CN210049972U - Rocket liquid propellant conveying system and conveying pipe assembly - Google Patents
Rocket liquid propellant conveying system and conveying pipe assembly Download PDFInfo
- Publication number
- CN210049972U CN210049972U CN201920883236.2U CN201920883236U CN210049972U CN 210049972 U CN210049972 U CN 210049972U CN 201920883236 U CN201920883236 U CN 201920883236U CN 210049972 U CN210049972 U CN 210049972U
- Authority
- CN
- China
- Prior art keywords
- flange
- tunnel
- assembly
- main body
- liquid propellant
- 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.)
- Active
Links
Images
Landscapes
- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
The utility model discloses a rocket liquid propellant conveying system and transmission pipe subassembly, the mutual detachable connection through the flange between the transmission pipe subassembly in this transmission subassembly, tunnel pipe subassembly and the outside connects the subassembly, each part that forms each subassembly can weld the equipment alone, though each subassembly also is the welding assembly body, its welding operation can all be carried out alone, do not need to go on in the assembly process from top to bottom again, operating space is good, the welding position is convenient, thereby can guarantee the quality of welding seam well, reduce the appearance of welding defect; then each subassembly rethread corresponding flange is gone on detachably and is connected, can be so that with the relative detachable connection between the first storage tank and the second storage tank that above each part is connected, two storage tanks can be decomposed as required, realize that the storage tank is removable, guarantee that single storage tank has good maintainability, reduce the storage tank cost of maintenance, satisfy low-cost repeatedly usable's requirement.
Description
Technical Field
The utility model relates to a rocket liquid transmission pipeline technical field, in particular to rocket liquid propellant conveying system and transmission pipe subassembly.
Background
Rocket fuel propellant is usually stored in a fuel propellant container, and in the case of liquid propellant, the inner cavity of the fuel propellant container is transported to a corresponding position through a pipeline to be ejected from a rocket engine in a large amount in the form of fluid jet, so as to generate thrust propulsion. The fuel propellant tends to combust with the oxidizer to produce a large quantity of gas which expands and is ejected from the nozzle, increasingly accelerates, and rushes out of the bottom of the rocket to produce thrust to bring the rocket to extremely high velocities.
The fuel propellant and the oxidizer are stored separately from the inside of the container, and in the case of liquid propellants, the oxidizer is also in the liquid state, and the fuel propellant container and the oxidizer storage container are usually arranged one above the other, and the discharge line of the fuel propellant container needs to pass through the inside of the oxidizer storage container to achieve the transport of the fuel propellant.
Referring to fig. 1, fig. 1 is a schematic structural diagram of a tunnel tube and a delivery tube forming assembly for delivering propellant in the prior art.
The tunnel pipe and the conveying pipe are combined to form a common conveying channel for fuel propellant in the liquid rocket storage tank, and the liquid rocket storage tank has the advantages of small occupied space, reduction of the protrusions outside the rocket due to the fact that the tunnel pipe and the conveying pipe can be arranged in the storage tank, and the rocket body can keep a good aerodynamic shape. The combination of the tunnel pipe and the delivery pipe is widely applied to the development and production of liquid rocket storage tanks of various countries, and the classic rocket models including Chinese long standing rocket series, American Deltar/Dalishen series, SpaceX falcon series, Soviet Union number/proton number series, European Alian series and the like all adopt a tunnel pipe/delivery pipe combination scheme.
The tunnel pipe/conveying pipe combination mode in the existing rocket mainly adopts a tailor welding mode for connection, and the components of the tunnel pipe/conveying pipe combination mode are shown in a figure 1, wherein a tunnel pipe 1 ', a corrugated pipe 2', a switching section 3 'and a lower storage box 9' are welded into a whole in the lower storage box assembling process; after the upper and lower storage boxes are assembled, the conveying pipe 10 'penetrates through the tunnel pipe and then is assembled with the switching section 3' through welding; then, the conveying pipe 10 'and the first adapter flange 4' are welded and assembled to form an installation flange seat outwards arranged on the bottom of the ellipsoid of the lower storage box; and finally, fixing the bolts 7 'and the nuts 8' to realize the fixation of the first adapter flange 4 'and the second adapter flange 5', and finishing the combined assembly of the tunnel pipe/conveying pipe.
The existing combination mode has the defects in the aspects of processing technology and performance, and specifically comprises the following steps:
1) excessive welding operation exists in the process of assembling the upper storage box and the lower storage box, and the welding quality is uncertain due to difficult positioning due to space limitation;
2) because tunnel pipe and conveyer pipe pass through welding combination assembly, lead to upper and lower two storages to become whole inseparable, to the memory that needs used repeatedly, in case the conveyer pipe or other positions of storage box appear the problem and probably will split the storage, cause cost of maintenance higher, do not accord with low-cost used repeatedly's requirement.
Therefore, how to overcome the above-mentioned defects in the prior art is a technical problem to be solved by those skilled in the art.
SUMMERY OF THE UTILITY MODEL
The utility model provides a rocket liquid propellant transmission pipe assembly, including delivery pipe subassembly, tunnel pipe subassembly and outside extension pipe subassembly, the delivery pipe subassembly includes the delivery pipe main part, the tunnel pipe subassembly includes the tunnel pipe main part, outside extension pipe subassembly includes the extension pipe main part, the end that the extension pipe main part is towards the delivery pipe main part is provided with the flange, the periphery wall of the extension pipe main part still is provided with flange; the conveying pipe main body and the tunnel pipe main body are coaxially arranged, at least part of pipe sections of the conveying pipe main body are sleeved in an inner cavity of the tunnel pipe main body, and a first flange is arranged at the outer end part of the conveying pipe main body and is used for being matched and connected with the joint flange; and the outer end part of the tunnel pipe main body is provided with a second flange which is used for being fixed with the connecting flange.
From the above description, the utility model discloses the outer tip of well conveyer pipe main part and the takeover main part pass through first flange detachable connection, the outer tip of tunnel pipe main part and the takeover main part also pass through second flange detachable connection, thereby realize with conveyer pipe subassembly, tunnel pipe subassembly and outside take over the mutual dismantlement between the subassembly, each subassembly can weld the equipment alone like this, though each subassembly also is the welding assembly body, its welding operation can all be carried out alone, do not need to go on in the assembly process from top to bottom again, operating space is good, welding position is convenient, thereby can guarantee the quality of welding seam well, reduce welding defect's appearance; then each subassembly rethread corresponding flange is gone on detachably and is connected, can be so that with the relative detachable connection between the first storage tank and the second storage tank that above each part is connected, two storage tanks can be decomposed as required, realize that the storage tank is removable, guarantee that single storage tank has good maintainability, reduce the storage tank cost of maintenance, satisfy low-cost repeatedly usable's requirement.
Optionally, the flange structure further comprises a middle adapter flange, and two ends of the middle adapter flange are both flange structures and are respectively connected with the second flange and the connecting flange in a matched manner.
Optionally, from inside to outside, middle adapter flange includes interconnect's major diameter section and toper section in proper order, the diameter of toper section reduces from inside to outside gradually, the minimum internal diameter of toper section is greater than the external diameter of takeover main part, the port position of major diameter section the port position of toper section set up respectively with the second flange the flange structure that flange cooperation is connected.
Optionally, the intermediate adapter flange is of a split structure and at least comprises two arc-shaped sections along the circumferential direction, all the arc-shaped sections are spliced and combined to form an integral flange, and two adjacent arc-shaped sections are detachably connected.
Optionally, the intermediate transfer flange includes first arc flange and second arc flange, first arc flange and second arc flange enclose to close and form whole flange, first arc flange with the terminal surface that second arc flange meets all is provided with the mounting panel of inside radial extension, and the mounting panel of the two passes through bolt or fix with screw.
Optionally, the inner diameters of the adapter body and the adapter flange are the same, the adapter body and the adapter flange are circumferentially sealed and fixed by welding, and the adapter flange is located on the large-diameter section of the intermediate adapter flange.
Optionally, the tunnel pipe assembly further includes a corrugated pipe coaxially disposed with the tunnel pipe main body, the corrugated pipe is welded to an inner end portion of the tunnel pipe main body, and an outer end portion of the conveying pipe main body is inserted into the tunnel pipe main body through the corrugated pipe.
Optionally, the outer peripheral wall of the tunnel pipe main body is fixed with the bottom of the ellipsoid of the annular storage tank in a sealing mode.
Optionally, the conveying pipe main body and the first flange are circumferentially sealed and fixed by welding
In addition, the utility model provides a rocket liquid propellant conveying system, including first tank and second tank, be used for splendid attire liquid fuel and oxidizer respectively, its characterized in that, the liquid outlet of first tank passes through rocket liquid propellant transfer pipe subassembly through any one of the aforesaid second tank is in order to communicate the combustion chamber.
The utility model discloses a rocket liquid propellant conveying system has above-mentioned rocket liquid propellant transfer line subassembly, so this conveying system also has the above-mentioned technological effect of rocket liquid propellant transfer line subassembly.
Drawings
FIG. 1 is a schematic structural view of a prior art tunnel tube and delivery tube forming assembly for delivering propellant;
FIG. 2 is a schematic view of a rocket propellant transfer tube assembly according to the present invention;
fig. 3 is a schematic structural view of a tunnel tube assembly according to an embodiment of the present invention;
FIG. 4 is a left side view of FIG. 3;
FIG. 5 is a cross-sectional view taken along line M-M of FIG. 4;
FIG. 6 is a schematic structural view of a spout assembly according to an embodiment of the present invention;
fig. 7 is a schematic structural view of an external pipe connecting assembly according to an embodiment of the present invention;
FIG. 8 is a cross-sectional view of FIG. 7;
fig. 9 is a cross-sectional view of an intermediate transfer flange according to an embodiment of the present invention;
fig. 10 is a three-dimensional schematic view of an intermediate transfer flange according to an embodiment of the present invention.
Wherein, in fig. 1:
1' -a tunnel tube; 2' -a bellows; 3' -a transition section; 4' -a first adaptor flange; 5' -a second adaptor flange; 7' -bolt; 8' -a nut; 9' -lower storage box; 10' -a delivery tube;
wherein, in fig. 2 to 10:
1-a tunnel tube assembly; 11-a tunnel tube body; 12-a second flange; 13-a bellows; 14-tunnel pipe transition section;
2-a delivery tube assembly; 21-a delivery tube body; 22-a first flange;
3-external connecting pipe component; 31-a nozzle body; 32-a joint flange; 33-a connecting flange;
4-intermediate adapter flange; 41-large diameter section; 42-a conical section; 43-minor diameter flange; 44-large diameter flange; 45-mounting a plate; 45 a-mounting holes;
5-bolt;
100-external piping;
200-ring storage box ellipsoid bottom.
Detailed Description
In view of the technical shortcomings of prior art rocket liquid propellant transfer tube assemblies, a great deal of research has been conducted and a technical solution to the above technical shortcomings has been proposed.
In order to make those skilled in the art better understand the technical solution of the present invention, the present invention will be further described in detail with reference to the accompanying drawings and specific embodiments.
Referring to fig. 2 to 10, fig. 2 is a schematic structural view of a rocket liquid propellant transfer tube assembly according to the present invention; fig. 3 is a schematic structural view of a tunnel tube assembly according to an embodiment of the present invention; FIG. 4 is a left side view of FIG. 3; FIG. 5 is a cross-sectional view taken along line M-M of FIG. 4; 6 is a schematic structural view of the delivery tube assembly in an embodiment of the present invention; fig. 7 is a schematic structural view of an external pipe connecting assembly according to an embodiment of the present invention; fig. 8 is a cross-sectional view of fig. 7.
The utility model provides a rocket liquid propellant conveying system, this conveying system include duct assembly 2, mainly used carry the required liquid fuel of rocket propulsion or oxidant. The conveying system comprises a first storage tank and a second storage tank, wherein liquid fuel and oxidant are respectively stored in the first storage tank and the second storage tank, the inner cavities of the first storage tank and the second storage tank are mutually isolated and communicated with a combustion chamber of the rocket through corresponding conveying pipes, so that the liquid fuel and the oxidant are mixed and combusted to generate power.
Wherein in order to keep the piping as small as possible, not protruding outside the tanks, it is usual to arrange that a part of the pipe section of the conveyor pipe assembly 2 of one of the tanks passes through the inside of the other tank. The present document continues by taking the example of the first tank's transfer pipe assembly 2 partially passing inside the second tank.
In one embodiment the first tank is located above the second tank, and the liquid outlet of the first tank is passed through the second tank by a rocket liquid propellant transfer tube assembly to communicate with the combustion chamber. I.e. the surface of the first reservoir has a liquid outlet at which the duct assembly 2 is mounted, and liquid fuel within the first reservoir can flow along the duct assembly 2 through the second reservoir and on to the combustion chamber of the rocket.
The utility model provides a delivery pipe assembly 2 includes delivery pipe assembly 2, tunnel pipe subassembly 1 and outside extension pipe subassembly 3. The duct assembly 2 comprises a duct body 21, the tunnel tube assembly 1 comprises a tunnel tube body 11, and the outer nozzle assembly 3 comprises a nozzle body 31. The conveying pipe body 21, the tunnel pipe body 11 and the adapter pipe body 31 are generally aluminum alloy pipes, but may be pipe fittings made of other materials as long as the use requirements are met.
The conveying pipe main body 21 is coaxially arranged with the tunnel pipe main body, and at least part of the pipe section of the conveying pipe main body 21 is sleeved inside the tunnel pipe main body 11. The delivery pipe body 21 has an inner end communicating with the first tank and an outer end passing through the second tank to be connected to an external pipe 100 located outside the second tank.
The outer end of the delivery pipe body 21 has a first flange 22 for mating connection with a coupling flange 32, which coupling flange 32 is arranged at the end of the adapter body 31 facing the delivery pipe body 21. The outer end of the tunnel pipe body 11 is further provided with a second flange 12 for fixation with a connection flange 33. The connection flange 33 is provided to the outer circumferential wall of the nipple body 31.
From the above description, the outer end of the middle conveying pipe body 21 of the present invention is detachably connected to the connecting pipe body 31 through the first flange 22, and the outer end of the tunnel pipe body 11 is also detachably connected to the connecting pipe body 31 through the second flange 12, so as to achieve the mutual detachment between the conveying pipe assembly 2, the tunnel pipe assembly 1 and the external connecting pipe assembly 3, so that each assembly can be independently welded and assembled, although each assembly is also a welded assembly, the welding operation can be independently performed, and the assembly process does not need to be performed in the up-down assembly process, the operation space is good, the welding positioning is convenient, so that the quality of the welding seam can be well ensured, and the occurrence of welding defects can be reduced; then each subassembly rethread corresponding flange is gone on detachably and is connected, can be so that with the relative detachable connection between the first storage tank and the second storage tank that above each part is connected, two storage tanks can be decomposed as required, realize that the storage tank is removable, guarantee that single storage tank has good maintainability, reduce the storage tank cost of maintenance, satisfy low-cost repeatedly usable's requirement.
Referring to fig. 9 and 10, fig. 9 is a cross-sectional view of an intermediate adapter flange 4 according to an embodiment of the present invention; fig. 10 is a three-dimensional schematic view of an intermediate adapter flange 4 according to an embodiment of the present invention.
In one embodiment, the rocket liquid propellant transfer pipe assembly may further include an intermediate adapter flange 4, and both ends of the intermediate adapter flange 4 are of flange structures and are respectively connected with the second flange 12 and the connecting flange 33 in a matching manner. That is, the tunnel pipe body 11 and the nozzle body 31 are detachably connected by the intermediate adapter flange 4. As shown in the figure, the flanges at the two ends of the intermediate adapter flange 4 are respectively defined as a large-diameter flange 44 and a small-diameter flange 43, the large-diameter flange 44 is connected with the second flange 12 in a matching way, the small-diameter flange 43 is connected with the connecting flange 33 in a matching way, and the two flanges can be fixedly connected through bolts 5.
The tunnel pipe main body 11 is connected with the adapter main body 31 through the intermediate adapter flange 4, so that the use strength of the whole pipe fitting can be improved, and the shape of the intermediate adapter flange 4 can be designed according to the actual application environment so as to facilitate connection.
Normally, the diameter of the tunnel pipe body 11 is larger than that of the adapter pipe body 31, and therefore, in order to achieve connection reliability, the following arrangement is also possible.
In the above embodiments, from inside to outside, the intermediate adapter flange 4 sequentially includes the large-diameter section 41 and the tapered section 42 that are connected to each other, the diameter of the tapered section 42 gradually decreases from inside to outside, the minimum inner diameter of the tapered section 42 is greater than the outer diameter of the adapter tube main body 31, and the port positions of the large-diameter section 41 and the tapered section 42 are respectively provided with flange structures that are connected to the second flange 12 and the connecting flange 33 in a matching manner.
Specifically, the inner diameter of the large diameter section 41 may be substantially the same as the tunnel pipe body 11, and the minimum pipe diameter of the outer end of the tapered section 42 may be substantially the same as the nozzle body 31.
The middle adapter flange 4 is designed into a non-uniform diameter form, so that the pipe section is conveniently connected, and the use strength of the pipe assembly is improved.
In order to facilitate the installation of the intermediate adapter flange 4, in the above embodiments, the intermediate adapter flange 4 may be a split structure, and at least includes two arc-shaped sections along the circumferential direction, all the arc-shaped sections are spliced and combined to form an integral flange, and two adjacent arc-shaped sections are detachably connected.
That is, the intermediate adapter flange 4 may include two arcuate segments, or may include three or more segments. The preferred mode of this paper is that middle adapter flange 4 is two arc sections, and middle adapter flange 4 includes first arc flange and second arc flange, and first arc flange and second arc flange enclose to close and form whole flange, and the terminal surface that first arc flange and second arc flange meet all is provided with the inside mounting panel 45 that radially extends, and the mounting panel 45 of the two passes through bolt or fix with screw.
Two or more mounting holes 45a may be provided in the mounting plate, and bolts may be passed through the mounting holes 45a to fixedly connect the adjacent two arc-shaped segments.
In the above embodiments, the inner diameters of the joint flange 32 and the nozzle body 31 may be the same, and they are fixed by welding and circumferential sealing, and the joint flange 32 is located on the large diameter section 41 of the intermediate adapter flange 4.
In the above embodiments, in order to improve the assembling accuracy, the tunnel pipe assembly 1 may further include the bellows 13 disposed coaxially with the tunnel pipe body 11, the bellows 13 being welded to the inner end portion of the tunnel pipe body 11, and the outer end portion of the transport pipe body 21 being inserted into the interior of the tunnel pipe body 11 through the bellows 13.
The bellows 13 may provide a certain amount of vibration compensation during rocket flight.
Furthermore, the outer peripheral wall of the tunnel tube body 11 is hermetically fixed to the annular reservoir ellipsoidal bottom 200 by welding.
The utility model provides a rocket liquid propellant transfer line subassembly can be according to following order when assembling:
welding a conveying pipe main body 21 and a first flange 22 to form a conveying pipe assembly 2, welding a tunnel pipe main body 11, a corrugated pipe 13 and a tunnel pipe adapter section 14 with a second flange 12 to form a tunnel pipe assembly 1, and welding a connecting pipe main body 31 and a joint flange 32 to form an external connecting pipe assembly 3;
placing the conveyor pipe assembly 2 inside the tunnel pipe assembly 1;
the first flange 22 and the joint flange 32 are connected by detachable parts such as bolts, pins or screws, the intermediate adapter flange 4 is installed, and the flange structures at the two ends of the intermediate adapter flange 4 are fixedly connected with the second flange 12 and the connecting flange 33 in the external connecting pipe component 3 respectively.
The utility model discloses a rocket liquid propellant conveying system has above-mentioned rocket liquid propellant transfer line subassembly, so this conveying system also has the above-mentioned technological effect of rocket liquid propellant transfer line subassembly.
The rocket liquid propellant conveying system and the conveying pipe assembly provided by the utility model are introduced in detail above. The principles and embodiments of the present invention have been explained herein using specific examples, and the above descriptions of the embodiments are only used to help understand the method and its core ideas of the present invention. It should be noted that, for those skilled in the art, without departing from the principle of the present invention, the present invention can be further modified and modified, and such modifications and modifications also fall within the protection scope of the appended claims.
Claims (10)
1. A rocket liquid propellant conveying pipe assembly is characterized by comprising a conveying pipe assembly (2), a tunnel pipe assembly (1) and an external connecting pipe assembly (3), wherein the conveying pipe assembly (2) comprises a conveying pipe main body (21), the tunnel pipe assembly (1) comprises a tunnel pipe main body (11), the external connecting pipe assembly (3) comprises a connecting pipe main body (31), a connecting flange (32) is arranged at the end part, facing the conveying pipe main body (21), of the connecting pipe main body (31), and a connecting flange (33) is further arranged on the outer peripheral wall of the connecting pipe main body (31); the conveying pipe main body (21) and the tunnel pipe main body (11) are coaxially arranged, at least part of pipe sections of the conveying pipe main body (21) are sleeved in an inner cavity of the tunnel pipe main body (11), and the outer end part of the conveying pipe main body (21) is provided with a first flange (22) which is used for being matched and connected with the joint flange (32); the outer end of the tunnel pipe body (11) is provided with a second flange (12) for fixing with the connecting flange (33).
2. A rocket liquid propellant transfer tube assembly as recited in claim 1, further comprising an intermediate adaptor flange (4), both ends of said intermediate adaptor flange (4) being of flange construction for mating connection with said second flange (12) and said attachment flange (33), respectively.
3. A rocket liquid propellant transfer tube assembly as recited in claim 2, wherein said intermediate adapter flange (4) comprises a large diameter section (41) and a tapered section (42) connected to each other in sequence from inside to outside, the diameter of said tapered section (42) is gradually reduced from inside to outside, the minimum inner diameter of said tapered section (42) is larger than the outer diameter of said nozzle body (31), and the port position of said large diameter section (41) and the port position of said tapered section (42) are respectively provided with a flange structure for being matched and connected with said second flange (12) and said connecting flange (33).
4. A rocket liquid propellant transfer tube assembly as recited in claim 3, wherein said intermediate adaptor flange (4) is a split structure comprising at least two arc-shaped segments circumferentially, all arc-shaped segments being joined together to form a unitary flange, adjacent arc-shaped segments being detachably connected.
5. A rocket liquid propellant transfer tube assembly as claimed in claim 4, wherein said intermediate adaptor flange (4) comprises a first arcuate flange and a second arcuate flange, said first arcuate flange and said second arcuate flange enclosing to form a unitary flange, the end surfaces of said first arcuate flange and said second arcuate flange being provided with mounting plates (45) extending radially inwardly, the mounting plates (45) of both being secured by bolts or screws.
6. A rocket liquid propellant transfer tube assembly as recited in claim 3, wherein said nozzle body (31) and said adapter flange (32) have the same inside diameter and are circumferentially sealingly secured by welding, said adapter flange (32) being located in a large diameter section (41) of said intermediate adapter flange (4).
7. A rocket liquid propellant transport tube assembly as claimed in claim 2, wherein said tunnel tube assembly (1) further comprises a bellows (13) disposed coaxially with said tunnel tube body (11), said bellows (13) being welded to an inner end portion of said tunnel tube body (11), an outer end portion of said transport tube body (21) being inserted through said bellows (13) into an interior of said tunnel tube body (11).
8. A rocket liquid propellant transfer tube assembly as recited in claim 2, wherein said tunnel tube body (11) has an outer peripheral wall sealingly secured to an annular reservoir ellipsoidal floor (200) by welding.
9. A rocket liquid propellant transfer tube assembly as recited in claim 1, wherein said transfer tube body (21) is secured to said first flange (22) by a welded circumferential seal.
10. A rocket liquid propellant delivery system comprising a first reservoir and a second reservoir for containing a liquid fuel and an oxidizer, respectively, wherein the liquid outlet of said first reservoir is passed through said second reservoir to communicate with a combustion chamber by means of a rocket liquid propellant transfer tube assembly as recited in any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920883236.2U CN210049972U (en) | 2019-06-12 | 2019-06-12 | Rocket liquid propellant conveying system and conveying pipe assembly |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920883236.2U CN210049972U (en) | 2019-06-12 | 2019-06-12 | Rocket liquid propellant conveying system and conveying pipe assembly |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210049972U true CN210049972U (en) | 2020-02-11 |
Family
ID=69397633
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920883236.2U Active CN210049972U (en) | 2019-06-12 | 2019-06-12 | Rocket liquid propellant conveying system and conveying pipe assembly |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN210049972U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112282968A (en) * | 2020-10-09 | 2021-01-29 | 北京宇航系统工程研究所 | Low-temperature common-bottom storage tank for conveying propellant in inner |
| CN112483278A (en) * | 2020-10-27 | 2021-03-12 | 北京宇航系统工程研究所 | Eight-way shunt structure with POGO vibration suppression function |
| CN112832927A (en) * | 2021-01-21 | 2021-05-25 | 江苏深蓝航天有限公司 | Fuel storage tank |
-
2019
- 2019-06-12 CN CN201920883236.2U patent/CN210049972U/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112282968A (en) * | 2020-10-09 | 2021-01-29 | 北京宇航系统工程研究所 | Low-temperature common-bottom storage tank for conveying propellant in inner |
| CN112483278A (en) * | 2020-10-27 | 2021-03-12 | 北京宇航系统工程研究所 | Eight-way shunt structure with POGO vibration suppression function |
| CN112483278B (en) * | 2020-10-27 | 2022-03-04 | 北京宇航系统工程研究所 | Eight-way shunt structure with POGO vibration suppression function |
| CN112832927A (en) * | 2021-01-21 | 2021-05-25 | 江苏深蓝航天有限公司 | Fuel storage tank |
| CN112832927B (en) * | 2021-01-21 | 2022-05-31 | 江苏深蓝航天有限公司 | Fuel storage tank |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN210049972U (en) | Rocket liquid propellant conveying system and conveying pipe assembly | |
| US8769954B2 (en) | Frequency-tunable bracketless fluid manifold | |
| CN109798203B (en) | Storage tank bottom structure and connection structure of storage tank bottom and engine | |
| WO2007057629A1 (en) | Aircraft fuel pipe coupling | |
| CN104260901A (en) | Modular two-component propulsion system | |
| US20030093987A1 (en) | Integrated tankage for propulsion vehicles and the like | |
| CN104847981A (en) | Connecting apparatus of dual-wall high-pressure gas pipelines | |
| CN114291300B (en) | Ground-moon shuttle aircraft propulsion system | |
| US7093337B1 (en) | Integrated tankage for propulsion vehicles and the like | |
| CN110985880A (en) | Liquefied gas cylinder and manufacturing method thereof | |
| CN206290870U (en) | A kind of flange sleeve cartridge type controllable telescopic pipe | |
| CN115007973A (en) | Device and method for efficiently welding communicating pipes between large-volume storage tanks | |
| CN109883713B (en) | Process spray pipe capable of reducing axial thermal stress | |
| EP4056882B1 (en) | Multi-seal coupling for a hydrogen fuel system of a gas turbine engine and gas turbine engine | |
| CN215862282U (en) | Gas pipeline compensation device | |
| CN202325900U (en) | Air suction type combined pulse detonation engine for secondary detonation | |
| CN219102267U (en) | Combined type sealing double-wall pipe for combustible gas | |
| CN212804733U (en) | Liquid-gas flow divider and attitude control system with same | |
| CN220177747U (en) | Aircraft refuels and connects belt cleaning device | |
| CN208703377U (en) | A kind of heat preservation pipe prefabricated foaming three-way connection | |
| CN201237059Y (en) | Novel cladding member of corrugated expansion joint | |
| CN208687182U (en) | A kind of heat preservation pipe prefabricated foaming reducer union | |
| CN212657396U (en) | Fuel filling joint | |
| CN117704182A (en) | Corrugated pipe position compensation pipe fitting | |
| CN217234715U (en) | Double-wall pipe outer pipe connecting structure of LNG power ship |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |