CN106240798A - A kind of spar/energy-storage battery integral structure - Google Patents
A kind of spar/energy-storage battery integral structure Download PDFInfo
- Publication number
- CN106240798A CN106240798A CN201610826843.6A CN201610826843A CN106240798A CN 106240798 A CN106240798 A CN 106240798A CN 201610826843 A CN201610826843 A CN 201610826843A CN 106240798 A CN106240798 A CN 106240798A
- Authority
- CN
- China
- Prior art keywords
- spar
- energy
- storage battery
- integral structure
- temperature
- 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.)
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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; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
- B64D27/24—Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/08—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
Abstract
The open a kind of spar/energy-storage battery integral structure of the present invention, belongs to field of flight vehicle design.The present invention uses square-section spar, and energy-storage battery is fixed in spar by rib and fastening screw, makes spar concentrate stand under load；Have PMI froth bed in spar, both served as sandwich and born shear stress, again as insulation material be energy-storage battery insulation；There is radiator fan at spar two ends, and it is energy-storage battery heat radiation that the space between available rib forms convection current.The present invention, on the premise of ensureing energy-storage battery operating temperature, can be substantially improved spar mechanical characteristic, simplify structure simultaneously, alleviate weight, make solar powered aircraft have higher flight efficiency.
Description
Technical field
The invention belongs to field of flight vehicle design, specific design one can be improved spar mechanical characteristic, control energy storage electricity
Pond operating temperature, alleviate the spar/energy-storage battery integration new structure of aircaft configuration quality.
Background technology
Solar powered aircraft, for reducing resistance, generally uses high aspect ratio wing, and the rigidity of structure is poor, and duty lower wing becomes
Shape is serious.During long boat, solar powered aircraft needs energy-storage battery to store excess energy in the daytime, for night flying, and most solar energys
Aircraft uses lithium ion battery as energy-storage battery, and its operating temperature interval is usually 0-40 DEG C.Solar powered aircraft flies in low latitude
During row, ambient temperature is higher, and energy-storage battery work produces heat, and temperature can need to dispel the heat it more than 60 DEG C；Night is at advection
During layer flight, ambient temperature is low, and energy-storage battery temperature is less than-50 DEG C, needs to be incubated 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 outside batteries covers PMI foam and is used for being incubated, and foam outer needs to use
Wrap up one layer of hard shell battery is protected.This energy-storage battery arrangement form concentrates stress not only bad for spar, also
Can bring unnecessary construction weight, and during the boat of solar powered aircraft, voyage be heavily dependent on energy consumption and weight, therefore this
Plant arrangement form and be unfavorable for the lifting of solar powered aircraft performance.
Summary of the invention
For overcoming the deficiency of above-mentioned existing solar powered aircraft energy-storage battery arrangement, the invention provides a kind of 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 spar structure is utilized energy-storage battery to be incubated and dispels the heat.
One spar/energy-storage battery integral structure of the present invention, along the axially arranged energy-storage battery of spar, energy storage in spar
Gap is left between battery circumference and spar inwall.Heat-insulation window is installed at spar two ends simultaneously, and spar two ends are also separately installed with
Blower fan and exhaust fan.
From there through mounting temperature sensor real-time perception spar internal temperature information in spar, and feed back to control electricity
Road, is compared by the temperature threshold of control circuit with setting, it is achieved the on-off control to blower fan Yu exhaust fan；And then realize
The insulation of energy-storage battery and radiating control.
It is an advantage of the current invention that:
1, spar of the present invention/energy-storage battery integral structure, energy-storage battery is distributed in wing girder so that flight course
The corresponding lift that middle energy-storage battery weight produces to wing realizes self-balancing at spar, improves wing mechanical characteristic, can be big
Big reduction spar weight；
2, spar of the present invention/energy-storage battery integral structure, the PMI foam layer in spar, is serving as spar structure
Meanwhile, also as heat-barrier material, when the night flying insulation of energy-storage battery, it is to avoid it is extra that conventional vacuum form is brought
Weight；
3, spar of the present invention/energy-storage battery integral structure, the radiator fan at spar two ends, can be in energy-storage battery temperature in the daytime
When spending higher, by cross-ventilation, heat is shed, simple in construction, easy to control；
4, spar of the present invention/energy-storage battery integral structure, the rib of spar inwall can make energy-storage battery be completely embedded into the wing
In beam, limit energy-storage battery circumferentially displaced, retain convection channel at energy-storage battery sidewall, it is ensured that radiating effect simultaneously；
5, spar of the present invention/energy-storage battery integral structure, the fastening screw on spar is used for limiting energy-storage battery along machine
The span to displacement, convenient change battery exhibition in spar the most according to demand to position, and the beneficially dismounting of energy-storage battery and dimension
Protect；
6, spar of the present invention/energy-storage battery integral structure, owing to energy-storage battery is not arranged in nacelle or fuselage,
Nacelle reduces with structure design limit with the profile of fuselage, can effectively reduce resistance by design, alleviate weight, to solar energy
The feasibility that aircraft the most uninterruptedly cruises is significant.
Accompanying drawing explanation
Fig. 1 is spar of the present invention/energy-storage battery integral structure overall structure schematic diagram；
Fig. 2 is spar of the present invention/energy-storage battery integral structure central spar structure and energy-storage battery mounting means schematic diagram；
Fig. 3 is radiator fan and heat-insulation window installation site schematic diagram 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-rib
4-fastening screw 5-heat-insulation window 6-radiator fan
7-temperature sensor 8-control circuit 101-carbon fiber skin
102-PMI foam layer 103-Kev draws inwall
Detailed description of the invention
Below in conjunction with the accompanying drawings the present invention is done the most specifically name.
One spar/energy-storage battery integral structure of the present invention, is designed as tubular structure, internal peace by the spar 1 of wing
Dress energy-storage battery 2, as shown in Figure 1.
As in figure 2 it is shown, the design of described wingbar 1 has three layers, the most respectively carbon fiber skin 101, PMI foam
Interlayer 102, Kev draw inwall 103.Carbon fiber skin 101 strength and stiffness are good, are primarily subjected to draw, pressure and shearing force；PMI steeps
Foam interlayer 102 light weight, is primarily subjected to moment of flexure and moment of torsion, and anti-unstability ability is strong；Kev draws inwall 103 intensity high, and good toughness is used
In bearing pulling force and shearing force, prevent foam layer from rupturing.Above-mentioned carbon fiber skin 101 and Kev draw inwall 103 very thin thickness,
Being about 0.2～0.3mm, PMI foam layer 102 is relatively thick, about 8～10mm, can be effectively improved spar stress, alleviate the sun
Can aero-structure weight.
Spar 1 is internal has energy-storage battery 2 along spar 1 is axially arranged, and the quantity of energy-storage battery 2 is according to solar powered aircraft night
The required energy of cruise and energy-storage battery energy density determine, and the spacing of adjacent energy-storage battery 2 is by spar 1 loading conditions and wing
Aeroelastic characteristic determines.Energy-storage battery 2 is supported by " work " the font rib 3 being all provided with in spar 1 inwall circumference, it is achieved storage
Can battery circumferentially positioned；And by being positioned at energy-storage battery 2 rear and front end, through the fastening screw 4 of spar 1 opposite flank,
Realize the axial location of energy-storage battery 2.Support energy-storage battery 2 by rib 3, make energy-storage battery 2 circumference and spar 1 inwall circumference
Between formed gap, as convection channel.
As it is shown on figure 3, be installed with heat-insulation window 5 on the end face of spar 1 two ends, heat-insulation window 5 uses shutter, passes through
Gas pressure can automatically open up and close, as shown in Figure 4；And spar 1 inner sealing can be realized after heat-insulation window 5 is closed.Spar 1
End, two ends is also equipped with radiator fan 6, makes radiator fan 6 be close to inside heat-insulation window 5 fixing.The heat radiation at above-mentioned spar 1 two ends
In fan 6, one is blower fan by radiator fan 6, external void can suck spar 1 internal；Another radiator fan 6 is
Exhaust fan, can discharge spar 1 by spar 1 inner air.
One spar/energy-storage battery integral structure of the present invention, is controlled by control module, it is achieved enter inside spar 1/
Automatically controlling of aerofluxus.Described control module includes temperature sensor 7 and control circuit 8, as shown in Figure 3.Wherein, temperature sensing
Device 7 is installed on spar 1 internal face, for real-time perception spar 1 internal temperature information, and feeds back to control circuit 8.Control electricity
It is outside that road 8 is installed on spar 1, is mountable to wing inwall.As it is shown in figure 5, control circuit 8 is used for obtaining temperature sensor in real time
The temperature value measured, and temperature value is compared, when temperature value is more than with the temperature threshold (40 °) of setting in control circuit 8
During design temperature threshold value (solar powered aircraft is in the daytime when low altitude flight), control circuit 8 sends control signal, controls spar 1 liang
End radiator fan 6 open, make a radiator fan 6 dry in spar 1, another radiator fan 6 air draught in beam, make every
Hot window 5 automatically opens up under gas pressure, and then forms cross-ventilation in spar 1, and air-flow, through convection channel, takes away energy storage
A part of heat of battery 2, thus reach radiating and cooling purpose.(the solar energy when ambient temperature is less than the temperature threshold set
Plane night is when stratosphere flight), control circuit 8 sends control signal, and the radiator fan 6 controlling spar 1 two ends cuts out, this
Time heat-insulation window 5 be also at closed mode, spar 1 inner air and outer air generation convection current can be avoided, and owing to spar 1 cross section is elongated, two ends
The temperature loss that conduction of heat causes is negligible.Certain heat can be produced, by the PMI of spar 1 during energy-storage battery work
Foam layer 102 insulation effect, these heat major parts will not shed, thus reaches to be incubated purpose.
Said temperature sensor 7 axially can arrange multiple along spar 1 at equal intervals, axial multiple positions in perception spar 1 simultaneously
The temperature value put.The temperature value that each temperature sensor 7 is measured is received from there through control circuit 8, and by each temperature value and temperature
Degree threshold value contrasts, if the temperature value of some temperature sensor measurement is less than temperature threshold, just opens heat insulation function, instead
Heat sinking function open, thus be more accurately controlled temperature, reach to protect the purpose of battery.
Claims (8)
1. spar/energy-storage battery integral structure, it is characterised in that: in spar, along the axially arranged energy-storage battery of spar,
Gap is left between energy-storage battery circumference and spar inwall；Heat-insulation window is installed at spar two ends simultaneously, and spar two ends are pacified the most respectively
Equipped with blower fan and exhaust fan.
2. a kind of spar/energy-storage battery integral structure, it is characterised in that: spar is designed as three layers of machine
Structure, the most respectively carbon fiber skin, PMI foam layer, Kev draw inwall.
3. a kind of spar/energy-storage battery integral structure, it is characterised in that: carbon fiber skin and Kev
Drawing inner wall thickness is 0.2～0.3mm；PMI foam layer thickness is 8～10mm.
4. a kind of spar/energy-storage battery integral structure, it is characterised in that: energy-storage battery is by the wing
The rib being all provided with in beam inwall circumference supports.
5. a kind of spar/energy-storage battery integral structure, it is characterised in that: energy-storage battery is by being positioned at
At energy-storage battery rear and front end, the fastening screw running through spar opposite flank realizes axially location.
6. a kind of spar/energy-storage battery integral structure, it is characterised in that: heat-insulation window uses shutter
Structure, can be automatically opened up by gas pressure and close.
7. a kind of spar/energy-storage battery integral structure, it is characterised in that: also include control module, control
Molding block has temperature sensor and control circuit；Temperature sensor is used for real-time perception spar internal temperature information, and feeds back
To control circuit；Control circuit is used for obtaining in real time the temperature value of temperature sensor measurement, and by temperature value and control circuit
The temperature threshold set compares, and when temperature value is more than design temperature threshold value, control circuit sends control signal, controls to inhale
Fan is opened with exhaust fan；When ambient temperature is less than the temperature threshold set, control circuit sends control signal, controls blower fan
Close with exhaust fan.
8. a kind of spar/energy-storage battery integral structure, it is characterised in that: temperature sensor is along spar
Axially arrange at equal intervals, received the temperature value of each temperature sensor measurement by control circuit, and by each temperature value and temperature
Threshold value contrasts, if the temperature value of one of them temperature sensor measurement is less than temperature threshold, just controls blower fan and row
Fan cuts out, otherwise controls blower fan and open with exhaust fan.
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 |
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| Publication Number | Publication Date |
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| CN106240798A true CN106240798A (en) | 2016-12-21 |
| CN106240798B CN106240798B (en) | 2018-05-18 |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3544083A1 (en) * | 2018-03-22 | 2019-09-25 | Airbus Defence and Space GmbH | Battery assembly for load bearing structural integration of batteries in a vehicle |
| WO2020077121A1 (en) | 2018-10-10 | 2020-04-16 | Rpr Aero, Inc. | Aircraft spars with integrated power cells, and associated systems and methods |
| EP3733511A1 (en) * | 2019-04-30 | 2020-11-04 | The Boeing Company | Removable battery compression devices |
| US11217839B2 (en) | 2018-02-12 | 2022-01-04 | Airbus Defence and Space GmbH | Battery arrangement for structurally integrating batteries in a vehicle |
| CN113955073A (en) * | 2021-10-19 | 2022-01-21 | 西北工业大学 | A filled type battery case structure for aircraft wallboard structure |
| CN114162335A (en) * | 2020-09-11 | 2022-03-11 | 海鹰航空通用装备有限责任公司 | Near space vehicle energy storage battery thermal management system |
| US11302979B2 (en) | 2018-02-12 | 2022-04-12 | Airbus Defence and Space GmbH | Battery arrangement for the structural integration of batteries in a vehicle |
| EP3931095A4 (en) * | 2019-03-01 | 2022-11-16 | Pratt & Whitney Canada Corp. | Aircraft having hybrid-electric propulsion system with electric storage located in wings |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| EP3931095A4 (en) * | 2019-03-01 | 2022-11-16 | Pratt & Whitney Canada Corp. | Aircraft having hybrid-electric propulsion system with electric storage located in wings |
| EP3733511A1 (en) * | 2019-04-30 | 2020-11-04 | The Boeing Company | Removable battery compression devices |
| US11440430B2 (en) | 2019-04-30 | 2022-09-13 | The Boeing Company | Removable battery compression devices |
| CN114162335A (en) * | 2020-09-11 | 2022-03-11 | 海鹰航空通用装备有限责任公司 | Near space vehicle energy storage battery thermal management system |
| CN113955073A (en) * | 2021-10-19 | 2022-01-21 | 西北工业大学 | A filled type battery case structure for aircraft wallboard structure |
| 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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| CN106240798B (en) | 2018-05-18 |
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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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