CN115520370A

CN115520370A - Wing system integrated with power battery module and electric airplane

Info

Publication number: CN115520370A
Application number: CN202211162443.1A
Authority: CN
Inventors: 钱仲焱; 吴昊; 黄劲松; 查振羽; 赵星晨; 郝放
Original assignee: Commercial Aircraft Corp of China Ltd
Current assignee: Commercial Aircraft Corp of China Ltd
Priority date: 2022-09-22
Filing date: 2022-09-22
Publication date: 2022-12-27
Also published as: WO2024060585A1

Abstract

The invention relates to a wing system integrated with a power battery module, which comprises: a wing box including a plurality of wing support members arranged to define at least one power cell mounting bay therebetween, and a power cell disposed in the at least one power cell mounting bay such that the plurality of wing support members making up the at least one power cell mounting bay serve as at least a portion of a battery enclosure for the power cell. In the wing system according to the invention, the wing box section serves as a part of the battery housing, so that the battery cells or cells are accommodated therein, thereby providing effective and safe protection and necessary functions for the power battery module, reducing the weight of the power battery system, and improving the structural and space utilization. In addition, the invention also relates to an electric airplane.

Description

Wing system integrated with power battery module and electric airplane

Technical Field

The invention relates to the technical field of electric airplanes, in particular to a wing system integrated with a power battery module. In addition, the invention also relates to an electric airplane.

Background

Global warming is a problem that all people must currently face in common. Since 1750 s, CO has been accumulated globally ₂ The emission is more than 1 million tons, the emission per year reaches 380 million tons at present, and is more than 6 times of that before the industrial revolution, and the huge influence and destructive power of global warming are shown.

With the rise of the awareness of environmental protection, in the current transportation means (rail transit, automobiles, ships and airplanes), rail transit including urban high-speed rails and urban rails has basically and completely realized electrification, and ships and aircrafts are also actively developing electrification, but electric airplanes in the aircrafts are more widely applied.

The electric aircraft drives the aircraft by adopting a motor and a power battery to replace the existing internal combustion engine and aviation fuel, so that a plurality of excellent characteristics are obtained, such as: the electric airplane does not discharge polluted gas into the air; compared with the airplane in the traditional power mode, the electric airplane generates smaller vibration, and brings good riding experience to passengers.

The weight energy density of the power battery is still at a low level due to the technical level of the current power battery, and the weight of the power battery system accounts for about 40% of the maximum takeoff weight of the airplane under the condition of meeting the range requirement with market competitiveness.

Generally speaking, a power battery module mainly comprises an external shell and an electric core (or called a battery monomer) inside the shell, the external shell structure mainly provides safety protection for components of the internal battery module, in order to meet safety requirements, the external shell structure is usually made of high-strength steel, the weight of the shell accounts for about 30% of that of the whole power battery module, and a heavy shell causes further reduction of the weight energy density of the power battery system, so that the range distance and the commercial load weight of the electric aircraft are reduced.

Therefore, there is a need for a wing system integrated with a power battery module, which can be applied to an electric aircraft, and can provide effective safety protection and necessary functions for the power battery module, reduce the weight of the power battery system, and improve the structural and space utilization rate, so as to reduce the overall weight of the aircraft, improve the range of the aircraft, and increase the effective load, so as to overcome one or more disadvantages in the prior art.

Disclosure of Invention

The invention aims to provide a wing system integrated with a power battery module, which can be used on an electric airplane.

According to an aspect of the present invention, there is provided a wing system integrated with a power battery module, the wing system may include:

a wing box comprising a plurality of wing support members arranged to define at least one power cell installation compartment therebetween, and

the power battery unit is arranged in the at least one power battery unit installation cabin, so that a plurality of wing supporting members forming the at least one power battery unit installation cabin are used as at least one part of a battery shell of the power battery unit.

In the wing system according to the invention, the wing box section can serve as a part of the battery housing, so that the battery cell or the battery cell is accommodated therein, thereby providing effective and safe protection and necessary functions for the components of the power battery module (in particular the battery cell or the battery cell), reducing the weight of the power battery system, and improving the structural and space utilization. According to the prototype test carried out by the inventor, the system can significantly reduce the number of parts and the weight of the whole electric airplane. For example, the system can improve the strength performance of the power battery module by about 40%, and can reduce the weight of the power battery module to about 7.2% of the weight of the whole electric aircraft.

According to the above aspect of the invention, preferably, the plurality of wing support members may be connected together by at least two of one or more positive fit connections and one or more non-positive fit connections.

Through the arrangement, the wing supporting member has a redundant connection mode, and when one connection mode fails, load transmission can be carried out through the redundant design, so that the wing supporting member has the advantage that enough safety guarantee can be still provided for the power battery module under the extreme condition.

According to the above aspect of the present invention, preferably, the form-fit connection may be in the form of a plug-in connection, and the force-fit connection may be in the form of a connection by a fastener.

It is advantageous to realize a form-fitting connection by means of a plug connection and a force-fitting connection by means of a fastener connection. On one hand, the wing structure of the airplane can be modified or revised based on the structure of the existing airplane wing without greatly modifying the wing of the airplane; on the other hand, the two connection modes are detachable, so that the battery can be disassembled and assembled more conveniently and quickly for multiple times, for example, the battery is used for replacing or maintaining a battery, overhauling operation and the like.

According to the above aspect of the invention, preferably, the wing system may further include a mechanical connection fillet provided at a corner of the power cell mounting compartment, and the mechanical connection fillet may be provided with a fastener mounting hole for fixing together adjacent wing support members of the plurality of wing support members by means of a fastener.

The mechanical connection angle piece is arranged at the weak connection position such as the corner, so that the connection strength between wing support members can be further increased, and the strength performance of the power battery module and the wing system can be improved.

According to the above aspect of the invention, preferably, a bonding fillet may be provided at an inner portion of the corner of the power cell installation compartment to bond adjacent wing support members of the plurality of wing support members together with an adhesive.

By arranging the adhesive corner pieces in the circumferential direction, one or more form-fitting or force-fitting connections can be added to or in some cases replaced. In addition, the bonding structure can solve the problem of poor sealing performance of the joint of the wing supporting member (such as the corner part), effectively improve the sealing performance and the air tightness between the power battery module and the wing box section structural member, and has the advantages of preventing external air and moisture from permeating into the power battery module.

According to the above aspect of the present invention, preferably, at least one of the plurality of wing support members may be made of carbon fiber prepreg, wherein the carbon fiber prepreg is laid in a laying direction and machined in a final shape of the at least one wing support member after curing at normal temperature.

Through the arrangement, the weight of the wing can be further reduced while the supporting strength of the wing and the strength performance of the power battery module are maintained, so that the range of an airplane provided with the wing system is increased, and the energy efficiency is improved.

According to the above aspect of the invention, preferably, the plurality of wing support members may include a first wing support member and a second wing support member, wherein the first wing support member and the second wing support member are arranged crosswise to define at least one power cell mounting compartment therebetween.

According to the above aspect of the present invention, preferably, the first wing support member may comprise a beam of the wing box, and comprise a first beam and a second beam, and wherein the first beam is arranged parallel to the second beam.

In this way, customization is avoided and costs are reduced by virtue of the structural form of the existing spar in the wing and enabling adaptation to common cell shapes.

According to the above aspect of the present invention, preferably, the first beam may be provided with first pins and first pin holes for plug-in connection and first fastener mounting holes for fasteners to pass through, and the second beam may be provided with second pins and second pin holes for plug-in connection, component mounting holes and second fastener mounting holes for fasteners to pass through.

The cooperation through corresponding bolt and bolt hole forms the shape fit and connects, and forms the power fit through the cooperation between fastener mounting hole and the fastener and be connected to form the convenient and easily obtained redundant connection form of equipment, and with the help of corresponding mounting hole, can make things convenient for being connected (for example power line or signal line are connected, in order to be used for input/output electric power, and carry out corresponding monitoring and control etc.) between components and parts and the battery electric body or electric core.

According to the above aspect of the invention, preferably, the second wing support member may comprise a rib of the wing box, and comprise a first rib, a second rib and a third rib disposed between the first rib and the second rib, and wherein the first rib, the second rib and the third rib are arranged parallel to each other.

In this way, it is possible to avoid customization and reduce costs by virtue of the existing rib structure form in the wing and enabling adaptation to common cell shapes.

According to the above aspect of the present invention, preferably, the first and second ribs may be disposed at both ends of the first and second girders, respectively, to form a rectangular structure, and the third rib is connected to the middle of the first and second girders. For example, the battery cells typically have a generally rectangular shape, and such a beam, rib arrangement can form a rectangular power cell mounting compartment therebetween to better accommodate the battery cells or cells therein.

According to the above aspect of the invention, preferably, a connection corner box disposed at the end portions of the second spar and the second rib which are close to each other may be further included, and the connection corner box may include a recess which constrains a corner formed by the second spar and the second rib, a taper which abuts against a structure in the wing adjacent to the wing box section and which includes a corresponding fastener mounting hole, and a Y-shaped structure in which a corresponding fastener mounting hole is also provided.

The arrangement can be adapted to the internal space and the component arrangement relation of the existing wing on one hand, the structural strength of the power battery cell installation cabin is enhanced through the related components, and on the other hand, through the specific structural form of the connecting corner box, additional shape matching and force matching structures can be formed.

According to the above aspect of the present invention, preferably, the wing system may further include a first cover and a second cover, wherein the first cover, the second cover, and the plurality of wing support members cooperate to form a battery enclosure for the power battery cell.

In this way, a closed space is enclosed in the circumferential direction by means of a plurality of wing support members of the aircraft and is enclosed from above and below by means of a first cover and a second cover, respectively, in order to form a complete battery housing which is substantially closed in each direction.

According to the above aspect of the invention, preferably, the first and second covers may each comprise first and second nuts and are connected to the wing box by means of co-operating threaded fasteners.

Similarly, the connection mode can ensure the connection strength and facilitate the disassembly and the assembly of the shell, so that the maintenance of the power battery module is facilitated.

According to the above aspect of the present invention, preferably, the threaded fasteners may be fastened to the respective fastener mounting holes by means of wet mounting, and the threaded fasteners may be made of stainless steel.

Like this, on the one hand can increase the joint strength that the fastener is connected, on the other hand can avoid effectively taking place the heterostatic corrosion with between the carbon-fibre composite.

According to the above aspect of the invention, preferably, the contact surfaces between the first cover surface of the first cover and the second cover surface of the second cover and the skin of the wing box may be provided with an adhesive.

Through the binder, can improve leakproofness and gas tightness between power battery module and the wing box section supporting member, possess and prevent the inside advantage of outside air and moisture infiltration power battery module.

