CN119821680A - Aircraft fuel tank and fuel supply method - Google Patents
Aircraft fuel tank and fuel supply method Download PDFInfo
- Publication number
- CN119821680A CN119821680A CN202510246811.8A CN202510246811A CN119821680A CN 119821680 A CN119821680 A CN 119821680A CN 202510246811 A CN202510246811 A CN 202510246811A CN 119821680 A CN119821680 A CN 119821680A
- Authority
- CN
- China
- Prior art keywords
- oil outlet
- shell
- oil
- end cover
- fuel
- 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.)
- Granted
Links
Landscapes
- Cooling, Air Intake And Gas Exhaust, And Fuel Tank Arrangements In Propulsion Units (AREA)
Abstract
本发明公开了一种飞行器燃油油箱及供油方法，属于燃油供应技术领域。一种飞行器燃油油箱，包括壳体，壳体的两端分别设置有前端盖和后端盖，壳体的内部设置有气囊，前端盖上设置有与气囊连通的进气管，壳体与气囊之间填充有燃油，壳体上设置有出油结构，出油结构与进出油口连接，出油结构位于气囊的外部；后端盖上设置有排气孔。采用本发明所述的飞行器燃油油箱及供油方法，能够解决现有的飞行器燃油供应不稳定的问题，并且可以减少油箱内燃油的残留率。
The present invention discloses an aircraft fuel tank and a fuel supply method, belonging to the technical field of fuel supply. An aircraft fuel tank comprises a shell, a front end cover and a rear end cover are respectively provided at both ends of the shell, an air bag is provided inside the shell, an air inlet pipe connected to the air bag is provided on the front end cover, fuel is filled between the shell and the air bag, an oil outlet structure is provided on the shell, the oil outlet structure is connected to the oil inlet and outlet, and the oil outlet structure is located outside the air bag; an exhaust hole is provided on the rear end cover. The aircraft fuel tank and fuel supply method described in the present invention can solve the problem of unstable fuel supply of existing aircraft and reduce the residual rate of fuel in the tank.
Description
Technical Field
The invention relates to the technical field of fuel supply, in particular to an aircraft fuel tank and a fuel supply method.
Background
The hypersonic aircraft has the technical characteristics of high speed, high maneuverability and high precision, the existing missile defense system can not intercept, and can implement remote accurate striking on land and offshore high-value targets, so that the hypersonic aircraft is an advanced asymmetric striking means. However, the requirement for high mobility presents a significant challenge to the design of the fuel supply system.
A conventional fuel tank structure is shown in fig. 10. The fuel is filled in the rubber bag, and the drain pipe is inserted and is established in the rubber bag, and the fuel in the rubber bag is discharged through the drain pipe, because the drain pipe is shorter to set up in the oil tank center, make the fuel can not abundant discharge through the drain pipe, lead to the residual rate of fuel in the oil tank higher. And in the flight process of the aircraft, the fuel in the fuel tank moves along with the morphology of the aircraft, and as the liquid outlet pipe is arranged at one end of the fuel tank, when the fuel inclines to the other end of the aircraft, the fuel cannot be discharged through the liquid outlet pipe, and the stability of fuel supply is affected.
Therefore, the development of a tank for providing an aircraft with a stable supply of fuel is of great importance for the stable operation of the aircraft.
Disclosure of Invention
The invention aims to provide an aircraft fuel tank and an oil supply method, which solve the problem of unstable fuel supply of the existing aircraft with high maneuverability.
The invention provides an aircraft fuel oil tank, which comprises a shell, wherein a front end cover and a rear end cover are respectively arranged at two ends of the shell, an air bag is arranged in the shell, an air inlet pipe communicated with the air bag is arranged on the front end cover, fuel oil is filled between the shell and the air bag, an oil outlet structure is arranged on the shell and connected with an oil inlet and outlet, the oil outlet structure is positioned outside the air bag, and an exhaust hole is arranged on the rear end cover.
Preferably, the exhaust hole is positioned at the top of the rear end cover, and the oil inlet and outlet are positioned at the center of the rear end cover.
Preferably, the two ends of the air bag are respectively and fixedly connected with the centers of the front end cover and the rear end cover in a sealing way.
Preferably, the surface area of the balloon is greater than the inner surface area of the housing.
Preferably, the oil outlet structure comprises an oil outlet channel, the oil outlet channel is embedded in the side wall of the shell, the oil outlet channel is arranged along the length direction of the shell, a plurality of first oil outlet holes are formed in the oil outlet channel, the oil outlet channel is communicated with a cavity in the shell through the first oil outlet holes, and the oil outlet channel is connected with the oil inlet and outlet through an oil outlet cavity in the rear end cover.
Preferably, the oil outlet channels are uniformly distributed inside the inner wall of the shell.
Preferably, the oil outlet structure comprises an oil outlet pipe, the oil outlet pipe is arranged on the inner surface of the side wall of the shell along the length direction of the shell, a plurality of second oil outlet holes are formed in the oil outlet pipe, the oil outlet pipe is communicated with the cavity inside the shell through the second oil outlet holes, and the oil outlet pipe is connected with the oil inlet and the oil outlet through an oil outlet cavity arranged inside the rear end cover.
Preferably, the oil outlet pipes are uniformly distributed on the inner surface of the side wall of the shell, and the oil outlet pipes are provided with second oil outlet holes with different opening directions.
Preferably, the oil outlet cavities are radially distributed on the rear end cover, and the exhaust holes and the oil outlet cavities are distributed in a staggered manner.
The fuel supply method based on the aircraft fuel tank comprises the following steps of:
S1, communicating an oil inlet and an oil outlet with an external oil source through a connecting pipe, enabling fuel oil to enter an oil outlet duct or an oil outlet pipe through the connecting pipe and the oil inlet and outlet, enabling the fuel oil to enter the inside of a shell through a first oil outlet or a second oil outlet, discharging gas in the shell through an exhaust hole, and stopping oiling after the fuel oil overflows from the exhaust hole;
S2, the air inlet pipe is communicated with an external air source, the air source enters the air bag through the air inlet pipe, the air bag provides extrusion force for fuel in the shell, the fuel in the shell enters the oil outlet channel or the oil outlet pipe through the first oil outlet hole or the second oil outlet hole, and then is discharged out of the shell through the oil outlet cavity and the oil inlet and outlet hole, so that the fuel is provided for the combustion chamber.
The fuel oil tank and the fuel oil supply method of the aircraft have the advantages and positive effects that:
1. According to the invention, the oil outlet pipe or the oil outlet duct is arranged in the shell, the oil outlet pipe and the oil outlet duct are uniformly distributed on the inner surface or the inside of the inner wall of the shell in an array, and the plurality of first oil outlet holes and the plurality of second oil outlet holes are arranged on the oil outlet pipe and the oil outlet duct, so that the first oil outlet holes or the second oil outlet holes can be always immersed in fuel oil when the aircraft flies in a maneuvering way, and the stability of fuel oil supply is ensured.
2. According to the invention, the air bag is arranged in the shell and provides extrusion force for fuel oil in the shell, and the surface area of the air bag is larger than that of the inner surface of the shell, so that the air bag can almost fill the whole shell, and the reduction of the residual rate of the fuel oil in the shell is facilitated.
The technical scheme of the invention is further described in detail through the drawings and the embodiments.
Drawings
FIG. 1 shows a fuel tank according to the invention a schematic three-dimensional structure;
FIG. 2 is a schematic view of an axial cross-section of a fuel tank according to a first embodiment of the present invention;
FIG. 3 is an enlarged view of FIG. 2A;
FIG. 4 is a schematic view of a radial cross-sectional structure of a fuel tank according to a first embodiment of the present invention;
FIG. 5 shows a rear end cap of the present invention schematic cross-sectional structure;
FIG. 6 is a schematic axial cross-sectional view of a fuel tank according to a second embodiment of the present invention;
FIG. 7 is an enlarged view of B in FIG. 6;
FIG. 8 is a schematic view of a radial cross-sectional structure of a fuel tank according to a second embodiment of the present invention;
FIG. 9 is a schematic view of a fuel tank fuel supply structure according to the present invention;
fig. 10 is a structural view of a conventional fuel tank.
Reference numerals
1. The device comprises a shell, a front end cover, a rear end cover, a 4, an oil inlet and outlet, a 5, an exhaust hole, a 6, a fixed joint, a 7, an air bag, an 8, an oil outlet channel, a 9, a first oil outlet, a10, an air inlet pipe, a 11, an oil outlet cavity, a 12, an oil outlet pipe, a 13, a second oil outlet, a 14, a high-pressure gas cylinder, a 15, a gate valve, a16, a primary pressure reducing valve, a 17, a secondary pressure reducing valve, a 18, an electric explosion valve, a 19, a filling valve, a 20, an exhaust valve, a 21, a temperature sensor, a 22, a filter, a 23, a filling valve, a 24, a first pressure sensor, a 25, a fuel pump, a 26, a second pressure sensor, a 27 and a membrane valve.
Detailed Description
In the description of the present invention, it should be noted that, the azimuth or positional relationship indicated by the terms "upper", "lower", "inner", "outer", etc., are based on the azimuth or positional relationship shown in the drawings, or the azimuth or positional relationship in which the inventive product is conventionally put in use, are merely for convenience of describing the present invention and simplifying the description, and are not indicative or implying that the apparatus or element to be referred to must have a specific azimuth, be configured and operated in a specific azimuth, and therefore should not be construed as limiting the present invention. In the description of the present invention, it should also be noted that, unless explicitly specified and limited otherwise, the terms "configured," "mounted," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, integrally connected, mechanically connected, electrically connected, directly connected, indirectly connected through an intermediate medium, or in communication between two elements. The specific meaning of the above terms in the present invention will be understood in specific cases by those of ordinary skill in the art.
In the present application, unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs. If there is a discrepancy, the meaning described in the present specification or the meaning obtained from the content described in the present specification is used. In addition, the terminology used herein is for the purpose of describing embodiments of the application only and is not intended to be limiting of the application. For the purpose of accurately describing the technical content of the present application, and for the purpose of accurately understanding the present application, the following explanation or definition is given for terms used in the present specification before the explanation of the specific embodiments:
Embodiments of the present invention will be described in detail below with reference to the accompanying drawings.
Example 1
As shown in fig. 1, 2, 3, 4, and 5. An aircraft fuel tank comprises a shell 1, wherein the shell 1 is of a cylindrical structure in the embodiment. The housing 1 may also be provided in a rectangular or other shaped configuration as desired. The two ends of the shell 1 are respectively provided with a front end cover 2 and a rear end cover 3, and the front end cover 2 and the rear end cover 3 are fixedly connected with the shell 1 through screws. The front end cover 2, the rear end cover 3 and the housing 1 are sealed by rubber gaskets.
The inside of casing 1 is provided with gasbag 7, and the front end of gasbag 7 passes through fixed joint 6 and the central sealing fixed connection of front end housing 2, guarantees the leakproofness of gasbag 7. The rear end of the air bag 7 is directly adhered and fixed at the center of the rear end cover 3, so that the tightness of the rear end of the air bag 7 is ensured. The rear end of the air bag 7 can also be fixed in the center of the rear end cover 3 in a sealing way by adopting a fixing joint 6. The front end cover 2 is provided with the air inlet pipe 10 communicated with the air bag 7, the air inlet pipe 10 is in sealing connection with the air bag 7, gas is injected into the air bag 7 through the air inlet pipe 10, extrusion force is provided for fuel in the shell 1, and the fuel in the shell 1 is discharged beneficially. The surface area of the air bag 7 is larger than the inner surface area of the shell 1, so that the air bag 7 can be smoothly unfolded when the air bag 7 is inflated, and the air bag 7 can almost completely fill the whole inner space of the oil tank, so that the residual rate of fuel in the shell 1 is reduced.
The fuel oil is filled between the shell 1 and the air bag 7, an oil outlet structure is arranged on the shell 1, and the oil outlet structure is connected with the oil inlet and outlet 4. The oil inlet and outlet port 4 is positioned at the center of the rear end cover 3. The oil outlet structure is positioned outside the air bag 7 and is used for discharging the fuel in the shell 1 or filling the fuel in the shell 1.
The rear end cover 3 is provided with an exhaust hole 5, and the exhaust hole 5 is positioned at the top of the rear end cover 3. The exhaust hole 5 is used for fully exhausting the gas in the shell 1, so as to prevent unstable fuel flow after air is mixed in the fuel.
The oil outlet structure comprises an oil outlet duct 8, and the oil outlet duct 8 is embedded in the side wall of the shell 1. The oil outlet channels 8 are uniformly distributed inside the inner wall of the housing 1. In this embodiment, the oil outlet channels 8 are distributed in a circumferential array inside the inner wall of the housing 1. The oil outlet duct 8 is arranged along the length direction of the shell 1, a plurality of first oil outlet holes 9 are uniformly formed in the oil outlet duct 8, and the oil outlet duct 8 is communicated with the cavity inside the shell 1 through the first oil outlet holes 9. The fuel enters the oil outlet passage 8 through the first oil outlet hole 9, or enters the housing 1 through the oil outlet passage 8 and the first oil outlet hole 9.
The oil outlet duct 8 is connected with the oil inlet and outlet port 4 through an oil outlet cavity 11 arranged in the rear end cover 3. The oil outlet chamber 11 is radially distributed on the rear end cover 3. The end of the oil outlet cavity 11, which is close to the oil outlet channel 8, is a blind end, so that fuel is prevented from flowing out through the oil outlet cavity 11. The exhaust holes 5 and the oil outlet cavity 11 are distributed in a staggered way.
The inner diameter of the oil outlet passage 8, the aperture of the first oil outlet hole 9, the number of the oil outlet passages 8, and the number of the first oil outlet holes 9 are determined by the fuel flow rate and the flow resistance. The oil outlet channels 8 are arranged in the side wall of the shell 1 in a circumferential array, and the first oil outlet holes 9 are immersed in the fuel oil all the time when the aircraft is in maneuvering flight, so that stable oil supply of the fuel oil is realized.
Example two
As shown in fig. 6, 7 and 8. An aircraft fuel tank comprises a shell 1, wherein the shell 1 is of a cylindrical structure. The housing 1 may also be provided in a rectangular or other shaped configuration as desired. The two ends of the shell 1 are respectively provided with a front end cover 2 and a rear end cover 3, and the front end cover 2 and the rear end cover 3 are fixedly connected with the shell 1 through screws. The front end cover 2, the rear end cover 3 and the housing 1 are sealed by rubber gaskets.
The inside of casing 1 is provided with gasbag 7, and the front end of gasbag 7 passes through fixed joint 6 and the central sealing fixed connection of front end housing 2, guarantees the leakproofness of gasbag 7. The rear end of the air bag 7 is directly adhered and fixed at the center of the rear end cover 3, so that the tightness of the rear end of the air bag 7 is ensured. The rear end of the air bag 7 can also be fixed in the center of the rear end cover 3 in a sealing way by adopting a fixing joint 6. The front end cover 2 is provided with the air inlet pipe 10 communicated with the air bag 7, the air inlet pipe 10 is in sealing connection with the air bag 7, gas is injected into the air bag 7 through the air inlet pipe 10, extrusion force is provided for fuel in the shell 1, and the fuel in the shell 1 is discharged beneficially. The surface area of the air bag 7 is larger than the inner surface area of the shell 1, so that the air bag 7 can be smoothly unfolded when the air bag 7 is inflated, and the air bag 7 can almost completely fill the whole inner space of the oil tank, so that the residual rate of fuel in the shell 1 is reduced.
The fuel oil is filled between the shell 1 and the air bag 7, an oil outlet structure is arranged on the shell 1, and the oil outlet structure is connected with the oil inlet and outlet 4. The oil inlet and outlet port 4 is positioned at the center of the rear end cover 3. The oil outlet structure is positioned outside the air bag 7 and is used for discharging the fuel in the shell 1 or filling the fuel in the shell 1.
The rear end cover 3 is provided with an exhaust hole 5, and the exhaust hole 5 is positioned at the top of the rear end cover 3. The exhaust hole 5 is used for fully exhausting the gas in the shell 1, so as to prevent unstable fuel flow after air is mixed in the fuel.
The oil outlet structure comprises an oil outlet pipe 12, and the oil outlet pipe 12 is fixedly arranged on the inner surface of the side wall of the shell 1 along the length direction of the shell 1. The oil outlet pipe 12 may be fixed to the inner surface of the casing 1 by welding. The oil outlet pipe 12 is uniformly distributed on the inner surface of the side wall of the casing 1. In this embodiment, the oil outlet pipes 12 are distributed in a circumferential array on the side wall of the casing 1. The oil outlet pipe 12 is provided with a plurality of second oil outlet holes 13, and the oil outlet pipe 12 is communicated with the cavity inside the shell 1 through the second oil outlet holes 13. The oil outlet pipe 12 is provided with second oil outlet holes 13 of different opening directions so that fuel can enter the oil outlet pipe 12 from different directions.
