CN106240798B - A kind of spar/energy-storage battery integral structure - Google Patents
A kind of spar/energy-storage battery integral structure Download PDFInfo
- Publication number
- CN106240798B CN106240798B CN201610826843.6A CN201610826843A CN106240798B CN 106240798 B CN106240798 B CN 106240798B CN 201610826843 A CN201610826843 A CN 201610826843A CN 106240798 B CN106240798 B CN 106240798B
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- Prior art keywords
- spar
- energy
- storage battery
- temperature
- integral structure
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- 238000004146 energy storage Methods 0.000 title claims abstract description 72
- 238000009413 insulation Methods 0.000 claims description 13
- 229920007790 polymethacrylimide foam Polymers 0.000 claims description 7
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 6
- 239000004917 carbon fiber Substances 0.000 claims description 6
- 238000005259 measurement Methods 0.000 claims description 5
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 5
- 230000005611 electricity Effects 0.000 claims description 4
- 230000008447 perception Effects 0.000 claims description 3
- 239000012141 concentrate Substances 0.000 abstract description 2
- 239000012774 insulation material Substances 0.000 abstract 1
- 239000010410 layer Substances 0.000 description 8
- 238000010586 diagram Methods 0.000 description 4
- 239000006260 foam Substances 0.000 description 4
- 238000004321 preservation Methods 0.000 description 3
- 229920006934 PMI Polymers 0.000 description 2
- 238000010276 construction Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000006870 function Effects 0.000 description 2
- 230000017525 heat dissipation Effects 0.000 description 2
- 239000011229 interlayer Substances 0.000 description 2
- 238000010008 shearing Methods 0.000 description 2
- 238000009423 ventilation Methods 0.000 description 2
- HBBGRARXTFLTSG-UHFFFAOYSA-N Lithium ion Chemical compound [Li+] HBBGRARXTFLTSG-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 229910001416 lithium ion Inorganic materials 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000000116 mitigating effect Effects 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 239000005437 stratosphere Substances 0.000 description 1
- 239000011800 void material Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/32—Wings specially adapted for mounting power plant
-
- 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
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
-
- 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
- B64D33/00—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/08—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Photovoltaic Devices (AREA)
- Secondary Cells (AREA)
- Hybrid Cells (AREA)
- Charge And Discharge Circuits For Batteries Or The Like (AREA)
Abstract
The present invention discloses a kind of spar/energy-storage battery integral structure, belongs to field of flight vehicle design.The present invention is fixed on by rib and fastening screw in spar using square-section spar, energy-storage battery, and spar is made to concentrate stand under load；There are PMI froth beds in spar, not only served as sandwich and born shear stress, but also kept the temperature as thermal insulation material for energy-storage battery；There is radiator fan at spar both ends, and form convection current using the gap between rib radiates for energy-storage battery.The present invention can substantially improve spar mechanical characteristic on the premise of energy-storage battery operating temperature is ensured, while simplify structure, mitigate weight, solar powered aircraft is made to have higher flight efficiency.
Description
Technical field
The invention belongs to field of flight vehicle design, the specific one kind that designs can improve spar mechanical characteristic, control energy storage electricity
Pond operating temperature, the spar/energy-storage battery integration new structure for mitigating aircaft configuration quality.
Background technology
Solar powered aircraft is reduces resistance, and generally use high aspect ratio wing, the rigidity of structure is poor, and working condition lower wing becomes
Shape is serious.Long endurance solar powered aircraft needs energy-storage battery storing excess energy in the daytime, for night flying, most solar energy
For aircraft using lithium ion battery as energy-storage battery, operating temperature section is usually 0-40 DEG C.Solar powered aircraft flies in low latitude
During row, environment temperature is higher, and energy-storage battery work generates heat, and temperature can be more than 60 DEG C, it is necessary to radiate to it；Night is in advection
During layer flight, environment temperature is low, and energy-storage battery temperature is less than -50 DEG C, it is necessary to be kept the temperature to it.Conventional solar powered aircraft or by energy storage
Battery arrangement is in the nacelle or fuselage of the leading edge of a wing, and for keeping the temperature, foam outer needs to use outside batteries covering PMI foams
One layer of hard shell of package protects battery.This energy-storage battery arrangement form concentrates stress not only bad for spar, also
Extra construction weight can be brought, and the endurance of solar powered aircraft, voyage are heavily dependent on energy consumption and weight, therefore this
Kind arrangement form is unfavorable for the promotion of solar powered aircraft performance.
The content of the invention
To overcome the shortcomings of above-mentioned existing solar powered aircraft energy-storage battery arrangement, the present invention provides one kind by spar
With the integral structure form of energy-storage battery composition, energy-storage battery is arranged in spar, on the one hand utilizes energy-storage battery weight
For spar off-load, on the other hand energy-storage battery is kept the temperature and radiated using spar structure.
A kind of spar/energy-storage battery integral structure of the present invention, energy-storage battery, energy storage are axially set in spar along spar
Gap is left between battery circumferential direction and spar inner wall.Heat-insulation window is installed at spar both ends simultaneously, and spar both ends are also separately installed with
Blower fan and exhaust fan.
From there through the mounting temperature sensor real-time perception spar internal temperature information in spar, and feed back to control electricity
The switch control to blower fan and exhaust fan by control circuit compared with the temperature threshold set, is realized in road；And then it realizes
The heat preservation of energy-storage battery and radiating control.
The advantage of the invention is that：
1st, spar of the present invention/energy-storage battery integral structure, energy-storage battery are distributed in wing girder so that flight course
Middle energy-storage battery weight realizes self-balancing to the corresponding lift that wing generates at spar, improves wing mechanical characteristic, can be big
It is big to reduce spar weight；
2nd, spar of the present invention/energy-storage battery integral structure, the PMI foam layers in spar, is serving as spar structure
Meanwhile also as heat-barrier material, for the heat preservation of energy-storage battery during night flying, avoid conventional vacuum form bring it is additional
Weight；
3rd, spar of the present invention/energy-storage battery integral structure, the radiator fan at spar both ends can be in energy-storage battery temperature in the daytime
When degree is higher, heat is shed by cross-ventilation, it is simple in structure, it is easy to control；
4th, spar of the present invention/energy-storage battery integral structure, the rib of spar inner wall can make energy-storage battery be completely embedded into the wing
In beam, limitation energy-storage battery is circumferentially displaced, while retains convection channel in energy-storage battery side wall, it is ensured that heat dissipation effect；
5th, spar of the present invention/energy-storage battery integral structure, fastening screw on spar is for limiting energy-storage battery along machine
The span to displacement, it is convenient to change exhibition of the battery in spar according to demand to position, and the dismounting beneficial to energy-storage battery and dimension
Shield；
6th, spar of the present invention/energy-storage battery integral structure, since energy-storage battery is not arranged in nacelle or fuselage,
The shape of nacelle and fuselage is reduced with structure design limitation, can be effectively reduced resistance by design, be mitigated weight, to solar energy
The feasibility that aircraft uninterruptedly cruises round the clock is of great significance.
Description of the drawings
Fig. 1 is spar of the present invention/energy-storage battery integral structure overall structure diagram；
Fig. 2 is spar of the present invention/energy-storage battery integral structure wing centre section girder construction and energy-storage battery mounting means schematic diagram；
Fig. 3 is radiator fan and heat-insulation window schematic view of the mounting position in spar of the present invention/energy-storage battery integral structure；
Fig. 4 is heat-insulation window opening ways schematic diagram in spar of the present invention/energy-storage battery integral structure；
Fig. 5 is spar of the present invention/energy-storage battery integral structure control mode block diagram.
In figure：
1- spar 2- energy-storage battery 3- ribs
4- fastening screw 5- heat-insulation window 6- radiator fans
7- temperature sensor 8- control circuit 101- carbon fiber skins
102-PMI foam layer 103- Kevs draw inner wall
Specific embodiment
Specifically name is done further to the present invention below in conjunction with the accompanying drawings.
The spar 1 of wing is designed as tubular structure, inside peace by a kind of spar/energy-storage battery integral structure of the present invention
Energy-storage battery 2 is filled, as shown in Figure 1.
As shown in Fig. 2, the wingbar 1 design has three layers, respectively carbon fiber skin 101, PMI foams from outside to inside
Interlayer 102, Kev draw inner wall 103.101 strength and stiffness of carbon fiber skin are good, are primarily subjected to drawing, pressure and shearing force；PMI steeps
102 light weight of foam interlayer, is primarily subjected to moment of flexure and torque, and anti-unstability ability is strong；Kev draws 103 intensity of inner wall high, and good toughness is used
In bearing pulling force and shearing force, foam layer is prevented to be broken.Above-mentioned carbon fiber skin 101 and Kev draw 103 very thin thickness of inner wall,
About 0.2~0.3mm, PMI foam layer 102 is relatively thick, about 8~10mm, can be effectively improved spar stress, mitigates the sun
It can aero-structure weight.
Energy-storage battery 2 is provided with along spar 1 is axial inside spar 1, the quantity of energy-storage battery 2 is according to solar powered aircraft night
Energy needed for cruise and energy-storage battery energy density determine, and the spacing of adjacent energy-storage battery 2 is by 1 loading conditions of spar and wing
Aeroelastic characteristic determines.Energy-storage battery 2 is supported by " work " the font rib 3 being all provided in 1 inner wall circumferential direction of spar, realizes storage
Can battery it is circumferentially positioned；And by being located at 2 rear and front end of energy-storage battery, through the fastening screw 4 of 1 opposite flank of spar,
Realize the axially position of energy-storage battery 2.Energy-storage battery 2 is supported by rib 3, makes energy-storage battery 2 circumferential circumferential with 1 inner wall of spar
Between form gap, as convection channel.
As shown in figure 3, being installed with heat-insulation window 5 on 1 both ends end face of spar, heat-insulation window 5 uses shutter, passes through
Gas pressure can be automatically opened and closed, as shown in Figure 4；And 1 inner sealing of spar can be achieved after heat-insulation window 5 is closed.Spar 1
Both ends end is also equipped with radiator fan 6, radiator fan 6 is made to be close to 5 inside of heat-insulation window fixed.The heat dissipation at above-mentioned 1 both ends of spar
In fan 6, one is blower fan by radiator fan 6, can suck external void inside spar 1；Another radiator fan 6 is
1 inner air of spar can be discharged spar 1 by exhaust fan.
A kind of spar/energy-storage battery integral structure of the present invention, is controlled by control module, realize inside spar 1 into/
Exhaust automatically controls.The control module includes temperature sensor 7 and control circuit 8, as shown in Figure 3.Wherein, temperature sensing
Device 7 is installed on 1 internal face of spar, for 1 internal temperature information of real-time perception spar, and feeds back to control circuit 8.Control electricity
Road 8 is installed on outside spar 1, is mountable to wing inner wall.As shown in figure 5, control circuit 8 is used for obtaining temperature sensor in real time
The temperature value of measurement, and by temperature value compared with the temperature threshold (40 °) of setting in control circuit 8, when temperature value is more than
During design temperature threshold value (solar powered aircraft is in the daytime in low-latitude flying), control circuit 8 sends control signal, controls 1 liang of spar
The radiator fan 6 at end is opened, and a radiator fan 6 is made to dry into spar 1, another air draught out of beam of radiator fan 6, make every
Hot window 5 automatically opens under gas pressure, and then cross-ventilation is formed in spar 1, and air-flow passes through convection channel, takes away energy storage
A part of heat of battery 2, so as to reach radiating and cooling purpose.(the solar energy when temperature threshold of the environment temperature less than setting
Plane night is in stratosphere flight), control circuit 8 sends control signal, and the radiator fan 6 at 1 both ends of control spar is closed, this
When heat-insulation window 5 be also at closed state, can avoid 1 inner air and outer air of spar that convection current, and since 1 section of spar is elongated, both ends occurs
Temperature loss can be ignored caused by heat transfer.Energy-storage battery can generate certain heat when working, and pass through the PMI of spar 1
102 insulation effect of foam layer, these heats will not largely shed, so as to reach heat preservation purpose.
Above-mentioned temperature sensor 7 can set multiple at equal intervals along spar 1 is axial, while perceive axial multiple positions in spar 1
The temperature value put.The temperature value that each temperature sensor 7 measures is received from there through control circuit 8, and by each temperature value and temperature
Degree threshold value is compared, if the temperature value of some temperature sensor measurement is less than temperature threshold, just opens heat insulation function, instead
Heat sinking function open, so as to being more accurately controlled temperature, achieve the purpose that protect battery.
Claims (6)
1. a kind of spar/energy-storage battery integral structure, it is characterised in that：In spar, energy-storage battery is axially set along spar,
Gap is left between energy-storage battery circumferential direction and spar inner wall；Heat-insulation window is installed at spar both ends simultaneously, and spar both ends are also pacified respectively
Equipped with blower fan and exhaust fan；
Control module is further included, control module has temperature sensor and control circuit；Temperature sensor is used for the real-time perception wing
Beam internal temperature information, and feed back to control circuit；Control circuit is used for obtaining the temperature value of temperature sensor measurement in real time, and
By temperature value compared with the temperature threshold set in control circuit, when temperature value is more than design temperature threshold value, control electricity
Road sends control signal, and control blower fan is opened with exhaust fan；When environment temperature is less than the temperature threshold set, control circuit hair
Go out control signal, control blower fan is closed with exhaust fan；
Temperature sensor is axially set at equal intervals along spar, and the temperature of each temperature sensor measurement is received by control circuit
Value, and each temperature value is compared with temperature threshold, if the temperature value of one of temperature sensor measurement is less than temperature threshold
During value, just blower fan is controlled to be closed with exhaust fan, otherwise control blower fan is opened with exhaust fan.
2. a kind of spar/energy-storage battery integral structure as described in claim 1, it is characterised in that：Spar is designed as three-layered node
Structure, respectively carbon fiber skin, PMI foam layers, Kev draw inner wall from outside to inside.
3. a kind of spar/energy-storage battery integral structure as claimed in claim 2, it is characterised in that：Carbon fiber skin and Kev
Drawing inner wall thickness is 0.2~0.3mm；PMI foam layers thickness is 8~10mm.
4. a kind of spar/energy-storage battery integral structure as described in claim 1, it is characterised in that：Energy-storage battery passes through in the wing
The rib support being all provided in beam inner wall circumferential direction.
5. a kind of spar/energy-storage battery integral structure as described in claim 1, it is characterised in that：Energy-storage battery is by being located at
At energy-storage battery rear and front end, the fastening screw through spar opposite flank realizes axially position.
6. a kind of spar/energy-storage battery integral structure as described in claim 1, it is characterised in that：Heat-insulation window uses shutter
Structure can be automatically opened and closed by gas pressure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610826843.6A CN106240798B (en) | 2016-09-14 | 2016-09-14 | A kind of spar/energy-storage battery integral structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610826843.6A CN106240798B (en) | 2016-09-14 | 2016-09-14 | A kind of spar/energy-storage battery integral structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106240798A CN106240798A (en) | 2016-12-21 |
| CN106240798B true CN106240798B (en) | 2018-05-18 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201610826843.6A Active CN106240798B (en) | 2016-09-14 | 2016-09-14 | A kind of spar/energy-storage battery integral structure |
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Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102018202114A1 (en) | 2018-02-12 | 2019-08-14 | Airbus Defence and Space GmbH | Battery assembly for the structural integration of batteries in a vehicle |
| DE102018202120A1 (en) | 2018-02-12 | 2019-08-14 | Airbus Defence and Space GmbH | Battery assembly for the structural integration of batteries in a vehicle |
| DE102018204420A1 (en) * | 2018-03-22 | 2019-09-26 | Airbus Defence and Space GmbH | Battery assembly for load-bearing structural integration of batteries in a vehicle |
| US11434014B2 (en) | 2018-10-10 | 2022-09-06 | Imagine Aero Inc. | Aircraft spars with integrated power cells, and associated systems and methods |
| US20200277062A1 (en) * | 2019-03-01 | 2020-09-03 | Pratt & Whitney Canada Corp. | Aircraft having hybrid-electric propulsion system with electric storage located in wings |
| US11440430B2 (en) | 2019-04-30 | 2022-09-13 | The Boeing Company | Removable battery compression devices |
| CN114162335B (en) * | 2020-09-11 | 2024-05-07 | 海鹰航空通用装备有限责任公司 | Energy storage battery thermal management system of near space vehicle |
| CN113955073B (en) * | 2021-10-19 | 2023-10-20 | 西北工业大学 | A filled battery case structure for aircraft wallboard structure |
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| US5810284A (en) * | 1995-03-15 | 1998-09-22 | Hibbs; Bart D. | Aircraft |
| CN1429165A (en) * | 2000-04-03 | 2003-07-09 | 威罗门飞行公司 | Liquid hydrogen stratospheric aircraft |
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| CN106240798A (en) | 2016-12-21 |
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Inventor after: Zhang Liang Inventor after: Ma Chengjing Inventor after: Yang Muqing Inventor after: Wang Shaoqi Inventor after: Xia Xinglu Inventor before: Ma Dongli Inventor before: Zhang Liang Inventor before: Yang Muqing Inventor before: Wang Shaoqi Inventor before: Xia Xinglu |
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