CN112537456B - Modular aircraft tank subassembly and aircraft - Google Patents
Modular aircraft tank subassembly and aircraft Download PDFInfo
- Publication number
- CN112537456B CN112537456B CN202011326419.8A CN202011326419A CN112537456B CN 112537456 B CN112537456 B CN 112537456B CN 202011326419 A CN202011326419 A CN 202011326419A CN 112537456 B CN112537456 B CN 112537456B
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- Prior art keywords
- oil
- aircraft
- tank
- fuel
- tank assembly
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- 239000002828 fuel tank Substances 0.000 claims abstract description 86
- 239000000446 fuel Substances 0.000 claims abstract description 36
- 238000009423 ventilation Methods 0.000 claims abstract description 12
- 239000003921 oil Substances 0.000 claims description 131
- 239000000295 fuel oil Substances 0.000 claims description 9
- 125000006850 spacer group Chemical group 0.000 claims description 5
- 239000003570 air Substances 0.000 description 21
- 238000007599 discharging Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 239000004677 Nylon Substances 0.000 description 1
- 239000012080 ambient air Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 239000000945 filler Substances 0.000 description 1
- 239000010763 heavy fuel oil Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 229920001778 nylon Polymers 0.000 description 1
- 230000035899 viability Effects 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
- B64D37/04—Arrangement thereof in or on aircraft
-
- 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)
- Cooling, Air Intake And Gas Exhaust, And Fuel Tank Arrangements In Propulsion Units (AREA)
Abstract
The application relates to a modularized aircraft fuel tank assembly and an aircraft. A modular aircraft fuel tank assembly comprising: the first oil tank comprises an oil filling port, a first oil outlet and a first air vent; the second oil tank comprises a first oil inlet, an oil supply port, an oil return port and a second ventilation port, the first oil outlet is connected with the first oil inlet, and the first ventilation port is connected with the second ventilation port; a temperature sensor for detecting the temperature of fuel in an aircraft fuel tank assembly; the ventilation balance valve is used for balancing the air pressure inside the aircraft fuel tank assembly and the outside; and the oil quantity sensor is used for detecting the oil quantity in the aircraft oil tank assembly. The modularized aircraft fuel tank assembly is simple in structure, high in safety and convenient to increase a range-extending fuel tank.
Description
Technical Field
The application relates to the field of aircraft manufacturing, in particular to a modularized aircraft fuel tank assembly and an aircraft.
Background
The general airplane mostly adopts an integral oil tank, and utilizes the internal volume of the airplane structure to store fuel oil by using a vulnerable wing leading edge or a structural space formed by a skin and a wing beam. The integral fuel tank has high requirements on structural tightness, and if the wing leading edge or the skin of the integral fuel tank is slightly damaged, fuel can leak, so that disastrous results are caused.
Moreover, the structural form of the whole oil tank is not beneficial to quick modification of the airplane so as to increase the range, and the structural modification difficulty of the oil tank is large, the cost is high and the period is long.
Disclosure of Invention
Based on the problem of above-mentioned background art, the application provides a modular aircraft tank subassembly and aircraft, and modular aircraft tank subassembly includes a plurality of fuel tanks, has overcome because of the easy slight fuel leakage that damages and lead to of wing leading edge or covering, and the security is high.
One embodiment of the present application provides a modular aircraft oil tank assembly comprising: the first oil tank comprises an oil filling port, a first oil outlet and a first air vent; the second oil tank comprises a first oil inlet, an oil supply port, an oil return port and a second vent port, the oil supply port is used for conveying fuel oil to the engine, the oil return port is used for enabling redundant fuel oil of the engine to flow back to the fuel tank assembly of the fuel aircraft, the first oil outlet is connected with the first oil inlet, and the first vent port is connected with the second vent port; a temperature sensor for detecting a temperature of fuel within the aircraft fuel tank assembly; a vent balancing valve for balancing air pressure within the aircraft tank assembly with ambient air; and the fuel quantity sensor is used for detecting the fuel quantity in the aircraft fuel tank assembly.
According to some embodiments of the application, both sides of the first tank and both sides of the second tank are cambered surfaces.
According to some embodiments of the present application, the modular aircraft fuel tank assembly further comprises a first lightning protection sheet connected at both ends to the first fuel tank and the second fuel tank, respectively.
According to some embodiments of the present application, the modular aircraft fuel tank assembly further comprises a third fuel tank, the third fuel tank comprises a second oil inlet, a second oil outlet, a third vent and a fourth vent, the third fuel tank set up between the first fuel tank and the second fuel tank, the first oil outlet is connected to the second oil inlet, the second oil outlet is connected to the first oil inlet, the first vent is connected to the third vent, the fourth vent is connected to the second vent.
According to some embodiments of the application, both sides of the third tank are cambered surfaces.
According to some embodiments of the present application, the modular aircraft tank assembly further comprises a second lightning protection sheet and a third lightning protection sheet, wherein two ends of the second lightning protection sheet are respectively connected to the first oil tank and the third oil tank, and two ends of the third lightning protection sheet are respectively connected to the third oil tank and the second oil tank.
According to some embodiments of the application, the modular aircraft tank assembly further comprises a fuel drain valve disposed on the second tank.
According to some embodiments of the present application, the modular aircraft tank assembly further comprises a low oil level switch disposed on the second tank.
An embodiment of the present application provides an aircraft comprising a modular aircraft tank assembly as described above, a wing rib of a wing being provided with a mounting aperture corresponding to the aircraft tank assembly, the aircraft tank assembly being provided in the wing rib.
According to some embodiments of the present application, the aircraft tank assembly is provided with spacers corresponding to the location of the ribs.
The modularized airplane fuel tank assembly comprises a plurality of fuel tanks, the modularized design is realized, the adjacent fuel tanks are flexibly communicated, various deformations of wings under pneumatic load can be adapted, the structural form is simple, and the manufacturing cost is low; the aircraft fuel tank assembly can be installed in the wing ribs of the wings, so that fuel leakage caused by easy damage of the front edges or skins of the wings of the integral fuel tank is avoided, and the aircraft fuel tank assembly is safe and reliable.
Drawings
In order to more clearly illustrate the technical solutions of the present application, the drawings required for the description of the embodiments are briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without exceeding the protection scope of the present application.
FIG. 1 is a schematic illustration of a modular aircraft fuel tank assembly in accordance with an embodiment of the present application;
FIG. 2 is a schematic view of a connection between a first fuel tank and a second fuel tank according to an embodiment of the present invention;
fig. 3 is a schematic view of a modular aircraft fuel tank assembly with an extended range fuel tank in accordance with an embodiment of the present application.
Detailed Description
The technical solutions of the present application will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present application, and it is obvious that the described embodiments are some, not all, of the embodiments of the present application. 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 application.
Example 1
As shown in fig. 1 and 2, one embodiment of the present application provides a modular aircraft fuel tank assembly 100 for storing fuel on board an aircraft. The aircraft fuel tank assembly 100 comprises a plurality of fuel tanks connected in sequence, and in this embodiment, the aircraft fuel tank assembly 100 comprises: a first tank 1 and a second tank 2.
The first oil tank 1 includes an oil filler port 11, a first oil outlet, and a first air vent. In this embodiment, the oil filling port 11 is located on the top surface of the first oil tank 1 for filling the aircraft oil tank assembly 100 with oil. When the aircraft tank assembly 100 is mounted on the wing, the oil filling port 11 is connected with an oil port on the wing for connecting an external oil pipe. The first oil outlet and the first air vent are positioned on one end surface of the first oil tank 1.
The second oil tank 2 comprises a first oil inlet, an oil supply port, an oil return port and a second ventilation port. The first oil inlet and the second vent are positioned on one end surface of the second oil tank 2, and the oil supply port and the oil return port are positioned on the other end surface of the second oil tank 2. The fuel supply port is used for supplying fuel in the aircraft tank assembly 100 to the engine, and the fuel return port is used for returning excess fuel of the engine to the aircraft tank assembly 100. The first oil outlet is connected with the first oil inlet, the first air vent is connected with the second air vent, and the first oil tank 1 is connected with the second oil tank 2. In this embodiment, when the aircraft fuel tank assembly 100 is mounted on the wing, the first fuel tank 1 is located slightly higher than the second fuel tank 2, so that the fuel in the first fuel tank 1 can flow to the second fuel tank 2 through the first oil outlet and the first oil inlet.
The first oil outlet is connected with the first oil inlet and is connected with the first oil inlet through an oil-resistant hose 3, and the first air vent is connected with the second air vent and is connected with the second air vent through an air vent hose. The adjacent fuel tanks are flexibly communicated, so that the modularized aircraft fuel tank assembly 100 can adapt to various deformations of wings under pneumatic load, and the safety of the fuel tanks is improved.
The modular aircraft tank assembly 100 also includes a temperature sensor, a vent balancing valve, and a fuel level sensor. The temperature sensor is used for the temperature of the fuel in the aircraft fuel tank assembly 100. Optionally, a temperature sensor is provided on the second fuel tank 2 to facilitate detection of the temperature of the fuel within the aircraft fuel tank assembly 100. The vent balancing valve is used to balance the air pressure inside the aircraft tank assembly 100 with the outside. Optionally, a ventilation balance valve is arranged on the first fuel tank 1, the ventilation balance valve is communicated with outside air, and the expansion space at the top of the connected fuel tank is communicated through a ventilation hose, so that the balance between the inside of the aircraft fuel tank assembly 100 and the outside air pressure is ensured, and negative pressure is prevented from being formed in the aircraft fuel tank assembly 100 due to the consumption of fuel. The fuel level sensor is used to detect the amount of fuel within the aircraft fuel tank assembly 100. The temperature sensor, the ventilation balance valve and the oil quantity sensor are all selected from existing elements.
The modularized aircraft fuel tank assembly 100 of the embodiment can be installed in a wing rib of a wing, so that fuel leakage caused by easy damage of a wing leading edge or a skin of an existing fuel tank structure is avoided, and the safety of the aircraft is improved.
According to an optional technical scheme of this application, two sides of first oil tank 1 and two sides of second oil tank 2 are the cambered surface. The first and second fuel tanks 1, 2 are approximately racetrack shaped in cross-section to facilitate the installation of the aircraft fuel tank assembly 100 into the mounting holes of the wing ribs. The cross-sections of the first and second tanks 1, 2 may be provided in other shapes as needed.
According to an alternative embodiment of the present application, the modular aircraft tank assembly 100 further comprises a first lightning protection sheet 51. One end of the first lightning protection sheet 51 is connected to the first oil tank 1, and the other end is connected to the second oil tank 2. The first lightning protection sheet 51 is connected with the first oil tank 1 and the second oil tank 2, so that the potentials of the first oil tank 1 and the second oil tank 2 can be kept equal, and the safety of the aircraft oil tank assembly 100 is improved.
As shown in fig. 3, according to an alternative embodiment of the present application, the modular aircraft tank assembly 100 further comprises a third tank 6. The third oil tank 6 serves as a range-extended oil tank for storing range-extended fuel oil. The third tank 6 is provided between the first tank 1 and the second tank 2. The third oil tank 6 comprises a second oil inlet, a second oil outlet, a third air port and a fourth air port, the second oil inlet and the third air port are arranged on the end face, close to the first oil tank 1, of the third oil tank 6, and the second oil outlet and the fourth air port are arranged on the end face, close to the second oil tank 2, of the third oil tank 6. The first oil outlet of the first oil tank 1 is connected with the second oil inlet of the third oil tank 6, the second oil outlet of the third oil tank 6 is connected with the first oil inlet of the second oil tank 2, the first air vent of the first oil tank 1 is connected with the third air vent of the third oil tank 6, and the fourth air vent of the third oil tank 6 is connected with the second air vent of the second oil tank 2. All connect through resistant oily hose between each oil inlet and the oil-out, all connect through the breather hose between each blow vent, realize the flexonics between the adjacent oil tank.
The modularized aircraft fuel tank assembly 100 of the application only needs to set the third fuel tank 6 between the first fuel tank 1 and the second fuel tank 2 when fuel with extended range is needed, and the third fuel tank is communicated with the second fuel tank 2. This application modular increases journey oil tank can install fast on the basis of first oil tank 1 and second oil tank 2, and is with low costs, need not reequip convenient operation to first oil tank 1 and second oil tank 2.
According to an optional technical scheme of this application, both sides of third oil tank 6 are the cambered surface. The third tank 6 has the same cross-sectional shape as the first and second tanks 1 and 2, and facilitates the installation of the aircraft tank assembly 100.
According to an alternative aspect of the present application, the modular aircraft tank assembly 100 further includes a second lightning protection sheet 52 and a third lightning protection sheet 53. One end of the second lightning protection sheet 52 is connected with the first oil tank 1, and the other end is connected with the third oil tank 6. One end of the third lightning protection sheet 53 is connected with the third oil tank 6, and the other end is connected with the second oil tank 2. Through setting up the lightning protection piece for the electric potential of a plurality of fuel tanks equals in aircraft tank subassembly 100, improves aircraft tank subassembly 100's security.
According to an alternative embodiment of the present application, the modular aircraft tank assembly 100 further comprises a fuel drain valve. Since the second tank 2 is located at the lowest position, a drain valve is provided on the second tank 2, and the drain valve is used for discharging deposits in the aircraft tank assembly 100 and also for discharging fuel in the aircraft tank assembly 100.
According to an alternative embodiment of the present application, the modular aircraft tank assembly 100 further comprises a low oil level switch, which is arranged on the second tank 2. The fuel in the aircraft tank assembly 100 is gradually reduced with use, and when the fuel quantity is lower than a preset value, the low fuel level switch sends out an alarm signal for reminding a pilot that the aircraft has a small residual fuel quantity.
Optionally, the fuel tanks are made of light materials such as aluminum alloy or nylon, so as to reduce the weight of the modular aircraft fuel tank assembly 100.
Example 2
The present embodiment provides an aircraft comprising a modular aircraft tank assembly 100 and a wing as described above. The wing rib of the wing is provided with a mounting hole corresponding to the aircraft tank assembly 100, and the aircraft tank assembly 100 is arranged in the wing rib. The aircraft tank assembly 100 is supported by a plurality of ribs.
Alternatively, for a wing in a double spar configuration, the aircraft tank assembly 100 is mounted within the rib intermediate the two spars, the aircraft tank assembly 100 being protected by the remaining high strength double spar. For a wing with a single spar configuration, the aircraft tank assembly 100 is mounted in the rib intermediate the spars and longitudinal walls, and the aircraft tank assembly 100 is protected by the spars and longitudinal walls which have high residual strength.
The modularized aircraft fuel tank assembly 100 of the embodiment has high reliability in fuel storage, avoids fuel leakage caused by slight damage, scratch and other accidental conditions of the front edge of the wing and the skin, reduces the possibility of direct damage and leakage of the fuel tank when the aircraft accidentally falls into the ground, and improves the viability of a driver and passengers.
According to an alternative embodiment of the present application, spacers 7 are provided at locations of the aircraft tank assembly 100 corresponding to the ribs. Optionally, the spacers 7 are rubber spacers and are adhered to the outer wall of each fuel tank to prevent the fuel tank from being scratched due to direct contact with the wing ribs.
The embodiments of the present application are described in detail above. The principle and the implementation of the present application are explained herein by applying specific examples, and the above description of the embodiments is only used to help understand the technical solutions and the core ideas of the present application. Therefore, the person skilled in the art should, according to the idea of the present application, change or modify the embodiments and applications of the present application based on the scope of protection of the present application. In view of the above, the description should not be taken as limiting the application.
Claims (9)
1. A modular aircraft fuel tank assembly, the aircraft fuel tank assembly being provided in a wing rib of a wing, the aircraft fuel tank assembly comprising: the device comprises a first oil tank, a second oil tank, a third oil tank, a temperature sensor, a ventilation balance valve and an oil mass sensor; the first oil tank comprises an oil filling port, a first oil outlet and a first air vent;
the second oil tank comprises a first oil inlet, an oil supply port, an oil return port and a second ventilation port, the oil supply port is used for conveying fuel oil to the engine, and the oil return port is used for enabling redundant fuel oil of the engine to flow back to the aircraft oil tank assembly;
when the aircraft does not need range-extending fuel oil, the first oil outlet is connected with the first oil inlet, and the first air vent is connected with the second air vent;
the third oil tank comprises a second oil inlet, a second oil outlet, a third air port and a fourth air port;
when the aircraft needs range-extending fuel oil, the third fuel tank is arranged between the first fuel tank and the second fuel tank, the first oil outlet is connected with the second oil inlet, the second oil outlet is connected with the first oil inlet, the first vent hole is connected with the third vent hole, and the fourth vent hole is connected with the second vent hole;
the temperature sensor is used for detecting the temperature of fuel oil in the aircraft fuel tank assembly;
the ventilation balance valve is used for balancing the air pressure inside the aircraft oil tank assembly and the outside;
the fuel quantity sensor is used for detecting the fuel quantity in the aircraft fuel tank assembly;
the first reservoir is higher than the second reservoir so that fuel in the first reservoir can flow to the second reservoir.
2. The modular aircraft tank assembly of claim 1, wherein both side surfaces of the first tank and both side surfaces of the second tank are curved surfaces.
3. The modular aircraft fuel tank assembly of claim 1 further comprising a first lightning protection sheet, both ends of said first lightning protection sheet being connected to said first fuel tank and said second fuel tank, respectively, when extended range fuel is not required for the aircraft.
4. The modular aircraft tank assembly of claim 1, further comprising a fuel drain valve disposed on the second tank.
5. The modular aircraft tank assembly of claim 1, further comprising a low oil level switch disposed on the second tank.
6. A modular aircraft tank assembly as claimed in claim 1, in which both side faces of the third tank are cambered surfaces.
7. The modular aircraft fuel tank assembly of claim 4, further comprising a second lightning protection sheet and a third lightning protection sheet, wherein when the aircraft requires extended range fuel, two ends of the second lightning protection sheet are connected to the first fuel tank and the third fuel tank respectively, and two ends of the third lightning protection sheet are connected to the third fuel tank and the second fuel tank respectively.
8. An aircraft, comprising the modularized aircraft oil tank assembly of any one of claims 1 to 7 and a wing, wherein a rib of the wing is provided with a mounting hole corresponding to the aircraft oil tank assembly, and the aircraft oil tank assembly is arranged in the rib.
9. An aircraft according to claim 8, wherein the aircraft tank assembly is provided with spacers corresponding to the location of the ribs.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011326419.8A CN112537456B (en) | 2020-11-24 | 2020-11-24 | Modular aircraft tank subassembly and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011326419.8A CN112537456B (en) | 2020-11-24 | 2020-11-24 | Modular aircraft tank subassembly and aircraft |
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| Publication Number | Publication Date |
|---|---|
| CN112537456A CN112537456A (en) | 2021-03-23 |
| CN112537456B true CN112537456B (en) | 2022-10-21 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202011326419.8A Active CN112537456B (en) | 2020-11-24 | 2020-11-24 | Modular aircraft tank subassembly and aircraft |
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Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113148195B (en) * | 2021-04-26 | 2022-12-02 | 浙江万丰飞机制造有限公司 | General aircraft fuel tank of aviation kerosene fixed wing |
Family Cites Families (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1153040A (en) * | 1966-06-14 | 1969-05-21 | United Aircraft Corp | Improvements in and relating to an Auxillary Fuel System Especially for Aircraft |
| JP5487093B2 (en) * | 2010-12-17 | 2014-05-07 | 三菱航空機株式会社 | Lightning-resistant fastener, lightning-proof fastener mounting structure, aircraft |
| CN106240351A (en) * | 2016-08-09 | 2016-12-21 | 南京金龙客车制造有限公司 | A kind of fuel tank of passenger car assembly |
| CN107336838B (en) * | 2017-08-17 | 2023-11-14 | 绍兴宝旌复合材料有限公司 | Unmanned aerial vehicle oil tank |
| CN207050950U (en) * | 2017-08-25 | 2018-02-27 | 中国航空工业集团公司沈阳飞机设计研究所 | The fuel tank analogue means and wing model of a kind of flutter wind tunnel model |
| CN108674674B (en) * | 2018-05-25 | 2023-09-26 | 中国科学院工程热物理研究所 | Uncontrolled type strategy oil consumption tank suitable for supersonic unmanned aerial vehicle and unmanned aerial vehicle |
| CN209258408U (en) * | 2018-12-24 | 2019-08-16 | 沈阳旋飞航空技术有限公司 | A kind of UAV Fuel system |
| CN210970664U (en) * | 2019-08-30 | 2020-07-10 | 潍柴(扬州)亚星新能源商用车有限公司 | Double-oil-tank oil supply system for vehicle |
| CN111137830A (en) * | 2020-01-17 | 2020-05-12 | 中国人民解放军陆军勤务学院 | Open-air flexible modularization combination formula oil tank group |
| CN111746807A (en) * | 2020-07-09 | 2020-10-09 | 中国人民解放军总参谋部第六十研究所 | Series-parallel hybrid oil circuit system for unmanned aerial vehicle |
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Inventor after: Sheng Wenxing Inventor after: Chen Fangyu Inventor after: Liang Xiaofei Inventor before: Sheng Wenxing |
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