CN111232231A - Wing built-in aviation oil tank pressurizing device - Google Patents
Wing built-in aviation oil tank pressurizing device Download PDFInfo
- Publication number
- CN111232231A CN111232231A CN202010081306.XA CN202010081306A CN111232231A CN 111232231 A CN111232231 A CN 111232231A CN 202010081306 A CN202010081306 A CN 202010081306A CN 111232231 A CN111232231 A CN 111232231A
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- Prior art keywords
- inner cavity
- pipe
- pressurizing
- aviation
- fuel tank
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/005—Accessories not provided for in the groups B64D37/02 - B64D37/28
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/02—Tanks
- B64D37/06—Constructional adaptations thereof
- B64D37/10—Constructional adaptations thereof to facilitate fuel pressurisation
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/32—Safety measures not otherwise provided for, e.g. preventing explosive conditions
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/32—Safety measures not otherwise provided for, e.g. preventing explosive conditions
- B64D2037/325—Fuel tanks with provisions for reduction hydraulic ram shocks due to projectile impacts
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Supply Devices, Intensifiers, Converters, And Telemotors (AREA)
- Loading And Unloading Of Fuel Tanks Or Ships (AREA)
Abstract
The invention relates to the technical field of aviation fuel tanks, in particular to a wing built-in aviation fuel tank pressurizing device, which comprises an aviation fuel tank, wherein a pressurizing insertion pipe is inserted and installed in an inner cavity at the upper end of the aviation fuel tank, an installation support is vertically installed at the outer edge of the upper end of the aviation fuel tank, and second rotating grooves which are mutually symmetrical are arranged on the left and right arc side surfaces of the connecting position of a boss at the upper end of the aviation fuel tank and the pressurizing insertion pipe, and the wing built-in aviation fuel tank pressurizing device has the: according to the invention, through the matching of the lower insertion pipe of the buffer box, the air inlet pressurization is buffered on the premise of preventing oil from flowing back, and the effective control on the pressurization rate is realized by matching with the throttle valve; through setting up motor drive's interior bushing pipe, realize the intercommunication between second through-hole and the third through-hole, realize improving pressure boost speed in the quick pressurized process of needs, reduce the buffering time that the pressure boost needs for the aircraft operation is more stable.
Description
Technical Field
The invention relates to the technical field of aviation aircraft fuel tanks, in particular to a wing built-in type aviation fuel tank pressurizing device.
Background
In the process of operation and flight of an aviation aircraft, due to the fact that the pressure is weak in the high altitude, in order to ensure stable oil supply in aircraft wings, a pressurizing device needs to be added into an oil tank, and oil is supplied stably and timely.
The existing pressurizing device usually adopts an air pump or a hydraulic cylinder to reduce and pressurize the oil tank, however, in the process of switching the needed pressurization, the increase of the air pressure of the oil tank can be realized only by certain working time, in the pressurized time period, the oil supply of the airplane is insufficient, the problems of airplane bumping and the like are easily caused, meanwhile, the air pressure inside the oil tank is changed greatly, the buffering time is short, the quick jump of the pressure is easily caused, and the problems of deformation and the like of the oil tank are further caused.
Therefore, the wing built-in type aviation oil tank pressurizing device is provided to solve the problem of stable pressurization of the oil tank.
Disclosure of Invention
The invention aims to provide a wing built-in type aviation oil tank pressurizing device to solve the problems in the background technology.
In order to achieve the purpose, the invention provides the following technical scheme:
a wing built-in aviation oil tank pressurizing device comprises an aviation oil tank, wherein a pressurizing insertion pipe is inserted and installed in an upper end inner cavity of the aviation oil tank, an installation support is vertically installed at the outer edge of the upper end of the aviation oil tank, second rotating grooves which are symmetrical to each other are arranged on the left and right arc side surfaces of the connecting position of an upper end boss of the aviation oil tank and the pressurizing insertion pipe, an air inlet pipe is connected to the upper end of the pressurizing insertion pipe, a first rotating groove is formed in the outer wall of the upper end of the pressurizing insertion pipe, which corresponds to the second rotating groove, at the height, the lower end of the pressurizing insertion pipe is inserted and installed in the inner cavity of the aviation oil tank, second through holes which are linearly distributed are formed in the outer wall of the middle section of the pressurizing insertion pipe, an inner lining pipe is inserted and installed in the inner wall of the middle section of the pressurizing insertion pipe, first internal, the upper end right side of baffle-box intercommunication air pump, the lower extreme of baffle-box is provided with the back flow, the other end of back flow communicates the upper end inner chamber of aviation oil tank, the upper end of lower apron is provided with the oil filter, and the lower extreme of lower apron is provided with four lower intubate that circumference array distributes, the outer wall of intubate is provided with the first through-hole of linear distribution down, the interlude outer wall of interior bushing pipe is provided with the third through-hole that is as high as the second through-hole, and the upper end outer wall of interior bushing pipe is provided with the second internal thread, and the connecting rod is installed in the perpendicular grafting of the upper end left and right sides of interior bushing pipe, the outside upper end of connecting rod is connected with the.
Preferably, the pipelines on the left and right sides of the upper end of the buffer tank are provided with pressure gauges, the upper end of the buffer tank is provided with a pressure release valve, and a return valve is arranged on a return pipe at the lower end of the buffer tank.
Preferably, the inner cavity of the upper end of the lower cover plate is communicated with the inner cavity of the pressurizing insertion pipe, the upper end of the lower cover plate is provided with a second external thread, the second external thread is in threaded fit connection with the first internal thread, and the oil filter is installed in the inner cavity of the upper end of the lower cover plate.
Preferably, the inner cavity of the lower cover plate is provided with a shunting inner cavity, the upper end of the shunting inner cavity is communicated with the lower end of the oil filter, and the lower end of the shunting inner cavity is respectively communicated with the inner cavities of four lower insertion tubes distributed in a circumferential array.
Preferably, the driving motor is fixed in the middle of the upper end of the mounting bracket, and a motor rotating shaft at the lower end of the driving motor is rotatably connected with the mounting bracket through a bearing.
Preferably, the upper end of the beam rotating rod is fixedly connected with a motor rotating shaft of the driving motor, the upper end of the connecting rod is provided with a mounting hole, and the connecting rod is fixedly connected with the beam rotating rod through the mounting hole.
Preferably, the second internal thread is equal in height to the second rotating groove and the second rotating groove, a first external thread is arranged at one end of the connecting rod connected with the lining pipe, and the first external thread is in threaded connection with the second internal thread.
Preferably, the lining pipe is rotatably sleeved in the inner cavity of the pressurizing insertion pipe, the lower end face of the lining pipe is tightly attached to the upper end face of the lower cover plate, and the third through holes and the second through holes in the lining pipe are distributed in a staggered mode at the same height.
Preferably, the lower insertion pipe is inserted at the lower end of oil liquid in the inner cavity of the aviation oil tank, and the third through hole and the second through hole are located in the inner cavity at the upper end of the oil liquid.
Compared with the prior art, the invention has the beneficial effects that:
1. according to the invention, through the matching of the lower insertion pipe of the buffer box, the air inlet pressurization is buffered on the premise of preventing oil from flowing back, and the effective control on the pressurization rate is realized by matching with the throttle valve;
2. according to the invention, the inner lining pipe driven by the motor is arranged, so that the communication between the second through hole and the third through hole is realized, the rapid pressurization process is realized, the pressurization speed is improved, the buffering time required by pressurization is reduced, and the aircraft runs more stably.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is an enlarged view of the structure at A in FIG. 1;
FIG. 3 is an enlarged view of the structure at B in FIG. 1;
FIG. 4 is a schematic perspective view of an aviation fuel tank of the present invention;
FIG. 5 is a perspective view of a pressurized cannula of the present invention;
FIG. 6 is a perspective view of the lower insert rod of the present invention;
FIG. 7 is a perspective view of the lining pipe according to the present invention;
fig. 8 is a schematic perspective view of a connecting rod according to the present invention.
In the figure: 1. an aviation fuel tank; 2. pressurizing and inserting the tube; 3. a liner tube; 4. a lower cover plate; 5. a lower cannula; 6. a connecting rod; 7. a beam rotating rod; 8. mounting a bracket; 9. a drive motor; 10. a bearing; 11. an air inlet pipe; 12. a throttle valve; 13. a pressure gauge; 14. a buffer tank; 15. a pressure relief valve; 16. a reflux valve; 17. a return pipe; 18. a first through hole; 19. an air pump; 20. an oil filter; 21. a shunt lumen; 22. a first internal thread; 23. a first rotary tank; 24. a second through hole; 25. a second internal thread; 26. a first external thread; 27. mounting holes; 28. a second external thread; 29. a third through hole; 30. a second rotary tank.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1 to 8, the present invention provides a technical solution:
the utility model provides a built-in aviation oil tank pressure device of wing, includes aviation oil tank 1, and the upper end inner chamber of aviation oil tank 1 is pegged graft and is installed pressurization intubate 2, and the upper end of pressurization intubate 2 is connected with intake pipe 11, and the right side intercommunication buffer tank 14 of intake pipe 11, the upper end right side intercommunication air pump 19 of buffer tank 14 utilize the cooperation of air pump 19 and intake pipe 11 to realize the purpose to the pressure boost of aviation oil tank 1 admitting air.
The outer wall of the pipe between the intake pipe 11 and the surge tank 14 is provided with a throttle valve 12, and the rate of intake air is controlled by the throttle valve 12.
The lower extreme of buffer tank 14 is provided with back flow 17, and the upper end inner chamber of air tank 1 is communicated to the other end of back flow 17, utilizes buffer tank 14 to realize providing the buffering to the quick jump of the pressure change that admits air, avoids causing the influence to air tank 1, and the in-process of pressure release avoids causing fluid negative pressure blowout simultaneously.
The pipelines on the left side and the right side of the upper end of the buffer tank 14 are provided with pressure gauges 13, the upper end of the buffer tank 14 is provided with a pressure release valve 15, a return pipe 17 at the lower end of the buffer tank 14 is provided with a return valve 16, the pressure release of the inner cavity of the aviation oil tank 1 is realized by the pressure release valve 15, and a return flow channel of oil is controlled by the return valve 16.
The lower end of the pressurizing insertion pipe 2 is inserted into an inner cavity of the aviation oil tank 1, a first internal thread 22 is arranged on the inner wall of the lower end of the pressurizing insertion pipe 2, a lower cover plate 4 is arranged on the lower end of the pressurizing insertion pipe 2, the inner cavity of the upper end of the lower cover plate 4 is communicated with the inner cavity of the pressurizing insertion pipe 2, a second external thread 28 is arranged on the upper end of the lower cover plate 4, the second external thread 28 is in thread fit connection with the first internal thread 22, the oil filter 20 is installed in the inner cavity of the upper end of the lower cover plate 4, and the second external thread 28 is in thread fit with the first internal thread 22 to achieve sealing.
The lower end of the lower cover plate 4 is provided with four lower insertion pipes 5 distributed in a circumferential array, the outer wall of each lower insertion pipe 5 is provided with a first through hole 18 distributed linearly, each lower insertion pipe 5 is inserted at the lower end of oil liquid in an inner cavity of the aviation oil tank 1, the inner cavity of the lower cover plate 4 is provided with a shunting inner cavity 21, the lower ends of the shunting inner cavities 21 are respectively communicated with the inner cavities of the four lower insertion pipes 5 distributed in the circumferential array, and the purpose of slow air intake and pressure compensation is achieved by means of cooperation of the lower insertion pipes 5 and the first through holes.
The upper end of the lower cover plate 4 is provided with an oil filter 20, the upper end of the shunting inner cavity 21 is communicated with the lower end of the oil filter 20, and oil is filtered during backflow by the oil filter 20, so that the blockage of a pipeline is avoided.
The inner wall of the middle section inner cavity of the pressurizing insertion pipe 2 is inserted with the lining pipe 3, the lining pipe 3 is rotatably sleeved in the inner cavity of the pressurizing insertion pipe 2, the lower end face of the lining pipe 3 is tightly attached to the upper end face of the lower cover plate 4, and the lower end of the lining pipe 3 is installed in a sealing mode through the lower cover plate 4.
The outer wall of the upper end of the inner lining pipe 3 is provided with a second internal thread 25, the connecting rod 6 is vertically installed on the left side and the right side of the upper end of the inner lining pipe 3 in an inserting mode, a first external thread 26 is arranged at one end, connected with the inner lining pipe 3, of the connecting rod 6, the first external thread 26 is connected with the second internal thread 25 in a threaded mode, and the first external thread 26 is matched with the second internal thread 25 in a threaded mode to achieve fixed connection between the inner lining pipe 3 and the connecting rod 6.
The left and right arc side surfaces of the connecting position of the boss at the upper end of the aviation oil tank 1 and the pressurizing insertion pipe 2 are provided with second rotating grooves 30 which are symmetrical to each other, the outer wall of the upper end of the pressurizing insertion pipe 2, which is at the height corresponding to the second rotating grooves 30, is provided with a first rotating groove 23, the height of the second internal thread 25 is equal to that of the second rotating grooves 30 and the second rotating grooves 30, and the connecting rod 6 can rotate at a certain angle by utilizing the second rotating grooves 30 and the second rotating grooves 30.
The outer side upper end of connecting rod 6 is connected with crossbeam bull stick 7 perpendicularly, the upper end of crossbeam bull stick 7 is rotated and is connected with driving motor 9, the vertical installing support 8 of upper end outer fringe of aviation fuel tank 1, driving motor 9 is fixed at the upper end intermediate position of installing support 8, and rotate through bearing 10 between motor shaft and the installing support 8 of driving motor 9 lower extreme and be connected, the motor shaft of the upper end fixed connection driving motor 9 of crossbeam bull stick 7, the upper end of connecting rod 6 is provided with mounting hole 27, connecting rod 6 passes through mounting hole 27 fixed connection crossbeam bull stick 7, utilize installing support 8 to realize the fixed mounting of driving motor 9, utilize mounting hole 27 to realize being connected between connecting rod 6 and the crossbeam bull stick 7, and then drive connecting rod 6 through driving motor 9 and rotate, bushing pipe 3 rotates in connecting rod 6 drives.
The outer wall of the middle section of the pressurizing insertion pipe 2 is provided with second through holes 24 which are linearly distributed, the outer wall of the middle section of the lining pipe 3 is provided with third through holes 29 which are as high as the second through holes 24, the third through holes 29 and the second through holes 24 on the lining pipe 3 are as high as the second through holes 24 and are distributed in a staggered mode, the third through holes 29 and the second through holes 24 are located in an inner cavity at the upper end of oil, and the air inlet rate is adjusted by means of communication or staggered closing of the third through holes 29 and the second through holes 24, so that the buffering time required by pressurization is shortened, and the airplane can.
The working principle is as follows: firstly, the sealing connection between the pressurizing insertion pipe 2 and the lower cover plate 4 is realized by utilizing the thread matching between the second external thread 28 and the first internal thread 22, the sealing installation of the lower end of the lining pipe 3 is realized by utilizing the lower cover plate 4, the fixed connection between the lining pipe 3 and the connecting rod 6 is realized by utilizing the thread matching between the first external thread 26 and the second internal thread 25, the fixed installation of the driving motor 9 is realized by utilizing the installation support 8, and the connection between the connecting rod 6 and the beam rotating rod 7 is realized by utilizing the installation hole 27.
The purpose of air inlet pressurization of the aviation fuel tank 1 is realized by the matching of the air pump 19 and the air inlet pipe 11, in the air inlet process, the air inlet speed is controlled by using the throttle valve 12, when the aircraft runs stably, the slow air inlet pressure compensation purpose is realized by using the matching of the lower insertion pipe 5 and the first through hole 18, when the aircraft climbs the height, the power operation is increased, so that the oil supply amount is increased, at the moment, the connecting rod 6 is driven to rotate by the driving motor 9, the connecting rod 6 drives the lining pipe 3 to rotate, the connecting rod 6 realizes the rotation of a certain angle by utilizing the second rotating groove 30 and the second rotating groove 30, and then make the intercommunication of third through-hole 29 and second through-hole 24, increase the air intake rate, reduce the buffering time that the pressure boost needs, utilize buffer tank 14 to realize providing the buffering to the quick jump of the pressure change that admits air, avoid causing the influence to aviation oil tank 1 for the aircraft operation is more stable.
When the aircraft stopped operating, need carry out timely pressure release to aviation oil tank 1 inner chamber, utilize relief valve 15 to realize carrying out the pressure release to aviation oil tank 1 inner chamber, utilize the backward flow runner of 16 control fluid in the return valve, utilize oil filter 20 to realize filtering fluid when the backward flow, avoid causing the jam of pipeline, simultaneously at the in-process of pressure release, utilize baffle-box 14 to avoid causing fluid negative pressure blowout.
The oil filter 20 is prior art and will not be described in detail; the drive motor 9 is of the type: a precision planetary gear of the PF; the air pump 19 is of the type: a mute air pump of 750W-30L.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (9)
1. The utility model provides a built-in aviation oil tank pressure device of wing, includes aviation oil tank (1), its characterized in that: the inner cavity of the upper end of the aviation oil tank (1) is provided with a pressurizing insertion pipe (2) in an inserted manner, the outer edge of the upper end of the aviation oil tank (1) is vertically provided with a mounting bracket (8), the left and right arc sides of the connecting position of the boss of the upper end of the aviation oil tank (1) and the pressurizing insertion pipe (2) are provided with second rotating grooves (30) which are symmetrical to each other, the upper end of the pressurizing insertion pipe (2) is connected with an air inlet pipe (11), the outer wall of the upper end of the pressurizing insertion pipe (2) and the second rotating grooves (30) at the corresponding height is provided with a first rotating groove (23), the lower end of the pressurizing insertion pipe (2) is inserted into the inner cavity of the aviation oil tank (1), the outer wall of the middle section of the pressurizing insertion pipe (2) is provided with second through holes (24) which are distributed linearly, the inner wall of the inner cavity, the lower end of the pressurizing insertion pipe (2) is provided with a lower cover plate (4), the right side of the air inlet pipe (11) is communicated with a buffer tank (14), the outer wall of a pipeline between the air inlet pipe (11) and the buffer tank (14) is provided with a throttle valve (12), the right side of the upper end of the buffer tank (14) is communicated with an air pump (19), the lower end of the buffer tank (14) is provided with a return pipe (17), the other end of the return pipe (17) is communicated with an upper end inner cavity of the aviation oil tank (1), the upper end of the lower cover plate (4) is provided with an oil filter (20), the lower end of the lower cover plate (4) is provided with four lower insertion pipes (5) distributed in a circumferential array manner, the outer wall of each lower insertion pipe (5) is provided with a first through hole (18) distributed in a linear manner, the outer wall of the middle section of each inner lining pipe (3) is, the left side and the right side of the upper end of the inner lining pipe (3) are vertically provided with connecting rods (6) in an inserted connection mode, the upper end of the outer side of each connecting rod (6) is vertically connected with a beam rotating rod (7), and the upper end of each beam rotating rod (7) is rotatably connected with a driving motor (9).
2. The wing built-in aviation fuel tank pressurizing device according to claim 1, wherein: the pipeline of the upper end left and right sides of buffer tank (14) all is provided with manometer (13), and the upper end of buffer tank (14) is provided with relief valve (15), is provided with on back flow (17) of buffer tank (14) lower extreme back flow valve (16).
3. The wing built-in aviation fuel tank pressurizing device according to claim 1, wherein: the inner cavity of the upper end of the lower cover plate (4) is communicated with the inner cavity of the pressurizing insertion pipe (2), the upper end of the lower cover plate (4) is provided with a second external thread (28), the second external thread (28) is in threaded fit connection with the first internal thread (22), and the oil filter (20) is installed in the inner cavity of the upper end of the lower cover plate (4).
4. The wing built-in aviation fuel tank pressurizing device according to claim 1, wherein: the inner cavity of the lower cover plate (4) is provided with a shunting inner cavity (21), the upper end of the shunting inner cavity (21) is communicated with the lower end of an oil filter (20), and the lower end of the shunting inner cavity (21) is respectively communicated with the inner cavities of four lower insertion pipes (5) distributed in a circumferential array mode.
5. The wing built-in aviation fuel tank pressurizing device according to claim 1, wherein: the driving motor (9) is fixed in the middle of the upper end of the mounting bracket (8), and a motor rotating shaft at the lower end of the driving motor (9) is rotatably connected with the mounting bracket (8) through a bearing (10).
6. The wing built-in aviation fuel tank pressurizing device according to claim 1, wherein: the upper end of the beam rotating rod (7) is fixedly connected with a motor rotating shaft of the driving motor (9), the upper end of the connecting rod (6) is provided with a mounting hole (27), and the connecting rod (6) is fixedly connected with the beam rotating rod (7) through the mounting hole (27).
7. The wing built-in aviation fuel tank pressurizing device according to claim 1, wherein: the second internal thread (25) is equal in height to the second rotating groove (30) and the second rotating groove (30), a first external thread (26) is arranged at one end, connected with the lining pipe (3), of the connecting rod (6), and the first external thread (26) is in threaded connection with the second internal thread (25) fixedly.
8. The wing built-in aviation fuel tank pressurizing device according to claim 1, wherein: the inner lining pipe (3) is rotatably sleeved in the inner cavity of the pressurizing insertion pipe (2), the lower end face of the inner lining pipe (3) is tightly attached to the upper end face of the lower cover plate (4), and the third through hole (29) and the second through hole (24) in the inner lining pipe (3) are distributed in a high-altitude staggered mode.
9. The wing built-in aviation fuel tank pressurizing device according to claim 1, wherein: the lower insertion pipe (5) is inserted at the lower end of oil liquid in the inner cavity of the aviation oil tank (1), and the third through hole (29) and the second through hole (24) are located in the inner cavity of the upper end of the oil liquid.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011007266.0A CN112124603A (en) | 2020-02-06 | 2020-02-06 | Aviation oil tank pressurization control method suitable for airplane flight |
| CN202010081306.XA CN111232231B (en) | 2020-02-06 | 2020-02-06 | Wing built-in aviation oil tank pressurizing device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010081306.XA CN111232231B (en) | 2020-02-06 | 2020-02-06 | Wing built-in aviation oil tank pressurizing device |
Related Child Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011007266.0A Division CN112124603A (en) | 2020-02-06 | 2020-02-06 | Aviation oil tank pressurization control method suitable for airplane flight |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111232231A true CN111232231A (en) | 2020-06-05 |
| CN111232231B CN111232231B (en) | 2020-12-08 |
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Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011007266.0A Withdrawn CN112124603A (en) | 2020-02-06 | 2020-02-06 | Aviation oil tank pressurization control method suitable for airplane flight |
| CN202010081306.XA Active CN111232231B (en) | 2020-02-06 | 2020-02-06 | Wing built-in aviation oil tank pressurizing device |
Family Applications Before (1)
| Application Number | Title | Priority Date | Filing Date |
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| CN202011007266.0A Withdrawn CN112124603A (en) | 2020-02-06 | 2020-02-06 | Aviation oil tank pressurization control method suitable for airplane flight |
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| CN (2) | CN112124603A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114044152A (en) * | 2021-12-17 | 2022-02-15 | 中国航空工业集团公司西安飞机设计研究所 | Bidirectional oil supply balancing system and correcting method for internal combustion oil tank of left wing and right wing of airplane |
| CN116353836A (en) * | 2023-04-19 | 2023-06-30 | 南京儒一航空机械装备有限公司 | Pressure maintaining oil tank for aircraft |
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2020
- 2020-02-06 CN CN202011007266.0A patent/CN112124603A/en not_active Withdrawn
- 2020-02-06 CN CN202010081306.XA patent/CN111232231B/en active Active
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| JPH0840394A (en) * | 1994-07-28 | 1996-02-13 | Mitsubishi Heavy Ind Ltd | Fuel transport device of aircraft |
| DE4436747C1 (en) * | 1994-10-14 | 1996-05-15 | Daimler Benz Aerospace Airbus | Method for storing fuel in aircraft tank |
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| CN109625297A (en) * | 2018-12-11 | 2019-04-16 | 石家庄飞机工业有限责任公司 | A kind of fuel system for Small General Aircraft |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114044152A (en) * | 2021-12-17 | 2022-02-15 | 中国航空工业集团公司西安飞机设计研究所 | Bidirectional oil supply balancing system and correcting method for internal combustion oil tank of left wing and right wing of airplane |
| CN114044152B (en) * | 2021-12-17 | 2023-11-28 | 中国航空工业集团公司西安飞机设计研究所 | Bidirectional oil supply balance system and correction method for internal combustion oil tanks of left and right wings of aircraft |
| CN116353836A (en) * | 2023-04-19 | 2023-06-30 | 南京儒一航空机械装备有限公司 | Pressure maintaining oil tank for aircraft |
| CN116353836B (en) * | 2023-04-19 | 2023-09-29 | 南京儒一航空机械装备有限公司 | Pressure maintaining oil tank for aircraft |
Also Published As
| Publication number | Publication date |
|---|---|
| CN112124603A (en) | 2020-12-25 |
| CN111232231B (en) | 2020-12-08 |
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