CN116378857A - Rocket engine simulation test device and method - Google Patents
Rocket engine simulation test device and method Download PDFInfo
- Publication number
- CN116378857A CN116378857A CN202310366914.9A CN202310366914A CN116378857A CN 116378857 A CN116378857 A CN 116378857A CN 202310366914 A CN202310366914 A CN 202310366914A CN 116378857 A CN116378857 A CN 116378857A
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- rocket engine
- simulation
- simulation test
- test device
- pressure measuring
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- 238000004088 simulation Methods 0.000 title claims abstract description 105
- 238000012360 testing method Methods 0.000 title claims abstract description 83
- 238000000034 method Methods 0.000 title description 4
- 230000000712 assembly Effects 0.000 claims abstract description 12
- 238000000429 assembly Methods 0.000 claims abstract description 12
- 239000007921 spray Substances 0.000 claims abstract description 8
- 238000010998 test method Methods 0.000 claims abstract description 8
- 239000003814 drug Substances 0.000 claims description 7
- 238000007789 sealing Methods 0.000 abstract description 20
- 238000004880 explosion Methods 0.000 abstract description 5
- 238000011161 development Methods 0.000 abstract description 4
- 239000002699 waste material Substances 0.000 abstract description 4
- 238000010304 firing Methods 0.000 description 7
- 238000010586 diagram Methods 0.000 description 6
- 238000002955 isolation Methods 0.000 description 5
- 239000007787 solid Substances 0.000 description 5
- 230000000903 blocking effect Effects 0.000 description 4
- 238000013461 design Methods 0.000 description 4
- 108010066057 cabin-1 Proteins 0.000 description 3
- 230000006835 compression Effects 0.000 description 3
- 238000007906 compression Methods 0.000 description 3
- 238000004026 adhesive bonding Methods 0.000 description 2
- 239000002775 capsule Substances 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 239000004677 Nylon Substances 0.000 description 1
- 102100033121 Transcription factor 21 Human genes 0.000 description 1
- 101710119687 Transcription factor 21 Proteins 0.000 description 1
- 239000004676 acrylonitrile butadiene styrene Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 229920001778 nylon Polymers 0.000 description 1
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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
- F02K9/96—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by specially adapted arrangements for testing or measuring
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Testing Of Engines (AREA)
Abstract
The invention relates to a rocket engine simulation test device, which comprises a simulation cabin shell and a plurality of volume blocks, wherein the volume blocks are provided with hollow channels for simulating a cavity of a rocket engine, and the hollow channels of the volume blocks are different in specification; the volume blocks are alternatively detachably mounted in the simulation cabin shell. The invention also relates to a rocket engine simulation test method based on the simulation test device. According to the invention, the igniter airtight explosion test of rocket engines with different initial cavity volumes can be realized by replacing the volume blocks with different specifications, and the rocket engine igniter airtight explosion test device has a very wide application range and a very wide cost-effectiveness ratio. In addition, when the simulation cabin, the pressure measuring end cover assembly, the sealing end cover, the interstage isolator and the simulation spray pipe are simultaneously configured, the simulation test devices with different structures can be assembled according to the combination of the simulation cabin shell and different assemblies, so that the requirements of various simulation tests of the rocket engine are met, the equipment waste condition can be greatly reduced, and the development cost of the rocket engine is reduced.
Description
Technical Field
The invention belongs to the technical field of rocket engines, and particularly relates to a rocket engine simulation test device and method.
Background
The solid rocket engine is used as a power device and is applied to various missile weapon systems in a large quantity, as shown in fig. 1, and is a double-pulse solid rocket engine, and mainly comprises an ignition device 100, an interstage isolation mechanism 200, a combustion chamber 300, a charge 400, a blocking cover 500, a spray pipe 600 and the like. The interstage isolation mechanism 200, the ignition device 100 and the blanking cover 500 need to be verified by a simulation test after the design is completed to confirm whether the design meets the use requirement, and meanwhile, the design needs to be checked and accepted by the simulation test after the production.
In general, the simulation tester used in the simulation test needs to ensure that the cavity volume is the same as the cavity volume in the real engine, so that different solid rocket engine schemes need to design different simulation testers; while also requiring different types of simulation testers to be designed for bottoming or acceptance of solid rocket engine components such as ignition device 100, interstage isolation mechanism 200, blanking cover 500, and the like.
As can be seen, the conventional simulation test apparatus lacks versatility, so that each test or each engine needs to be designed and processed with a set of simulation testers, which causes more equipment waste and increases the development cost of the engine.
Disclosure of Invention
The invention relates to a rocket engine simulation test device and a rocket engine simulation test method, which at least can solve part of defects in the prior art.
The invention relates to a rocket engine simulation test device, comprising:
a simulation pod housing;
a plurality of volumes, the volumes having hollow channels to simulate the cavities of a rocket engine, and the hollow channels of each volume being of a different specification; each volume block is alternatively detachably mounted in the simulation cabin shell.
As one embodiment, the simulated pod housing comprises a first pod segment and a second pod segment adapted for coaxial removable tandem connection; each volume block comprises a plurality of first volume blocks matched with the first cabin section and a plurality of second volume blocks matched with the second cabin section, wherein each first volume block is alternatively detachably arranged in the first cabin section, and each second volume block is alternatively detachably arranged in the second cabin section.
As one of the implementation modes, the rocket engine simulation test device further comprises a pressure measuring end cover assembly, wherein the pressure measuring end cover assembly comprises a pressure measuring end cover suitable for being connected with the end part of the simulation cabin shell, a pressure measuring unit arranged on the pressure measuring end cover and an ignition medicine bag arranged on the inner side of the pressure measuring end cover.
As one embodiment, the rocket engine simulation test device further comprises a sealing end cover and a simulation spray pipe for simulating the spray pipe of the rocket engine, wherein the sealing end cover and the simulation spray pipe are alternatively arranged at the other end of the simulation cabin shell.
As one embodiment, the rocket engine simulation test device further comprises an interstage isolator; the analog tank housing includes first and second tank sections in coaxial removable series, the interstage isolator being configured to be sandwiched between the first and second tank sections.
As one embodiment, the pressure measuring end cap assemblies are respectively installed at two ends of the simulation cabin shell.
The invention also relates to a rocket engine simulation test method, which is implemented based on the rocket engine simulation test device, and the igniter closed burst test of the rocket engine with different initial cavity volumes is performed by replacing the volume blocks with different specifications.
As one embodiment, the end cap of the simulated pod housing remote from the firing end is replaced with a simulated nozzle for blanking and acceptance testing.
As one embodiment, the rocket engine simulation test device further comprises an interstage isolator; the analog tank housing includes first and second tank sections in coaxial removable series, the interstage isolator being configured to be sandwiched between the first and second tank sections.
As one of the implementation modes, the two ends of the simulation cabin shell are respectively provided with a pressure measuring end cover assembly so as to carry out the bottom touching and acceptance test of the interstage isolator; the pressure measuring end cover assembly comprises a pressure measuring end cover, a pressure measuring unit and an ignition medicine bag, wherein the pressure measuring end cover is suitable for being connected with the end part of the analog cabin shell, the pressure measuring unit is arranged on the pressure measuring end cover, and the ignition medicine bag is arranged on the inner side of the pressure measuring end cover.
The invention has at least the following beneficial effects:
according to the invention, the simulated cabin is formed by combining the simulated cabin shell and the volume block, the igniter closed explosion test of the rocket engine with different initial cavity volumes can be realized by replacing the volume blocks with different specifications, the method has the advantages of extremely wide application range, less required equipment quantity, low cost and higher efficiency and cost ratio.
According to the invention, when the rocket engine simulation test device is simultaneously provided with the simulation cabin, the pressure measuring end cover assembly, the sealing end cover, the interstage isolator and the simulation spray pipe, the rocket engine simulation test device with different structures can be assembled according to the combination of the simulation cabin shell and different assemblies, so that the requirements of various simulation tests of the rocket engine are met, the equipment waste condition can be greatly reduced, and the development cost of the rocket engine is reduced.
Drawings
In order to more clearly illustrate the embodiments of the invention or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, it being obvious that the drawings in the following description are only some embodiments of the invention, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic diagram of a solid rocket engine provided in the background art;
FIG. 2 is a schematic structural diagram of a simulation pod according to an embodiment of the present invention;
FIG. 3 is a schematic view of a pressure end cap assembly according to an embodiment of the present invention;
fig. 4 is a schematic structural diagram of a seal end cap according to an embodiment of the present invention;
FIG. 5 is a schematic structural diagram of a simulated nozzle according to an embodiment of the present invention;
FIG. 6 is a schematic diagram of an interstage separator according to an embodiment of the present invention;
FIGS. 7 and 8 are schematic structural diagrams of a rocket engine simulation test device for performing an igniter seal burst test;
FIG. 9 is a schematic view of a rocket engine simulation test device in performing a blanking cover bottoming and acceptance test;
fig. 10 is a schematic view of a rocket motor simulation test device in the case of performing a bottoming and acceptance test of an interstage separator.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely, and it is apparent that the described embodiments are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
Example 1
Referring to fig. 2 and fig. 7 to fig. 10, an embodiment of the present invention provides a rocket engine simulation test device, including:
a simulation pod housing;
a plurality of volumes, the volumes having hollow channels to simulate the cavities of a rocket engine, and the hollow channels of each volume being of a different specification; each volume block is alternatively detachably mounted in the simulation cabin shell.
The volume block comprises but is not limited to an Acrylonitrile Butadiene Styrene (ABS) material or a nylon material, and has the advantages of meeting the requirements of simulation tests, along with low cost and the like.
The volume block can be tightly embedded in the simulation cabin shell, so that the stability of the position of the volume block in a simulation test is ensured, and the accuracy and the reliability of a test result are ensured. The two ends of the simulation cabin shell are preferably provided with limiting rings respectively for limiting the axial movement of the volume block.
The simulation pod housing and the volume block form a simulation pod 1.
In one embodiment, as shown in fig. 2, the hollow passage employs a tapered section in a direction from the outside to the inside near the firing end of the simulated capsule shell, and the ignition charge 22 disposed at the firing end of the simulated capsule shell is preferably disposed within the tapered section. Further, the tail end of the tapered cavity section is sequentially connected with the constant-section cavity section and the gradually-expanding cavity section, and the mode can better simulate the airtight burst test of the igniter.
In one embodiment, as shown in fig. 2, the simulated pod housing comprises a first pod segment 11 and a second pod segment 13 adapted to be removably connected in series coaxially; each of the blocks comprises a plurality of first blocks 12 matched with the first cabin section 11 and a plurality of second blocks 14 matched with the second cabin section 13, wherein each first block 12 is alternatively detachably arranged in the first cabin section 11, and each second block 14 is alternatively detachably arranged in the second cabin section 13.
Wherein the first and second segments 11, 13 may be of the same or different lengths, and preferably the cross-sectional shape and size of the two are the same. The first cabin section 11 and the second cabin section 13 are preferably in flange connection, and sealing treatment can be carried out between the first cabin section 11 and the second cabin section by clamping a sealing ring and the like.
Preferably, the first cabin section 11 and the second cabin section 13 can be used for the igniter sealing burst test of the rocket engine separately, and the combination of the first cabin section 11 and the second cabin section can also be used for the igniter sealing burst test of the rocket engine. In one embodimentThe first compartment 11 may be used for an initial cavity volume of 100cm 3 ～1000cm 3 An igniter airtight burst test of the rocket engine; the second compartment 13 may be used for an initial cavity volume of 900cm 3 ～2000cm 3 An igniter airtight burst test of the rocket engine; when the first cabin section 11 is combined with the second cabin section 13, the initial cavity volume is 1000cm 3 ～3000cm 3 The igniter of the rocket engine is subjected to airtight burst test. It can be seen that based on the above scheme, an initial cavity volume of 100cm can be achieved 3 ～3000cm 3 The igniter sealing explosion test of the rocket engine has a very wide application range.
In performing simulation tests, the ends of the simulation pod housing typically need to be closed. Defining one end of the simulated pod housing as the firing end and the other as the closed end, the firing end is required to be provided with a firing cartridge 22.
The rocket engine simulation test device further comprises a sealing end cover 3, wherein the sealing end cover 3 mainly serves to seal the end of the simulation cabin shell, and is suitable for being detachably connected with the simulation cabin shell, including but not limited to flange connection and the like.
In one embodiment, as shown in fig. 3, the rocket engine simulation test device further comprises a pressure testing end cap assembly 2, wherein the pressure testing end cap assembly 2 comprises a pressure testing end cap 21 which is suitable for being connected with the end of the simulation cabin shell, a pressure testing unit arranged on the pressure testing end cap 21 and an ignition medicine bag 22 arranged on the inner side of the pressure testing end cap 21.
The pressure end cap 21 is preferably removably attached to the analog pod housing, including but not limited to, by way of a flange connection or the like.
Preferably, as shown in fig. 3, the pressure measuring unit includes a pressure sensor 23 and a pressure measuring adapter 24, where the pressure measuring adapter 24 is connected to the pressure measuring end cover 21, including but not limited to a threaded connection, and the pressure sensor 23 is mounted on the pressure measuring adapter 24.
Preferably, as shown in fig. 3, a wire through hole is provided on the pressure measuring end cover 21, the wire through hole is preferably a stepped hole, a sealing plug 25 is filled in the outer large hole, and a compression bolt 26 is further screwed on the outer hole of the wire through hole to fully press and tightly seal the sealing plug 25; the sealing plug 25 and the compression bolt 26 are respectively provided with a wiring hole, and the lead wires on the ignition medicine bag 22 sequentially pass through the wiring holes on the sealing plug 25 and the wiring holes on the compression bolt 26.
In one embodiment, as shown in fig. 5, the rocket engine simulation test device further comprises a simulation nozzle 4 for simulating the nozzle of the rocket engine. Preferably, as shown in fig. 5, the simulated nozzle 4 includes a base cover 41, a nozzle body 42 formed on the base cover 41, and a blocking cover 43 disposed in the nozzle body 42, wherein the nozzle body 42 is preferably integrally formed with the base cover 41, the nozzle body 42 has a converging section and an expanding section, the blocking cover 43 is fixed on the converging section (including but not limited to fixing means such as glue bonding), and a conical ring 44 is fixed in the expanding section (including but not limited to fixing means such as glue bonding), and the conical ring 44 abuts against an outer shoulder of the blocking cover 43.
The rocket engine simulation test device is preferably provided with the seal cover 3 and the simulation nozzle 4 at the same time, wherein the seal cover 3 and the simulation nozzle 4 are alternatively arranged at the other end (i.e. the closed end) of the simulation cabin shell. When the sealing end cover 3 is arranged at the closed end of the simulated cabin shell, an igniter sealing burst test of the rocket engine can be performed; when the simulated spout 4 is installed at the closed end of the simulated pod housing, a blanking over bottoming and acceptance test may be performed. Therefore, different simulation tests of the rocket engine can be carried out only by replacing different end covers at the closed end, and the universality and the flexibility are higher.
In one embodiment, as shown in FIG. 6, the rocket engine simulation test device further comprises an interstage isolator 5; the simulated cabin shell comprises a first cabin section 11 and a second cabin section 13 which are connected in series in a coaxial and detachable manner, and the interstage isolator 5 is configured and adapted to be sandwiched between the first cabin section 11 and the second cabin section 13.
Preferably, the inter-stage separator 5 includes a connecting ring 51 and an isolating mechanism 52, the isolating mechanism 52 is mounted on the connecting ring 51 and seals an inner ring of the connecting ring 51, the mounting manner includes but is not limited to screw/bolt fixing, for example, screw holes are formed around the inner ring of the connecting ring 51, screw holes are formed around the edge of the isolating mechanism 52, the number of screw holes on the connecting ring 51 and the isolating mechanism 52 is the same and distributed in a one-to-one correspondence manner, and then the isolating mechanism 52 can be fixed on the connecting ring 51 through a plurality of screws; the outer ring of the connecting ring 51 is provided with a connecting structure for connection with the first and second tank sections 11, 13, for example, the outer ring of the connecting ring 51 is of a flange ring structure, and the first tank section 11, the connecting ring 51 and the second tank section 13 are flange-assembled.
By configuring the interstage isolator 5, a bottoming and acceptance test of the isolation mechanism 52 of the rocket motor can be achieved. Wherein preferably an end cap at the closed end of the analog pod housing has a pressure sensing function, such as a pressure cell provided on the side end cap; preferably, as shown in fig. 10, the pressure measuring end cover assemblies 2 are respectively installed at two ends of the analog cabin shell, so that an additional configuration of an end cover is not needed, the number of required equipment can be reduced, the pressure measuring end cover assemblies 2 with closed ends can be reused, and the pressure measuring end cover assemblies 2 can be installed to the ignition end of the analog cabin shell for use after the isolation mechanism 52 is used for bottoming and acceptance test.
In this embodiment, preferably, the rocket engine simulation test device is configured with the pressure measuring end cover assembly 2, the sealing end cover 3, the inter-stage isolator 5 and the simulation spray pipe 4, and according to the combination of the simulation cabin shell and different assemblies, the rocket engine simulation test device can be assembled into simulation test devices with different structures, thereby meeting the requirements of various simulation tests of the rocket engine, greatly reducing the equipment waste condition and reducing the development cost of the rocket engine.
Example two
The embodiment of the invention provides a rocket engine simulation test method, which is implemented based on the rocket engine simulation test device.
The igniter sealing explosion test of rocket engines with different initial cavity volumes is carried out by replacing the volume blocks with different specifications.
As shown in fig. 7 and 8, the combined structure of the pressure measuring end cover assembly 2+ the simulation cabin 1+ the seal end cover 3 is preferably adopted in the igniter sealing burst test.
In one embodiment, the end cap of the simulated pod housing remote from the firing end is replaced with a simulated nozzle 4 for blanking over and acceptance testing. In this scenario, as shown in fig. 9, a combined structure of the pressure cap assembly 2+ analog cabin 1+ analog nozzle 4 is employed.
Further, as shown in fig. 10, for the case of configuring the inter-stage separator 5, the pressure measuring end cap assemblies 2 are respectively installed at both ends of the simulation cabin shell to perform the bottom touching and acceptance test of the inter-stage separator 5, that is, the combined structure of the pressure measuring end cap assemblies 2+the simulation cabin 1+the pressure measuring end cap assemblies 2 is adopted.
The foregoing description of the preferred embodiments of the invention is not intended to be limiting, but rather is intended to cover all modifications, equivalents, alternatives, and improvements that fall within the spirit and scope of the invention.
Claims (10)
1. A rocket engine simulation test device, comprising:
a simulation pod housing;
a plurality of volumes, the volumes having hollow channels to simulate the cavities of a rocket engine, and the hollow channels of each volume being of a different specification; each volume block is alternatively detachably mounted in the simulation cabin shell.
2. A rocket engine simulation test device according to claim 1, wherein: the simulation cabin shell comprises a first cabin section and a second cabin section which are suitable for coaxial, detachable and serial connection; each volume block comprises a plurality of first volume blocks matched with the first cabin section and a plurality of second volume blocks matched with the second cabin section, wherein each first volume block is alternatively detachably arranged in the first cabin section, and each second volume block is alternatively detachably arranged in the second cabin section.
3. A rocket engine simulation test device according to claim 1 and further comprising a pressure cap assembly, said pressure cap assembly comprising a pressure cap adapted to be connected to a simulation pod housing end, a pressure cell disposed on said pressure cap and an ignition charge disposed inside said pressure cap.
4. A rocket engine simulation test device according to claim 3, further comprising a seal cap and a simulation nozzle for simulating a nozzle of a rocket engine, wherein said seal cap and said simulation nozzle are alternatively mounted at the other end of said simulation pod.
5. A rocket engine simulation test device according to claim 3 wherein: also comprises an interstage isolator; the analog tank housing includes first and second tank sections in coaxial removable series, the interstage isolator being configured to be sandwiched between the first and second tank sections.
6. A rocket engine simulation test device according to claim 5, wherein: and the two ends of the simulation cabin shell are respectively provided with the pressure measuring end cover assemblies.
7. A rocket engine simulation test method, which is characterized in that the rocket engine simulation test device is implemented based on the rocket engine simulation test device of claim 1 or 2, and igniter closed burst tests of rocket engines with different initial cavity volumes are performed by replacing volume blocks with different specifications.
8. A rocket engine simulation test method according to claim 7, wherein: and replacing the end cover of the simulated cabin shell, which is far away from the ignition end, with a simulated spray pipe so as to perform plugging cover bottoming and acceptance test.
9. A rocket engine simulation test method according to claim 7, wherein: the rocket engine simulation test device also comprises an interstage isolator; the analog tank housing includes first and second tank sections in coaxial removable series, the interstage isolator being configured to be sandwiched between the first and second tank sections.
10. A rocket engine simulation test method according to claim 9, wherein: respectively installing pressure measuring end cover assemblies at two ends of the simulation cabin shell to perform bottoming and acceptance test of the interstage isolator; the pressure measuring end cover assembly comprises a pressure measuring end cover, a pressure measuring unit and an ignition medicine bag, wherein the pressure measuring end cover is suitable for being connected with the end part of the analog cabin shell, the pressure measuring unit is arranged on the pressure measuring end cover, and the ignition medicine bag is arranged on the inner side of the pressure measuring end cover.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310366914.9A CN116378857A (en) | 2023-04-07 | 2023-04-07 | Rocket engine simulation test device and method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310366914.9A CN116378857A (en) | 2023-04-07 | 2023-04-07 | Rocket engine simulation test device and method |
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| Publication Number | Publication Date |
|---|---|
| CN116378857A true CN116378857A (en) | 2023-07-04 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310366914.9A Pending CN116378857A (en) | 2023-04-07 | 2023-04-07 | Rocket engine simulation test device and method |
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| Country | Link |
|---|---|
| CN (1) | CN116378857A (en) |
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2023
- 2023-04-07 CN CN202310366914.9A patent/CN116378857A/en active Pending
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