According to the above aspect of the present invention, preferably, the adhesive may be an epoxy adhesive. In this way, the disassembly and assembly of the wing support members can advantageously be facilitated, for example when it is necessary to disassemble the power cell installation bay (release the connection between the wing support members), the properties of the epoxy adhesive can be exploited, and its adhesive strength can be eliminated or at least partially reduced, for example by means of heat or by means of an adhesive remover, so that the wing support members bonded together can be detached from one another.

According to another aspect of the present invention, an electric aircraft is provided, which may include the wing system integrated with the power battery module described in the above aspect, wherein the wing system may be located between a wing root to a wing kirk point in a wingspan direction, and between a wing main front spar and a wing main rear spar in a wing direction.

According to the calculation of the inventor, the electric airplane provided with the wing system can improve the range by about 5%, obviously increase the economic benefit and reduce the pollutant emission.

Therefore, the wing system integrated with the power battery module can meet the use requirement, overcome the defects of the prior art and achieve the preset purpose.

Drawings

To further clarify the description of the wing system integrated with power battery modules according to the present invention, the invention will be described in detail with reference to the drawings and the following detailed description, in which:

FIG. 1 is a schematic perspective view of a wing box structure in a power cell module integrated wing system according to a non-limiting embodiment of the present invention, wherein the power cell module is not positioned;

FIG. 2 is a schematic view of a wing system integrated with power cell modules, with the power cell modules placed and with the upper skin not shown for clarity, according to a non-limiting embodiment of the present invention;

FIG. 3 is an exploded schematic view of a portion of a wing box structure in a wing system integrated with a power cell module according to a non-limiting embodiment of the present invention;

FIG. 4 is an enlarged schematic view of a portion of the wing box structure shown in FIG. 1;

fig. 5 is a schematic view of a first cover of a power cell module according to a non-limiting embodiment of the present invention;

fig. 6 is a schematic view of a second cover of a power cell module according to a non-limiting embodiment of the present invention;

FIG. 7 is a schematic illustration of a bolted connection of a wing box structure in a power cell module integrated wing system according to a non-limiting embodiment of the present invention;

FIG. 8 is a schematic top view of a wing box structure in a power cell module integrated wing system according to a non-limiting embodiment of the present invention;

FIG. 9 is a schematic perspective view of a wing box structure in a power cell module integrated wing system according to a non-limiting embodiment of the present invention; and

fig. 10 is a schematic diagram of the relationship of the relevant structural members and components with the power battery module mounted thereon, according to a non-limiting embodiment of the present invention.

The figures are purely diagrammatic and not drawn true to scale.

List of reference numbers in the figures and examples:

100-a wing system integrated with a power battery module, comprising:

10-a wing box, comprising:

10A, a power battery monomer installation cabin;

11-a first airfoil support member comprising:

111-a first beam comprising:

111A-a first bolt;

111B-a first plug hole;

111C-first fastener mounting hole;

112-a second beam comprising:

112A-second bolt

112B-second plug hole

112C-second fastener mounting hole

112D-component mounting holes;

12-a second wing support member comprising:

121-a first rib comprising:

121A-third plug hole;

121B-third fastener mounting holes;

122-a second rib comprising:

122A-a third latch;

122B-fourth fastener mounting holes;

123-a third rib comprising:

123A-a fourth latch;

13-a first closure comprising:

131-a first nut;

132-a first cap surface;

14-a second closure comprising:

141-a second nut;

142-a second closure surface;

20-a power cell, comprising:

21-a main positive connector;

22-a primary negative connector;

23-a high voltage connector;

24-a venting valve;

30-a battery housing;

40-a mechanical connection gusset comprising:

41-fastener mounting holes;

50-bonding corner pieces;

60-a junction corner box comprising:

61-a recess;

62-a conical portion;

a 63-Y shaped structure;

70-a fastener comprising:

71-a first fastener;

72-a second fastener;

73-third fastener.

Detailed Description

It is to be understood that the invention may assume various alternative orientations and step sequences, except where expressly specified to the contrary. It is also to be understood that the specific devices illustrated in the attached drawings, and described in the specification, are simply exemplary embodiments of the inventive concepts disclosed and defined herein. Thus, specific orientations, directions or other physical characteristics relating to the various embodiments disclosed should not be considered limiting unless expressly stated otherwise.

Fig. 1 is a schematic perspective view of a power cell module integrated wing system 100 according to a non-limiting embodiment of the present invention, wherein the power cell module is not positioned. For example, the wing system 100 may be used for installation and use in an electric aircraft.

As an example, the wing system 100 integrated with power cells according to the invention can be located inside or be an integral part of the wing of an electric aircraft and between the wing root to the wing k nk point in the spanwise direction and between the main front and rear spars of the wing in the spanwise direction.

The inner ends of the main front beam and the main rear beam can be respectively connected with a reinforced bulkhead inside the body of the electric airplane, and the outer ends of the main front beam and the main rear beam can extend to a KINK point. The kirk point may be a turning point between the wing sections. For example, at the point of inflection of the leading edge between the inner and middle panels, or between the inner and outer panels of the wing.

As shown in the figures and in accordance with a non-limiting embodiment of the present invention, the wing system 100 may include: wing box 10 and power battery cell 20.

As is known in the art, wings generate lift during the flight of an aircraft, which is the fundamental guarantee that the aircraft can fly. The wing box 10 is the main force-bearing part of the wing, bearing all the loads generated on the wing.

In general, the wing box 10 may include a plurality of wing support members, such as longitudinal support members and transverse support members, etc., having a desired strength and stiffness to withstand the respective aerodynamic loads to ensure flight safety of the aircraft.

For a beam wing, the wing support members may be spars, ribs, or the like of the wing to form the backbone of the wing, and may also include a wing skin. The skin is a member that surrounds the exterior of the wing frame and may be secured to the frame, for example by adhesive or rivets, to form the aerodynamic profile of the wing.

As shown in detail in fig. 1, a plurality of wing support members according to the present invention are arranged to define at least one power cell bay 10A therebetween, for example, 2 power cell bays 10A arranged side-by-side as shown in fig. 1.

Fig. 2 is a schematic view of a power cell module integrated wing system 100 according to a non-limiting embodiment of the present invention, in which power cells 20 have been placed, and the upper skin is not shown for clarity.

It can be seen that the power battery cell 20 can be placed in the power battery cell installation compartment 10A and tightly fit together with the wing support members (e.g., their respective inner surfaces) forming the power battery cell installation compartment 10A to form a complete set of power battery modules. The battery housing 30 of the power battery module may be served by the plurality of wing support members constituting the power battery cell installation compartment 10A. In addition, the power battery cell installation compartment 10A also supports various cables, electrical components, and the like, which are coupled with the power battery cell 20, which will be described in detail below.

Herein, the power battery module may refer to a battery module including the power battery cells 20, corresponding connectors, cables, valves, and the like.

Fig. 3 is an exploded schematic view of the structure of a wing box 10 in a power cell module integrated wing system 100 according to a non-limiting embodiment of the present invention.

As shown and by way of non-limiting example, the wing support members may include a first wing support member 11 and a second wing support member 12.

The first wing support member 11 may be a longitudinal support member, and in the embodiment of the figures is a spar of the wing box 10, and comprises a first spar 111 and a second spar 112. The first beam 111 may also be referred to as a rear beam, and the second beam 112 may also be referred to as a front beam. For example, the front spar may be the main front spar of a wing of an aircraft, and the rear spar may be the main rear spar of the wing of the aircraft.

Preferably, as shown in fig. 3, the first and

second spars

111, 112 may be arranged substantially parallel to each other and extend in the longitudinal/spanwise direction of the wing, respectively, i.e. substantially perpendicular to the fuselage (or longitudinal axis of the fuselage) of the aircraft.

The second wing support member 12 may be a lateral support member, and in the embodiment of the drawings is a rib of the wing box 10, and comprises a first rib 121, a second rib 12B and a third rib 12C disposed between the first rib 121 and the second rib 12B. For example, the first rib 121 may be disposed closest to the fuselage and the second rib 12B may be disposed farthest from the fuselage.

Preferably, the first rib 121, the second rib 12B and the third rib 12C may be arranged substantially parallel to each other and substantially perpendicular to the first beam 111 and the second beam 112, respectively, so as to form a substantially rectangular frame structure as a whole, and include therein two power battery cell mounting compartments 10A, which may also be formed in substantially rectangular shapes, respectively.

By way of non-limiting example and as shown, the roots of the first and

second beams

111, 112 may be attached to ribs fixed to the fuselage. For example, in the example of fig. 3, the first rib 121 may be fixedly connected to the fuselage. Preferably, the root portions of the first and

second beams

111 and 112 may be connected to the first rib 121 by a shape-fitting. Additionally, or alternatively, the root portions of the first and

second beams

111 and 112 may be connected to the first rib 121 by force fitting. Further, the root portions of the first beam 111 and the second beam 112 may also be connected to the first rib 121 by bonding (e.g., by means of an adhesive or the like).

As used herein, a so-called "form-fit" connection may be a bayonet, snap-fit connection, hook-on, tongue-on, etc., in particular, one of the two or more components that mate with each other having a particular shape, e.g., a concave shape, while the other of the two or more components that mate with each other may have another complementary particular shape, e.g., a convex shape, etc., such that the structures that mate with each other form at least a partial self-lock to achieve a fit therebetween, etc., such that one or more degrees of freedom of at least one of the one or more components of the two or more components are constrained. Usually, the form-fitting connections are all detachable, and the order of the mounting and dismounting of the individual components is substantially reversed.

As used in this application, a so-called "force-fit" connection is a connection which, in contrast to a "form-fit", can be, for example, a threaded connection, riveting, strapping, gluing, etc. by means of a further auxiliary connection part which exerts one or more constraining forces.

For the purpose of illustrating the principles of the invention, the form fit is described below in connection with the form of a plug-in connection and the force fit is described below in connection with the form of a screw-fastening connection and an adhesive connection. It should be understood, however, that the detailed description is for convenience only and is not intended to limit the scope of the invention.

With continued reference to fig. 3, as a non-limiting example, the first beam 111 may be provided with a first pin 111A and a first pin hole 111B for a plug connection, and a first fastener mounting hole 111C for a fastener to pass through.

The first latch 111A may be provided, for example, at an end of the first beam 111 near the first rib 121, and shaped in the form of a substantially rectangular tab extending from the end of the first beam 111. The first latch hole 111B may be provided at an end portion distant from the first rib 121 and an intermediate portion of the first beam 111, and shaped as an elongated rectangular opening of a substantially slit shape. First fastener mounting holes 111C may be provided at both end portions and a middle portion of the first beam 111, respectively.

The first pin 111A, the first pin hole 111B, and the first fastener mounting hole 111C may include a plurality of, for example, at least 4 first pin holes 111B and at least 8 first fastener mounting holes 111C shown in the drawings, respectively.

In alternative embodiments, different arrangements and numbers of the first pins 111A, the first pin holes 111B, and the first fastener mounting holes 111C may be provided.

The second beam 112 may be provided with a second pin 112A and a second pin hole 112B for plug-in connection, a second fastener mounting hole 112C for a fastener to pass through, and a component mounting hole 112D.

The second latch 112A may be provided at an end of the second beam 112 near the first rib 121 and shaped in the form of a substantially rectangular tab extending from the end of the second beam 112. The second latch hole 112B may be provided at an end portion distant from the first rib 121 and an intermediate portion of the second beam 112, and is shaped as an elongated rectangular opening of a substantially slit shape.

Second fastener mounting holes 112C may be provided at both end portions and a middle portion of the second beam 112, respectively. In addition, the component mounting holes 112D may include a plurality of openings of various shapes and numbers to accommodate connection of the battery cells 20 or cells disposed in the power battery cell mounting compartment 10A to corresponding components.

The second pin 112A, the second pin hole 112B, and the second fastener mounting hole 112C may respectively include a plurality. For example, at least 3 second latch holes 112B and at least 8 second fastener mounting holes 112C are shown in the figures.

In alternative embodiments, different arrangements and numbers of second pins 112A, second pin holes 112B, and second fastener mounting holes 112C may be provided.

With continued reference to fig. 3, the first and

second ribs

121 and 122 may be disposed at both ends of the first and

second beams

111 and 112, respectively, to form a rectangular structure, and the third rib 123 may be connected to middle portions of the first and

second beams

111 and 112 at both ends.

By way of non-limiting example, the first rib 121 may include a third latch hole 121A and a third fastener mounting hole 121B. For example, the third latch holes 121A may include 2 and be respectively provided at both ends of the first rib 121 and shaped as an elongated rectangular opening of a substantially slit shape. The shape of the third pin holes 121A may match the cross-sectional shape of the first pin 111A of the first beam 111 and the second pin 112A of the second beam 112, respectively, such that the first pin 111A and the second pin 112A can be shape-fitted into the respective third pin holes 121A, respectively, i.e. a shape-fitting connection is achieved therebetween. In this embodiment, the form-fit connection is a plug-in fit. The third fastener mounting hole 121B may be used for fastening connection with a power battery module or other corresponding components (e.g., the second cover 14, which will be described in detail below).

The second rib 122 may include a third bolt 122A and a fourth fastener mounting hole 122B. For example, the third pins 122A may include 3 and be respectively disposed at both ends of the second rib 122 and shaped in the form of substantially rectangular tabs. The cross-sectional shape of the third pin 122A may be matched to the shape of the first pin hole 111B of the first beam 111 and the second pin hole 112B of the second beam 112, respectively, so that the third pin 122A can be shape-fitted into the respective first pin hole 111B and second pin hole 112B, respectively, i.e., a shape-fitting connection is achieved therebetween. In this embodiment, the form-fit connection is a plug-in fit. The fourth fastener mounting hole 122B may be used for fastening connection with a power battery module or other corresponding components (e.g., the second cover 14, which will be described in detail below).

The third rib 123 may include a fourth plug 123A. For example, the fourth pins 123A may include 4, 2 provided at both ends of the third rib 123, respectively, and each shaped in the form of a substantially rectangular tab.

The cross-sectional shape of the fourth pin 123A may be matched to the shape of the first pin hole 111B at the intermediate portion of the first beam 111 and the second pin hole 112B at the intermediate portion of the second beam 112, respectively, so that the fourth pin 123A can be shape-fitted into the respective first pin hole 111B and second pin hole 112B, respectively, i.e., a shape-fitted connection is achieved therebetween. In this embodiment, the form-fit connection is a plug-fit connection.

According to the invention, at least one of the plurality of wing support members may be produced from a carbon fibre prepreg, wherein the carbon fibre prepreg is applied in the application direction and, after curing at room temperature, is machined, for example by milling, to the final shape of the at least one wing support member.

As a non-limiting example, one, more or all of the first beam 111, the second beam 112, the first rib 121, the second rib 122 and the third rib 123 may be laid down using carbon fiber prepreg in a laying direction, and machined according to their desired final shape after curing at room temperature, for example, by milling.

Fig. 4 is an enlarged schematic view of a portion of the wing box 10 structure shown in fig. 1, showing an exemplary structural form of the mechanical connection tab 40 and the adhesive tab 50. As shown, the mechanical connection gusset 40 and the bonding gusset 50 are respectively formed in the form of a gusset having a substantially L-shaped cross section.

The mechanical connection corner piece 40 may be arranged outside the corner of the wing box 10, i.e. in a contactless relationship with the power cells 20. Preferably, the mechanical connection tabs 40 include fastener mounting holes 41. For example, each mechanical connection gusset 40 may include 2 fastener mounting holes 41 disposed in spaced-apart relation above and below. The mechanical connection tabs 40 may be used to assist in the mechanical connection between adjacent wing support members.

As used herein, the description "fastener mounting holes" is used to refer to through-holes or the like through which threaded fasteners, such as bolts, studs, screws, and the like, are passed for detachably assembling and fastening together elements or components including these fastener mounting holes with the aid of the threaded fasteners. In an alternative embodiment, the "fastener mounting hole" may also be a generally circular through hole that includes threads for use as a nut that mates with a corresponding fastener such as a bolt or screw, such that a separate fastener may be omitted.

A bonding fillet 50 may be provided at the interior of a corner of the power cell installation bay 10A to bond adjacent ones of the plurality of wing support members together with an adhesive, such as with an epoxy adhesive.

The two side surfaces of the adhesive fillet 50 may each abut a contact surface of a wing support member with which it is fitted to achieve a face-to-face adhesive bond. According to the present invention, the adhesive corner piece 50 may contact the power cell 20, e.g., against a corner, side, or portion thereof, etc.

As shown in detail in fig. 7, the respective contact surfaces of each of the first beam 111, the second beam 112, the first rib 121, the second rib 122, the third rib 123 and the second cover 14 may be coated with an epoxy adhesive, for example, uniformly coated. The entire contact surface of the adhesive fillet 50 may also be coated with an epoxy adhesive, for example uniformly coated to achieve a secure and reliable adhesive connection thereof.

Advantageously, the epoxy adhesive can facilitate the removal of parts that are bonded to each other, for example, using a special de-bonding process, without damaging the bonded parts and without reducing their strength or durability.

According to the invention and as a preferred embodiment, the number of mechanical connection gussets 40 can be set to 9, while the number of bonding gussets 50 can be set to 8. It can be seen that, in addition to the corners at which the connection corner boxes 60 (described in detail below with reference to the drawings) are provided, the mechanical connection corner piece 40 is provided on the outside of each corner (outside the first rib 212 in the span direction) of the power battery cell installation compartment 10A, and the adhesive corner piece 50 is provided on the outside of each corner of the power battery cell installation compartment 10A.

Similarly, one or both of the mechanical connection fillet 40 and the bonding fillet 50 may be formed by laying carbon fiber prepreg on a bending die, curing at room temperature, and machining according to the required edge shape, for example, by milling.

Preferably, the wing system 100 integrated with a power battery module according to the present invention may further include a first cover 13 and a second cover 14.

Fig. 5 is a schematic view of the first cover 13 of the power battery module according to a non-limiting embodiment of the present invention; and fig. 6 is a schematic view of the second cover 14 of the power battery module according to a non-limiting embodiment of the present invention.

According to the invention, the first cover 13 and the second cover 14 may cooperate with a plurality of wing support members to form a battery housing 30 of the power cell 20. For example, as shown in the figures, the first wing support member 11 and the second wing support member 12 may enclose the sides of the battery housing 30, while the first cover 13 and the second cover 14 may form the top and bottom, respectively, of the battery housing 30, thereby forming a substantially closed square box-like containment structure, i.e., a relatively complete battery housing 30, such as schematically illustrated in fig. 8-10.

As shown in fig. 5 and 6, the first cover 13 may include a plurality of first nuts 131, e.g., 4 nuts as shown in fig. 5, with 1 at each corner. The plurality of first nuts 131 may all be oriented in the fore-aft direction to couple to the first beam 111 and the second beam 112 in cooperation with fasteners. In alternative embodiments, the plurality of first nuts 131 may also have different orientations.

Likewise, the second cover 14 may comprise a plurality of second nuts 141, for example 8 nuts as shown in the figures, 1 in each corner and 2 on each of the two sides thereof. The plurality of second nuts 141 may have different orientations. For example, the 4 nuts of the corner may all be oriented in the fore-aft direction to mate with fasteners to connect to the first beam 111 and the second beam 112. While the side 4 nuts may be oriented in the spanwise direction to mate with fasteners to connect the respective ribs, for example to the first and

second ribs

121 and 122, respectively.

As shown, the wing box section 10 in the figure includes 2 power battery cell mounting bays 10A. Accordingly, 2 first covers 13 and 2 second covers 14 may be provided to enclose the two power battery cell installation compartments 10A from the upper and lower portions, respectively, to form two complete battery cases 30.

FIG. 7 is a schematic illustration of a bolted connection of a wing box 10 structure according to a non-limiting embodiment of the present invention; and figure 8 is a schematic top view of the wing box 10 structure in a power cell module integrated wing system 100 according to a non-limiting embodiment of the present invention.

In addition, referring back to fig. 1 in conjunction, the wing system 100 integrated with a power battery module according to the present invention may further include a connection corner box 60.

As shown and by way of non-limiting example, the connection corner box 60 may be disposed at ends of the second beam 112 and the second rib 122 that are proximate to each other. The connection angle box may include a recess 61, a taper 62 and a Y-shaped structure 63.

Preferably, the recess 61 may be an angled recess, such as a recess angled at approximately 90 degrees. The recess 61 may constrain the corner formed by the second beam 112 and the second rib 122. That is, the recess 61 and the second beam 112 and the second rib 122 may form a form-fit connection at the corner. The tapered portion 62 may abut a structure in the wing adjacent the wing box 10 and include corresponding fastener mounting holes. Such as the two fastener mounting holes shown in fig. 1 spaced above and below. In the example shown in the figures, the taper 62 may comprise an inclined planar surface for abutment against other components of the wing not shown in the figures. A corresponding fastener mounting hole is also provided in the Y-shaped formation 63, provided in one of the two limbs, to facilitate mounting of a fastener.