The oil outlet pipe 12 is connected with the oil inlet and outlet 4 through an oil outlet cavity 11 arranged in the rear end cover 3. The oil outlet chamber 11 is radially distributed on the rear end cover 3. The end of the oil outlet cavity 11, which is close to the oil outlet pipe 12, is a blind end, so that fuel is prevented from flowing out through the oil outlet cavity 11. The exhaust holes 5 and the oil outlet cavity 11 are distributed in a staggered way.
The inner diameter of the oil outlet pipe 12, the aperture of the second oil outlet hole 13, the number of the oil outlet pipes 12, and the number of the second oil outlet holes 13 are determined by the fuel flow rate and the flow resistance. The oil outlet pipes 12 are arranged on the inner wall of the shell 1 in an array manner, and the second oil outlet holes 13 are always immersed in the fuel oil when the aircraft is in maneuvering flight, so that stable oil supply of the fuel oil is realized.
As shown in fig. 9. The outside of the shell 1 is provided with a pressurizing unit, a filling unit and a charging and discharging unit. The pressurizing unit is used for introducing gas into the air bag 7 and extruding fuel oil in the shell 1. The filling unit is connected with the oil inlet and outlet 4 and is used for filling fuel into the shell 1. The adding and discharging unit is connected with the oil inlet and outlet 4 and is used for providing fuel oil for a combustion chamber or a wall cooling system pipeline.
The pressurizing unit comprises a high-pressure gas cylinder 14, and the high-pressure gas cylinder 14 is communicated with the air bag 7 through a connecting pipe. The connecting pipe is provided with a gate valve 15, a primary pressure reducing valve 16, a secondary pressure reducing valve 17 and an electric explosion valve 18. The pressurizing unit is used for providing the squeezing force of 0.1MPa for the airbag 7.
The filling unit comprises a filling valve 19 and an exhaust valve 20, wherein the filling valve 19 is connected with the oil inlet and outlet port 4 through a filling pipe, and the exhaust valve 20 is connected with the exhaust hole 5 through a connecting pipe.
The adding unit comprises an adding main pipe and a plurality of adding branch pipes which are connected in parallel. The adding and discharging branch pipe is communicated with the oil inlet and outlet 4 through an adding and discharging main pipe, and a temperature sensor 21, a filter 22, an adding and discharging valve 23 and a first pressure sensor 24 are arranged on the adding and discharging main pipe. The addition and discharge branch pipe is provided with a fuel pump 25, a second pressure sensor 26 and a diaphragm valve 27. When the fuel pump 25 is not activated, the diaphragm valve 27 closes, and when the fuel pump 25 is activated, the pressure rises and the diaphragm valve 27 opens.
The fuel supply method of the fuel tank of the aircraft comprises the following steps:
S1, communicating an oil inlet and outlet 4 with an external oil source through a connecting pipe, opening an exhaust valve 20 and a filling valve 19, enabling fuel to enter an oil outlet duct 8 or an oil outlet duct 12 through the connecting pipe and the oil inlet and outlet 4, then entering the inside of the shell 1 through a first oil outlet hole 9 or a second oil outlet hole 13, exhausting gas in the shell 1 through an exhaust hole 5, stopping filling oil after the fuel overflows from the exhaust hole 5, and closing the exhaust valve 20 and the filling valve 19.
S2, the air inlet pipe 10 is communicated with an external air source, and the gate valve 15 and the electric explosion valve 18 are opened. The gas in the high-pressure gas cylinder 14 enters the air bag 7 through the gas inlet pipe 10, the air bag 7 provides extrusion force for the fuel in the shell 1, the fuel in the shell 1 enters the oil outlet channel 8 or the oil outlet pipe 12 through the first oil outlet hole 9 or the second oil outlet hole 13, and then is discharged into the feeding and discharging main pipe through the oil outlet cavity 11 and the oil inlet and outlet 4.
The fuel pump 25 and the charging and discharging valve 23 are opened, and the fuel in the charging and discharging manifold is filtered by the filter 22 and then sent to the combustion chamber or the wall cooling system pipeline by the fuel pump 25 and the diaphragm valve 27.
Therefore, the fuel oil tank and the fuel oil supply method for the aircraft can solve the problem of unstable fuel oil supply of the existing aircraft, and can reduce the residual rate of fuel oil in the fuel oil tank.
It should be noted that the above-mentioned embodiments are merely for illustrating the technical solution of the present invention and not for limiting the same, and although the present invention has been described in detail with reference to the preferred embodiments, it should be understood by those skilled in the art that the technical solution of the present invention may be modified or substituted by the same, and the modified or substituted technical solution may not deviate from the spirit and scope of the technical solution of the present invention.
Claims (10)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202510246811.8A CN119821680B (en) | 2025-03-03 | 2025-03-03 | Aircraft fuel tank and fuel supply method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202510246811.8A CN119821680B (en) | 2025-03-03 | 2025-03-03 | Aircraft fuel tank and fuel supply method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN119821680A true CN119821680A (en) | 2025-04-15 |
| CN119821680B CN119821680B (en) | 2025-08-15 |
Family
ID=95296037
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202510246811.8A Active CN119821680B (en) | 2025-03-03 | 2025-03-03 | Aircraft fuel tank and fuel supply method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN119821680B (en) |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6491255B1 (en) * | 2000-12-15 | 2002-12-10 | Jeff Bracken | Crashworthy external auxiliary fuel tank for aircraft |
| CN103541841A (en) * | 2013-09-30 | 2014-01-29 | 中国人民解放军国防科学技术大学 | Force bearing type oil tank |
| CN119244375A (en) * | 2024-09-13 | 2025-01-03 | 南京航空航天大学 | Controllable center of mass ramjet fuel system for small large maneuverable aircraft and method of using the same |
-
2025
- 2025-03-03 CN CN202510246811.8A patent/CN119821680B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6491255B1 (en) * | 2000-12-15 | 2002-12-10 | Jeff Bracken | Crashworthy external auxiliary fuel tank for aircraft |
| CN103541841A (en) * | 2013-09-30 | 2014-01-29 | 中国人民解放军国防科学技术大学 | Force bearing type oil tank |
| CN119244375A (en) * | 2024-09-13 | 2025-01-03 | 南京航空航天大学 | Controllable center of mass ramjet fuel system for small large maneuverable aircraft and method of using the same |
Non-Patent Citations (1)
| Title |
|---|
| 马晓三;: "一种充气皮囊式压力缓冲装置及其使用方法研究", 机床与液压, no. 16, 28 August 2016 (2016-08-28), pages 152 - 154 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN119821680B (en) | 2025-08-15 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110030116B (en) | Semi-membrane type ignition module capable of achieving single or multiple ignition, suction and extrusion, working method and igniter filling method | |
| CN113417760B (en) | A solid propellant oxygen-combustion sub-packaging coupled combustion transparent window experimenter and experimental method | |
| CN110220653A (en) | Double-wall pipe air-tightness detection tool and detection method | |
| CN104891054B (en) | A kind of bladder propellant tank suitable for high-strength hydrogen peroxide | |
| CN103670391B (en) | Displacement experiment fluid control method and experiment device | |
| CN119821680A (en) | Aircraft fuel tank and fuel supply method | |
| CN113624443B (en) | Transmitting cylinder opening sealing device for underwater transmission and mounting method | |
| CN114320697B (en) | An air distributor for an engine and the engine | |
| CN108871700B (en) | Ship stern shaft seal inspection device | |
| CN211314392U (en) | Cylinder cover assembly and gas engine with same | |
| CN119821681B (en) | High maneuverability aircraft fuel tank, fuel supply system and fuel supply method | |
| CN215830562U (en) | Fluid reinforcing device | |
| CN115013188B (en) | A modular sub-assembly solid rocket engine test bench device and cold flow test method | |
| CN115096577B (en) | A comprehensive test device for pintle injectors | |
| CN112879112A (en) | Fluid reinforcing device | |
| CN212870248U (en) | Heating power pond subassembly and contain its water heater | |
| CN210372284U (en) | Jet hole type high-proportion pressure reduction energy dissipation valve | |
| RU2007121791A (en) | COAXIAL FEEDING SYSTEM | |
| CN220151942U (en) | Filling gun adopting compact waist drum valve fluid control | |
| CN222184981U (en) | High-pressure oil pipe layout structure and power unit | |
| CN223153314U (en) | Water storage and supply device for underwater fuel cell system | |
| CN218207102U (en) | Aviation fuel pump of anti high air lock | |
| EP3999325B1 (en) | Injection bonding of composite vane into pocket | |
| CN220151632U (en) | Pressure cylinder applicable to various air inlet and outlet modes | |
| CN212691771U (en) | Gas distributor channel structure and gas water heater |
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 | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |