CN113606057A - Axial sliding type partition plate suitable for multi-pulse solid rocket engine - Google Patents
Axial sliding type partition plate suitable for multi-pulse solid rocket engine Download PDFInfo
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- CN113606057A CN113606057A CN202110952343.8A CN202110952343A CN113606057A CN 113606057 A CN113606057 A CN 113606057A CN 202110952343 A CN202110952343 A CN 202110952343A CN 113606057 A CN113606057 A CN 113606057A
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- engine
- partition plate
- axial sliding
- pulse
- sliding type
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Classifications
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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
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/10—Shape or structure of solid propellant charges
- F02K9/12—Shape or structure of solid propellant charges made of two or more portions burning at different rates or having different characteristics
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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
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/24—Charging rocket engines with solid propellants; Methods or apparatus specially adapted for working solid propellant charges
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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
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/28—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants having two or more propellant charges with the propulsion gases exhausting through a common nozzle
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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
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/32—Constructional parts; Details not otherwise provided for
-
- 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
Abstract
The invention discloses an axial sliding type partition plate suitable for a multi-pulse solid rocket engine, and belongs to the technical field of multi-pulse solid engines. The invention mainly comprises a clapboard and a sealing ring. The combustion chamber of the solid rocket engine is divided into a plurality of parts by the axial sliding type partition plates, the combustion chamber slides to the rear section of engine through the axial sliding type partition plates, and the rear section of engine charge bears the pressure generated when the front section of engine works, so that the situation that the rear section of engine charge is ignited due to the broken partition plates is avoided; in addition, one-way crushing is realized through the prefabricated defect of the axial sliding type clapboard, the normal work of the engine at the later stage is ensured, namely, the multi-pulse solid rocket engine is shut down and started for multiple times through the prefabricated defect of the axial sliding type clapboard, the thrust and the interval time of each pulse are reasonably distributed, and the optimal management of the energy of the engine is realized. The invention has the advantages of suitability for complex medicine types, low cost, light weight, simple structure and convenient installation.
Description
Technical Field
The invention relates to an isolating device suitable for a multi-pulse solid rocket engine, and belongs to the technical field of multi-pulse solid rocket engines.
Background
The traditional solid rocket engine works after one-time ignition till the combustion is finished, can only provide one-time thrust and has poor maneuverability at the tail end of a trajectory. The multi-pulse rocket engine can reasonably and effectively manage the energy of the engine, and has the advantages of long range, high terminal guidance speed, good maneuverability and the like compared with the conventional rocket engine.
The multi-pulse engine realizes multiple ignition by using the isolating device, thereby realizing multi-pulse work. The isolating device is used as a core component of the pulse engine, divides an engine combustion chamber into a plurality of propellant units, can realize multiple ignition, enables the transmitter to be powered off and started for multiple times, reasonably distributes thrust and each pulse interval time, performs multiple thrust control, and realizes optimal management of engine energy.
The more developed isolating devices at home and abroad are provided with hard baffles and soft interlayers. The hard partition plates comprise ceramic one-way breaking type partition plates, metal diaphragm type partition plates, jet rod type metal partition plates and the like. The hard partition plate has the advantages of high strength, strong forward bearing capacity, good sealing performance and the like. Meanwhile, the hard partition plate has the defects of heavy structure, difficult heat insulation, sensitivity to material characteristics and the like. The soft interlayer has the advantages of simple structure, easy processing, light weight and the like. Meanwhile, the soft interlayer has the defects of poor structural mechanical property, limitation on the design of a medicine charging type and the like.
Disclosure of Invention
The invention aims to provide an axial sliding type clapboard suitable for a multi-pulse solid rocket engine, wherein a combustion chamber of the solid rocket engine is divided into a plurality of parts by the axial sliding type clapboard, the parts slide towards a rear section of engine through the axial sliding type clapboard, and the charge of the rear section of engine bears the pressure generated when the front section of engine works, so that the situation that the charge of the rear section of engine is ignited due to the crushing of the clapboard is avoided; in addition, one-way crushing is realized through the prefabricated defect of the axial sliding type clapboard, the normal work of the engine at the later stage is ensured, namely, the multi-pulse solid rocket engine is shut down and started for multiple times through the prefabricated defect of the axial sliding type clapboard, the thrust and the interval time of each pulse are reasonably distributed, and the optimal management of the energy of the engine is realized. The invention has the advantages of suitability for complex medicine types, low cost, light weight, simple structure and convenient installation.
The purpose of the invention is realized by the following technical scheme.
The invention discloses an axial sliding partition plate suitable for a multi-pulse solid rocket engine.
The axial sliding type partition plate mainly comprises a partition plate and a sealing ring. The side of the clapboard is provided with a groove for placing a sealing ring along the circumferential direction. The surface of the partition board close to the front section of the engine is provided with a prefabricated defect for realizing one-way crushing, and the size of the prefabricated defect is smaller than the area of the throat part of the spray pipe, so that fragments formed when the partition board is crushed are prevented from blocking the spray pipe; the total area of the vent holes formed after the prefabricated defects are broken is larger than the area of the throat part of the spray pipe, so that the blockage caused by the small gas channel is avoided. The sealing ring is arranged in the sealing ring groove of the partition plate and used for sealing a gap between the partition plate and the engine shell, so that the situation that fuel gas generated when the previous section of engine works is ignited and the fuel is charged in the latter section of engine is avoided.
The axial sliding type partition plate slides towards the rear section of engine, and the pressure generated when the rear section of engine charge bears the working of the front section of engine is utilized to prevent the partition plate from being broken to cause the rear section of engine charge to be ignited; in addition, the one-way crushing is realized through the prefabricated defects of the axial sliding type partition plate, so that the normal work of the subsequent section of engine is ensured, the axial sliding type partition plate can be quickly crushed along the prefabricated defects under the lower (8MPa) pressure load, the fuel gas of the subsequent section of engine can smoothly pass through, and meanwhile, the fragments of the axial sliding type partition plate are sprayed out from the spray pipe; the sliding of the axial sliding type clapboard in the combustion chamber does not influence the work of the engine and does not damage the structure of the engine. The multi-pulse solid rocket engine is shut down and started for multiple times through the prefabricated defective axial sliding type partition plate, thrust and pulse interval time are reasonably distributed, and optimal management of engine energy is achieved.
Preferably, the clapboard is made of high-temperature resistant material meeting the force bearing requirement. Preferably, the partition board is made of phenolic aldehyde laminated paperboard material
In order to ensure the bearing strength of the partition plate, the weak link of the partition plate is locally reinforced as the optimization. Preferably, the method for locally reinforcing the weak link of the separator comprises the following steps: the joint of the edge and the surface of the clapboard is chamfered, and the thickness of the weak part of the surface of the clapboard is locally increased.
Preferably, the sealing ring is made of low-cost and high-temperature-resistant silicon rubber.
Has the advantages that:
1. the invention discloses an axial sliding partition plate suitable for a multi-pulse solid rocket engine, which is characterized in that a combustion chamber of the solid rocket engine is divided into a plurality of parts by utilizing the axial sliding partition plate, and the pressure generated when the engine at the previous section works is borne by the partition plate in an axial sliding manner, so that the situation that the explosive charge of the engine at the next section is ignited due to the broken partition plate is avoided; in addition, the one-way crushing is realized through the prefabricated defect of the axial sliding type clapboard, the normal work of the subsequent section of engine is ensured, namely, the multi-pulse solid rocket engine is shut down and started for many times through the prefabricated defect of the axial sliding type clapboard, the thrust and the interval time of each pulse are reasonably distributed, and the optimal management of the energy of the engine is realized.
2. The invention discloses an axial sliding partition plate suitable for a multi-pulse solid rocket engine, which does not influence the explosive-charging combustion surface of a later section of engine, has no special requirement on the combustion surface of a propellant, and is suitable for complex explosive types.
3. In the prior art, the mass of the ceramic and metal partition plates is large, and the spray rod partition plate is composed of a metal support with holes and a plurality of spray rods inserted into the holes, so that the structural mass is large. The axial sliding partition plate suitable for the multi-pulse solid rocket engine is made of phenolic aldehyde laminated paper board materials, is low in cost and light in weight, and can effectively reduce the negative mass of the engine.
4. The invention discloses an axial sliding clapboard suitable for a multi-pulse solid rocket engine, which consists of a clapboard and a sealing ring, wherein a gap between the clapboard and the inner wall surface of a combustion chamber is sealed by the sealing ring and can slide along the axial direction under the action of the pressure of the combustion chamber. The next section of engine charge can be freely loaded, the partition plate is tightly attached to the next section of engine charge, a fixing structure is not needed, and the installation is convenient.
