CN109760819A - A kind of structure battery component of aircraft and aircraft - Google Patents
A kind of structure battery component of aircraft and aircraft Download PDFInfo
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- CN109760819A CN109760819A CN201811586248.5A CN201811586248A CN109760819A CN 109760819 A CN109760819 A CN 109760819A CN 201811586248 A CN201811586248 A CN 201811586248A CN 109760819 A CN109760819 A CN 109760819A
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Abstract
The present invention provides the structure battery component of a kind of aircraft and aircraft, belong to aircraft overall design technique field, structure battery component can play the function of load and power supply and/or storage simultaneously, total weight when structure and mutually indepedent battery is effectively reduced, it can be applied to aircraft, realize the loss of weight of Aircraft structure and battery system.Aircraft is a kind of aircraft with structure battery component, and a kind of structure battery component includes the covering of at least rib at both ends and circumferential direction；The both ends of covering have rib；Covering is the multi-layer board that at least there is a function laying；Function laying has bearing function, and has power supply and/or energy storage function；Make full use of the designability of composite structure, the structure of load and the battery of power supply and/or storage are combined into one, using the structure battery component with load, power supply and/or energy storage function, realize aircraft lighting, and more mission payload weight can be exchanged for, promote aircraft performance.
Description
Technical field
The invention belongs to aircraft overall design technique fields, are related to the aircraft with structure battery component.
Background technique
Existing aircraft includes two mutually independent subsystems of structure and power supply.Structure subsystem plays load function, makes
Aircraft has enough strength and stiffness to resist external load effect；Subsystem of powering is to maintain flight control, electronics
The normal operation of the subsystems such as equipment or even Powered Propulsion.
Structure subsystem and power supply subsystem loss of weight should be navigated under the premise of meeting itself functional restraint with being promoted as far as possible
Pocket performance.To realize lighting, the structure of existing aircraft uses composite laminated plate more and more, but laminate
Electroactive substance is free of in laying, therefore structure itself does not have power supply and charge storage ability.Existing aircraft power supply, which divides, is
Battery in system is mainly made of anode, cathode, diaphragm, electrolyte and outer packing shell etc., and electrochemical reaction occurs in battery,
And battery itself does not have biggish load ability.
For using high-altitude pseudo satellite, pseudolite as the aircraft of representative, required secondary cell quantity is more, and weight is big, and battery installation position is set
It is limited by inside configuration space, flight with equality factor.Meanwhile to undertake this biggish concentrfated load of secondary cell,
Battery installation position sets neighbouring structure and needs sufficiently to reinforce, and structure is caused to increase weight.In addition, secondary cell and airborne equipment etc. point are
There are certain distribution distances between system, cause connecting cable longer, and cable weight gain problem is significant.When aircraft weight limitation is tight
When severe, loss of weight is carried out to structure and battery respectively and has exposed biggish limitation, is not easy to realize.
For using use solar energy as the high-altitude pseudo satellite, pseudolite in energy source.On structure subsystem, existing such boat
Pocket uses girder structure, and construction weight accounts for the 30% to 40% of whole machine weight.In power supply subsystem, existing such aviation
Device uses secondary cell, and battery weight accounts for 50% or more whole machine weight, is connected to structure main load-bearing part by additional bracket.This
Class Aircraft requirements reduce structure and battery weight as far as possible to exchange more mission payload weight for, these mission payloads can be real
The now functions such as communication relay, reconnaissance and surveillance, Disaster Assessment.However, total weight that reality is structure and battery has been approached
The 90% of aircraft weight ties up the weight indicator of distribution of mission payload, causes carrying mission payload extremely limited, or apply
Pressure is developed in mission payload miniaturization.Individually reducing construction weight will be unable to bear the larger concentrfated load of battery bring；Individually
Reducing battery weight will be unable to provide the electric energy for maintaining it to work normally for mission payload, or even influence the long boat of high-altitude pseudo satellite, pseudolite
Shi Feihang reduces the efficiency-cost ratio of operation high-altitude pseudo satellite, pseudolite.
Therefore, load and power supply/storage requirement can be integrated while structure and battery weight can be effectively reduced by how designing one kind
The aircraft and associated components of amount, with regard to becoming very necessary problem.
(more and more Flight Vehicle Structures use fiber composite layer plywood, thus meeting structural strength and rigidity
Lighting is realized under design requirement.Fiber composite layer plywood is by multiple unidirectional fibres or Fabric prereg according to certain
Heat-pressure curing forms after ply stacking-sequence paving, and each unidirectional fibre or Fabric prereg constitute a laying, therefore fiber
Composite laminated plate has very strong designability.In the design of existing fiber composite structure, layer is generally only considered
The mechanical property of plywood.
Secondary cell is also known as rechargeable battery.Existing secondary cell includes anode, cathode, diaphragm, shell etc., passes through electricity
Reversible electrochemical reaction, which is realized, inside pond is charged and discharged.The parts such as battery case belong to the parasitic part of battery, itself is not
Chemical energy can be converted to electric energy, and there is certain quality, influence the energy density of secondary cell.When existing secondary cell is answered
When the aircraft that empty-weight limitation is harsh for big to electrical energy demands, required secondary cell quantity with limited it is secondary
Battery weight just becomes design contradiction.It needs especially to reinforce in addition, battery installation position sets neighbouring Flight Vehicle Structure, and causes to fly
Row device structure weight gain, it is difficult to reach lighting.
By taking existing solar energy unmanned plane as an example, it is desirable that reduction construction weight as far as possible is general to use to improve flying quality
The beam that carbon fibre composite laminate is constituted is as main load-bearing part.To realize flying for solar energy unmanned plane several weeks or even several months
Row needs to carry the secondary cell for accounting for 50% or more whole machine weight.Secondary cell needs to be connected to master by additional bracket and holds
In power part structure.Secondary cell on existing solar energy unmanned plane uses lithium-sulfur cell, and there are more lithium sulfides to fly for lithium-sulfur cell
The problems such as shuttle effect, battery volume acutely expand, capacitance fall-off is serious, and charge and discharge cycles number is relatively smaller, is not so good as alkaline nickel
Base secondary cell and lithium ion secondary battery are safe and reliable.
Structure battery is a kind of design new concept for taking into account mechanical property and electrical property.To solve the above-mentioned prior art not
Foot, how using the especially internal laying of fiber composite layer plywood designability, be allowed to have simultaneously load, power supply and
The function of storage safely and reliably realizes structure battery design concept, with regard to becoming very necessary problem.)
Summary of the invention
The object of the present invention is to provide a kind of aircrafts with structure battery component, which can be simultaneously
The function of load and power supply and/or storage is played, aircraft empty-weight can be effectively reduced, and promote aircraft performance.
It also proposes a kind of structure battery component, the function of load and power supply and/or storage can be played simultaneously, knot is effectively reduced
Total weight when structure and battery are mutually indepedent, can be applied to aircraft, realize Aircraft structure and battery system
Loss of weight.
The technical scheme is that a kind of structure battery component of aircraft, which is characterized in that including at least both ends
Rib and circumferential covering；The both ends of covering have rib；Covering is the multi-layer board that at least there is a function laying；Function paving
Layer has bearing function, and has power supply and/or energy storage function；Function laying includes anode, diaphragm, cathode；Diaphragm is located at sun
Prevent anode and cathode from directly contacting between pole and cathode；Anode, the two poles of the earth that cathode is battery, diaphragm includes electrolyte；Anode
In contain one or several conductive fiber filaments.
Preferably, it is made of the rib and circumferential covering at both ends, rib is located at the both ends of covering.
Preferably, from beam or wall and stringer form exhibition to load bearing frame, rib be tangential load bearing frame, if rib is
Dry, and extend to parallel arrangement, circumferential covering covering exhibition to tangential load bearing frame.
Preferably, from wall form exhibition to load bearing frame, rib is tangential load bearing frame, and rib is several, and edge
Open up to parallel arrangement, circumferential covering covering exhibition to tangential load bearing frame.
Preferably, rib is multi-layer board only with load function, or the multi-layer board comprising function laying.
It preferably, further include thermal insulation layer；Thermal insulation layer is located at the outer surface of covering, or further includes thermal insulation layer and photovoltaic group
Part；Photovoltaic module is located at the upper face of the outer surface of thermal insulator, and solar energy converts to obtain electric energy through photovoltaic module.
Preferably, function laying specific structure is further defined in that
Anode is a fibre bundle or several fibre bundles not contacted each other, and fibre bundle is one with conductive capability
A fiber filament or multiple carbon fiber wires；Diaphragm is the solid polymer electrolyte of anode periphery；Cathode be then containing with carbon energy
Enough form the polymeric matrix of the active material of electrochemical reaction；
Or function laying specific structure is further defined in that
Anode and cathode is located at first layer, third layer；Diaphragm is located at middle layer, and anode includes anode substrate and anode substrate
In the first fiber, cathode includes the third fiber in cathode base and cathode base；Diaphragm includes diaphragm matrix and diaphragm base
The second fiber in body；First fiber, third fiber are conductive, and the second fiber is electrical insulator；Anode substrate, matrix yin
Comprising being capable of forming the corresponding active material of electrochemical reaction in extremely；Diaphragm is the polymer comprising electrolyte.
A kind of structure battery component of aircraft, the rib at both ends is by a kind of structure battery component energy of above-mentioned aircraft
Enough it is glued or is mechanically connected.
A kind of aircraft, which is characterized in that including wing, some or all of wing is by a kind of several above-mentioned aviations
The structure battery component of device connects composition.
Preferably, aircraft further includes empennage, partly or entirely by a kind of structure electricity of several above-mentioned aircrafts
Pond component connection composition.
A kind of (function laying of structure battery, which is characterized in that including anode, diaphragm, cathode；Diaphragm be located at anode and
Prevent anode and cathode from directly contacting between cathode；Anode, the two poles of the earth that cathode is battery, diaphragm include electrolyte；Its feature exists
In containing one or several conductive fiber filaments in anode.
Preferably, anode is a fibre bundle or several fibre bundles not contacted each other, and fibre bundle is with conduction
One fiber filament of ability or multiple carbon fiber wires；Diaphragm is the solid polymer electrolyte of anode periphery；Cathode be then containing
There is the polymeric matrix for the active material that electrochemical reaction is capable of forming with carbon.
Preferably, there is gap between fibre bundle, be evenly arranged in the polymeric matrix of cathode.
Preferably, fibre bundle lines up multilayer, and the fibre bundle axis between multilayer is arranged in parallel；Or fibre bundle line up it is more
Layer, the fibre bundle axis between multilayer is staggered.
Preferably, anode and cathode is located at first layer, third layer；Diaphragm is located at middle layer, anode include anode substrate and
The first fiber in anode substrate, cathode include the third fiber in cathode base and cathode base；Diaphragm includes diaphragm matrix
With the second fiber in diaphragm matrix；First fiber, third fiber are conductive, and the second fiber is electrical insulator；Anode base
Comprising being capable of forming the corresponding active material of electrochemical reaction in body, substrate cathode；Diaphragm is the polymer comprising electrolyte.
Preferably, the first fiber, the second fiber and third fiber are that vertical or horizontal fibre bundle or fibre bundle are formed
Fabric.
Preferably, anode substrate, diaphragm matrix, cathode base are epoxy resin, rubber or resin and rubber composition.
Preferably, conductive fiber is the glass fibre that carbon fiber or outer surface apply conductive layer.
Preferably, electrical insulator is the carbon fiber that glass fibre or outer surface apply electric insulation layer.
A kind of structure battery, which is characterized in that be multi-layer board, the function laying including a kind of above-mentioned structure battery.)
The solution have the advantages that:
(1) aircraft of the invention makes full use of the designability of composite structure, by the structure and power supply of load
And/or the battery of storage is combined into one, and using the structure battery component with load, power supply and/or energy storage function, realizes aviation
Device lighting, and more mission payload weight can be exchanged for, promote aircraft performance；
(2) structure battery component of the invention makes full use of the characteristics of covering is far from wing section center, makes structure battery portion
Part has the mechanical property of preferable resist torque and torque, while so that structure battery component is preferably maintained aerofoil profile and supporting light
Lie prostrate component；
(3) structure battery component of the invention makes load, power supply and/or the storage more distribution of aircraft, on the one hand
The strength/rigidity constraint to aircraft structure design is greatly reduced, and alleviates the trim constraint of aircraft；On the other hand
Aircraft interior equipment and instrument installation space is not tied up, and avoids that cable between existing battery and electrical equipment is too long to ask
Topic, reduces the weight of power distribution assembly.
(technical effect of function laying:
Secondary cell function is implanted into load-carrying construction, can be reduced battery by the designability for making full use of composite material
The parasitism part such as shell, is conducive to the raising of battery energy density.
Function laying is based primarily upon the mature secondary cell technology such as alkaline Ni-based and lithium ion and realizes power supply and/or storage function
Can, charge and discharge cycles number is high, safe and reliable.
Structure battery component takes into account mechanical property and electrical property, with the mutually independent existing side of load-carrying construction and secondary cell
Case is compared, and can be effectively reduced total weight of Aircraft structure and power supply system, is conducive to the raising of aircraft performance.)
Detailed description of the invention
Fig. 1 is the schematic diagram that the present invention is applied to certain aircraft embodiment with structure battery component；
Fig. 2 is the overall schematic of structure battery component in embodiment；
Fig. 3 is the diagrammatic cross-section of structure battery component in embodiment, wherein (a) indicates the circumferential knot of structure battery component
Structure is made of covering, (b) is indicated that the circumferential structure of structure battery component is made of covering and thermal insulation layer, (c) is indicated structure battery
The circumferential direction of component is made of covering, thermal insulation layer and photovoltaic module；
Fig. 4 is the Multilayer Structure schematic diagram of covering in embodiment；
Fig. 5 is the schematic diagram of function laying embodiment one；
Fig. 6 is the schematic diagram of function laying embodiment two；
Specific embodiment
The present invention is described in further detail with reference to the accompanying drawing.
As shown in Figure 1, aircraft 1 has wing 2, it further include empennage 3, at least wing 2 is partly or entirely by several
Structure battery component 10 forms.The aircraft 1 is the high-altitude pseudo satellite, pseudolite using solar energy as energy source.Alternatively, aviation
Device 1 is also possible to unfinned solar energy high-altitude pseudo satellite, pseudolite, or the high-altitude pseudo satellite, pseudolite or other solid using other energy sources
Determine wing unmanned plane or manned aircraft.Aircraft 1 can be used for the fields such as communication relay, reconnaissance and surveillance, Disaster Assessment, have ten
Divide important military/civilian value.
For solar energy unmanned plane, some or all of components such as wing 2, empennage 3 can be by several structure battery portions
Part 10 is formed.
As shown in Fig. 2, a kind of structure battery component 10, rib 15 and circumferential covering 20 including at least both ends；Covering
20 both ends have rib 15；Covering 20 has load and power supply/energy storage function, i.e., while covering 20 is as main load-bearing part
Has the function of secondary cell.Rib 15 can be only load-carrying member, or load and power supply/storage while comprising function laying 25
Component.
Further, using the rib 15 at 10 both ends of structure battery component, adjacent structure battery component 10 is subjected to glue
It connects or is mechanically connected.
Under the premise of 20 loads of covering/function of supplying power is integrated, the specific constructive form of structure battery component 10 can be with
It is monocoque, one piece or multi-wall type.
A kind of structure battery component 10, specific constructive form are monocoque, by the rib 15 and circumferential covering 20 at both ends
Composition, rib 15 are located at the both ends of covering 20.
A kind of structure battery component 10: multi-wall type: exhibition is formed to the load bearing frame of (transverse direction) from wall, rib is tangential (vertical
To) load bearing frame, rib is several parallel arrangements (rib number is less), on circumferential covering covering wall and rib.
A kind of structure battery component 10: for one piece；It is made of and is opened up to the load bearing frame of (transverse direction) beam (or wall) and stringer,
Rib is the load bearing frame of tangential (longitudinal direction), and rib is several parallel arrangements (rib number is more), circumferential covering covering
Load bearing frame.
As shown in figure 3, structure battery component 10 includes the covering 20 of at least rib 15 at both ends and circumferential direction；It further include heat-insulated
Layer 21, thermal insulation layer 21 is located at the outer surface of covering 20, and composition material is foam or aeroge.Thermal insulation layer 21 protects covering 20 to exist
It can normal power supply and storage under low temperature environment.
It further include thermal insulation layer 21 and photovoltaic module 22, thermal insulation layer 21 is located at the outer surface of covering 20.Photovoltaic module 22 is located at
The upper face of the outer surface of thermal insulator 21.Photovoltaic module 22 is made of solar battery, facial mask, glue film and backboard.Wherein, too
Positive energy battery preferentially uses fexible film multijunction solar cell.Solar energy obtains electric energy through the conversion of photovoltaic module 22.
For the lower surface stressed-skin construction of a structure battery component, layer structure by photovoltaic module 7 or is not it
Its functional structure layer, internal layer are followed successively by thermal insulation layer 21 and covering 20.
Covering 20 is composite laminated plate (structure battery), is made of at least one function laying 25.
As shown in figure 4, the structure type of covering 20 is composite laminated plate (structure battery), composite laminated plate
At least there is a function laying 25 in (structure battery).
Function laying 25 is made of anode 31, diaphragm 32 and cathode 33.Diaphragm 32 is prevented between anode 31 and cathode 33
Only anode 31 and cathode 33 directly contact.Anode, the two poles of the earth that cathode is battery.Diaphragm 32 contains electrolyte.Function laying 25
Anode includes conductive fiber, and 25 cathode base of function laying is polymeric matrix.Contain one or several conductions in anode
Fiber filament.For fiber for bearing most of mechanical loading, polymeric matrix is for binder fibre and can bear a small amount of mechanical loading.
Function laying 25 contains electroactive substance, is converted the chemical energy in active material to by electrochemical reaction
Electric energy, at this point, covering 20 has load and function of supplying power.
The electroactive substance of function laying 25 realizes the chemical energy in active material by reversible electrochemical reaction
With mutually converting for electric energy.At this point, covering 20 has load, power supply and energy storage function.
Fig. 4 shows the laminate using a function laying 25.Laminate shown in Fig. 4 contains 5 layings.Composite layer
Plywood at least contains 1 function laying.When using multiple above-mentioned function layings 25, need to carry out between each function laying group
Electrical isolation measure.Add insulating layer between each layer.
Other layers of the composite laminated plate of covering 20 use bearing layer, and general utility functions laying 25 is not arranged in covering 20
Outermost layer.
Function laying 25 can have one of two kinds of forms of Fig. 5 or shown in fig. 6.
Specific embodiment 1:
As shown in figure 5, function laying 25 includes anode 31, diaphragm 32 and cathode 33；First layer structure, third layer are made respectively
For the anode 31 and cathode 33 of battery, diaphragm 32 of the media layer damage as battery.
(each layer is prepreg.Prepreg is Fabric prereg, i.e., has the first fiber 51 in anode, have in cathode
Third fiber 53 has the second fiber 55 in diaphragm 32)
Anode includes the first fiber 51 in anode substrate 52 and anode substrate；Cathode includes cathode base and cathode base
In third fiber 53；Diaphragm 32 includes the second fiber 55 in diaphragm matrix 21 and diaphragm.
Anode (polymer) matrix 52, diaphragm (polymer) matrix 56 of diaphragm and the cathode (polymer) of cathode of anode
Matrix 54 all has electrical insulating property.It can be epoxy resin, rubber or resin-rubber composition.Diaphragm can use other
Polymer.
The first fiber 51 in anode and the third fiber 53 in cathode are conductive, connect with metal collector or straight
It connects as collector.The first fiber 51 in anode and the third fiber in cathode can use carbon fiber, or use appearance
The glass fibre of face painting conductive layer.
The second fiber 55 in diaphragm has electrical insulating property, can use glass fibre, or apply electricity absolutely using outer surface
The carbon fiber of edge layer.
The fiber reinforcement form number and arrangement mode of each layer structure are not limited to situation shown in Fig. 5, and the plain weave being not limited to is knitted
Object form, the first fiber, 55 third fiber of the second fiber can be the fibre bundle or fibroplastic fabric of vertical and horizontal；Sun
Pole 31, diaphragm 32 and 33 one or more of cathode can use unidirectional pre-immersion material.
Anode (polymer) matrix 52 and cathode (polymer) matrix 54 include to be capable of forming the corresponding work of electrochemical reaction
Property particle；Inside contain electroactive substance, contains electrolyte in diaphragm matrix 56.
When lithium ion electrochemical reaction occurs in the function laying group 25 of fibrous composite shown in fig. 5, anode is poly-
Closing the electroactive substance in object matrix 52 is carbon (for example, graphite or polyacrylonitrile carbon fiber), cathode polymer matrix 54
Interior electroactive substance is lithium salts (for example, cobalt acid lithium or nickle cobalt lithium manganate), the electrolyte in membrane polymer matrix 56
Form is solid polymer, gel or solution.When using solid polymer electrolyte, which be can be used as
Membrane polymer matrix 56.
When alkaline nickel-based electrochemical reaction occurs in fibrous composite laying group 25 shown in fig. 5, anode polymer
Electroactive substance in matrix 52 is nickel hydroxide, and the electroactive substance in cathode polymer matrix 54 is non-nickel gold
Belong to oxide (for example, zinc oxide or iron oxide), the electrolyte form in membrane polymer matrix 56 is solution (for example, hydrogen-oxygen
Change potassium solution).
It leads ionic for anode in enhancing function laying 25, diaphragm, cathode polymer matrix, can polymerize at least anode
Ionic agent (for example, polyethylene glycol oxide) is led in the addition of one of object matrix 52, cathode polymer matrix 54 and membrane polymer 56.Together
When, for penetrating power of the enhancing electrolyte in membrane polymer matrix, can polymerize at least anode polymeric matrix 52, cathode
One of object matrix 54 and membrane polymer 56 add pore-foaming agent (for example, carbon black or silica gel).
It, can be at least anode polymeric matrix 52 and yin for the electric conductivity of anode or (with) cathode in enhancing function laying 25
One of pole polymeric matrix 54 adds conductive agent (for example, carbon black, carbon nanotube or graphene).
Specific embodiment two
Function laying 25 includes anode 31, diaphragm 32 and cathode 33.
Anode 31 is a fibre bundle or several fibre bundles not contacted each other, and fibre bundle is with conductive capability
One fiber filament or multiple fiber filaments.
Diaphragm 32 is the solid polymer electrolyte of 31 periphery of anode；31 periphery of anode can be coated in.
Cathode 33 is then the polymeric matrix containing electroactive substance, and is connect with metal collector.
If Fig. 6 shows, multiple fibre bundles with conductive capability are coated with solid polymer electrolyte outside；It is dipped in containing electrification
In the polymer matrix body for learning active particles.
Galvanic anode connects (collector is not drawn into Fig. 6) directly as collector or with metal collector.Fiber
The number and arrangement mode of beam are not limited to situation shown in Fig. 6.There is gap between fibre bundle, be evenly arranged.It can make parallel
It arranges or is staggered.
Anode 31 uses polyacrylonitrile carbon fiber silk or fibre bundle, and the electroactive substance in cathode 33 is lithium salts
(for example, cobalt acid lithium or nickle cobalt lithium manganate), the electrochemical reaction occurred in fibrous composite laying group 25 at this time is lithium ion
Electrochemical reaction.
For solar energy unmanned plane, specific work process are as follows: solar energy is changed into electricity by photoelectric effect by photovoltaic module
Can, the voltage between function laying anode and cathode is higher than some numerical value at this time, leads to that reverse electrification occurs in function laying
Reaction is learned, the chemical energy in electroactive substance is converted electrical energy into.Night does not produce electricl energy without solar energy, photovoltaic module,
Cause the voltage between function laying anode and cathode lower than some numerical value, causes the electrochemistry that forward direction occurs in function laying anti-
It answers, the chemical energy in electroactive substance is changed into electric energy.
The invention has the characteristics that:
1, aircraft of the invention can be high-altitude pseudo satellite, pseudolite, fixed-wing unmanned plane, manned aircraft etc.；The aircraft
Comprising wing, or include wing and empennage；At least some or all of wing is made of several structure battery components.
2, the structure battery component in the present invention includes at least covering, has battery function while covering is as main load-bearing part
Energy.
3, the covering in the present invention is composite laminated plate, at least there is a function laying, function paving in laminate
Electrochemical reaction occurs in layer group, electrochemical reaction can be reversible.
4, function laying, galvanic anode, cathode and diaphragm are all made of the layer structure type of fibre reinforced matrix, anode layer knot
Structure and cathode layer structure are separated by membrane layer structure, and the fiber in anode layer structure and cathode layer structure is conductive and matrix contains
Electro-chemical activity particle, fiber electrical isolation in membrane layer structure and contain electrolyte in matrix.
Claims (10)
1. a kind of structure battery component of aircraft, which is characterized in that the covering of rib (15) and circumferential direction including at least both ends
(20)；The both ends of covering (20) have rib (15)；Covering is the multi-layer board that at least there is a function laying (25)；Function paving
Layer (25) has bearing function, and has power supply and/or energy storage function；Function laying includes anode, diaphragm, cathode；Diaphragm
(32) prevent anode (31) and cathode (33) from directly contacting between anode (31) and cathode (33)；Anode, cathode are battery
The two poles of the earth, diaphragm (32) includes electrolyte；Contain one or several conductive fiber filaments in anode.
2. a kind of structure battery component of aircraft according to claim 1, which is characterized in that by the rib (15) at both ends
It is formed with circumferential covering (20), rib (15) is located at the both ends of covering (20).
3. a kind of structure battery component of aircraft according to claim 1, which is characterized in that by beam or wall and stringer group
The load bearing frame of Cheng Zhanxiang, rib are tangential load bearing frame, and rib is several, and is extended to parallel arrangement, circumferential illiteracy
Skin covering exhibition to tangential load bearing frame.
4. a kind of structure battery component of aircraft according to claim 1, which is characterized in that from wall form exhibition to hold
Power skeleton, rib are tangential load bearing frame, and rib is several, and is extended to parallel arrangement, circumferential covering covering exhibition to
With tangential load bearing frame.
5. a kind of structure battery component of aircraft according to any one of claims 1 to 4, which is characterized in that rib (15)
For only with the multi-layer board of load function, or the multi-layer board comprising function laying (25).
6. a kind of structure battery component of aircraft according to any one of claims 1 to 4, which is characterized in that further include every
Thermosphere (21)；Thermal insulation layer is located at the outer surface of covering, or further includes thermal insulation layer (21) and photovoltaic module (22)；Photovoltaic module position
Upper face in the outer surface of thermal insulator, solar energy convert to obtain electric energy through photovoltaic module.
7. a kind of structure battery component of aircraft according to any one of claims 1 to 6, which is characterized in that function laying
Specific structure is further defined in that
Anode is a fibre bundle or several fibre bundles not contacted each other, and fibre bundle is a fibre with conductive capability
Tie up silk or multiple carbon fiber wires；Diaphragm is the solid polymer electrolyte of anode periphery；Cathode (33) then for containing with carbon energy
Enough form the polymeric matrix of the active material of electrochemical reaction；
Or function laying specific structure is further defined in that
Anode and cathode is located at first layer, third layer；Diaphragm (32) is located at middle layer, and anode includes anode substrate (52) and anode
The first fiber (51) in matrix, cathode include the third fiber (53) in cathode base (54) and cathode base；Diaphragm (32)
Including the second fiber (55) in diaphragm matrix (56) and diaphragm matrix；First fiber (51), third fiber (53) have conduction
Property, the second fiber is electrical insulator；Comprising being capable of forming the corresponding active matter of electrochemical reaction in anode substrate, substrate cathode
Matter；Diaphragm is the polymer comprising electrolyte.
8. a kind of structure battery component of aircraft, which is characterized in that the rib at both ends, claim 1 to 7 is any described
A kind of structure battery component of aircraft is able to carry out splicing or mechanical connection.
9. a kind of aircraft, which is characterized in that including wing (2), some or all of wing (2) is by several claims 1
Structure battery component to a kind of 7 any aircrafts connects composition.
10. a kind of aircraft according to claim 9, which is characterized in that further include empennage (3), partly or entirely by
A kind of structure battery component of any aircraft of several claims 1 to 7 connects composition.
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| CN201811586248.5A CN109760819A (en) | 2018-12-24 | 2018-12-24 | A kind of structure battery component of aircraft and aircraft |
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| CN201811586248.5A CN109760819A (en) | 2018-12-24 | 2018-12-24 | A kind of structure battery component of aircraft and aircraft |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112693618A (en) * | 2020-12-29 | 2021-04-23 | 中国航空工业集团公司西安飞机设计研究所 | Energy storage-bearing integrated bionic common wing rib and manufacturing method thereof |
| CN115084735A (en) * | 2022-07-01 | 2022-09-20 | 重庆大学 | High-strength lithium ion battery composite material with honeycomb sandwich structure |
| US20220371739A1 (en) * | 2019-12-05 | 2022-11-24 | Airbus Operations Gmbh | Lightweight structure for a vehicle and aircraft |
| CN115520370A (en) * | 2022-09-22 | 2022-12-27 | 中国商用飞机有限责任公司 | Wing system and electric aircraft integrated with power battery module |
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