CN207712306U - A kind of hydrogen fuel aircraft - Google Patents
A kind of hydrogen fuel aircraft Download PDFInfo
- Publication number
- CN207712306U CN207712306U CN201721845991.9U CN201721845991U CN207712306U CN 207712306 U CN207712306 U CN 207712306U CN 201721845991 U CN201721845991 U CN 201721845991U CN 207712306 U CN207712306 U CN 207712306U
- Authority
- CN
- China
- Prior art keywords
- pipeline
- hydrogen fuel
- liquid hydrogen
- storage tank
- wing
- 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.)
- Expired - Fee Related
Links
- 229910052739 hydrogen Inorganic materials 0.000 title claims abstract description 73
- 239000001257 hydrogen Substances 0.000 title claims abstract description 73
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 title claims abstract description 64
- 239000000446 fuel Substances 0.000 title claims abstract description 60
- 239000007788 liquid Substances 0.000 claims abstract description 42
- 150000002431 hydrogen Chemical class 0.000 claims abstract description 9
- 230000008676 import Effects 0.000 claims abstract description 4
- 239000000463 material Substances 0.000 claims description 7
- 239000006260 foam Substances 0.000 claims description 5
- 229910001069 Ti alloy Inorganic materials 0.000 claims description 3
- 239000000956 alloy Substances 0.000 claims description 3
- UUAGAQFQZIEFAH-UHFFFAOYSA-N chlorotrifluoroethylene Chemical group FC(F)=C(F)Cl UUAGAQFQZIEFAH-UHFFFAOYSA-N 0.000 claims description 3
- 229920000573 polyethylene Polymers 0.000 claims description 3
- 238000002309 gasification Methods 0.000 abstract description 2
- 230000007704 transition Effects 0.000 abstract description 2
- 230000000694 effects Effects 0.000 description 9
- 238000010586 diagram Methods 0.000 description 8
- 239000002828 fuel tank Substances 0.000 description 5
- 238000000034 method Methods 0.000 description 4
- 230000008901 benefit Effects 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 238000002485 combustion reaction Methods 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- 239000004698 Polyethylene Substances 0.000 description 1
- 230000003749 cleanliness Effects 0.000 description 1
- 239000000571 coke Substances 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 230000010429 evolutionary process Effects 0.000 description 1
- 239000002803 fossil fuel Substances 0.000 description 1
- 239000003208 petroleum Substances 0.000 description 1
- -1 polyethylene Polymers 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 239000002937 thermal insulation foam Substances 0.000 description 1
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
- B64D37/30—Fuel systems for specific fuels
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
The utility model discloses a kind of hydrogen fuel aircraft.The hydrogen fuel aircraft includes：Liquid Hydrogen fuel storage tank, liquid hydrogen transfer pipeline, wing and fuselage；Liquid Hydrogen fuel storage tank is located in the lower layer space of fuselage；Liquid Hydrogen fuel storage tank includes multiple storage tanks, is located at the front, middle part and rear portion of fuselage；Liquid hydrogen transfer pipeline includes the first pipeline and the second pipeline；First pipeline includes multiple pipelines, and the pipeline of the first pipeline is for being connected to two adjacent storage tanks；The import of second pipeline and the Liquid Hydrogen fuel storage tank of waist connect；The fuel inlet of the outlet connection engine of second pipeline, the pipeline of the second pipeline are fixed on the leading edge portion of wing.The hydrogen fuel aircraft of the utility model uses liquid hydrogen for fuel, pollution-free, energy-saving and emission-reduction.By the reasonable Arrangement of liquid hydrogen conveyance conduit, the temperature of the leading edge of a wing is reduced using absorbing heat in liquid hydrogen gasification, postpones the generation of aerofoil surface flow transition, and then reduce the resistance suffered by aircraft, aeroplane performance is promoted, improves economy.
Description
Technical field
The utility model is related to aircraft circles, more particularly to a kind of hydrogen fuel aircraft.
Background technology
Modern aircraft is mainly using petroleum-type product as fuel.Oil is as a kind of non-renewable energy resources inner face in the world
Face exhausted danger.Meanwhile the burning of oil fuel causes greatly to pollute to environment, the generation to global greenhouse effect
Bear substantial responsibility.Future aircraft design to energy-saving and emission-reduction etc., more stringent requirements are proposed, various substitute fuel schemes meet the tendency of and
It is raw.
Hydrogen generates water again after extracting, burning in water, is " renewable formula " energy different from petroleum fuel.Hydrogen energy source
Major advantage has：Combustion heat value is high, the heat of 142.35 kilojoules, about the 3 of oil times is released after every kilogram of hydrogen burning, actually
3.9 times, 4.5 times of coke；Cleanliness without any pollution；Resourceful, there are about 1.4 × 10 for the hydrogen contained in immense ocean17Ton, calorific potential
It is 9000 times of fossil fuel on the earth.Therefore, the utility model provides a kind of hydrogen fuel aircraft, using hydrogen as fuel, realizes section
The effect of energy emission reduction.
Invention content
The purpose of this utility model is to provide a kind of hydrogen fuel aircraft, the effect realized energy-saving and emission-reduction, reduce pollution.
To achieve the above object, the utility model provides following scheme：
A kind of hydrogen fuel aircraft, the hydrogen fuel aircraft include：Liquid Hydrogen fuel storage tank, liquid hydrogen transfer pipeline, wing and machine
Body；The Liquid Hydrogen fuel storage tank is located in the lower layer space of the fuselage；
The Liquid Hydrogen fuel storage tank includes multiple storage tanks, is located at the front, middle part and rear portion of the fuselage；
The liquid hydrogen transfer pipeline includes the first pipeline and the second pipeline；
First pipeline includes multiple pipelines, and the pipeline of first pipeline is for being connected to two adjacent storage tanks；
The import of second pipeline is connect with the storage tank of the waist；The outlet connection of second pipeline is started
The pipeline of the fuel inlet of machine, second pipeline is fixed on the leading edge portion of the wing.
Optionally, the Liquid Hydrogen fuel storage tank specifically includes：Internal face, intermediate filling layer and outside wall surface；The internal face
For chlorotrifluoroethylene or polythene material；The intermediate filling layer is foam-filled layer；The outside wall surface is titanium alloy material.
Optionally, the pipeline of second pipeline is the pipeline of U-shaped.
Optionally, the pipeline of second pipeline is the pipeline of detour shape.
Optionally, the angle of sweep angle of the wing is 17 degree, and the aerofoil profile of the wing is laminar flow airfoil.
According to specific embodiment provided by the utility model, the utility model discloses following technique effects：
Use liquid hydrogen for fuel, pollution-free, energy-saving and emission-reduction.Since liquid hydrogen needs to gasify before combustion, this is needed in the process
Absorb a large amount of heat, the utility model is by the reasonable Arrangement of liquid hydrogen conveyance conduit, using absorbing heat in liquid hydrogen gasification
The temperature of the leading edge of a wing is reduced, the generation for turning to twist of aerofoil surface flowing is postponed using generated temperature gradient, in machine
Wing surface realizes larger range of Laminar Flow, and then reduces the resistance suffered by aircraft, promotes aeroplane performance, improves economy
Property.
Description of the drawings
In order to illustrate the embodiment of the utility model or the technical proposal in the existing technology more clearly, below will be to embodiment
Needed in attached drawing be briefly described, it should be apparent that, the accompanying drawings in the following description is only the utility model
Some embodiments for those of ordinary skill in the art without having to pay creative labor, can also basis
These attached drawings obtain other attached drawings.
Fig. 1 is the structural schematic diagram of the utility model hydrogen fuel aircraft embodiment 1；
Fig. 2 is the structural schematic diagram of the utility model hydrogen fuel aircraft embodiment 2；
Fig. 3 is the structural schematic diagram of the Liquid Hydrogen fuel storage tank of the utility model hydrogen fuel aircraft；
Fig. 4 is to turn to twist the schematic diagram for postponing effect in position to Airfoil Sections in the utility model hydrogen fuel aircraft.
Specific implementation mode
The following will be combined with the drawings in the embodiments of the present invention, carries out the technical scheme in the embodiment of the utility model
Clearly and completely describe, it is clear that the described embodiments are only a part of the embodiments of the utility model, rather than whole
Embodiment.Based on the embodiments of the present invention, those of ordinary skill in the art are without making creative work
The every other embodiment obtained, shall fall within the protection scope of the present invention.
To keep the above objects, features, and advantages of the utility model more obvious and easy to understand, below in conjunction with the accompanying drawings and have
Body embodiment is described in further detail the utility model.
Fig. 1 is the structural schematic diagram of the utility model hydrogen fuel aircraft embodiment 1.In order to keep the feature of the utility model bright
Aobvious understandable, Fig. 1 is only labelled with significant components, other specific components about hydrogen fuel aircraft, is not indicated in Fig. 1.Such as Fig. 1
Shown, the hydrogen fuel aircraft includes：
Liquid Hydrogen fuel storage tank (1-1,1-2,1-3), liquid hydrogen transfer pipeline (2-1 and 2-2), wing 3 and fuselage 4；The liquid
Hydrogen fuel storage tank is located in the lower layer space of the fuselage.
The Liquid Hydrogen fuel storage tank includes multiple storage tanks, is located at the front, middle part and rear portion of the fuselage 4；In figure
For 3, Liquid Hydrogen fuel storage tank 1-1 is located at the front of fuselage 4, and Liquid Hydrogen fuel storage tank 1-2 is located at the middle part of fuselage 4, liquid hydrogen
Fuel tank 1-3 is located at the rear portion of fuselage 4.The structure of fuel tank is divided into internal face, intermediate filling layer, three layers of outside wall surface, interior
Wall surface uses low temperature material, such as chlorotrifluoroethylene or superhigh molecular weight polyethylene material, intermediate filling layer to be filled out for foam
Filling to transmit for reducing heat keeps liquid hydrogen low temperature, outside wall surface to ensure fuel tank using the material with higher stiffness and intensity
It is firm, such as titanium alloy material.
The liquid hydrogen transfer pipeline includes the first pipeline 2-1 and the second pipeline 2-2；The first pipeline 2-1 includes multiple
Pipeline, the pipeline of the first pipeline 2-1 is for being connected to two adjacent storage tanks；The import of the second pipeline 2-2 with it is described
The Liquid Hydrogen fuel storage tank 1-2 connections at 4 middle part of fuselage；The fuel inlet 5 of the outlet connection engine of the second pipeline 2-2, institute
The pipeline for stating the second pipeline 2-2 is fixed on the leading edge portion of the wing.The pipeline of the second pipeline 2-2 in the present embodiment is U
The pipeline of shape.
The angle of sweep angle of wing 3 is 17 degree in the utility model, and the aerofoil profile of wing 3 is laminar flow airfoil.In airliner
The early stage of evolutionary process, the introducing of swept-back wing concept postpone drag divergence by improving critical Mach number to weaken shock strength,
So that high transonic speed (Mach 0.8-0.85) is flown, if but more than drag divergence Mach number, pneumatic efficiency is with regard to big
It is big to reduce.The combination of swept-back wing and supercritical airfoil, from greatly enhancing drag divergence Mach number so that have higher
The high transonic flight of efficiency is achieved, this has also caused the angle of sweep of airliner to be locked in the range of 30 ° or so.Separately
On the one hand, in airliner flight Reynolds number (about 108Magnitude) under the conditions of, swept-back wing and its surface pressure around supercritical airfoil
Distribution causes frictional resistance to be much higher than laminar sublayer so that around wing boundary layer inevitably with turbulent flow property, this
It is that leading edge attached wire turns to twist and boundary-layer opens up unstability to stream because swept-back wing easily promotes.Studies have shown that when angle of sweep is low
When 25 °, determine that the principal element for turning to twist is Tollmien-Schlichting (T-S) unstability.When angle of sweep is more than 30 °
When, Crossflow Instabilities begin to embody.The unstability of attached wire is not only related with angle of sweep, but also can be by machine
The influence of nose of wing radius.So although swept-back wing has positive influences to improving drag divergence Mach number, it is also serious simultaneously
The application of natural laminar flow aerofoil profile and wing is limited to.The advantages of when angle of sweep is larger, which is the cruise Mach number of aircraft, to compare
Height, but the larger aerofoil surface fluidised form in angle of sweep can be turned to twist to be influenced (cross flow transition) by crossing current, it is unfavorable
In the realization of laminarization, so leading edge of a wing angle of sweep is reduced to 17 °, and laminar flow airfoil is used, weakens crossing current and turn the influence twisted,
Be conducive to the realization of aerofoil surface laminarization, while needing the cruise Mach number appropriate for reducing aircraft.
According to specific embodiment provided by the utility model, the utility model discloses following technique effects：Utilize fuselage
Lower layer space stores Liquid Hydrogen fuel, and upper space is for object or the personnel's seating of freighting.Three fuel before, during and after being respectively set
Storage tank, fuel tank are divided into internal face, intermediate foam filled layer, three layers of outside wall surface, and internal face uses low temperature material, middle layer
Liquid hydrogen low temperature, outside wall surface is kept to ensure using the material with higher stiffness and intensity for foam-filled transmitted for reducing heat
Fuel tank it is firm；Turn to twist the influence for flowing wing to weaken crossing current by the way that wing setting is reduced to 17 °；Liquid hydrogen is led to
Piping is recycled in wing close to up-front position, causes aerofoil surface temperature near the leading edge of a wing low by absorbing heat
In incoming static temperature, to postpone the generation for turning to twist, achievees the effect that reduce frictional resistance, promotes flying qualifies of aircraft.
Fig. 2 is the structural schematic diagram of the utility model hydrogen fuel aircraft embodiment 2.Figure label is corresponding with Fig. 1,
In, unlike Fig. 1：The pipeline of the second pipeline 2-2 is the pipeline of detour shape in the present embodiment.
Fig. 3 is the structural schematic diagram of the Liquid Hydrogen fuel storage tank of the utility model hydrogen fuel aircraft.As shown, Liquid Hydrogen fuel
The structure of storage tank is divided into internal face, heat insulation foam filled layer (intermediate filling layer), three layers of outside wall surface.
Fig. 4 is to turn to twist the schematic diagram for postponing effect in position to Airfoil Sections in the utility model hydrogen fuel aircraft.As schemed
Show, liquid hydrogen is recycled in wing close to up-front position by pipeline, makes machine near the leading edge of a wing by absorbing heat
Thriving face temperature is less than incoming static temperature, to postpone the generation for turning to twist, reaches and reduces frictional resistance, promotes flying qualifies of aircraft
Effect.
Each embodiment is described by the way of progressive in this specification, the highlights of each of the examples are with other
The difference of embodiment, just to refer each other for identical similar portion between each embodiment.
Specific case used herein is expounded the principles of the present invention and embodiment, above example
Explanation be merely used to help understand the method and its core concept of the utility model；Meanwhile for the general technology of this field
Personnel, according to the thought of the utility model, there will be changes in the specific implementation manner and application range.In conclusion
The content of the present specification should not be construed as a limitation of the present invention.
Claims (5)
1. a kind of hydrogen fuel aircraft, which is characterized in that the hydrogen fuel aircraft includes：Liquid Hydrogen fuel storage tank, liquid hydrogen transfer pipeline,
Wing and fuselage；The Liquid Hydrogen fuel storage tank is located in the lower layer space of the fuselage；
The Liquid Hydrogen fuel storage tank includes multiple storage tanks, is located at the front, middle part and rear portion of the fuselage；
The liquid hydrogen transfer pipeline includes the first pipeline and the second pipeline；
First pipeline includes multiple pipelines, and the pipeline of first pipeline is for being connected to two adjacent storage tanks；
The import of second pipeline is connect with the storage tank of the waist；The outlet connection engine of second pipeline
The pipeline of fuel inlet, second pipeline is fixed on the leading edge portion of the wing.
2. hydrogen fuel aircraft according to claim 1, which is characterized in that the Liquid Hydrogen fuel storage tank specifically includes：Inner wall
Face, intermediate filling layer and outside wall surface；The internal face is chlorotrifluoroethylene or polythene material；The intermediate filling layer is bubble
Foam filled layer；The outside wall surface is titanium alloy material.
3. hydrogen fuel aircraft according to claim 1, which is characterized in that the pipeline of second pipeline is the pipeline of U-shaped.
4. hydrogen fuel aircraft according to claim 1, which is characterized in that the pipeline of second pipeline is the pipe of detour shape
Road.
5. hydrogen fuel aircraft according to claim 1, which is characterized in that the angle of sweep angle of the wing is 17 degree, institute
The aerofoil profile for stating wing is laminar flow airfoil.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721845991.9U CN207712306U (en) | 2017-12-26 | 2017-12-26 | A kind of hydrogen fuel aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721845991.9U CN207712306U (en) | 2017-12-26 | 2017-12-26 | A kind of hydrogen fuel aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207712306U true CN207712306U (en) | 2018-08-10 |
Family
ID=63049996
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721845991.9U Expired - Fee Related CN207712306U (en) | 2017-12-26 | 2017-12-26 | A kind of hydrogen fuel aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207712306U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107972877A (en) * | 2017-12-26 | 2018-05-01 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of hydrogen fuel aircraft |
| FR3096029A1 (en) * | 2019-09-16 | 2020-11-20 | Airbus | AIRCRAFT CONTAINING HYDROGEN TANKS |
| EP4253252A1 (en) * | 2022-03-29 | 2023-10-04 | Airbus Operations Limited | An aircraft |
| US11905028B2 (en) | 2021-01-19 | 2024-02-20 | Rolls-Royce Plc | Aircraft comprising hydrogen storage tanks |
-
2017
- 2017-12-26 CN CN201721845991.9U patent/CN207712306U/en not_active Expired - Fee Related
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107972877A (en) * | 2017-12-26 | 2018-05-01 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of hydrogen fuel aircraft |
| CN107972877B (en) * | 2017-12-26 | 2024-03-15 | 中国空气动力研究与发展中心高速空气动力研究所 | Hydrogen fuel aircraft |
| FR3096029A1 (en) * | 2019-09-16 | 2020-11-20 | Airbus | AIRCRAFT CONTAINING HYDROGEN TANKS |
| US11905028B2 (en) | 2021-01-19 | 2024-02-20 | Rolls-Royce Plc | Aircraft comprising hydrogen storage tanks |
| EP4253252A1 (en) * | 2022-03-29 | 2023-10-04 | Airbus Operations Limited | An aircraft |
| GB2617108A (en) * | 2022-03-29 | 2023-10-04 | Airbus Operations Ltd | An aircraft |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20180810 Termination date: 20201226 |