5. The axial sliding type partition plate is made of high-temperature-resistant materials, achieves good sealing performance and heat insulation performance under low thickness, obviously improves the filling coefficient of the charged powder, can achieve any proportion division of the charged powder of the multi-pulse engine through free sliding of the axial sliding partition plate along the axial direction, and reasonably distributes thrust and pulse interval time.
Drawings
FIG. 1 is a cross-sectional view of an axially slidable bulkhead of the present invention suitable for use in a multi-pulse solid rocket engine;
FIG. 2 is a cross-sectional view of a separator plate of the present invention;
FIG. 3 is a top view of the separator plate of the present invention;
FIG. 4 is a schematic view of an axially sliding bulkhead double pulse engine of the present invention;
FIG. 5 is a top view of the rear baffle of the axial sliding type diaphragm double pulse engine of the present invention;
the device comprises 1-second pulse igniter, 2-front end enclosure, 3-elastic cushion, 4-engine shell, 5-pine strip, 6-second pulse charge, 7-partition sealing ring, 8-partition, 9-first pulse charge, 10-rear medicine baffle plate, 11-rear sealing ring, 12-first pulse igniter, 13-spray pipe and 14-spray pipe plugging cover.
Detailed Description
For a better understanding of the objects and advantages of the present invention, reference should be made to the following detailed description taken in conjunction with the accompanying drawings and examples.
Example 1:
as shown in fig. 4, the axial sliding bulkhead type solid rocket double-pulse engine disclosed in this embodiment includes a second pulse igniter 1, a front head 2, an elastic pad 3, an engine housing 4, a pine strip 5, a second pulse charge 6, a bulkhead seal ring 7, a bulkhead 8, a first pulse charge 9, a rear drug baffle plate 10, a rear seal ring 11, a first pulse igniter 12, a nozzle 13, and a nozzle blanking cover 14. The second pulse igniter 1 is arranged at the end close to the second pulse charge 6 and is screwed in and fixed by the front end enclosure 2. The elastic pad 3 is arranged between the front end socket 2 and the second pulse charge 6, so that the vibration of the second pulse charge 6 is reduced. The strip of pine 5 is interposed between the engine case 4 and the second and first impulse charges 6, 9, limiting the movement of the engine charge in the radial direction. The lower surface of the diaphragm 8 is pre-tightened against the second pulse charge 6 and the diaphragm seal ring 7 is placed in a lateral groove between the engine housing 4 and the diaphragm 6. The rear medicine baffle plate 10 is disposed between the first pulse charge 9 and the nozzle 12, and is used for restricting the shaking of the first pulse charge 9. The first pulse charge 9 and the second pulse charge 6 are designed as freely-charged inner and outer fuel columns. The nozzle 13 is connected with the engine shell 4 through threads, and the rear sealing ring 11 is arranged at the sealing groove of the engine shell 4 and the nozzle 13. The first pulse igniter 12 is screwed and fixed at the convergent section of the lance 13. A spout closure 14 is placed at the expanded section of spout 13.
As shown in FIG. 1, the axial sliding partition plate suitable for the multi-pulse solid rocket engine disclosed by the embodiment is composed of a partition plate and a sealing ring. The axial sliding type partition board is arranged at the position A and made of phenolic aldehyde laminated paperboard. And a sealing ring is arranged at the position B of the axial sliding type partition plate and is made of a silicon rubber material.
As shown in figure 2, a part a of the clapboard is a lateral groove for placing a clapboard sealing ring, a part b of the clapboard is a prefabricated defect for unidirectional crushing when the clapboard bears pressure, and the prefabricated defect is in the shape of an inverted right triangle, 2mm wide and 1mm deep. The part c of axial slidingtype baffle is local reinforcing position for strengthen the weak link of baffle, prevent that the baffle from bearing breakage when first pulse pressure.
As shown in figure 3, the prefabricated defects of the separator are circular and are evenly distributed at 8 positions along the circumferential direction. The size of the round fragments formed after crushing is smaller than the area of the throat part of the spray pipe, and the round fragments can be sprayed out through the spray pipe; the total area of the fuel gas channel formed after crushing is larger than the area of the throat part of the spray pipe, so that the second pulse charging generated fuel gas is prevented from being blocked in the combustion chamber.
When the first pulse engine works, an ignition signal is connected from the outside of the engine through an ignition wire, the first pulse igniter 12 is excited, the first pulse charge 9 is ignited, and fuel gas is sprayed out of the engine through the spray pipe 13. The axial sliding type clapboard 8 moves to the end of the second pulse charging material 6 along the axial direction under the action of the pressure of the fuel gas and bears the pressure of the first pulse fuel gas by the second pulse charging material 6. In the experiment, the axial sliding type partition plate can bear 12MPa pressure generated when the first pulse engine works and effectively seal fuel gas generated when the first pulse engine works. After the first pulse engine finishes working, delaying a certain time and starting the second pulse engine to work. When the second pulse engine works, an ignition signal is connected from the outside of the engine through an ignition wire, and the second pulse igniter 1 is excited to ignite the second pulse charge 6 and generate fuel gas. And under the action of the gas pressure generated by the second pulse engine, the partition plate is broken along the prefabricated defect to form a gas channel. The fragments of the partition plate are sprayed out from the combustion chamber and the spray pipe, and the surface of the partition plate is provided with vent holes, wherein the total area of the vent holes is larger than the area of the throat part of the spray pipe. The second pulse fuel gas is sprayed out of the spray pipe 12 after passing through the vent holes of the partition plate. In the experiment, the fuel gas can be broken in one direction under the pressure of 8MPa generated by the second pulse engine, and the fuel gas can smoothly pass through the fuel gas.
As shown in figure 5, the rear medicine baffle plate is designed into a circular hole radiation shape, so that the fuel gas generated by combustion of the outer combustion surface of the first pulse engine medicine can smoothly flow out, and the movement of the medicine in the working process of the engine can be avoided.
The axially slidable partition in the above embodiments is suitable for use in a multiple pulse engine. The axial sliding type partition plate is arranged in the combustion chamber of the engine, the requirement that the multi-pulse engine works in sequence can be met, when the rear-stage engine works, the axial sliding type partition plate is broken along prefabricated defects, and fragments are sprayed out through the combustion chamber and the spray pipe. Thrust and each pulse interval time can be reasonably distributed through the axial sliding type partition plate, and optimal management of engine energy is achieved. The axial sliding type partition plate is suitable for complex medicine types, low in cost, light in weight, simple in structure and convenient to install.
The above detailed description is intended to illustrate the objects, aspects and advantages of the present invention, and it should be understood that the above detailed description is only exemplary of the present invention and is not intended to limit the scope of the present invention, and any modifications, equivalents, improvements and the like made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (8)
1. An axial sliding partition plate suitable for a multi-pulse solid rocket engine is characterized in that: dividing a combustion chamber of the solid rocket engine into a plurality of parts by using the axial sliding type partition plate;
the axial sliding type partition plate mainly comprises a partition plate and a sealing ring; the side surface of the clapboard is provided with a groove for placing a sealing ring along the circumferential direction; the surface of the partition board close to the front section of the engine is provided with a prefabricated defect for realizing one-way crushing, and the size of the prefabricated defect is smaller than the area of the throat part of the spray pipe, so that fragments formed when the partition board is crushed are prevented from blocking the spray pipe; the total area of the vent holes formed after the prefabricated defects are broken is larger than the area of the throat part of the spray pipe, so that the blockage caused by the small gas channel is avoided; the sealing ring is arranged in the sealing ring groove of the partition plate and used for sealing a gap between the partition plate and the engine shell, so that the situation that fuel gas generated when the previous section of engine works is ignited and the fuel is charged in the latter section of engine is avoided.
2. An axially sliding bulkhead adapted for use in a multi-pulse solid rocket engine according to claim 1, wherein: the axial sliding type partition plate slides towards the rear section of engine, and the pressure generated when the rear section of engine charge bears the working of the front section of engine is utilized to prevent the partition plate from being broken to cause the rear section of engine charge to be ignited; in addition, the one-way crushing is realized through the prefabricated defects of the axial sliding type partition plate, so that the normal work of the subsequent section of engine is ensured, the axial sliding type partition plate can be quickly crushed along the prefabricated defects under the lower pressure load, the fuel gas of the subsequent section of engine can smoothly pass through, and meanwhile, the fragments of the axial sliding type partition plate are sprayed out from the spray pipe; the sliding of the axial sliding type clapboard in the combustion chamber does not influence the work of the engine and does not damage the structure of the engine; the multi-pulse solid rocket engine is shut down and started for multiple times through the prefabricated defective axial sliding type partition plate, thrust and pulse interval time are reasonably distributed, and optimal management of engine energy is achieved.
