CN220743358U - Telescopic auxiliary oil tank in aircraft - Google Patents
Telescopic auxiliary oil tank in aircraft Download PDFInfo
- Publication number
- CN220743358U CN220743358U CN202322473296.6U CN202322473296U CN220743358U CN 220743358 U CN220743358 U CN 220743358U CN 202322473296 U CN202322473296 U CN 202322473296U CN 220743358 U CN220743358 U CN 220743358U
- Authority
- CN
- China
- Prior art keywords
- oil tank
- tank barrel
- section oil
- barrel
- rear end
- 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.)
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- 239000002828 fuel tank Substances 0.000 claims description 76
- 238000007789 sealing Methods 0.000 claims description 6
- 239000007788 liquid Substances 0.000 claims description 2
- 239000003921 oil Substances 0.000 abstract description 117
- 235000017166 Bambusa arundinacea Nutrition 0.000 abstract description 18
- 235000017491 Bambusa tulda Nutrition 0.000 abstract description 18
- 241001330002 Bambuseae Species 0.000 abstract description 18
- 235000015334 Phyllostachys viridis Nutrition 0.000 abstract description 18
- 239000011425 bamboo Substances 0.000 abstract description 18
- 239000000446 fuel Substances 0.000 abstract description 14
- 239000010763 heavy fuel oil Substances 0.000 abstract description 4
- 238000012423 maintenance Methods 0.000 abstract description 3
- 239000000243 solution Substances 0.000 description 3
- 238000000034 method Methods 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 239000002699 waste material Substances 0.000 description 2
- 230000003044 adaptive effect Effects 0.000 description 1
- 230000008602 contraction Effects 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
Classifications
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Details Of Rigid Or Semi-Rigid Containers (AREA)
Abstract
The utility model belongs to the technical field of aircraft bellytank design, concretely relates to scalable bellytank in aircraft, when concrete application, usable back end oil tank section of thick bamboo rear end flange fixed bolster is fixed in the aircraft, simultaneously, it is scalable between Duan Youxiang section of thick bamboo, middle section oil tank section of thick bamboo, the anterior segment oil tank section of thick bamboo behind the three-section that constitutes the bellytank, when dismouting or maintenance, the accessible slides and contracts the anterior segment oil tank section of thick bamboo into the middle section oil tank section of thick bamboo, and with the middle section oil tank section of thick bamboo contract into in the back segment oil tank section of thick bamboo, reserve sufficient space for the operation, and can be according to the oiling how many, the shrinkage of adjustment anterior segment oil tank section of thick bamboo, the adjustment bellytank's of suitability effective volume, can practice thrift the precious space resource on the aircraft, and can reduce the residual fuel surplus in the bellytank, the fuel utilization ratio is improved.
Description
Technical Field
The application belongs to the technical field of aircraft auxiliary fuel tank design, and particularly relates to an aircraft interior telescopic auxiliary fuel tank.
Background
In order to increase the range of the aircraft, the aircraft is provided with an auxiliary fuel tank, and mainly comprises an external auxiliary fuel tank and an internal auxiliary fuel tank.
The externally-hung auxiliary oil tank is hung below the fuselage or the wing, so that the aerodynamic performance of the aircraft is seriously affected, and when the maneuverability of the aircraft needs to be improved, the externally-hung auxiliary oil tank needs to be thrown away, so that dangers are easily caused, the externally-hung auxiliary oil tank is difficult to recycle, and the waste is serious;
the external structure and the size of the auxiliary fuel tank in the aircraft are fixed, enough space needs to be reserved for disassembly, assembly and maintenance operations in the aircraft, the space on the aircraft is difficult to fully utilize for fuel loading, and when the loaded fuel is less, a large amount of space on the aircraft can be occupied, so that the waste of precious space resources on the aircraft is caused.
The present application has been made in view of the existence of the above-mentioned technical drawbacks.
It should be noted that the above disclosure of the background art is only for aiding in understanding the inventive concept and technical solution of the present application, which is not necessarily prior art to the present application, and should not be used for evaluating the novelty and creativity of the present application in the case where no clear evidence indicates that the above content has been disclosed at the filing date of the present application.
Disclosure of Invention
It is an object of the present application to provide an aircraft interior retractable auxiliary fuel tank that overcomes or mitigates at least one of the technical drawbacks known to exist.
The technical scheme of the application is as follows:
an aircraft interior retractable auxiliary fuel tank comprising:
the rear section oil tank barrel is plugged at the rear end and is opened at the front end;
the flange fixing bracket at the rear end of the rear section oil tank barrel is connected to the rear end of the rear section oil tank barrel;
the front end connecting ring of the rear section oil tank barrel is sleeved on the periphery of the front end of the rear section oil tank barrel;
the middle section oil tank barrel is opened at two ends, and the rear end extends into the middle section oil tank barrel from the front end of the rear section oil tank barrel;
the slip ring at the rear end of the middle section oil tank barrel is positioned in the rear section oil tank barrel and sleeved on the periphery of the rear end of the middle section oil tank barrel;
the rear end connecting ring of the middle section oil tank barrel is sleeved on the periphery of the middle section oil tank barrel and is connected with the front end connecting ring of the rear section oil tank barrel through bolts;
the bearing frame at the rear end of the middle section oil tank barrel is supported in the rear end of the middle section oil tank barrel;
the front end connecting ring of the middle section oil tank barrel is sleeved on the periphery of the front end of the middle section oil tank barrel;
the front section oil tank barrel is opened at the rear end, the front end is plugged, and the rear end extends into the middle section oil tank barrel from the front end;
the slip ring at the rear end of the front section oil tank barrel is positioned in the middle section oil tank barrel and sleeved on the periphery of the rear end of the front section oil tank barrel;
the rear end connecting ring of the front section oil tank barrel is sleeved on the periphery of the front section oil tank barrel and is connected with the front end connecting ring of the middle section oil tank barrel through bolts;
the bearing frame at the rear end of the front section oil tank barrel is supported in the rear end of the front section oil tank barrel;
the front end bearing frame of the front section oil tank barrel is supported in the front end of the front section oil tank barrel.
According to at least one embodiment of the present application, in the above-mentioned telescopic auxiliary fuel tank in an aircraft, the rear end slip ring of the middle section fuel tank barrel and the rear section fuel tank barrel are sealed by two sealing rings;
the rear end slip ring of the front section oil tank cylinder and the middle section oil tank cylinder are sealed by two sealing rings.
According to at least one embodiment of the application, in the telescopic auxiliary fuel tank in the aircraft, the rear end of the rear section fuel tank barrel is connected with the fuel inlet pipe and the fuel supply pipe.
According to at least one embodiment of the present application, in the above-mentioned telescopic auxiliary fuel tank in an aircraft, a discharge piston is disposed on a rear end sidewall of a rear-section fuel tank barrel.
According to at least one embodiment of the application, in the telescopic auxiliary fuel tank in the aircraft, the fuel level sensor is arranged on the side wall of the rear end of the rear section fuel tank barrel.
According to at least one embodiment of the application, in the telescopic auxiliary fuel tank in the aircraft, the outer wall of the front section fuel tank barrel is axially connected with a cross beam, and the cross beam is connected with a lifting lug, and the lifting lug is close to the front end of the front section fuel tank barrel.
According to at least one embodiment of the present application, in the above-mentioned telescopic auxiliary fuel tank in an aircraft, the method further includes:
the rear section guide sleeves are connected between the rear section oil tank barrel rear end flange fixing bracket and the rear section oil tank barrel front end connecting ring along the circumferential direction;
the middle section guide sleeves are connected to the front end connecting ring of the middle section oil tank barrel along the circumferential direction, penetrate through the rear end connecting ring of the middle section oil tank barrel and the front end connecting ring of the rear section oil tank barrel and extend into the rear section guide sleeves;
the front end support ring of the front section oil tank barrel is sleeved at the front end of the front section oil tank barrel;
the front section guide posts are connected to the front end support ring of the front section oil tank barrel along the circumferential direction, penetrate through the rear end connecting ring of the front section oil tank barrel and the front end connecting ring of the middle section oil tank barrel, and extend into the middle section guide sleeves.
The utility model provides a scalable bellytank in aircraft, when specific application, usable back end flange fixed bolster of back section tank section of thick bamboo is fixed in the aircraft, simultaneously, it is scalable between the three sections back Duan Youxiang section of thick bamboo that constitute the bellytank, the middle section of thick bamboo of oil tank, the anterior segment of thick bamboo of oil tank is scalable, when dismouting or maintenance, the accessible slides and is in the middle section of thick bamboo of oil tank, and in the middle section of thick bamboo of oil tank is contracted the back section of thick bamboo of oil tank, reserve sufficient space for the operation, and can be according to the how much of oiling, the shrinkage volume of adjustment anterior segment of thick bamboo of oil tank, the middle section of thick bamboo of oil tank, the effective volume of the adjustment bellytank of suitability, can practice thrift the valuable space resource on the aircraft, and can reduce the residual fuel surplus in the bellytank, and improve fuel utilization ratio.
Drawings
FIG. 1 is a schematic illustration of an in-flight retractable auxiliary fuel tank provided in an embodiment of the present application;
wherein:
1-a rear-section oil tank barrel; 2-a rear end flange fixing bracket of the rear section oil tank barrel; 3-a front end connecting ring of the rear-section oil tank barrel; 4-a middle section oil tank barrel; 5-a slip ring at the rear end of the middle section oil tank barrel; 6, a connecting ring at the rear end of the middle section oil tank barrel; 7-a bearing frame at the rear end of the middle section oil tank barrel; 8-a connecting ring at the front end of the middle section oil tank barrel; 9-a front section oil tank barrel; 10-a slip ring at the rear end of the front section oil tank barrel; 11-a connecting ring at the rear end of the front section oil tank barrel; 12-a bearing frame at the rear end of the front section oil tank barrel; 13-a front end bearing frame of the front section oil tank barrel; 14-a discharge piston; 15-an oil liquid level sensor; 16-a cross beam; 17-lifting lugs; 18-a rear section guide sleeve; 19-a middle section guide sleeve; 20-a front end supporting ring of the front section oil tank barrel; 21-front section guide post.
For the purpose of better illustrating the embodiments, certain elements of the drawings may be omitted, enlarged or reduced and do not represent the actual product dimensions; furthermore, the drawings are for illustrative purposes only and are not to be construed as limiting the present patent.
Detailed Description
In order to make the technical solution of the present application and the advantages thereof more apparent, the technical solution of the present application will be more fully described in detail below with reference to the accompanying drawings, it being understood that the specific embodiments described herein are only some of the embodiments of the present application, which are for explanation of the present application, not for limitation of the present application. It should be noted that, for convenience of description, only the portion relevant to the present application is shown in the drawings, and other relevant portions may refer to a general design, and without conflict, the embodiments and technical features in the embodiments may be combined with each other to obtain new embodiments.
Furthermore, unless defined otherwise, technical or scientific terms used in the description of this application should be given the ordinary meaning as understood by one of ordinary skill in the art to which this application belongs. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," "outer," and the like as used in this description are merely used to indicate relative directions or positional relationships, and do not imply that a device or element must have a particular orientation, be configured and operated in a particular orientation, and that the relative positional relationships may be changed when the absolute position of the object being described is changed, and thus should not be construed as limiting the present application. The terms "first," "second," "third," and the like, as used in the description herein, are used for descriptive purposes only and are not to be construed as indicating or implying any particular importance to the various components. The use of the terms "a," "an," or "the" and similar referents in the description of the utility model are not to be construed as limited in number to the precise location of at least one. As used in this description, the terms "comprises," "comprising," or the like are intended to cover an element or article that appears before the term and that is listed after the term and its equivalents, without excluding other elements or articles.
Furthermore, unless specifically stated and limited otherwise, the terms "mounted," "connected," and the like in the description herein are to be construed broadly and refer to either a fixed connection, a removable connection, or an integral connection, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can also be communicated with the inside of two elements, and the specific meaning of the two elements can be understood by a person skilled in the art according to specific situations.
The present application is described in further detail below in conjunction with fig. 1.
An aircraft interior retractable auxiliary fuel tank comprising:
the rear section oil tank barrel 1 is plugged at the rear end and opened at the front end;
the flange fixing bracket 2 at the rear end of the rear section oil tank barrel is connected with the rear end of the rear section oil tank barrel 1;
the front end connecting ring 3 of the rear section oil tank barrel is sleeved on the periphery of the front end of the rear section oil tank barrel 1;
the middle section oil tank barrel 4 is opened at two ends, and the rear end extends into the rear section oil tank barrel 1 from the front end;
the slip ring 5 at the rear end of the middle section oil tank barrel is positioned in the rear section oil tank barrel 1 and sleeved on the periphery of the rear end of the middle section oil tank barrel 4;
the rear end connecting ring 6 of the middle section oil tank barrel is sleeved on the periphery of the middle section oil tank barrel 4 and is connected with the front end connecting ring 3 of the rear section oil tank barrel through bolts;
the bearing frame 7 at the rear end of the middle section oil tank barrel is supported in the rear end of the middle section oil tank barrel 4;
the front end connecting ring 8 of the middle section oil tank barrel is sleeved on the periphery of the front end of the middle section oil tank barrel 4;
a front section oil tank barrel 9, the rear end of which is open, the front end of which is plugged, and the rear end of which extends into the front end of the middle section oil tank barrel 4;
the rear end slip ring 10 of the front section oil tank barrel is positioned in the middle section oil tank barrel 4 and sleeved on the periphery of the rear end of the front section oil tank barrel 9;
the rear end connecting ring 11 of the front section oil tank barrel is sleeved on the periphery of the front section oil tank barrel 9 and is connected with the front end connecting ring 8 of the middle section oil tank barrel through bolts;
the bearing frame 12 at the rear end of the front section oil tank barrel is supported in the rear end of the front section oil tank barrel 9;
the front end bearing frame 13 of the front section oil tank barrel is supported in the front end of the front section oil tank barrel 9.
The telescopic auxiliary fuel tank in the aircraft disclosed in the above embodiment can be fixed in the aircraft by using the flange fixing bracket 2 at the rear end of the rear fuel tank barrel in specific application, and simultaneously, the three rear fuel tank barrels 1, the middle fuel tank barrel 4 and the front fuel tank barrel 9 forming the auxiliary fuel tank are telescopic, when the auxiliary fuel tank is disassembled or maintained, the front fuel tank barrel 9 can be retracted into the middle fuel tank barrel 4 through sliding, the middle fuel tank barrel 4 can be retracted into the rear fuel tank barrel 1, enough space is reserved for operation, the contraction amount of the front fuel tank barrel 9 and the middle fuel tank barrel 4 can be adjusted according to the amount of fuel injection, the effective volume of the auxiliary fuel tank can be adjusted in an adaptive manner, precious space resources on the aircraft can be saved, the residual fuel remaining amount in the auxiliary fuel tank can be reduced, and the fuel utilization rate can be improved.
In the telescopic auxiliary fuel tank in the aircraft disclosed in the above embodiment, the setting of the connecting ring 6 at the rear end of the middle fuel tank barrel and the sliding ring 10 at the rear end of the front fuel tank barrel can limit the sliding ring 5 at the rear end of the middle fuel tank barrel and the sliding ring 10 at the rear end of the front fuel tank barrel when the middle fuel tank barrel 4 and the front fuel tank barrel 9 are telescopic, so as to avoid the separation of the middle fuel tank barrel 4 and the front fuel tank barrel 9.
In some alternative embodiments, in the above-mentioned telescopic auxiliary fuel tank in the aircraft, the space between the rear end slip ring 5 of the middle fuel tank barrel and the rear fuel tank barrel 1 is sealed by two sealing rings;
the rear end slip ring 10 of the front section oil tank barrel and the middle section oil tank barrel 4 are sealed by two sealing rings.
In some alternative embodiments, in the above-mentioned telescopic auxiliary fuel tank in the aircraft, the end of the rear section fuel tank barrel 1 is connected with a fuel inlet pipe and a fuel supply pipe, and fuel is fed and supplied to the rear end of the rear section fuel tank barrel 1.
In some alternative embodiments, in the telescopic auxiliary fuel tank in the aircraft, the discharge piston 14 is arranged on the side wall of the rear end of the rear section fuel tank barrel 1, so as to control the discharge of residual fuel in the auxiliary fuel tank.
In some alternative embodiments, in the retractable auxiliary fuel tank in the aircraft, the fuel level sensor 15 is disposed on the rear end sidewall of the rear fuel tank barrel 1, so as to be capable of detecting the fuel level in the auxiliary fuel tank.
In some alternative embodiments, in the telescopic auxiliary fuel tank in the aircraft, the outer wall of the front section fuel tank barrel 9 is connected with a cross beam 16 along the axial direction, the cross beam 16 is connected with a lifting lug 17, the lifting lug is close to the front end of the front section fuel tank barrel 9, and can be connected into the aircraft body, and the auxiliary fuel tank is reliably fixed by being matched with the flange fixing bracket 2 at the rear end of the rear section fuel tank barrel.
In some optional embodiments, in the above-mentioned telescopic auxiliary fuel tank in the aircraft, the method further includes:
the rear section guide sleeves 18 are connected between the rear section oil tank barrel rear end flange fixing bracket 2 and the rear section oil tank barrel front end connecting ring 3 along the circumferential direction;
the middle section guide sleeves 19 are connected to the front end connecting ring 8 of the middle section oil tank barrel along the circumferential direction, penetrate through the rear end connecting ring 6 of the middle section oil tank barrel and the front end connecting ring 3 of the rear section oil tank barrel and extend into the rear section guide sleeves 18;
the front end support ring 20 of the front section oil tank barrel is sleeved at the front end of the front section oil tank barrel 9;
the front section guide posts 21 are connected to the front section oil tank barrel front end support ring 20 along the circumferential direction, penetrate through the front section oil tank barrel rear end connection ring 11 and the middle section oil tank barrel front end connection ring 8, and extend into the middle section guide sleeves 19.
In the telescopic auxiliary fuel tank in the aircraft disclosed in the above embodiment, the design of the rear section guide sleeve 18, the middle section guide sleeve 19 and the front section guide post 21 can provide the guiding function for the extension and retraction of the middle section fuel tank barrel 4 and the front section fuel tank barrel 9, so that the clamping stagnation is avoided, and the stability of the overall structure of the auxiliary fuel tank can be enhanced.
In the description, each embodiment is described in a progressive manner, and each embodiment is mainly described by the differences from other embodiments, so that the same similar parts among the embodiments are mutually referred.
Having thus described the technical aspects of the present application with reference to the preferred embodiments illustrated in the accompanying drawings, it should be understood by those skilled in the art that the scope of the present application is not limited to the specific embodiments, and those skilled in the art may make equivalent changes or substitutions to the relevant technical features without departing from the principles of the present application, and those changes or substitutions will now fall within the scope of the present application.
Claims (7)
1. An aircraft interior retractable auxiliary fuel tank, comprising:
a rear section oil tank barrel (1), the rear end of which is blocked and the front end of which is open;
the flange fixing bracket (2) at the rear end of the rear section oil tank barrel is connected with the rear end of the rear section oil tank barrel (1);
the front end connecting ring (3) of the rear section oil tank barrel is sleeved on the periphery of the front end of the rear section oil tank barrel (1);
the two ends of the middle section oil tank barrel (4) are open, and the rear end of the middle section oil tank barrel extends into the middle section oil tank barrel (1) from the front end of the rear section oil tank barrel;
the slip ring (5) at the rear end of the middle section oil tank barrel is positioned in the rear section oil tank barrel (1) and sleeved on the periphery of the rear end of the middle section oil tank barrel (4);
the rear end connecting ring (6) of the middle section oil tank barrel is sleeved on the periphery of the middle section oil tank barrel (4), and is connected with the front end connecting ring (3) of the rear section oil tank barrel through bolts;
the bearing frame (7) at the rear end of the middle section oil tank barrel is supported in the rear end of the middle section oil tank barrel (4);
the front end connecting ring (8) of the middle section oil tank barrel is sleeved on the periphery of the front end of the middle section oil tank barrel (4);
the front section oil tank barrel (9) is opened at the rear end, the front end is plugged, and the rear end extends into the middle section oil tank barrel (4) from the front end;
the rear end slip ring (10) of the front section oil tank barrel is positioned in the middle section oil tank barrel (4) and sleeved on the periphery of the rear end of the front section oil tank barrel (9);
the rear end connecting ring (11) of the front section oil tank barrel is sleeved on the periphery of the front section oil tank barrel (9), and is connected with the front end connecting ring (8) of the middle section oil tank barrel through bolts;
the bearing frame (12) at the rear end of the front section oil tank barrel is supported in the rear end of the front section oil tank barrel (9);
the front end bearing frame (13) of the front section oil tank barrel is supported in the front end of the front section oil tank barrel (9).
2. The retractable auxiliary fuel tank in an aircraft according to claim 1, wherein,
the rear end slip ring (5) of the middle section oil tank barrel and the rear section oil tank barrel (1) are sealed by two sealing rings;
the rear end slip ring (10) of the front section oil tank barrel and the middle section oil tank barrel (4) are sealed by two sealing rings.
3. The retractable auxiliary fuel tank in an aircraft according to claim 1, wherein,
the end part of the rear end of the rear section oil tank barrel (1) is connected with an oil inlet pipe and an oil supply pipe.
4. The retractable auxiliary fuel tank in an aircraft according to claim 1, wherein,
a discharge piston (14) is arranged on the side wall of the rear end of the rear section oil tank barrel (1).
5. The retractable auxiliary fuel tank in an aircraft according to claim 1, wherein,
an oil liquid level sensor (15) is arranged on the side wall of the rear end of the rear section oil tank barrel (1).
6. The retractable auxiliary fuel tank in an aircraft according to claim 1, wherein,
the outer wall of the front section oil tank barrel (9) is axially connected with a cross beam (16), the cross beam (16) is connected with a lifting lug (17), and the lifting lug is close to the front end of the front section oil tank barrel (9).
7. The retractable auxiliary fuel tank in an aircraft according to claim 1, wherein,
further comprises:
the rear section guide sleeves (18) are connected between the rear section oil tank barrel rear end flange fixing bracket (2) and the rear section oil tank barrel front end connecting ring (3) along the circumferential direction;
the middle section guide sleeves (19) are connected to the front end connecting ring (8) of the middle section oil tank barrel along the circumferential direction, penetrate through the rear end connecting ring (6) of the middle section oil tank barrel and the front end connecting ring (3) of the rear section oil tank barrel, and extend into the rear section guide sleeves (18);
the front end support ring (20) of the front section oil tank barrel is sleeved at the front end of the front section oil tank barrel (9);
the front section guide posts (21) are connected to the front section oil tank barrel front end support ring (20) along the circumferential direction, penetrate through the front section oil tank barrel rear end connecting ring (11) and the middle section oil tank barrel front end connecting ring (8) and extend into the middle section guide sleeves (19).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322473296.6U CN220743358U (en) | 2023-09-12 | 2023-09-12 | Telescopic auxiliary oil tank in aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322473296.6U CN220743358U (en) | 2023-09-12 | 2023-09-12 | Telescopic auxiliary oil tank in aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220743358U true CN220743358U (en) | 2024-04-09 |
Family
ID=90552215
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202322473296.6U Active CN220743358U (en) | 2023-09-12 | 2023-09-12 | Telescopic auxiliary oil tank in aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220743358U (en) |
-
2023
- 2023-09-12 CN CN202322473296.6U patent/CN220743358U/en active Active
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