CN115788703A - Interstage isolation device for double-pulse engine - Google Patents
Interstage isolation device for double-pulse engine Download PDFInfo
- Publication number
- CN115788703A CN115788703A CN202211508690.2A CN202211508690A CN115788703A CN 115788703 A CN115788703 A CN 115788703A CN 202211508690 A CN202211508690 A CN 202211508690A CN 115788703 A CN115788703 A CN 115788703A
- Authority
- CN
- China
- Prior art keywords
- metal
- diaphragm
- auxiliary ring
- metal diaphragm
- isolation device
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000002955 isolation Methods 0.000 title claims abstract description 26
- 239000002184 metal Substances 0.000 claims abstract description 86
- 238000002485 combustion reaction Methods 0.000 claims abstract description 20
- 238000005192 partition Methods 0.000 claims description 22
- 239000012528 membrane Substances 0.000 claims description 6
- 238000002679 ablation Methods 0.000 claims description 3
- 230000009545 invasion Effects 0.000 claims description 2
- 239000007787 solid Substances 0.000 abstract description 5
- 238000009413 insulation Methods 0.000 description 11
- 239000007789 gas Substances 0.000 description 5
- 239000002360 explosive Substances 0.000 description 3
- 238000009434 installation Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 239000002737 fuel gas Substances 0.000 description 2
- 238000007789 sealing Methods 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000000919 ceramic Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 238000011900 installation process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000010008 shearing Methods 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
Images
Landscapes
- Diaphragms And Bellows (AREA)
Abstract
The invention provides an interstage isolation device for a double-pulse engine, and relates to the technical field of solid rocket engines. The invention improves the metal clapboard and the metal diaphragm in the diaphragm type isolating device: an auxiliary ring is arranged on the metal clapboard, and a circle of square groove is carved on the front surface of the metal diaphragm close to the outer edge. When the primary combustion chamber works, because the thickness of the auxiliary ring and the thickness of the metal diaphragm are specially designed, the pressure of the gas in the primary combustion chamber acting on the interstage isolating device is more distributed on the surface of the auxiliary ring and the outer edge of the metal diaphragm capable of bearing higher pressure; when the secondary combustion chamber is started, because the groove is not filled with the auxiliary ring at one side close to the circle center, the diaphragm can be broken and broken along the path of the square groove by a smaller pressure acting on the back of the diaphragm, so that the starting time of the secondary combustion chamber can be reduced, the energy utilization rate of the engine is improved, and the accurate control of the engine is facilitated.
Description
Technical Field
The invention belongs to the field of solid rocket engines, and particularly relates to an interstage isolation device for a double-pulse engine. The structure can effectively improve the starting speed of the secondary combustion chamber of the double-pulse engine and improve the working efficiency of the engine.
Background
Solid rocket engines have been widely used in strategic, tactical missile or aerospace applications. The pulse solid rocket engine capable of being ignited and started for multiple times can effectively control the energy output of the engine according to the requirement of combat use, and flexibly control the thrust interval and the thrust form in flight. The double-pulse engine divides the solid rocket engine into two parts to realize the classification of the thrust. The method reasonably arranges the acceleration and deceleration process in the flying process of the missile and the aircraft mainly by changing the working time of two-stage combustion chambers of the engine, thereby avoiding energy loss caused by factors such as resistance and the like, and realizing some special ballistic requirements, such as higher hitting height, higher hitting speed, variable speed flying before hitting a target and the like.
The isolating devices of the double-pulse engine can be divided into a ceramic type, an injection rod type and a metal diaphragm type. The metal diaphragm type is used for realizing the isolation of a combustion chamber by utilizing a spoke type support and the metal diaphragm. The metal diaphragm can ensure the sealing performance of the secondary combustion chamber when the primary combustion chamber works, and prevent the explosive columns in the secondary combustion chamber from being ignited; when the secondary combustion chamber is ignited, the metal diaphragm is provided with a preset defect groove, and the metal diaphragm can be broken along the preset groove under certain pressure. The metal diaphragm type isolation device has no limitation on the form of the explosive column, is convenient to assemble and has strong reliability, so that the metal diaphragm type isolation device is widely adopted.
At present, the aerospace industry field has had higher and higher requirements to the performance of dipulse engine, and this needs to design more practical, efficient interstage isolating device, and an outstanding interstage isolating device needs to satisfy: good forward opening capacity, high reverse pressure bearing capacity, high sealing performance and good heat insulation performance. The design has the advantages of light weight, simple structure, easy assembly and strong reliability under the condition of fully meeting the requirements, and can improve the overall performance of the pulse engine.
Disclosure of Invention
The invention aims to solve the technical problem of providing an interstage isolation device for a double-pulse engine. Compared with the prior art structure, the scheme has the advantages of better forward opening capability and higher reverse pressure-bearing capability. According to the relevant knowledge of material mechanics, the stress analysis is carried out on the metal diaphragm, the pressure distribution acting on the surface of the metal diaphragm is improved through reasonable structural design, the crushing difficulty of the metal diaphragm is weakened by utilizing stress concentration, and the starting time of the secondary combustion chamber is further shortened. The structure is simple, the weight is light, the passive mass of the engine can be reduced, and the energy utilization rate of the engine is improved.
Technical scheme
The invention aims to provide an interstage isolation device for a double-pulse engine.
The technical scheme of the invention is as follows:
an interstage isolation device for a double pulse engine, comprising: metal baffle, metal diaphragm, supplementary ring structure, adiabatic gasket, the insulating layer, thermal-insulated end cap, its characterized in that: use insulating layer (3) between metal diaphragm (1) and metal diaphragm (2) to separate, the threaded rod of supplementary ring structure (4) passes the hole of above-mentioned three kinds of part outer fringe, fix on metal diaphragm by the boss and a plurality of nut of self structure, make metal diaphragm's ring channel just laminate to supplementary ring on, paste adiabatic gasket (5) at metal diaphragm's surface, also install thermal-insulated end cap (6) in the trompil department at the metal diaphragm back, with the invasion of high temperature gas of preventing, the ablation inner structure.
The interstage isolation device for the double pulse engine as claimed in claim 1, wherein: a circular hole is formed in the center of the metal diaphragm, V-shaped grooves are formed in the surface of the metal diaphragm in the 6 directions at the interval of 60 degrees from the circle center, the 6 divided small metal diaphragms respectively correspond to the six through holes of the metal partition plate, a circle of annular square groove is formed in the position, close to the edge of the metal diaphragm, the annular square groove can be tightly attached to the auxiliary ring, and the metal diaphragm can be fixed at an ideal position.
The interstage isolation device for the double pulse engine as claimed in claim 1, wherein: the maximum diameter of the auxiliary ring and the maximum diameter of the annular square groove are required to be equal, the minimum diameter of the annular square groove is slightly smaller than the auxiliary ring, an annular gap exists at the position, close to the center of a circle, of the groove, and when pressure acts on the back face, the concentration of shear stress can occur at the position, so that the metal diaphragm can be rapidly broken and crushed.
The interstage isolation device for the double pulse engine according to claim 1, wherein: the thickness from the groove to the edge part on the metal diaphragm is larger than the thickness from the groove to the circle center part, namely the thickness of the inner area of the diaphragm is smaller than that of the outer area, after combination is required, the height of the front surface of the auxiliary ring is the same as that of the outer area of the metal diaphragm, so that the gas pressure in the primary combustion chamber can be more distributed to the auxiliary ring and the outer area of the diaphragm with stronger bearing capacity, and the reliability of the double-pulse engine is improved.
The invention has the following beneficial effects:
the metal diaphragm is fixed at an ideal position by installing the auxiliary ring structure, namely, the small diaphragms divided by the V-shaped grooves respectively correspond to the through holes on the metal partition plate, so that the uniform stress of the metal diaphragm is ensured, and the stability of the whole interstage isolation device is improved; because the width of the auxiliary ring is smaller than that of the groove, the outer edge is fastened during assembly, and a certain gap is formed between the inner edge and the inner wall of the groove, the metal partition plate can be broken along the edge of the groove under a small pressure due to the concentration of shear stress when the metal partition plate is opened, so that the starting time of a secondary combustion chamber is shortened, and the accurate control of an engine is realized; when the double-pulse engine is broken, a uniform broken edge can be formed, so that the flow of fuel gas in a combustion chamber is influenced to a smaller extent, and the working efficiency of the double-pulse engine is improved; because the outer thickness of the metal diaphragm is greater than the inner thickness, the height of the auxiliary ring is the same as that of the outer side of the metal diaphragm, and more pressure given by the primary combustion chamber acts on the auxiliary ring and the outer side of the metal diaphragm with stronger pressure resistance, so that the isolation device has higher reliability; the structure is simple, convenient to install, light in weight and suitable for the aviation field.
Drawings
FIG. 1: assembled sectional view of interstage isolation device for double-pulse engine
FIG. 2: front view of metal diaphragm of interstage isolation device
FIG. 3: rear view of metal diaphragm of interstage isolation device
FIG. 4: schematic diagram of metal partition and auxiliary ring structure of interstage isolation device
FIG. 5: metal partition and auxiliary ring structure rear view of interstage isolation device
FIG. 6: combined schematic diagram of metal diaphragm, metal partition plate and auxiliary ring of interstage isolation device
In the figure: 1-metal partition plate, 2-metal diaphragm, 3-heat insulation layer, 4-auxiliary ring structure, 5-heat insulation gasket and 6-heat insulation plug
Detailed Description
The invention will now be further described with reference to the accompanying drawings in which:
with reference to fig. 1, 2, 3, 4, 5 and 6, the present invention provides a technical solution for an inter-stage isolation device of a double-pulse engine. Fig. 1 is an assembled sectional view of an interstage isolator device for a double pulse engine, fig. 2 is a front view of a metal diaphragm of the interstage isolator device, fig. 3 is a rear view of the metal diaphragm of the interstage isolator device, fig. 4 is a schematic view of a metal diaphragm and an auxiliary ring structure of the interstage isolator device, fig. 5 is a rear view of the metal diaphragm and the auxiliary ring structure of the interstage isolator device, and fig. 6 is a schematic view of a combination of the metal diaphragm, the metal diaphragm and the auxiliary ring of the interstage isolator device.
When the primary combustion chamber of the double-pulse engine works, the gas generated by the combustion of the explosive column generates an acting force opposite to the flowing direction of the gas on the interstage isolating device, and due to the special design of the metal diaphragm and the auxiliary ring, more pressure acts on the auxiliary ring and the outer area of the metal diaphragm with stronger pressure resistance. When the secondary combustion chamber is ignited, the through hole for the fuel gas to enter the metal partition plate directly acts on the back surface of the metal partition plate, and the auxiliary ring equivalently provides a fulcrum due to the fact that a circle of gap is formed between the groove and the auxiliary ring, so that shearing force is concentrated in the area, the metal partition plate can be easily broken and crushed at the annular square groove, and a relatively tidy crushing edge is formed. A heat insulation layer is arranged between the metal partition plate and the metal diaphragm, a heat insulation gasket is pasted on the surface of the metal partition plate and used for protecting the partition plate and the diaphragm from being damaged by ablation, and a heat insulation plug is plugged into a nut mounting hole at the rear part of the metal partition plate and used for preventing high-temperature gas from invading.
When the interstage isolation device is assembled, the heat insulation layer is installed on the front surface of the metal partition plate, then the metal membrane is attached to the surface of the heat insulation layer, the threaded rod of the auxiliary ring structure penetrates through the installation through holes of the three parts, the back of the metal partition plate is fixed through the nut, the size of the parts is just good, the metal partition plate is tightly installed on the auxiliary ring, finally, the heat insulation gasket is pasted on the front surface, and the heat insulation plug is plugged into the nut installation hole. The installation process embodies the advantages of compact structure and convenient installation.
Claims (4)
1. An interstage isolation device for a double pulse engine, comprising: metal baffle, metal diaphragm, supplementary ring structure, adiabatic gasket, the insulating layer, thermal-insulated end cap, its characterized in that: use insulating layer (3) between metal partition (1) and the metal diaphragm (2) to separate, the threaded rod of supplementary ring structure (4) passes the hole of above-mentioned three kinds of part outer fringe, fix on metal partition by the boss and a plurality of nut of self structure, make the ring channel of metal diaphragm just laminate to supplementary ring, paste adiabatic gasket (5) at the surface of metal diaphragm, also install thermal-insulated end cap (6) in the trompil department at the metal partition back, with the invasion of preventing high temperature gas, the ablation inner structure.
2. The interstage isolation device for the double pulse engine according to claim 1, wherein: a circular hole is formed in the center of the metal membrane, V-shaped grooves are formed in the surface of the metal membrane in the 6 directions at intervals of 60 degrees from the circle center, the 6 divided metal membranes are respectively corresponding to the six through holes of the metal partition plate, a circle of annular square groove is formed in the position, close to the edge of the metal membrane, the annular square groove can be tightly attached to the auxiliary ring, and the metal membrane is fixed at an ideal position.
3. The interstage isolation device for the double pulse engine according to claim 1, wherein: the maximum diameter of the auxiliary ring is equal to that of the annular square groove, the minimum diameter of the annular square groove is slightly smaller than that of the auxiliary ring, an annular gap exists at the position, close to the circle center, of the groove, and when pressure acts on the back face, the concentration of shear stress can occur at the position, so that the metal diaphragm can be rapidly broken.
4. The interstage isolation device for the double pulse engine as claimed in claim 1, wherein: the thickness from the groove to the edge part on the metal diaphragm is larger than the thickness from the groove to the circle center part, namely, the thickness of the inner area of the diaphragm is smaller than that of the outer area, after combination is required, the height of the front surface of the auxiliary ring is the same as that of the outer area of the metal diaphragm, so that more gas pressure in the primary combustion chamber can be distributed to the auxiliary ring and the outer area of the diaphragm with stronger bearing capacity, and the reliability of the double-pulse engine is improved.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211508690.2A CN115788703A (en) | 2022-11-29 | 2022-11-29 | Interstage isolation device for double-pulse engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211508690.2A CN115788703A (en) | 2022-11-29 | 2022-11-29 | Interstage isolation device for double-pulse engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115788703A true CN115788703A (en) | 2023-03-14 |
Family
ID=85442859
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211508690.2A Pending CN115788703A (en) | 2022-11-29 | 2022-11-29 | Interstage isolation device for double-pulse engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115788703A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4085584A (en) * | 1976-11-05 | 1978-04-25 | The United States Of America As Represented By The Secretary Of The Air Force | Barrier system for dual-pulse rocket motor |
| CN102168631A (en) * | 2011-04-14 | 2011-08-31 | 北京航空航天大学 | Aluminum film baffle device and pulse solid engine applying same |
| CN105464839A (en) * | 2014-09-29 | 2016-04-06 | 北京宇航系统工程研究所 | Mould pressing corrugated type flexible flame isolation device |
| CN106257117A (en) * | 2016-08-18 | 2016-12-28 | 湖北三江航天红林探控有限公司 | A kind of combined type one-way conduction isolating valve |
| CN107781062A (en) * | 2017-09-28 | 2018-03-09 | 北京理工大学 | A kind of Double pulse solid rocket motor interstage sealing structure device |
| CN111022217A (en) * | 2019-11-01 | 2020-04-17 | 湖北三江航天红林探控有限公司 | Interstage isolation and conduction device for double-pulse igniter |
-
2022
- 2022-11-29 CN CN202211508690.2A patent/CN115788703A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4085584A (en) * | 1976-11-05 | 1978-04-25 | The United States Of America As Represented By The Secretary Of The Air Force | Barrier system for dual-pulse rocket motor |
| CN102168631A (en) * | 2011-04-14 | 2011-08-31 | 北京航空航天大学 | Aluminum film baffle device and pulse solid engine applying same |
| CN105464839A (en) * | 2014-09-29 | 2016-04-06 | 北京宇航系统工程研究所 | Mould pressing corrugated type flexible flame isolation device |
| CN106257117A (en) * | 2016-08-18 | 2016-12-28 | 湖北三江航天红林探控有限公司 | A kind of combined type one-way conduction isolating valve |
| CN107781062A (en) * | 2017-09-28 | 2018-03-09 | 北京理工大学 | A kind of Double pulse solid rocket motor interstage sealing structure device |
| CN111022217A (en) * | 2019-11-01 | 2020-04-17 | 湖北三江航天红林探控有限公司 | Interstage isolation and conduction device for double-pulse igniter |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102168631B (en) | Aluminum film baffle device and pulse solid engine applying same | |
| US20030046923A1 (en) | Pintle injector rocket with expansion-deflection nozzle | |
| US10563619B2 (en) | Aerospace turbofan engines | |
| CN107529585B (en) | Melt film type partition plate suitable for multi-pulse solid rocket engine | |
| CN113417760B (en) | Solid propellant oxygen combustion split charging coupling combustion transparent window experimental device and experimental method | |
| CN111810318A (en) | Single-chamber double-thrust solid rocket engine and rocket | |
| GB2473113A (en) | Pulse detonation inlet management system | |
| CN114060854A (en) | Rotary detonation engine for concentrating detonation waves at inner side of combustion chamber | |
| CN107781062B (en) | A kind of Double pulse solid rocket motor interstage sealing structure device | |
| CN115788703A (en) | Interstage isolation device for double-pulse engine | |
| RU2727532C1 (en) | Turbojet engine | |
| CN107795408A (en) | A kind of unchoked solid rocket ramjet gas flow adjusting means | |
| CN117145655B (en) | Flexible heat-proof sealing structure for jet pipe and tail cabin of solid rocket engine | |
| US8117847B2 (en) | Hybrid missile propulsion system with reconfigurable multinozzle grid | |
| CN105784447A (en) | Pressure intensity automatically balanced condensed-phase combustion product pollution-free collecting device | |
| CN111022217B (en) | Interstage isolation and conduction device for double-pulse igniter | |
| CN112798284A (en) | Modularized solid rocket scramjet engine test platform | |
| CN111502859A (en) | Initiating explosive-free gas-solid hybrid rocket engine | |
| CN210738694U (en) | Interstage isolation device of pulse engine | |
| CN102524004B (en) | Hail suppressing and rain increasing catalyst body seeder | |
| CN114753943B (en) | Single-sided pressure-bearing double-pulse isolation device of double-pulse engine | |
| CN202005180U (en) | Body-spread catalyst spreading device for hail suppression and rain enhancement | |
| CN109707537B (en) | Light and small rocket engine structural layout | |
| CN109882315B (en) | Pulse detonation engine | |
| CN217999735U (en) | Pulse engine assembly of integral structure |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |