CN113525698A - Oil tank for aircraft - Google Patents
Oil tank for aircraft Download PDFInfo
- Publication number
- CN113525698A CN113525698A CN202010297008.4A CN202010297008A CN113525698A CN 113525698 A CN113525698 A CN 113525698A CN 202010297008 A CN202010297008 A CN 202010297008A CN 113525698 A CN113525698 A CN 113525698A
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- Prior art keywords
- oil
- tank
- fuel
- aircraft
- storage tank
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- 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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- 239000000446 fuel Substances 0.000 claims abstract description 26
- 239000002828 fuel tank Substances 0.000 claims description 22
- 239000006260 foam Substances 0.000 claims description 20
- 239000000463 material Substances 0.000 claims description 20
- 229920005989 resin Polymers 0.000 claims description 3
- 239000011347 resin Substances 0.000 claims description 3
- 238000000034 method Methods 0.000 abstract description 2
- 239000003921 oil Substances 0.000 description 155
- 239000000295 fuel oil Substances 0.000 description 15
- 238000012423 maintenance Methods 0.000 description 8
- 230000000694 effects Effects 0.000 description 4
- 238000011010 flushing procedure Methods 0.000 description 4
- 238000007789 sealing Methods 0.000 description 4
- 239000012535 impurity Substances 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000008901 benefit Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 239000000565 sealant Substances 0.000 description 2
- 238000000926 separation method Methods 0.000 description 2
- 229920001875 Ebonite Polymers 0.000 description 1
- 229920001967 Metal rubber Polymers 0.000 description 1
- 239000011248 coating agent Substances 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 238000000748 compression moulding Methods 0.000 description 1
- 239000012141 concentrate Substances 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 238000001914 filtration Methods 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 239000004033 plastic Substances 0.000 description 1
- 229920003023 plastic Polymers 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 239000011435 rock Substances 0.000 description 1
- 239000004449 solid propellant Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT 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
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Details Of Rigid Or Semi-Rigid Containers (AREA)
Abstract
The invention discloses an oil tank for an aircraft, and relates to the technical field of aircraft design. One embodiment of the method comprises: oil tank cabin and play oil pipe, the bottom in oil tank cabin includes first bottom surface, second bottom surface and is located first bottom surface with oil storage tank between the second bottom surface, the one end that goes out oil pipe is located in the oil storage tank, the second bottom surface is an inclination and is greater than the inclined plane of aircraft flight angle, when the aircraft flies the second bottom surface is located the rear of first bottom surface. The embodiment can greatly reduce the dead oil ratio and improve the fuel utilization rate.
Description
Technical Field
The invention relates to the technical field of aircraft design, in particular to an oil tank for an aircraft.
Background
The oil tank of the existing aircraft has a certain distance with the oil outlet pipe due to the design requirement, and the oil tank is generally arranged to be parallel to the axis of the fuselage. Taking the aircraft as an example, when the aircraft flies, the aircraft flight gesture is generally the flight of rising, this just leads to fuel to concentrate at the oil tank rear portion in the oil tank, after the fuel consumption reaches certain degree, because there is certain distance between oil outlet pipe and the oil tank floor, when the aircraft jolts the fuel and rocks, the oil outlet pipe can not absorb the fuel from the oil tank, this has just caused to form the dead oil in the oil tank, according to statistics, the dead oil generally accounts for about 10% of whole fuel volume, the dead oil is more, the aircraft cost effectiveness ratio is lower.
In the process of implementing the invention, the inventor finds that at least the following problems exist in the prior art:
the design of the oil tank of the existing aircraft causes the dead oil occupation ratio, reduces the fuel oil utilization rate, cannot realize full oil drainage and full flushing, can cause damage to an engine due to foam in the fuel oil, and cannot help oil tank maintenance personnel to determine the maintenance time well.
Disclosure of Invention
In view of this, the embodiment of the present invention provides an oil tank for an aircraft, which can greatly reduce a dead oil ratio, improve a fuel utilization rate, achieve sufficient oil drainage and sufficient flushing, reduce a foam content in fuel, reduce damage to an engine, and facilitate an oil tank maintenance worker to determine a maintenance time.
To achieve the above object, according to one aspect of an embodiment of the present invention, a fuel tank for an aircraft is provided.
A tank for an aircraft, comprising: oil tank cabin and play oil pipe, the bottom in oil tank cabin includes first bottom surface, second bottom surface and is located first bottom surface with oil storage tank between the second bottom surface, the one end that goes out oil pipe is located in the oil storage tank, the second bottom surface is an inclination and is greater than the inclined plane of aircraft flight angle, when the aircraft flies the second bottom surface is located the rear of first bottom surface.
Optionally, the oil tank compartment includes a first compartment and a second compartment, the oil storage tank is located in the second compartment, wherein: the bottom of the first chamber comprises a first portion of the first bottom surface, and the bottom of the second chamber comprises a second portion of the first bottom surface, the oil storage tank and the second bottom surface.
Optionally, the difference between the width of the oil reservoir and the outer diameter of the oil outlet pipe is a predetermined value.
Optionally, two sides of a plane in the oil storage tank, which is in contact with the oil outlet pipe, are inclined planes.
Optionally, the bottom of the oil storage tank is provided with an oil drain valve.
Optionally, be provided with the foam structure material that is insoluble in oil in the oil storage tank, just foam structure material parcel the oil pipe be located one end in the oil storage tank.
Optionally, a transparent observation window is arranged at the bottom of the oil storage tank.
Optionally, the observation window is made of a resin material.
Optionally, the fuel tank is a monoblock fuel tank or a soft fuel tank.
Optionally, the flowline is a rigid pipe.
One embodiment of the above invention has the following advantages or benefits: the bottom in fuel tank compartment includes first bottom surface, the second bottom surface and is located the oil storage tank between first bottom surface and the second bottom surface, the one end that goes out oil pipe is located in the oil storage tank, the second bottom surface is the inclined plane that an inclination is greater than aircraft flight angle, the second bottom surface is located the rear of first bottom surface when aircraft flight, make and to reduce the dead oil by a wide margin and account for the ratio, improve fuel utilization, the bottom of oil storage tank is provided with the fuel drain valve, make to utilize the fuel drain valve can fully oil drain and fully wash, be provided with the foam structure material that is insoluble in oil in the oil storage tank, can reduce the foam content in the fuel, reduce the damage to the engine, the bottom of oil storage tank is provided with transparent observation window, can be favorable to the oil tank maintainer to confirm the opportunity of maintaining.
Further effects of the above-mentioned non-conventional alternatives will be described below in connection with the embodiments.
Drawings
The drawings are included to provide a better understanding of the invention and are not to be construed as unduly limiting the invention. Wherein:
FIG. 1 is a schematic view of a fuel tank for an aircraft according to one embodiment of the invention;
FIG. 2 is a schematic representation of a tank condition of an aircraft in flight according to one embodiment of the invention;
fig. 3 is a schematic view of a tank for an aircraft according to another embodiment of the invention.
Detailed Description
Exemplary embodiments of the present invention are described below with reference to the accompanying drawings, in which various details of embodiments of the invention are included to assist understanding, and which are to be considered as merely exemplary. Accordingly, those of ordinary skill in the art will recognize that various changes and modifications of the embodiments described herein can be made without departing from the scope and spirit of the invention. Also, descriptions of well-known functions and constructions are omitted in the following description for clarity and conciseness.
The aircraft oil tank usually has whole oil tank and soft oil tank two kinds, and whole oil tank borrows aircraft self structure to form the enclosure space as the oil tank, and soft oil tank forms the enclosure space as the oil tank through compression molding technology with plastics or other materials, no matter is whole oil tank or soft oil tank, and its design all forms an enclosure space and holds the fuel. The aircraft of each embodiment of the invention takes an aircraft as an example, wherein the aircraft can be an unmanned aerial vehicle or a manned aircraft.
An embodiment of the present invention provides an oil tank for an aircraft, including: the bottom of the oil tank cabin comprises a first bottom surface, a second bottom surface and an oil storage groove positioned between the first bottom surface and the second bottom surface, one end of the oil outlet pipe is positioned in the oil storage groove, the second bottom surface is an inclined plane with an inclination angle larger than the flight angle of the airplane, and the second bottom surface is positioned behind the first bottom surface when the airplane flies.
The fuel tank for an aircraft according to an embodiment of the present invention will be further described below with reference to embodiments one to six. Among them, in the following embodiments (embodiment one to embodiment six): the first bottom surface and the second bottom surface can be rectangular, the first bottom surface can be a plane or an inclined plane which is horizontally arranged, the second bottom surface and the inclined direction of the first bottom surface when the first bottom surface is arranged to be the inclined plane are inclined specifically towards the direction of the upper cover of the oil tank cabin, the oil tank cabin comprises a side wall, a bottom and the upper cover, and the other end of the oil outlet pipe extends out of one side wall of the oil tank cabin, which is close to the rear part of the airplane.
The oil outlet pipe of each embodiment of the invention is preferably a hard pipe, and the specific material is metal or hard rubber pipe, but is not limited to the above material. The form of the hard pipe can increase the safety of the oil supply of the airplane.
The fuel tank of the various embodiments of the present invention may be a solid fuel tank or a flexible fuel tank. The sealing technology of the whole oil tank generally adopts two modes of riveting and coating the sealant for sealing, the riveting quality and the sealing effect of the sealant are related to the appearance to be sealed, the oil tank is designed into a regular rectangle in the embodiment of the invention, the good sealing effect can be achieved, and the fuel content can be conveniently calculated by the dipstick through the height of the oil level and the shape of the oil tank. Therefore, the oil tank provided by the embodiment of the invention can be suitable for various aircrafts such as unmanned aerial vehicles and manned aircrafts, can be realized as an integral oil tank or a soft oil tank as required, and has a wide application range.
The first embodiment is as follows:
as shown in fig. 1, the fuel tank for an aircraft of the present embodiment includes: an oil tank 1-1 and an oil outlet pipe 1-2, the oil tank 1-1 includes a side wall 1-3, a bottom, and an upper cover (not shown in the figure), the bottom of the oil tank 1-1 includes a first bottom 1-4, a second bottom 1-5, and an oil storage tank 1-6 located between the first bottom 1-4 and the second bottom 1-5, one end of the oil outlet pipe 1-2 is located in the oil storage tank 1-6, the other end of the oil outlet pipe 1-2 extends from one side wall 1-3 of the oil tank 1-1 near the rear of the aircraft, the oil tank 1-1 specifically includes a first tank body 1-1-1 and a second tank body 1-1-2, the oil storage tank 1-6 is located in the second tank body 1-1-2, the bottom of the first tank body 1-1-1 includes a first portion of the first bottom 1-4, the bottom of the second cabin body 1-1-2 comprises a second part of the first bottom surface 1-4, an oil storage tank 1-6 and a second bottom surface 1-5, the second bottom surface 1-5 is an inclined surface with an inclination angle larger than the flight angle of the airplane, and the second bottom surface 1-5 is positioned behind the first bottom surface 1-4 when the airplane flies. The fuel oil through holes 1-8 are arranged below the separation parts 1-7 of the first cabin body 1-1-1 and the second cabin body 1-1-2, and the reverse valves (not shown in the figure) are arranged at the fuel oil through holes 1-8. As shown in fig. 1, the first bottom surface 1-4 is defined as a first portion located in the first chamber 1-1-1 and a second portion located in the second chamber 1-1-2.
Considering that the fuel tank is deformed during the flight of the aircraft in practical application, the width of the oil storage tank 1-6 is designed to be slightly larger than the outer diameter of the oil outlet pipe 1-2, and specifically, the difference between the width of the oil storage tank 1-6 and the outer diameter of the oil outlet pipe 1-2 can be a preset value, and the preset value can be set according to practical requirements.
The tank body 1-1 of the present embodiment is not limited to two, and may be provided in a plurality as needed, and specifically, the number of the first tank body 1-1-1 may be two or more. So as to sequentially consume the fuel oil of different cabins.
The state of the oil tank can be as shown in figure 2 when the airplane flies, because the second bottom surface 1-5 of the embodiment of the invention is an inclined surface with an inclination angle larger than the flying angle of the airplane, the second bottom surface 1-5 and the ground level 2-1 still form a certain angle when the airplane flies, dead oil in the oil tank is collected in the oil storage tank 1-6 due to the gravity effect, and the height of the fuel oil in the oil storage tank 1-6 (a in figure 2 represents the fuel oil level) completely meets the height of the fuel oil required by the oil outlet pipe 1-2 when the oil is absorbed, so the proportion of the dead oil in the oil tank can be fully reduced, and the utilization rate of the fuel oil is improved.
Example two:
this embodiment is based on the oil tank of embodiment one, and the both sides of the plane that contacts with the oil outlet pipe in the oil storage tank are further set as the inclined plane, namely, different from embodiment one: the bottom surface of the oil storage tank of the second embodiment is provided with three parts, wherein the middle part is contacted with one end of the oil outlet pipe and is arranged horizontally, and two sides of the middle part are inclined planes, so that the fuel utilization rate can be further improved.
Example three:
in this embodiment, an oil drain valve is further provided at the bottom of the oil reservoir based on the oil tank of the first embodiment.
Because the aircraft is deposited for a long time or when overhauing, the oil tank needs the oil drain, and this embodiment can realize fully the oil drain with the oil tank through with the fuel outlet valve design in the oil storage tank bottom. And because this embodiment adopts the design of oil outlet pipe form rather than the oil hammer form, can not cause the fuel outlet valve to block up (and the oil hammer is the movable part then can lead to the fuel outlet valve to block up).
In addition, after the aircraft is manufactured or during maintenance at ordinary times, the oil tank has flushing requirements, and the oil drain valve of the embodiment can be fully utilized to fully flush the oil tank.
Example four:
this embodiment is based on the oil tank of embodiment one, is further provided with the foam structure material that is insoluble in oil in the oil storage tank, and the foam structure material parcel goes out the one end that is located the oil storage tank of oil pipe. When the oil outlet pipe absorbs oil, the foam structure material can play a role in filtering oil, and filters foams (namely air bubbles) in fuel oil, so that the foam content of the fuel oil passing through the oil outlet pipe is reduced, and the damage to an engine is reduced.
Example five:
in the fuel tank of the first embodiment, the bottom of the fuel storage tank is further provided with a transparent observation window, impurities are generally deposited at the bottom of the fuel tank due to the fact that the impurities are higher in density than the fuel, and the degree of the impurities contained in the fuel can be conveniently observed through the transparent observation window so as to determine the maintenance time of the fuel tank.
The observation window can be made of resin material to avoid the observation window being crushed during the deformation of the oil tank.
Example six:
this embodiment can be implemented based on one or more of the first to fifth embodiments, and the fuel tank for an aircraft shown in fig. 3 is described as an example below.
As shown in fig. 3, the fuel tank for an aircraft of the present embodiment includes: the fuel tank 1-1 comprises a side wall 1-3, a bottom part, and an upper cover (not shown in the figure), the bottom part of the fuel tank 1-1 comprises a first bottom surface 1-4, a second bottom surface 1-5, and a fuel storage tank 1-6 located between the first bottom surface 1-4 and the second bottom surface 1-5, one end of the fuel outlet pipe 1-2 is located in the fuel storage tank 1-6, and the other end of the fuel outlet pipe 1-2 extends from one side wall 1-3 of the fuel tank 1-1 near the rear part of the aircraft.
The oil tank cabin 1-1 specifically comprises a first cabin body 1-1-1 and a second cabin body 1-1-2, an oil storage tank 1-6 is located in the second cabin body 1-1-2, the bottom of the first cabin body 1-1-1 comprises a first part of a first bottom surface 1-4, the bottom of the second cabin body 1-1-2 comprises a second part of the first bottom surface 1-4, the oil storage tank 1-6 and a second bottom surface 1-5, the second bottom surface 1-5 is an inclined surface with an inclination angle larger than the flight angle of the airplane, and the second bottom surface 1-5 is located behind the first bottom surface 1-4 when the airplane flies.
The fuel oil through holes 1-8 are arranged below the separation parts 1-7 of the first cabin body 1-1-1 and the second cabin body 1-1-2, and the reverse valves (not shown in the figure) are arranged at the fuel oil through holes 1-8.
An oil-insoluble foam structure material 3-1 is arranged in the oil storage tank 1-6, and the foam structure material 3-1 wraps one end of the oil outlet pipe 1-2, which is positioned in the oil storage tank 1-6.
And an oil drain valve 3-2 and a transparent observation window 3-3 are respectively arranged at the bottom of the oil storage tank 1-6 and positioned at the two sides of the foam structure material 3-1. It should be noted that the oil drain valve 3-2 and the transparent observation window 3-3 according to the embodiment of the present invention are not limited to the above arrangement, and may be arranged on the same side of the foam structural material 3-1.
The oil drain valves, the foam structure materials, the observation windows and the like of the third to fifth embodiments can also be arranged according to the positions of the corresponding components of the embodiment shown in fig. 3.
According to the technical scheme of the embodiment of the invention, the bottom of the oil tank cabin comprises a first bottom surface, a second bottom surface and an oil storage groove positioned between the first bottom surface and the second bottom surface, one end of an oil outlet pipe is positioned in the oil storage groove, the second bottom surface is an inclined surface with an inclination angle larger than the flight angle of an aircraft, when the aircraft flies, the second bottom surface is positioned behind the first bottom surface, so that the dead oil ratio can be greatly reduced, the fuel oil utilization rate is improved, the bottom of the oil storage groove is provided with an oil drain valve, so that the oil drain valve can be used for fully draining and fully flushing, an oil-insoluble foam structure material is arranged in the oil storage groove, the foam content in the fuel oil can be reduced, the damage to an engine is reduced, and the bottom of the oil storage groove is provided with a transparent observation window, so that maintenance personnel of an oil tank can determine the maintenance time.
The above-described embodiments should not be construed as limiting the scope of the invention. Those skilled in the art will appreciate that various modifications, combinations, sub-combinations, and substitutions can occur, depending on design requirements and other factors. Any modification, equivalent replacement, and improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. A tank for an aircraft, characterized in that it comprises: oil tank cabin (1-1) and play oil pipe (1-2), the bottom of oil tank cabin (1-1) includes first bottom surface (1-4), second bottom surface (1-5) and is located first bottom surface (1-4) with oil storage tank (1-6) between second bottom surface (1-5), the one end that goes out oil pipe (1-2) is located in oil storage tank (1-6), second bottom surface (1-5) are the inclined plane that an inclination is greater than aircraft flight angle, when aircraft flight second bottom surface (1-5) are located the rear of first bottom surface (1-4).
2. The tank according to claim 1, characterized in that the tank compartment (1-1) comprises a first (1-1-1) and a second (1-1-2) compartment, the oil sump (1-6) being located in the second compartment (1-1-2), wherein: the bottom of the first tank body (1-1-1) comprises a first part of the first bottom surface (1-4), and the bottom of the second tank body (1-1-2) comprises a second part of the first bottom surface (1-4), the oil storage tank (1-6) and the second bottom surface (1-5).
3. Tank according to claim 1, characterized in that the difference between the width of the reservoir (1-6) and the outer diameter of the outlet pipe (1-2) is a predetermined value.
4. The fuel tank as claimed in claim 1, wherein the flat surface of the reservoir (1-6) which contacts the outlet pipe (1-2) is inclined on both sides.
5. A fuel tank according to claim 1, characterized in that a drain valve (3-2) is provided at the bottom of the fuel reservoir (1-6).
6. A tank according to claim 1, characterized in that an oil-insoluble foam structure material (3-1) is provided in the oil reservoir (1-6), and the foam structure material (3-1) covers an end of the outlet pipe (1-2) located in the oil reservoir (1-6).
7. A tank according to claim 1, characterized in that the bottom of the oil reservoir (1-6) is provided with a transparent viewing window (3-3).
8. Fuel tank according to claim 7, characterized in that the observation window (3-3) is made of a resin material.
9. Tank according to claim 1, characterized in that it is a monobloc tank or a soft tank.
10. Tank according to claim 1, characterized in that the outlet line (1-2) is a rigid pipe.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010297008.4A CN113525698A (en) | 2020-04-15 | 2020-04-15 | Oil tank for aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010297008.4A CN113525698A (en) | 2020-04-15 | 2020-04-15 | Oil tank for aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113525698A true CN113525698A (en) | 2021-10-22 |
Family
ID=78088301
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010297008.4A Pending CN113525698A (en) | 2020-04-15 | 2020-04-15 | Oil tank for aircraft |
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| Country | Link |
|---|---|
| CN (1) | CN113525698A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114212269A (en) * | 2021-12-15 | 2022-03-22 | 北京机电工程研究所 | Oil tank cabin and forming method |
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|---|---|---|---|---|
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| CN202152111U (en) * | 2011-06-30 | 2012-02-29 | 张治国 | Aircrash-prevention double-box inwards slanting slide plate-type airplane fuel tank |
| FR2991298A1 (en) * | 2012-05-29 | 2013-12-06 | Eurocopter France | TANK, FUEL STORAGE SYSTEM, AND AIRCRAFT |
| CN103660924A (en) * | 2013-12-10 | 2014-03-26 | 武汉理工大学 | Mining explosion-proof fuel tank |
| CN207374687U (en) * | 2017-11-11 | 2018-05-18 | 南京婆娑航空科技有限公司 | A kind of unmanned plane suspension type fuel tank |
| CN109573072A (en) * | 2018-12-20 | 2019-04-05 | 西安达纳森物联科技有限公司 | A kind of unmanned plane oil storage system that Anti-inclining shakes |
| CN209305863U (en) * | 2018-12-26 | 2019-08-27 | 成都纵横大鹏无人机科技有限公司 | A kind of unmanned sump and unmanned plane |
| CN110466784A (en) * | 2019-08-18 | 2019-11-19 | 王建荣 | A kind of fuel tanker anti-corrosion structure |
-
2020
- 2020-04-15 CN CN202010297008.4A patent/CN113525698A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH08100616A (en) * | 1994-10-03 | 1996-04-16 | Honda Motor Co Ltd | Vertical engine and outboard engine |
| CN201086827Y (en) * | 2007-08-03 | 2008-07-16 | 西安大地测绘工程有限责任公司 | Anti-bubble fuel tank |
| CN202152111U (en) * | 2011-06-30 | 2012-02-29 | 张治国 | Aircrash-prevention double-box inwards slanting slide plate-type airplane fuel tank |
| FR2991298A1 (en) * | 2012-05-29 | 2013-12-06 | Eurocopter France | TANK, FUEL STORAGE SYSTEM, AND AIRCRAFT |
| CN103660924A (en) * | 2013-12-10 | 2014-03-26 | 武汉理工大学 | Mining explosion-proof fuel tank |
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| CN109573072A (en) * | 2018-12-20 | 2019-04-05 | 西安达纳森物联科技有限公司 | A kind of unmanned plane oil storage system that Anti-inclining shakes |
| CN209305863U (en) * | 2018-12-26 | 2019-08-27 | 成都纵横大鹏无人机科技有限公司 | A kind of unmanned sump and unmanned plane |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114212269A (en) * | 2021-12-15 | 2022-03-22 | 北京机电工程研究所 | Oil tank cabin and forming method |
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