By way of non-limiting example, the connection angle box 60 may be machined, for example by milling, from an aluminum alloy material to follow the contour of the connection angle box 60.

As shown in detail in fig. 7, the wing system 100 integrated with a power battery module may also include a plurality of fasteners 70. The fasteners 70 may fasten the first wing support member 11, the second wing support member 12, the first cover 13, the second cover 14, and the mechanical connection tab 40 together at multiple locations to form a removable unitary structure. Preferably, after these structures have completed a positive-fit connection, for example, after the corresponding plug pins have been inserted in a positive-fit socket, a fastening connection is made by means of a plurality of fasteners 70, i.e. a force-fit connection between the components is achieved.

By way of example only, such as at the lower left corner in fig. 7, the first fastener 71 is first passed through the fastener mounting hole 41 in the mechanical attachment gusset 40, then through the second fastener mounting hole 112C in the second beam 112, and finally engaged in the threaded hole of the second nut 141 of the second cover 14 via a threaded connection.

In a preferred embodiment, the first fastening members 71 are fastened to the corresponding fastening member mounting holes by means of wet mounting, and the first fastening members 71 are made of stainless steel.

As used herein, by "wet-mount" is meant that an adhesive in a liquid state, such as an epoxy-based adhesive, is applied in advance at the perforated portion (threaded portion) of the fastener, and when necessary, the adhesive is subjected to a stripping treatment with a corresponding stripper to facilitate the detachment of the parts.

Similarly, the second fastener 72 may pass through the first fastener mounting hole 111C of the first beam 111 and be threaded into the fastener mounting hole 41 in the mechanical attachment gusset 40.

Likewise, the third fastener 73 may pass through the third fastener mounting hole 121B of the first rib 121 and be screwed into the screw hole of the second nut 141 of the second cover 14.

At the remaining corners, a screw connection may similarly be made by means of fasteners 70.

Fig. 9 is a schematic perspective view of the structure of a wing box 10 in a wing system 100 integrated with a power battery module according to a non-limiting embodiment of the present invention, wherein the structure of parts other than the power battery cells 20 has been assembled.

It should be understood that although the first and

second beams

111, 112 are shown in the figures as being unitary linear longitudinal members, in alternative embodiments, the first and

second beams

111, 112 may be formed by splicing together a plurality of beam segments, such as by joints or the like. In other embodiments, other configurations are also contemplated by those skilled in the art.

For example, instead of a rectilinear structure, the first beam 111 and/or the second beam 112 may also have a substantially L-shaped structure, a substantially U-shaped structure, or the like. At this time, the ribs that mate with the spars may also have corresponding mating shapes, so long as they are able to enclose the power cell mounting compartment 10A and have sufficient rigidity and strength to support the wing and associated structures.

In addition, although a wing box arrangement including two spars and three ribs is shown in the drawings, it should be understood that this arrangement is merely exemplary and that one skilled in the art may provide more or fewer spars and ribs to form various numbers and shapes of power cell mounting bays 10A depending on the design requirements of the actual power cell 20.

According to the present invention, the power battery cells 20 may include one or more groups, for example, 2 groups shown in the drawings, to be respectively accommodated in one power battery cell installation compartment 10A enclosed by the first beam 111, the second beam 112, the first rib 121, and the third rib 123; and another power battery cell installation compartment 10A enclosed by the first beam 111, the second beam 112, the second rib 122, and the third rib 123. The power battery cells 20 of the groups can be connected to corresponding components, thereby forming a power battery module. These components/parts may also be considered as part of the power cell 20 in achieving the intended purpose of the present invention.

Fig. 10 is a schematic diagram of the relevant structural and component relationships with which the power cells 20 are mounted, according to a non-limiting embodiment of the present invention.

As shown in fig. 10, the power battery cell 20 may include a battery cell (not shown), a main positive connector 21, a main negative connector 22, a high voltage connector 23, a vent valve 24, and the like attached to the battery cell.

It should be noted that the power battery module may further include components such as a connection line, an acquisition card, and the like, but these related components belong to a power battery module assembly, and are not directly related to the wing system integrated with the power battery module according to the present invention, and these components are known in the art, so the present invention is not described again.

The main positive connector 21, the main negative connector 22, the high-voltage connector 23, and the purge valve 24 may extend through and be fixedly supported by the component mounting holes 112D provided on the second beam 112.

After the installation of the relevant components inside the power battery module is completed, an adhesive may be provided between the first surface 132 of the first cover 13 and the contact surface between the second surface 142 of the second cover 14 and the skin of the wing box 10. For example, an adhesive is applied, e.g. uniformly applied, to the upper surface of the wing support member and the lower surface of the upper skin, and to the lower surface of the wing support member and the upper and lower surfaces of the lower skin. Preferably, the adhesive may comprise an epoxy adhesive.

Likewise, the skin may be made of a carbon fiber material. For example, the skin may be formed by applying carbon fiber prepreg to an outline mold in the application direction, curing at room temperature, and machining, for example by milling, the final skin outline.

The terms "upper", "lower", and the like for indicating the order of orientation or orientation, as used herein, are only used for better understanding the concept of the present invention as shown in the preferred embodiments by those of ordinary skill in the art, and are not intended to limit the present invention. Unless otherwise specified, all sequences, orientations, or orientations are used for the purpose of distinguishing one element/component/structure from another element/component/structure only, and do not imply any particular order, sequence of operations, direction, or orientation, unless otherwise specified. For example, in an alternative embodiment, the "first wing support member" may be the "second wing support member".

