assembled and connected. In addition, the housing 1 and the pod 4 may be formed integrally.
The present invention is not limited to the above preferred embodiments, and any modifications, equivalents and improvements made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (9)
1. A simple and reliable solid rocket engine ignition device, comprising:
the ignition device comprises a shell made of high-temperature-resistant materials, wherein a gas channel for placing ignition powder is arranged in the shell, a plurality of gas holes distributed in an array mode are formed in the peripheral surface of the shell, and the gas holes are respectively communicated with the gas channel;
ignition powder arranged in the gas channel;
the electric explosion tube is arranged in the gas channel; and
the air guide sleeve is connected with one end of the gas channel and is provided with a plurality of air guide holes communicated with the gas channel.
2. The solid rocket engine ignition device of claim 1 wherein said refractory material is a carbon fiber wound material or a high silica fiber wound material.
3. A simple and reliable solid rocket engine ignition device as recited in claim 1, wherein said air guide sleeve is made of aluminum alloy.
4. A simple and reliable solid rocket engine ignition device according to claim 3 wherein said deflector holes in the central region of said air guide sleeve have a diameter greater than the diameter of said deflector holes in the peripheral region.
5. A simple and reliable solid rocket engine ignition device according to claim 1 wherein said air guide sleeve is made of functionally graded material, the melting point of the material of said air guide sleeve being lower in the central region than in the peripheral region.
6. A simple and reliable solid rocket engine ignition device according to claim 1 wherein the central axis of each of said flow-guiding holes is disposed perpendicular to the combustion face of the propellant outside said housing.
7. The ignition device of a solid rocket engine as recited in claim 1, wherein said ignition charge is ignition charge powder or ignition tablets, said ignition charge powder or ignition tablets being wrapped with a wrapping layer and placed in said combustion gas channel.
8. The simple and reliable solid rocket engine ignition device according to claim 1, wherein two blocks are respectively and fixedly arranged at two ends in said gas channel, and said ignition charge is fixedly arranged between said two blocks in said gas channel.
9. A simple and reliable solid rocket engine ignition device according to claim 1, wherein one end of said air guide sleeve is extended into said gas channel, and one end of said air guide sleeve extended into said gas channel is connected with said casing by screw thread or is bonded by high temperature resistant inorganic glue.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210896378.9A CN115467763A (en) | 2022-07-27 | 2022-07-27 | Simple and reliable solid rocket engine ignition device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210896378.9A CN115467763A (en) | 2022-07-27 | 2022-07-27 | Simple and reliable solid rocket engine ignition device |
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| Publication Number | Publication Date |
|---|---|
| CN115467763A true CN115467763A (en) | 2022-12-13 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210896378.9A Pending CN115467763A (en) | 2022-07-27 | 2022-07-27 | Simple and reliable solid rocket engine ignition device |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4738100A (en) * | 1984-12-06 | 1988-04-19 | Werkzeugmaschinenfabrik Oerlikon Buehrle Ag | Boost-sustain-boost rocket |
| RU2445502C1 (en) * | 2010-08-23 | 2012-03-20 | Государственное образовательное учреждение высшего профессионального образования "Тульский государственный университет" (ТулГУ) | Ignition device of charges of solid-propellant rocket engines |
| CN111305973A (en) * | 2020-03-13 | 2020-06-19 | 宁波天擎航天科技有限公司 | Small-size solid rocket engine ignition |
-
2022
- 2022-07-27 CN CN202210896378.9A patent/CN115467763A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4738100A (en) * | 1984-12-06 | 1988-04-19 | Werkzeugmaschinenfabrik Oerlikon Buehrle Ag | Boost-sustain-boost rocket |
| RU2445502C1 (en) * | 2010-08-23 | 2012-03-20 | Государственное образовательное учреждение высшего профессионального образования "Тульский государственный университет" (ТулГУ) | Ignition device of charges of solid-propellant rocket engines |
| CN111305973A (en) * | 2020-03-13 | 2020-06-19 | 宁波天擎航天科技有限公司 | Small-size solid rocket engine ignition |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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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