3. An axially sliding bulkhead adapted for use in a multi-pulse solid rocket engine according to claim 2, wherein: the axially sliding diaphragm will quickly break along the pre-cast defect under a low pressure load of 8 MPa.
4. An axially sliding bulkhead adapted for use in a multi-pulse solid rocket engine according to claim 1, 2 or 3, wherein: the clapboard is made of high-temperature resistant material which meets the force bearing requirement.
5. An axially sliding bulkhead adapted for use in a multi-pulse solid rocket engine according to claim 4, wherein: the partition board is made of phenolic aldehyde laminated paper board materials.
6. An axially sliding bulkhead adapted for use in a multi-pulse solid rocket engine according to claim 1, 2 or 3, wherein: in order to ensure the bearing strength of the partition plate, the weak link of the partition plate is locally reinforced.
7. An axially sliding bulkhead adapted for use in a multi-pulse solid rocket engine according to claim 6, wherein: the mode of local enhancement is carried out the baffle weak link, including baffle edge and surperficial handing-over department chamfer, the local increase thickness in baffle surface weak department.
8. An axially sliding bulkhead adapted for use in a multi-pulse solid rocket engine according to claim 1, 2 or 3, wherein: the sealing ring is made of low-cost and high-temperature-resistant silicon rubber.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110952343.8A CN113606057A (en) | 2021-08-19 | 2021-08-19 | Axial sliding type partition plate suitable for multi-pulse solid rocket engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110952343.8A CN113606057A (en) | 2021-08-19 | 2021-08-19 | Axial sliding type partition plate suitable for multi-pulse solid rocket engine |
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| CN113606057A true CN113606057A (en) | 2021-11-05 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110952343.8A Pending CN113606057A (en) | 2021-08-19 | 2021-08-19 | Axial sliding type partition plate suitable for multi-pulse solid rocket engine |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114233517A (en) * | 2021-12-21 | 2022-03-25 | 西安零壹空间科技有限公司 | High-overload solid rocket engine and design method of explosive type thereof |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US4594945A (en) * | 1984-11-28 | 1986-06-17 | General Dynamics, Pomona Division | Thermal protection for propellant grains |
| US5613358A (en) * | 1990-09-26 | 1997-03-25 | Thiokol Corporation | Reduced cost membrane seal assembly for pulsed rocket motor |
| US20130014491A1 (en) * | 2011-07-14 | 2013-01-17 | Tasuku Suzuki | Combustion gas supply control device |
| CN110594038A (en) * | 2019-08-20 | 2019-12-20 | 西安航天动力技术研究所 | Multi-pulse excitation device |
| CN111058966A (en) * | 2019-12-30 | 2020-04-24 | 珠海凯利得新材料有限公司 | Manufacturing method of pulse engine hard partition plate |
| CN112610984A (en) * | 2020-12-14 | 2021-04-06 | 上海航天化工应用研究所 | Gas isolating device suitable for high temperature and high pressure |
-
2021
- 2021-08-19 CN CN202110952343.8A patent/CN113606057A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4594945A (en) * | 1984-11-28 | 1986-06-17 | General Dynamics, Pomona Division | Thermal protection for propellant grains |
| US5613358A (en) * | 1990-09-26 | 1997-03-25 | Thiokol Corporation | Reduced cost membrane seal assembly for pulsed rocket motor |
| US20130014491A1 (en) * | 2011-07-14 | 2013-01-17 | Tasuku Suzuki | Combustion gas supply control device |
| CN110594038A (en) * | 2019-08-20 | 2019-12-20 | 西安航天动力技术研究所 | Multi-pulse excitation device |
| CN111058966A (en) * | 2019-12-30 | 2020-04-24 | 珠海凯利得新材料有限公司 | Manufacturing method of pulse engine hard partition plate |
| CN112610984A (en) * | 2020-12-14 | 2021-04-06 | 上海航天化工应用研究所 | Gas isolating device suitable for high temperature and high pressure |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114233517A (en) * | 2021-12-21 | 2022-03-25 | 西安零壹空间科技有限公司 | High-overload solid rocket engine and design method of explosive type thereof |
| CN114233517B (en) * | 2021-12-21 | 2024-03-29 | 西安零壹空间科技有限公司 | Solid rocket engine for high overload and drug pattern design method thereof |
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Application publication date: 20211105 |