In summary, the wing system 100 integrated with power battery modules according to the embodiment of the invention overcomes the disadvantages of the prior art, and achieves the intended purpose.

While the present invention has been described with reference to the preferred embodiments, it will be understood by those skilled in the art that the foregoing examples are illustrative only and are not to be construed as limiting the invention. Therefore, various modifications and changes can be made to the present invention within the spirit and scope of the claims, and these modifications and changes will fall within the scope of the claims of the present invention.

Claims

1. A wing system (100) integrated with a power battery module, comprising:

a wing box (10) comprising a plurality of wing support members arranged to define at least one power cell bay (10A) therebetween, and

a power cell (20) disposed in the at least one power cell mounting bay (10A) such that the plurality of wing support members making up the at least one power cell mounting bay (10A) serve as at least a portion of a battery enclosure (30) of the power cell (20).

2. The wing system (100) integrated with power battery modules according to claim 1, wherein the plurality of wing support members are connected together by at least two of one or more form-fit connections and one or more force-fit connections.

3. The wing system (100) integrated with power battery modules according to claim 2, characterized in that the form-fit connection comprises a form of a plug connection and the force-fit connection comprises a form of a connection by means of a fastener.

4. The wing system (100) integrated with a power battery module according to claim 3, further comprising a mechanical connection fillet (40) provided at a corner of the power battery cell mounting bay (10A), the mechanical connection fillet being provided with a fastener mounting hole (41) for securing adjacent ones of the plurality of wing support members together with a fastener.

5. The power cell module integrated wing system (100) of claim 1, wherein a bonding fillet (50) is provided at an interior of a corner of the power cell mounting bay (10A) to bond adjacent ones of the plurality of wing support members together with an adhesive.

6. The power cell module integrated wing system (100) of claim 1, wherein at least one of the plurality of wing support members is laid out of carbon fiber prepreg, wherein the carbon fiber prepreg is laid in a lay-out direction and machined to a final shape of the at least one wing support member after curing at ambient temperature.

7. The power cell module integrated wing system (100) of claim 1, wherein the plurality of wing support members comprises a first wing support member (11) and a second wing support member (12), wherein the first wing support member (11) and the second wing support member (12) are arranged crosswise to define the at least one power cell bay (10A) therebetween.

8. The wing system (100) integrated with power battery modules according to claim 7, characterized in that the first wing support member (11) comprises a spar of the wing box (10) and comprises a first spar (111) and a second spar (112), and wherein the first spar (111) is arranged parallel to the second spar (112).

9. The power cell module integrated wing system (100) of claim 8, wherein the first beam (111) is provided with a first pin (111A) and a first pin hole (111B) for plug connection and a first fastener mounting hole (111C) for a fastener to pass through, and the second beam (112) is provided with a second pin (112A) and a second pin hole (112B) for plug connection, a second fastener mounting hole (112C) for a fastener to pass through, and a component mounting hole (112D).

10. The wing system (100) integrated with power battery modules according to claim 9, characterized in that the second wing support member (12) comprises a rib of the wing box (10) and comprises a first rib (121), a second rib (122) and a third rib (123) arranged between the first rib (121) and the second rib (122), and wherein the first rib (121), the second rib (122) and the third rib (123) are arranged parallel to each other.

11. The wing system (100) integrated with power battery modules according to claim 10, characterized in that the first rib (121) and the second rib (122) are arranged at both ends of the first beam (111) and the second beam (112), respectively, to form a rectangular structure, and the third rib (123) is connected to the middle of the first beam (111) and the second beam (112).

12. The power cell module integrated wing system (100) of claim 11, further comprising a connection corner box (60) disposed at ends of the second spar (112) and the second rib (122) that are proximate to each other,

wherein the connection corner box comprises a recess (61), a taper (62) and a Y-shaped structure (63), wherein the recess (61) constrains a corner formed by the second spar (112) and the second rib (122), the taper (62) abuts against a structure in the wing adjacent to the wing box (10) and comprises a corresponding fastener mounting hole, and the Y-shaped structure (63) also comprises a corresponding fastener mounting hole.

13. The power battery module integrated wing system (100) of any of claims 1-12, further comprising a first cover (13) and a second cover (14), wherein the first cover (13), the second cover (14), and the plurality of wing support members cooperate to form the battery enclosure (30) of the power battery cell (20).

14. The wing system (100) integrated with power battery modules according to claim 13, characterized in that the first cover (13) and the second cover (14) each comprise a first nut (131) and a second nut (141) and are connected to the wing box (10) by means of cooperating threaded fasteners.

15. The power cell module integrated wing system (100) of claim 14, wherein the threaded fasteners are wet-mounted into the respective fastener mounting holes and the threaded fasteners are made of stainless steel.

16. The wing system (100) integrated with a power battery module according to claim 13, characterized in that the contact surfaces between the first cover surface (132) of the first cover (13) and the second cover surface (142) of the second cover (14) and the skin of the wing box (10) are provided with an adhesive.

17. The power cell module integrated wing system (100) of claim 5 or 16, wherein the adhesive is an epoxy adhesive.

18. An electric aircraft comprising a wing system (100) integrated with a power battery module according to any one of claims 1 to 17, the wing system (100) being located between a wing root to a wing kirk point in a spanwise direction and between a wing main front spar and a main rear spar in a spanwise direction.