CN106628114A - Integrated unmanned aerial vehicle wing - Google Patents
Integrated unmanned aerial vehicle wing Download PDFInfo
- Publication number
- CN106628114A CN106628114A CN201610885444.7A CN201610885444A CN106628114A CN 106628114 A CN106628114 A CN 106628114A CN 201610885444 A CN201610885444 A CN 201610885444A CN 106628114 A CN106628114 A CN 106628114A
- Authority
- CN
- China
- Prior art keywords
- storage tank
- high pressure
- rib
- under high
- fuel
- 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.)
- Granted
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/34—Tanks constructed integrally with wings, e.g. for fuel or water
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/18—Spars; Ribs; Stringers
- B64C3/187—Ribs
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Remote Sensing (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
- Fuel Cell (AREA)
Abstract
The invention discloses an integrated unmanned aerial vehicle wing. The integrated unmanned aerial vehicle wing comprises a high-pressure fuel storage tank, skin, wing ribs and a back wall, wherein hydrogen and oxygen are stored in the high-pressure fuel storage tank; the high-pressure fuel storage tank is used for providing fuel for the whole airplane; and the skin wraps the high-pressure fuel storage tank, the wing ribs and the back wall to from the skeleton of the integrated unmanned aerial vehicle wing. Therefore, the integrated unmanned aerial vehicle wing can improve the fuel storage quality efficiency of the gas fuel aircraft and reduce the structure weight coefficient of the aircraft.
Description
Technical field
The present invention relates to Aerospace Engineering technical field of structures, particularly relates to a kind of integrated unmanned plane wing.
Background technology
Hydrogen energy source is generally acknowledged clean energy resource, has mass energy density high compared to traditional fossil energy, pollution-free,
The advantages of utilization rate is high, is one of direction of the most potential energy development of future aircraft, and hydrogen calorific value is up to 143MJ/kg, is carbon
Nearly 3 times, 240 times of lithium battery of hydrogen fuel, are the theoretical upper limits of all chemical energy source specific energies.Carrying identical quality fuels
In the case of, hydrogen energy source aircraft cruising time up to 3 times of hydrocarbon fuel aircraft, or in cruising time constant premise
Under, the fuel carrying amount of aircraft is reduced, increase payload weight, adapt to the mission requirements of diversification.
Under usual conditions, the density very little (being 0.0899g/L under gaseous state, be 70.8kg/m3 during liquid) of hydrogen, in order to improve
The quality efficiency of gaseous fuel storage, more using two ways, first gas liquefaction storage, and using efficient Thermo Isolation Technique
The heat exchange of liquid fuel and the external world is reduced as far as possible so as in being maintained at the environment of extremely low temperature for a long time, while storage tank is still suffered from
Pressure caused by micro leakage heat produced by liquid gas evaporation gasification.Its two be high-pressure gaseous storage, typically store pressure
All in more than 15MPa, current highest stores pressure up to 70MPa-100MPa.As can be seen that both storage modes are required
Storage tank intensity is high and with strict air-tightness, so as to bring larger construction weight so that the quality efficiency of fuel storage
It is difficult to improve.
As can be seen that either being stored in the way of high pressure gas hydrogen on board the aircraft, or stored all in the way of liquid hydrogen
Need quality big, bulky fuel reservoir, so as to occupy very big space in interior of aircraft, causes hydrogen energy source airframe
It is big compared with traditional energy airframe diameter, head resistance increase.Meanwhile, the pressure-resistance structure of fuel reservoir needs to pay very big matter
Amount cost.Therefore, no matter consider from the quality of pressure storage tank itself, or consider from the increase of resistance, be reduced hydrogen energy source
The actual gain brought.
The content of the invention
In view of this, it is an object of the invention to propose a kind of integrated unmanned plane wing, it is possible to increase gaseous fuel flies
The fuel storage quality efficiency of row device, reduces the airframe-to-fuel weight ratio of unmanned plane.
There is provided integrated unmanned plane wing based on the above-mentioned purpose present invention, including fuel under high pressure storage tank, covering, rib and
Wall afterwards；Be stored with hydrogen and oxygen in described fuel under high pressure storage tank, for providing fuel for whole aircraft；Described covering bag
Wrap the skeleton of integrated unmanned plane wing described in the fuel under high pressure storage tank, the rib and the rear wall construction.
In some embodiments of the invention, including between the plural rib, and each described rib mutually
The parallel and spaced arrangement of tool；
Two or more fuel under high pressure storage tank is arranged in series into into a row in the integrated unmanned plane wing, each column is high
Pressurized fuel storage tank sequentially passes through each described rib, and the rear wall sequentially passes through the rearward end of each rib.
In some embodiments of the invention, also including stringer, and the institute being arranged in parallel with the fuel under high pressure storage tank
State stringer to be buckled in successively on each described rib.
In some embodiments of the invention, described stringer is designed as：It is corresponding according to symmetrical shape up and down in rib
Formula is disposed with two stringers, is that a stringer is buckled in successively on the upper surface of each rib, laterally zygomorphic another purlin
Bar is buckled in successively on the lower surface of each rib；
Also, the spacing of two stringers of arrangement symmetrical above and below and two stringers of adjacent arrangement symmetrical above and below is according to institute
State the buckling critical stress of covering to determine.
In some embodiments of the invention, be designed with lightening hole on the rib, design structure height less and
Position with intensity surplus, while being used to provide space for aircraft wing internal wiring laying.
In some embodiments of the invention, storage tank pilot hole is designed with the rib, for fuel under high pressure storage tank
Assembling positioning datum, while mitigate rib construction weight.
In some embodiments of the invention, the storage tank pilot hole is big straight using the structure height design of the rib
Footpath pilot hole, for obtaining the fuel under high pressure storage tank of large volume.
In some embodiments of the invention, the fuel under high pressure storage tank include tank wall, attachment lug, air inlet and
Gas outlet；Wherein, the attachment lug that connects through two-by-two between fuel under high pressure storage tank is realized, and the tank wall head
2-6 attachment lug of arrangement, the tank wall afterbody arranges 2-6 attachment lug；Also, fuel under high pressure storage tank is described
The attachment lug of tank wall head is mutually embedded in the attachment lug of the tank wall afterbody of another fuel under high pressure storage tank, most
Punch on attachment lug afterwards, firmly connection is realized by connecting bolt；
In addition, the air inlet of fuel under high pressure storage tank is used as the entrance that ground fills fuel gas, fuel under high pressure storage tank
Gas outlet use as the supply outlet of fuel；Gas transfer pipeline is installed additional outside each fuel under high pressure storage tank, from the outlet
Mouth is drawn, then the other end of these single gas transfer pipelines is connected on gas delivery main road, by gas delivery main
Fuel cell on road direction unmanned aerial vehicle provides fuel.
In some embodiments of the invention, if the fuel under high pressure storage tank is applied to high-altitude, be divided into hydrogen-holder with
Oxygen storage tank, and the volume ratio of hydrogen-holder and oxygen storage tank can be set according to the needs of different situations；If the high compression ignition
Material storage tank is applied to low-to-medium altitude, then entirely hydrogen-holder.
From the above it can be seen that a kind of integrated unmanned plane wing that the present invention is provided, by fuel under high pressure storage tank
In be stored with hydrogen and oxygen, for providing fuel for whole aircraft；Covering wraps the fuel under high pressure storage tank, the rib
And the skeleton of integrated unmanned plane wing described in the rear wall construction.So as to the present invention can realize reducing wing structure weight
The purpose of amount, and the fuel oil coefficient (weight of fuel/main screw lift) of unmanned plane is increased, fuel storage quality is improve indirectly
Efficiency.
Description of the drawings
Fig. 1 is the structural representation of integrated unmanned plane wing in the embodiment of the present invention；
Fig. 2 is the structural representation of the integrated unmanned plane wing with covering in the embodiment of the present invention；
Fig. 3 is the structural representation that integrated unmanned plane wing is applied to low-to-medium altitude described in the embodiment of the present invention；
Fig. 4 is the structural representation that integrated unmanned plane wing is applied to high-altitude described in one embodiment of the invention；
Fig. 5 is the structural representation that integrated unmanned plane wing is applied to high-altitude described in one embodiment of the invention；
Fig. 6 is the structural representation of embodiment of the present invention mesohigh fuel reservoir；
Fig. 7 is the schematic enlarged-scale view of two fuel under high pressure storage tank junctions in the embodiment of the present invention.
Specific embodiment
To make the object, technical solutions and advantages of the present invention become more apparent, below in conjunction with specific embodiment, and reference
Accompanying drawing, the present invention is described in more detail.
It should be noted that the statement of all uses " first " and " second " is for differentiation two in the embodiment of the present invention
The entity of individual same names non-equal or the parameter of non-equal, it is seen that " first " " second " should not only for the convenience of statement
The restriction to the embodiment of the present invention is interpreted as, subsequent embodiment is no longer illustrated one by one to this.
Refering to the structural representation for shown in Fig. 1 and 2, being integrated unmanned plane wing in the embodiment of the present invention, the one
It is that the fuel under high pressure storage tank of aircraft is arranged in inside aircraft wing to change unmanned plane wing, that is to say, that can utilize the height of aircraft
The structure of pressurized fuel storage tank as aircraft wing main force support structure, the present invention instead of original wing spar using high pressure storage tank
Structure function.It is specific to implement to include：
The integrated unmanned plane wing includes fuel under high pressure storage tank 1, covering 2, rib 4 and rear wall 5.Wherein, it is described
Fuel under high pressure storage tank 1 in be stored with hydrogen and oxygen, may be used for whole aircraft and fuel be provided.In one embodiment,
Described unmanned plane is powered using hydrogen-oxygen fuel cell, and 1 point of fuel under high pressure storage tank is hydrogen-holder and oxygen storage tank, for supplying
Fuel needed for fuel cell power generation.Wherein, hydrogen can arrange hydrogen-holder with oxygen according to the needs of different situations
With the volume ratio of oxygen storage tank.In preferred embodiment, the unmanned plane in high-altitude flying, due to oxygen in upper atmosphere
Content is thin, so 1 point of fuel under high pressure storage tank is hydrogen-holder and oxygen storage tank, this can pass through the diameter of control fuel reservoir
And tangential arrangement quantity is realizing.When the unmanned plane circles in the air in low-to-medium altitude, due to low-to-medium altitude atmospheric oxygen content compared with
For abundance, can be used as fuel cell oxygen sources, now all of fuel under high pressure storage tank 1 is hydrogen-holder.Accordingly, it is determined that institute
State unmanned plane is that what occasion be applied to, if being applied to high-altitude, storage tank is divided into hydrogen-holder and oxygen storage tank, need by user
Asking carries out volume distribution, if it is entirely then hydrogen-holder to be applied to low-to-medium altitude.
As an embodiment for referring to, as shown in figure 3, the integrated unmanned plane wing is applied to low-to-medium altitude, can
Using the source of oxygen by the use of the oxygen in air as fuel cell reaction, fuel under high pressure storage tank 1 is entirely hydrogen-holder.
Used as the embodiment that another is referred to, the integrated unmanned plane wing is applied to high-altitude, according to filling fuel
Demand is designed to two kinds of storage tanks, concretely according to fuel flow rate at hydrogen-oxygen fuel use ratio, fuel cell inlet with
And the cruising time of aircraft calculates the hydrogen-oxygen fuel volume of required carrying.As shown in figure 4, being 2 for hydrogen-oxygen fuel volume ratio:
1.As shown in figure 5, being 3 for hydrogen-oxygen fuel volume ratio:2.
Described covering 2 wraps described fuel under high pressure storage tank 1, rib 4 and rear wall 5, i.e. high pressure storage tank 1, rib 4
And rear wall 5 builds the skeleton of the integrated unmanned plane wing, and wrapped up by the covering 2.Thus, it is possible to further maintain
The aerodynamic configuration of the aircraft wing based on fuel under high pressure storage tank, while this skeleton structure can also avoid covering 2 from holding
Larger deformation is produced during by aerodynamic loading.Its specific structure can be：
Including plural rib 4 and parallel to each other between each rib 4 and spaced arrangement of tool.Described
Fuel under high pressure storage tank 1 sequentially passes through each rib 4, meanwhile, rear wall 5 sequentially passes through the rearward end of each rib 4.Preferably, by
There are deflectable pneumatic rudder face, therefore wall after being provided with the rearward end of rib 4 in the integrated unmanned plane trailing edge
5, effect is the concentrated force of the pneumatic rudder face that transmission is arranged in trailing edge.Further, the rear end of rib and unmanned aerial vehicle
The junction of aileron is installed by described rear wall 5.Common rib is used in embodiment, naturally it is also possible to adopt strengthening wing
Rib, strengthens rib in addition to the function for having common rib, also as the local strengthening component of unmanned aerial vehicle component, bears larger
Concentrfated load and the plug-in part of suspension.For example：Aircraft wing is with fuselage junction in order to more stable structure, the wing
Rib is using reinforcement rib.
Used as an alternative embodiment of the invention, the integrated unmanned plane wing can also include stringer 3, and stringer 3
It is placed in parallel with the fuel under high pressure storage tank 1, and is buckled on each rib 4, effect is that the distribution for bearing on covering is pneumatic
Power is delivered to rib up.
That is, integrated unmanned plane wing described in this embodiment includes being stored up along the fuel under high pressure of spanwise arrangement
Tank 1, and the stringer 3 with certain cross sectional shape and to bear aileron transmission concentrfated load rear wall 5 and along tangential
The rib 4 to maintain wing profile shape of arrangement, it is good pneumatic outer to be formed in integral skeleton structure outer cladding covering 2
Shape.
It is preferred that described stringer 3 is designed as：Two purlins are disposed with according to symmetrical form rib is corresponding about 4
Bar 3, is that a stringer 3 is buckled in successively on the upper surface of each rib 4, laterally zygomorphic another stringer 3 buckle successively
On the lower surface of each rib 4.It is preferred that described stringer 3 is in " 7 " font, the interior recess of " 7 " font can be snapped in
The end angle of rib 4.Further, two stringers 3 of two stringers 3 of arrangement symmetrical above and below and adjacent arrangement symmetrical above and below
Spacing be the buckling critical stress according to covering 2 determining.Preferably, can leave for stringer 3 in the upper and lower surface of rib 4
The stringer breach installed and pass through, the installation site of stringer 3 is just positioned at the stringer indentation, there on rib 4.
As another preferably embodiment of the present invention, can be high by two or more in the integrated unmanned plane wing
Pressurized fuel storage tank 1 is arranged in series into a row, while the fuel under high pressure storage tank 1 of series connection is interconnected.That is each two fuel under high pressure storage
It is connected with each other between tank 1, it is possible to achieve gaseous fuel being uniformly distributed in storage tank, total hydrogen supply or oxygen supply can after connection
To be realized with a main pipe rail, it is to avoid redundancy weight.Further, if using single in the integrated unmanned plane wing
The form of row fuel under high pressure storage tank, then the row fuel under high pressure storage tank sequentially passes through the pneumatic focus of each Airfoil Sections.If
In the integrated unmanned plane wing in the form of multiple row fuel under high pressure storage tank, then each column fuel under high pressure storage tank is as far as possible
Be arranged in the pneumatic focus line neighbouring position of Airfoil Sections.
Preferably, described aircraft fuel storage tank is arranged in inside aircraft wing, can be required to set according to the carrying of fuel
Along the storage tank columns of spanwise arrangement.In one embodiment (as shown in fig. 1) the integrated unmanned plane wing is provided with two
The fuel under high pressure storage tank 1 of row series connection, and each column three high pressure storage tanks 1 of series connection.Refering to shown in Fig. 2, in being the embodiment of the present invention
The structural representation of fuel under high pressure storage tank, the fuel under high pressure storage tank 1 includes tank wall 101, attachment lug 102, air inlet 103
And gas outlet 104.Wherein, as shown in Figures 6 and 7, attachment lug 102 is connected through in fact between fuel under high pressure storage tank 1 two-by-two
It is existing, and the head of tank wall 101 (being provided with the end of gas outlet 103) is spaced 90 ° of arrangement 2-6 (embodiment cloth in fig. 6 and 7
Put 4) individual attachment lug 102,90 ° of the afterbody of tank wall 101 interval arrangement 2-6 (embodiment in fig. 6 and 7 arranges 4)
Individual attachment lug 102.Also, the attachment lug 102 of a head of fuel under high pressure storage tank 1 can be with another fuel under high pressure storage tank
The attachment lug 102 of 1 afterbody is mutually embedded, finally needs to be punched on attachment lug 102, realizes firmly connecting by connecting bolt
Connect.Meanwhile, the junction of two fuel under high pressure storage tanks is designed with fluting, there is provided the laying space of fuel gas transfer pipeline.
In addition, the air inlet 103 of fuel under high pressure storage tank is used as the entrance that ground fills fuel gas, fuel under high pressure storage
The gas outlet 104 of tank uses as the supply outlet of fuel.Gas transfer pipeline is installed additional outside each fuel under high pressure storage tank, from outlet
Mouth 104 is drawn, then the other end of these single gas transfer pipelines is connected on gas delivery main road, total by gas conveying
Pipeline to the fuel cell on unmanned aerial vehicle provides fuel.
What deserves to be explained is, in order to fixed gas delivery main road on rib 4, fuel channel pilot hole is designed with,
Mitigate rib structure weight simultaneously for providing assembling positioning datum for fuel tube.
In another embodiment, because storage tank itself Structural strength calls for storing fuel under high pressure are very high, designed
It is in fact too strong design that original wing beam action is played inside wing, furthermore is disposed with certain amount along wing chordwise direction
Storage tank, so the unmanned plane wing cover 2 is not used in bears bending normal stresses in design, be only used for maintaining outside wing
Shape, the thickness of covering 2 can further reduce, and alleviate wing structure weight.Preferably, the skin thickness of covering 2 is received by it
Pressure buckling critical stress determines.Covering 2 described in the embodiment of the present invention is almost not subject to bending normal stresses, so thickness phase
It is thin for the covering of aircraft wing in prior art.In addition, the contour shape of covering 2 is exactly to be close to stringer 3 and rib 4
And be wrapped to form.
In one preferably embodiment, because aircraft wing is the main part of generation lift on aircraft, and wing
Obtain the lift that be enough to balancing gravity, a guarantee for being to have flying speed, another seeks to the guarantor of aerodynamic configuration
Card.In this embodiment, the guarantee of aerodynamic configuration is exactly plural by what is arranged in the integrated unmanned plane wing
Rib 4.Wherein, the spacing each other of rib 4 is arranged and ensures that overall structure will not be produced during aerodynamic loading is born
Reduce the weight of structure on the premise of excessive deformation or destruction as far as possible.The spacing each other of rib 4 arranges too small,
The intensity and toughness of structure ensure that, but weight can be excessive, unfavorable to persistently continuing a journey, excessive, be difficult to ensure that aerodynamic configuration even
Recurring structure is destroyed.
Preferably, the spacing of rib 4 can determine by the size of the limit stress of covering 2, or according to stringer it is overall and
The equal requirement of local buckling's limit stress determines.Further, the material of the size of covering buckling critical stress and covering,
Thickness is related, can be drawn by finite element analysis software or experiment.
In another preferred embodiment, lightening hole is designed with rib 4, lightening hole plays mitigation machine on rib 4
The effect of wing structure weight, can design in structure height less and with the position of intensity surplus.Meanwhile, lightening hole can be additionally used in
Space is provided for the laying of wing internal wiring.
Further, storage tank pilot hole is designed with rib 4, the assembling positioning datum for fuel reservoir mitigates rib simultaneously
Construction weight.And, the storage tank pilot hole designs major diameter pilot hole to obtaining using the structure height of upper rib 4 as much as possible
The fuel reservoir of large volume is obtained, this is favourable for increase fuel carrying amount increases in other words unmanned plane cruising time.
In sum, a kind of integrated unmanned plane wing that the present invention is provided, creatively by fuel under high pressure storage tank and machine
Wing structure integrated design, improves overall structure efficiency；Also, fuel under high pressure storage tank also serves as wing structure, save big
The wing structure weight of amount, equivalent to improve full machine fuel carrying capacity；And, pressure fuel tank is arranged in wing
Portion can make full use of space limited on aircraft, it is to avoid fuselage was designed in order to look after the volume of fuel reservoir
Big situation；So as to the present invention has extensive, great dissemination；Finally, the whole integrated unmanned plane wing is tight
Gather, it is easy to control.
All such within the broad range that embodiments of the invention are intended to fall into claims replace,
Modification and modification.Therefore, all any omission, modification, equivalent, improvement within the spirit and principles in the present invention, made
Deng should be included within the scope of the present invention.
Claims (9)
1. a kind of integrated unmanned plane wing, it is characterised in that including fuel under high pressure storage tank, covering, rib and rear wall；It is described
Fuel under high pressure storage tank in be stored with hydrogen and oxygen, for providing fuel for whole aircraft；Described covering wraps described
The skeleton of integrated unmanned plane wing described in fuel under high pressure storage tank, the rib and the rear wall construction.
2. aircraft wing according to claim 1, it is characterised in that including the plural rib, and each
The parallel to each other and spaced arrangement of tool between the rib；
Two or more fuel under high pressure storage tank is arranged in series into into a row in the integrated unmanned plane wing, the high compression ignition of each column
Material storage tank sequentially passes through each described rib, and the rear wall sequentially passes through the rearward end of each rib.
3. aircraft wing according to claim 2, it is characterised in that also including stringer, and with fuel under high pressure storage
The stringer that tank is arranged in parallel is buckled in successively on each described rib.
4. aircraft wing according to claim 3, it is characterised in that described stringer is designed as：Correspond to up and down in rib
Be disposed with two stringers according to symmetrical form, be that a stringer is buckled in successively on the upper surface of each rib, up and down
Another symmetrical stringer is buckled in successively on the lower surface of each rib；
Also, the spacing of two stringers of arrangement symmetrical above and below and two stringers of adjacent arrangement symmetrical above and below is according to the illiteracy
The buckling critical stress of skin is determining.
5. aircraft wing according to claim 2, it is characterised in that lightening hole is designed with the rib, design exists
Structure height is less and with the position of intensity surplus, while being used to provide space for aircraft wing internal wiring laying.
6. aircraft wing according to claim 2, it is characterised in that storage tank pilot hole is designed with the rib, uses
In the assembling positioning datum of fuel under high pressure storage tank, while mitigating the construction weight of rib.
7. aircraft wing according to claim 6, it is characterised in that the storage tank pilot hole is the knot using the rib
Structure highly designs major diameter pilot hole, for obtaining the fuel under high pressure storage tank of large volume.
8. aircraft wing according to claim 2, it is characterised in that the fuel under high pressure storage tank includes tank wall, connection
Auricle, air inlet and gas outlet；Wherein, the attachment lug of connecting through two-by-two between fuel under high pressure storage tank realizes, and
And the tank wall header arrangement 2-6 attachment lug, 2-6 attachment lug of the tank wall afterbody arrangement；Also, one high
The company of the attachment lug of the tank wall head of pressurized fuel storage tank and the tank wall afterbody of another fuel under high pressure storage tank
Lug piece is mutually embedded in, and finally punches on attachment lug, and by connecting bolt firmly connection is realized；
In addition, the air inlet of fuel under high pressure storage tank is used as the entrance that ground fills fuel gas, fuel under high pressure storage tank goes out
Gas port is used as the supply outlet of fuel；Gas transfer pipeline is installed additional outside each fuel under high pressure storage tank, draw from the gas outlet
Go out, then the other end of these single gas transfer pipelines is connected on gas delivery main road, by gas delivery main's road direction
Fuel cell on unmanned aerial vehicle provides fuel.
9. the aircraft wing according to claim 2-8 any one, it is characterised in that if the fuel under high pressure storage tank application
In high-altitude, then it is divided into hydrogen-holder and oxygen storage tank, and hydrogen-holder and oxygen storage tank volume ratio is according to circumstances set；If described
Fuel under high pressure storage tank is applied to low-to-medium altitude, then entirely hydrogen-holder.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610885444.7A CN106628114B (en) | 2016-10-10 | 2016-10-10 | Integrated unmanned aerial vehicle wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610885444.7A CN106628114B (en) | 2016-10-10 | 2016-10-10 | Integrated unmanned aerial vehicle wing |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106628114A true CN106628114A (en) | 2017-05-10 |
| CN106628114B CN106628114B (en) | 2020-06-09 |
Family
ID=58854809
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610885444.7A Active CN106628114B (en) | 2016-10-10 | 2016-10-10 | Integrated unmanned aerial vehicle wing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106628114B (en) |
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108910017A (en) * | 2018-06-29 | 2018-11-30 | 江苏常探机器人有限公司 | Radar additional fin |
| CN111114752A (en) * | 2020-01-07 | 2020-05-08 | 北京航空航天大学 | Deformable wing |
| CN112046729A (en) * | 2020-08-11 | 2020-12-08 | 南京航空航天大学 | Support connection structure of variable camber trailing edge sectional type wing rib and flexible skin |
| CN112849412A (en) * | 2021-02-08 | 2021-05-28 | 陕西北斗金箭航空科技有限公司 | Hydrogen-electricity nacelle body integrated scouting and batting unmanned aerial vehicle |
| US20220266980A1 (en) * | 2021-02-25 | 2022-08-25 | Airbus Operations Limited | Wingbox with fuel tank attached to ribs |
| US20220388628A1 (en) * | 2021-06-07 | 2022-12-08 | Textron Innovations Inc. | Aircraft Airframes having Integral Fuel Tanks |
| CN115458784A (en) * | 2022-11-11 | 2022-12-09 | 安徽云翼航空技术有限公司 | Fuel cell system suitable for high-altitude unmanned aerial vehicle and control method thereof |
| CN115523806A (en) * | 2022-09-28 | 2022-12-27 | 北京宇航系统工程研究所 | Resistance rudder and hanging cable recovery integrated mechanism and recovery method |
| EP4187140A1 (en) * | 2021-11-26 | 2023-05-31 | APUS - Aviation Engineering GmbH | Airfoil structure, pressure vessel and method of producing the same |
| WO2023147949A1 (en) * | 2022-02-04 | 2023-08-10 | Rolls-Royce Plc | Storage tank for gaseous hydrogen |
| US11945599B2 (en) | 2021-03-09 | 2024-04-02 | Airbus Operations Gmbh | Flow body for an aircraft with integrated gas tank |
| CN117885887A (en) * | 2024-03-14 | 2024-04-16 | 成都航空职业技术学院 | Folding-twisting coupling bionic wing and bionic aircraft |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5810284A (en) * | 1995-03-15 | 1998-09-22 | Hibbs; Bart D. | Aircraft |
| US20080230654A1 (en) * | 2006-11-14 | 2008-09-25 | The Boeing Company | Hydrogen fueled blended wing body ring tank |
| CN202143004U (en) * | 2011-07-25 | 2012-02-08 | 程子芮 | Aerial generating system |
| CN103209894A (en) * | 2010-07-28 | 2013-07-17 | 空中客车运作有限责任公司 | Hydrogen tank for h2-injection |
| CN205256684U (en) * | 2015-12-03 | 2016-05-25 | 上海奥科赛飞机有限公司 | Hydrogen fuel driven fixed -wing aircraft |
| CN205615721U (en) * | 2016-05-10 | 2016-10-05 | 绍兴俊吉能源科技有限公司 | Hydrogen cell is applied to unmanned aerial vehicle's first aid structure |
-
2016
- 2016-10-10 CN CN201610885444.7A patent/CN106628114B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5810284A (en) * | 1995-03-15 | 1998-09-22 | Hibbs; Bart D. | Aircraft |
| US20080230654A1 (en) * | 2006-11-14 | 2008-09-25 | The Boeing Company | Hydrogen fueled blended wing body ring tank |
| CN103209894A (en) * | 2010-07-28 | 2013-07-17 | 空中客车运作有限责任公司 | Hydrogen tank for h2-injection |
| CN202143004U (en) * | 2011-07-25 | 2012-02-08 | 程子芮 | Aerial generating system |
| CN205256684U (en) * | 2015-12-03 | 2016-05-25 | 上海奥科赛飞机有限公司 | Hydrogen fuel driven fixed -wing aircraft |
| CN205615721U (en) * | 2016-05-10 | 2016-10-05 | 绍兴俊吉能源科技有限公司 | Hydrogen cell is applied to unmanned aerial vehicle's first aid structure |
Cited By (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108910017A (en) * | 2018-06-29 | 2018-11-30 | 江苏常探机器人有限公司 | Radar additional fin |
| CN111114752A (en) * | 2020-01-07 | 2020-05-08 | 北京航空航天大学 | Deformable wing |
| CN111114752B (en) * | 2020-01-07 | 2021-08-13 | 北京航空航天大学 | Deformable wing |
| CN112046729A (en) * | 2020-08-11 | 2020-12-08 | 南京航空航天大学 | Support connection structure of variable camber trailing edge sectional type wing rib and flexible skin |
| CN112046729B (en) * | 2020-08-11 | 2021-12-14 | 南京航空航天大学 | Support connection structure of variable camber trailing edge sectional type wing rib and flexible skin |
| CN112849412A (en) * | 2021-02-08 | 2021-05-28 | 陕西北斗金箭航空科技有限公司 | Hydrogen-electricity nacelle body integrated scouting and batting unmanned aerial vehicle |
| US20220266980A1 (en) * | 2021-02-25 | 2022-08-25 | Airbus Operations Limited | Wingbox with fuel tank attached to ribs |
| GB2604140A (en) * | 2021-02-25 | 2022-08-31 | Airbus Operations Ltd | Wingbox with fuel tank attached to ribs |
| US11945599B2 (en) | 2021-03-09 | 2024-04-02 | Airbus Operations Gmbh | Flow body for an aircraft with integrated gas tank |
| US20220388628A1 (en) * | 2021-06-07 | 2022-12-08 | Textron Innovations Inc. | Aircraft Airframes having Integral Fuel Tanks |
| US11787554B2 (en) * | 2021-06-07 | 2023-10-17 | Textron Innovations Inc. | Aircraft airframes having integral fuel tanks |
| EP4187140A1 (en) * | 2021-11-26 | 2023-05-31 | APUS - Aviation Engineering GmbH | Airfoil structure, pressure vessel and method of producing the same |
| WO2023094096A1 (en) * | 2021-11-26 | 2023-06-01 | Apus - Aviation Engineering Gmbh | Airfoil structure, pressure vessel and method of producing the same |
| WO2023147949A1 (en) * | 2022-02-04 | 2023-08-10 | Rolls-Royce Plc | Storage tank for gaseous hydrogen |
| CN115523806A (en) * | 2022-09-28 | 2022-12-27 | 北京宇航系统工程研究所 | Resistance rudder and hanging cable recovery integrated mechanism and recovery method |
| CN115458784A (en) * | 2022-11-11 | 2022-12-09 | 安徽云翼航空技术有限公司 | Fuel cell system suitable for high-altitude unmanned aerial vehicle and control method thereof |
| CN117885887A (en) * | 2024-03-14 | 2024-04-16 | 成都航空职业技术学院 | Folding-twisting coupling bionic wing and bionic aircraft |
| CN117885887B (en) * | 2024-03-14 | 2024-05-14 | 成都航空职业技术学院 | Folding-twisting coupling bionic wing and bionic aircraft |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106628114B (en) | 2020-06-09 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106628114A (en) | Integrated unmanned aerial vehicle wing | |
| Yusaf et al. | Sustainable hydrogen energy in aviation–A narrative review | |
| Adler et al. | Hydrogen-powered aircraft: Fundamental concepts, key technologies, and environmental impacts | |
| Bradley et al. | Development and experimental characterization of a fuel cell powered aircraft | |
| US20230243474A1 (en) | Systems and methods for storing, transporting, and using hydrogen | |
| CN102991729B (en) | A kind of Light mesh-type surface tension storage tank | |
| Renau et al. | Use of fuel cell stacks to achieve high altitudes in light unmanned aerial vehicles | |
| US10209686B2 (en) | Flight simulation and control method of a unmanned aerial vehicle with regenerative fuel cells and solar cells for high altitude long endurance, and a control apparatus thereof | |
| US11807383B2 (en) | Aircraft with hydrogen storage tanks | |
| Swider-Lyons et al. | Hydrogen fuel cells for small unmanned air vehicles | |
| Swider-Lyons et al. | Liquid hydrogen fuel system for small unmanned air vehicles | |
| US20040069897A1 (en) | Zero emitting electric air vehicle with semi-annular wing | |
| Amy et al. | Hydrogen as a renewable energy carrier for commercial aircraft | |
| Duy et al. | Review on the hybrid-electric propulsion system and renewables and energy storage for unmanned aerial vehicles | |
| Waddington et al. | Impact of Liquid-Hydrogen Fuel-Cell Electric Propulsion on Aircraft Configuration and Integration | |
| Li et al. | Research of near space hybrid power airship with a novel method of energy storage | |
| Sain et al. | Conceptual Design of Air and Thermal Management in a Nacelle-Integrated Fuel Cell System for an Electric Regional Aircraft | |
| Tiseira et al. | Concept design and energy balance optimization of a hydrogen fuel cell helicopter for unmanned aerial vehicle and aerotaxi applications | |
| CN106150762A (en) | The liquid hydrogen vaporization control method of hydrogen energy source unmanned plane | |
| Boretti | Progress of hydrogen subsonic commercial aircraft | |
| US20230348091A1 (en) | Aircraft with a multi-walled fuel tank and a method of manufacturing | |
| US11905027B1 (en) | Systems and methods for a liquified gas fuel tank incorporated into an aircraft | |
| Keiyinci et al. | Ground simulation of fuel cell/battery hybrid propulsion system for small unmanned air vehicles | |
| US20230348089A1 (en) | Systems and methods for a blended wing body aircraft with permanent tanks | |
| US20240025556A1 (en) | Methods and systems for venting a fuel tank on a blended wing body aircraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20210203 Address after: 523808 room 717, building 2, No.16, Keji 4th Road, Songshanhu Park, Dongguan City, Guangdong Province Patentee after: Guangdong yunchuang Hydrogen Power Technology Co., Ltd Address before: 100191 No. 37, Haidian District, Beijing, Xueyuan Road Patentee before: BEIHANG University |
|
| TR01 | Transfer of patent right |