motor arms and aircraft

Abstract

This application relates to the field of aircraft technology, and more particularly to a motor arm and an aircraft. The motor arm includes a housing and multiple battery modules. The housing includes a truss structure and a skin, the truss structure enclosing a cavity, and the skin covering the truss structure, at least partially concealing the cavity. Each battery module is disposed within the cavity, and the battery modules are arranged sequentially along the length of the housing. The motor arm of this application uses a truss structure for its housing, which is simple in construction, has a clear force transmission path, and allows battery modules to be arranged within the truss range, greatly increasing the number of battery modules that can be arranged, while also improving the structural strength of the housing and reducing its weight.

Description

Technical Field

[0001] This application relates to the field of aircraft technology, and more particularly to an electric arm and an aircraft. Background Technology

[0002] Currently, battery energy density is relatively low, mostly concentrated between 200W / kg and 300W / kg. For electric aircraft, especially EVTOL aircraft, a large number of batteries are required to meet the established performance requirements. Batteries are typically placed inside the aircraft fuselage, encroaching on internal space and reducing payload capacity. By placing some batteries within the motor arms on the wings, the effective payload space inside the fuselage can be increased, and the wing loading during flight can be reduced. In related technologies, the motor arm shell lacks a truss structure, directly using a thick metal shell to form a cavity. To ensure structural strength, the shell is usually quite thick, increasing the weight of the motor arm and reducing the volume of the internal cavity. This is detrimental to the placement of internal battery modules, hinders lightweight aircraft design, and makes maintenance and repair more difficult. Summary of the Invention

[0003] This application provides an electric arm and an aircraft that can effectively solve the above-mentioned or other potential technical problems.

[0004] The first aspect of this application is to provide a motor arm, comprising:

[0005] A housing, the housing comprising a truss structure and a skin, the truss structure enclosing a cavity, the skin covering the truss structure, the skin at least partially concealing the cavity;

[0006] Multiple battery modules are provided, each of which is disposed within the cavity and arranged sequentially along the length of the housing.

[0007] Optionally, the truss structure includes multiple stringers and multiple partition frames;

[0008] Each of the aforementioned stringers extends along the length of the shell;

[0009] Each of the partition frames is arranged at intervals along the length of the stringer, the partition frames extend circumferentially along each of the stringers, and the partition frames and the stringers are fixedly connected.

[0010] The cavity is formed by the enclosure between the partition frame and the stringer.

[0011] Optionally, the stringer includes a first wing and a second wing;

[0012] The first wing slat and the second wing slat are connected;

[0013] There is an included angle between the first slat and the second slat.

[0014] Optionally, the truss structure includes multiple diagonal braces;

[0015] Each of the aforementioned diagonal braces may be configured in one or more of the following ways:

[0016] The diagonal braces are connected to different positions within the same partition frame;

[0017] The diagonal braces are respectively connected to different partition frames;

[0018] The diagonal braces are respectively connected to different long trusses;

[0019] The diagonal braces are respectively connected to the long truss and the partition frame.

[0020] Optional, it includes multiple installation components;

[0021] Each of the mounting components is arranged sequentially along the length of the truss structure, and the mounting components are fixed to the truss structure;

[0022] The mounting components are located at least partially within the cavity;

[0023] Each of the battery modules is installed on its respective mounting assembly.

[0024] Optionally, the mounting assembly includes a central strip and two end strips;

[0025] The two end strips are located on either side of the middle strip along the length of the housing;

[0026] Both the middle strip and the end strip extend along the length direction perpendicular to the shell.

[0027] The battery module is fixed at both ends along the length of the housing to corresponding end strips;

[0028] The battery module is supported on the central strip along the length of the housing.

[0029] Optionally, mounting slots are provided at both ends of the battery module;

[0030] One end of the connector passes through the mounting groove and is connected to the end strip, while the other end of the connector is located at the end of the battery module opposite to the end strip.

[0031] Optionally, the battery module includes multiple individual battery cells;

[0032] Each of the battery cells is stacked sequentially, and each battery cell has a mounting hole;

[0033] The mounting holes of each of the battery cells are connected to form the mounting groove.

[0034] Optionally, both the middle strip and the end strip are connected at both ends to the two long trusses of the truss structure.

[0035] Optionally, the top of the skin is provided with a battery mounting port and a first cover for opening or closing the battery mounting port;

[0036] The bottom of the skin is provided with a battery maintenance port and a second cover for opening or closing the battery maintenance port.

[0037] A second aspect of this application provides an aircraft, comprising:

[0038] body;

[0039] Wings, which are connected to the fuselage;

[0040] An electric motor arm, which is connected to the wing.

[0041] By adopting the above-mentioned solution, this application has the following beneficial effects:

[0042] The housing of the motor arm in this application adopts a truss structure, which is simple in construction and has a clear force transmission path. Battery modules can be arranged within the truss range, which greatly increases the number of battery modules that can be arranged, improves the structural strength of the housing, and reduces the weight of the housing.

[0043] Additional advantages of this application will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of this application. Attached Figure Description

[0044] The above and other objects, features, and advantages of embodiments of this application will become more readily understood through the following detailed description with reference to the accompanying drawings. In the drawings, several embodiments of this application will be described by way of example and non-limitation, wherein:

[0045] Figure 1 This application shows a top view of the aircraft provided in an embodiment;

[0046] Figure 2 This illustration shows a partial structural diagram of the aircraft provided in an embodiment of this application;

[0047] Figure 3 This paper shows a perspective view of the motor arm of the aircraft provided in an embodiment of this application;

[0048] Figure 4 This invention provides a schematic diagram of the truss structure of the motor arm of an aircraft according to an embodiment of this application.

[0049] Figure 5 This illustration shows a first structural schematic diagram of the stringer structure of the motor arm of the aircraft provided in this application embodiment;

[0050] Figure 6 A cross-sectional view of the motor arm of the aircraft provided in an embodiment of this application is shown;

[0051] Figure 7 This document shows a partial top view of the motor arm of an aircraft provided in an embodiment of this application;

[0052] Figure 8 This paper shows a perspective structural diagram of the battery module of the motor arm of the aircraft provided in an embodiment of this application;

[0053] Figure 9 This diagram shows the layout of the battery module inside the motor arm of the aircraft provided in this embodiment.

[0054] Figure 10 This illustration shows a second structural diagram of the stringer of the motor arm truss structure of the aircraft provided in this application embodiment;

[0055] Figure 11 This diagram illustrates the truss structure of the motor arm of the aircraft provided in this embodiment, showing the fit between the stringers and the bulkheads.

[0056] Figure 12 This illustration shows a partial structural diagram of the truss structure of the motor arm of the aircraft provided in an embodiment of this application;

[0057] Figure 13 This is a perspective view of the frame of the truss structure of the motor arm of the aircraft provided in the embodiment of this application.

[0058] 100. Wing; 200. Motor arm; 210. Stringer; 2101. First wing slat; 2102. Second wing slat; 220. Spacer frame; 2201. Cutout groove; 230. Diagonal brace; 240. Skin; 300. Battery module; 310. Middle strip; 320. End strip; 330. Copper busbar; 340. Positive and negative terminals; 350. Individual battery cell; 360. Battery management system; 370. Mounting hole; 400. Front motor; 500. Rear motor mounting position. Detailed Implementation

[0059] The embodiments of this application are described in detail below. Examples of these embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application.

[0060] In the description of this application, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," and "circumferential" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0061] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this application, "multiple" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0062] In this application, unless otherwise expressly specified and limited, the terms "installation," "connection," "joining," "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components, unless otherwise expressly limited. Those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances.

[0063] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., refer to specific features, structures, materials, or characteristics described in connection with that embodiment or example, which are included in at least one embodiment or example of this application. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0064] Example 1

[0065] See Figures 1 to 13As shown, this application embodiment provides a motor arm 200, including a housing and a plurality of battery modules 300. The housing includes a truss structure and a skin 240, the truss structure enclosing a cavity, and the skin 240 covering the truss structure, at least partially concealing the cavity. Each of the battery modules 300 is disposed within the cavity, and the battery modules 300 are arranged sequentially along the length direction of the housing.

[0066] The housing of the motor arm 200 of this application adopts a truss structure, which is simple in construction and has a clear force transmission path. The battery modules 300 can be arranged within the truss range, which greatly increases the number of battery modules 300 that can be arranged, and improves the structural strength of the housing while reducing the weight of the housing.

[0067] See Figure 6 As shown in the embodiment of this application, the motor arm 200 is designed with integrated aerodynamics, structure and energy storage. In the outer contour of the cross-section of the motor arm 200, the curvature radius on both sides is large, the curvature radius at the bottom is in the middle, and the curvature radius at the top is the smallest. The upper and lower surfaces are arc-shaped transitions. The appearance structure of the motor arm 200 is similar to the fuselage of an aircraft.

[0068] In one possible implementation, see Figure 3 and Figure 4 As shown, the truss structure includes multiple trusses 210 and multiple partition frames 220. Each truss 210 extends along the length of the shell, and each partition frame 220 is sequentially spaced along the length of the truss 210. The partition frames 220 extend 210 circumferentially along each truss, and the partition frames 220 and the trusses 210 are fixedly connected, forming the cavity between them. The trusses 210 can be relatively long and have a thickness greater than that of the skin 240, serving to enhance the structural strength of the shell. Each partition frame 220 is fitted onto the truss 210, and the partition frames 220 and the trusses 210 can be connected by fasteners or by welding. The trusses 210 can be parallel, so that the structural sections of the shell with trusses 210 have a uniform cross-section, facilitating the arrangement of the same battery modules 300 within the uniform cross-section sections.

[0069] In one possible implementation, see Figure 4 As shown, the stringer 210 includes a first wing and a second wing, which are connected and form an included angle. The stringer 210 uses two wings with an included angle, increasing structural strength and making the stringer 210 less prone to bending.

[0070] See Figures 10 to 13As shown, the cross-section of the stringer 210 can be approximately T-shaped. The first wing 2101 can be arc-shaped for fitting and connecting with the skin, simplifying the connection structure with the skin. The second wing 2102 can be connected to the middle position of the first wing 2101 along the width direction. The partition frame 220 can be a closed ring and can be located inside each stringer 210. The partition frame 220 is provided with a notch 2201 corresponding to each stringer 210. The second wing 2102 of each stringer 210 can be inserted into the corresponding notch 2201 on the partition frame 220. The partition frame 220 is fixedly connected to at least one of the second wing 2102 and the first wing 2101.

[0071] In one possible implementation, see Figure 3 and Figure 4 As shown, the truss structure includes multiple diagonal braces 230, and each diagonal brace 230 adopts any one or more of the following configuration methods:

[0072] The diagonal braces 230 are respectively connected to different positions of the same partition frame 220;

[0073] The diagonal braces 230 are respectively connected to different partition frames 220;

[0074] The diagonal braces 230 are respectively connected to different long trusses 210;

[0075] The diagonal brace 230 is connected to the stringer 210 and the partition frame 220 respectively.

[0076] The motor arm 200 may comprise four long stringers 210, arranged on equal-section sections of the motor arm 200. Multiple partitions 220 are sequentially arranged along the length of each stringer 210. Diagonal braces 230 can be placed between every two partitions 220, with each end of the diagonal brace 230 connecting to two adjacent partitions 220. The diagonal braces 230 and the long stringers 210 bear the tension and bending moment of the motor, as well as the gravitational load of the distributed battery module 300 and related equipment. The partitions 220 are only for maintaining the shape of the outer skin 240 of the motor arm 200; therefore, the partitions 220 can be connected to the long stringers 210 in segments.

[0077] In this embodiment, the internal structure of the motor arm 200 is a truss structure, which is simple to construct and has a clear force transmission path. Battery modules 300 can be arranged within the truss range, which greatly increases the number of battery modules 300 that can be arranged.

[0078] It should be noted that the stringer 210, the frame 220, the diagonal brace 230, and the skin 240 can be made of metal, composite materials, or a combination of metal and composite materials.

[0079] In some possible implementations, the motor arm 200 may include a plurality of mounting components arranged sequentially along the length of the truss structure and fixed to the truss structure. The mounting components are at least partially located within the cavity, and each battery module 300 is mounted on a corresponding mounting component.

[0080] At least one set of battery modules 300 can be installed on the same mounting component. Preferably, two sets of battery modules 300 can be installed side by side on the same mounting component.

[0081] The mounting assembly can be connected at both ends to the second wing 2102 of the two stringers 210. The mounting assembly can be welded or fixed to the second wing 2102 by fasteners. The mounting assembly can be a whole plate or multiple strips. This application does not limit the specific structure of the mounting assembly.

[0082] For example, see Figure 6 , Figure 7 and Figure 8 As shown, the mounting assembly includes a central strip 310 and two end strips 320. The two end strips 320 are located on both sides of the central strip 310 along the length direction of the housing. Both the central strip 310 and the end strips 320 extend along the length direction perpendicular to the housing. The two ends of the battery module 300 along the length direction of the housing are respectively fixed to the corresponding end strips 320, and the middle of the battery module 300 along the length direction of the housing is supported by the central strip 310.

[0083] The battery module 300 has mounting slots at both ends. One end of the connector passes through the mounting slot and connects to the end strip 320. The other end of the connector is located at the end of the battery module 300 opposite to the end strip 320. Since there is no structure in the middle of the battery module 300 for easy connection and fixation, the battery module 300 can be directly supported on the middle strip 310 without connecting and fixing it to the middle strip 310. The middle strip 310 only serves to support the electromagnetic module, while the end strip 320 serves to connect and fix the battery module 300.

[0084] It should be noted that both the middle strip 310 and the end strip 320 can be fixedly connected to the two sides of the stringer 210 at both ends. The specific connection structure can be a fastener connection or a welding process connection.

[0085] A mounting assembly can be arranged between adjacent partition frames 220, allowing two battery modules 300 to be arranged side-by-side on the mounting assembly between the two partition frames 220 on the motor arm 200. Two sets of battery modules 300 between adjacent partition frames 220 are fixedly supported on the bottom middle strip 310 and two end strips 320. The middle strip 310 and the two end strips 320 can be located above or below the lower stringer 210 and connected to the stringer 210 by fasteners. Fixing holes can be provided on the end strips 320 at both ends to fix the battery modules 300. The middle strip 310 is only connected to the stringer 210 to support the battery modules 300, and is not fixed to the battery modules 300.

[0086] Optional, see Figure 8 As shown, the battery module 300 includes a plurality of individual battery cells 350, which are stacked sequentially. Each individual battery cell 350 has a mounting hole 370, and the mounting holes 370 of each individual battery cell 350 are connected to form the mounting groove.

[0087] In this application, the battery module 300 does not have a housing structure and is directly fixed in series by connectors, which simplifies the structure and avoids the housing structure occupying the internal space of the cavity. The connector can be a screw, with one end of the connector passing through the mounting hole 370 on each cell 350 and connecting to the fixing hole on the end strip 320, and the other end of the connector can be threaded to a nut, which is located on the top cell 350.

[0088] Of course, one end of the screw can have a cap, which is located on the top cell 350. The end of the screw away from the cap can pass through the mounting slot and through the mounting assembly. A nut is threaded onto the screw, and the nut is located on the side of the mounting assembly away from the battery module.

[0089] The battery module 300 is arranged within the motor arm 200, which provides the housing for the battery module 300. This allows for the removal of the PACK components from the battery module 300, improving battery recombination efficiency and increasing battery energy density. This integrated energy storage solution can accommodate 12 battery modules 300 arranged in a uniform cross-section, with two modules placed side-by-side within the same frame. Each battery module 300 consists of multiple pouch cells, and each or multiple modules are equipped with a battery management system 360.

[0090] See Figure 9As shown, the battery modules 300 can be connected in series and parallel via copper busbars 330, and are also connected to a power distributor via the copper busbars 330. The power distributor connects to the load equipment to supply power. The battery modules 300 are arranged within the motor arm 200, with large air ducts provided above, below, to the sides, and in the middle of the battery modules 300 for air cooling. Positive and negative terminals 340 can be provided on the battery modules 300 for easy connection to the copper busbars 330.

[0091] In this application, each battery module 300 has the same structure and can be interchanged at will, reducing the number of spare parts.

[0092] Optionally, both the middle strip 310 and the end strip 320 are connected at both ends to the two long trusses 210 of the truss structure.

[0093] In one possible implementation, the top of the skin 240 is provided with a battery mounting port and a first cover for opening or closing the battery mounting port. The first cover at the top is used to open the battery mounting port to facilitate the insertion of the battery module 300. The bottom of the skin 240 is provided with a battery maintenance port and a second cover for opening or closing the battery maintenance port. The second cover can be used to open the battery maintenance port when disassembling the battery module 300, facilitating the upward ejection of the battery module 300, so that the battery module 300 can be smoothly removed from the battery mounting port.

[0094] It should be noted that the top of the skin 240 can be set as a single, large first cover. Alternatively, multiple smaller first covers can be set on the top of the skin 240.

[0095] In this embodiment, the motor arm 200 adopts an opening design for easy installation and maintenance, facilitating the disassembly, replacement, and maintenance of the battery module 300. The truss structure of the motor arm 200 is mainly supported by long trusses 210, and openings can be designed between the long trusses 210 to facilitate battery inspection and maintenance, heat dissipation and ventilation, without affecting the overall structural efficiency.

[0096] Example 2

[0097] See Figures 1 to 13As shown in Embodiment 2 of this application, an aircraft is provided, including: a fuselage, a wing 100, and a motor arm 200. The wing 100 is connected to the fuselage. The motor arm 200 is connected to the wing 100. Rotors are respectively provided at both ends of the motor arm 200, and the rotors are electrically connected to a battery module 300, which provides rotational power to the rotors. The aircraft requires a motor arm 200 to house the motor rotors. A front motor mounting position is provided at the front end of the motor arm 200, and a rear motor mounting position 500 is provided at the rear end. A front motor 400 is mounted on the front motor mounting position. Motors are mounted at both ends of the motor arm 200. By arranging the power battery within the motor arm 200, the load on the wing 100 during flight is reduced, and the amount of battery space within the fuselage is reduced, saving internal space. Therefore, the area of ​​the motor arm 200 where the battery module 300 is located needs to be designed with a uniform cross-section. This design of the motor arm 200 integrates aerodynamics, structure, and energy storage, placing the battery module 300 within the motor arm 200. Large air ducts are provided above, below, to the sides, and in the middle of the battery module 300 for air cooling. Furthermore, the aerodynamic shape of the motor arm 200 is optimized to improve its aerodynamic performance.

[0098] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this application, and are not intended to limit them. Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of this application.

[0099] It should also be noted that the various specific technical features described in the above embodiments can be combined in any suitable manner without contradiction. To avoid unnecessary repetition, this application will not describe the various possible combinations separately.

Claims

1. A motor arm, characterized in that, include: A shell, comprising a truss structure and a skin, wherein the truss structure encloses a cavity, and the skin covers the truss structure, at least partially concealing the cavity; the truss structure comprises multiple stringers and multiple partitions, each stringer extending along the length of the shell, and each partition being sequentially spaced along the length of the stringers; the partitions extending circumferentially along each stringer and being fixedly connected to the stringers, the cavity being formed between the partitions and the stringers; each stringer comprising a first wing and a second wing, the first wing and the second wing being connected and having an included angle; the first wing being arc-shaped for fitting and connecting with the skin; the second wing being connected to the middle position of the first wing along its width; and each partition having a notch corresponding to each stringer, the second wing of each stringer being able to be inserted into the corresponding notch on the partition. Multiple battery modules are provided, each battery module is disposed within the cavity, and the battery modules are arranged sequentially along the length of the housing; Multiple mounting components are arranged sequentially along the length of the truss structure and fixed to the truss structure. Each mounting component is at least partially located within the cavity. Each battery module is mounted on a corresponding mounting component. Each mounting component includes a central strip and two end strips. The two end strips are located on both sides of the central strip along the length of the housing. Both the central strip and the end strips extend along the length perpendicular to the housing. The two ends of each battery module along the length of the housing are fixed to the corresponding end strips. The middle of each battery module along the length of the housing is supported by the central strip. Each end of each battery module has a mounting groove. One end of a connector passes through the mounting groove and connects to the end strip. The other end of the connector is located at the end of the battery module opposite to the end strip. Both the central strip and the end strips are connected at both ends to the second wing of two long trusses of the truss structure.

2. The motor arm according to claim 1, characterized in that, The truss structure includes multiple diagonal braces; Each of the aforementioned diagonal braces may be configured in one or more of the following ways: The diagonal braces are connected to different positions within the same partition frame; The diagonal braces are respectively connected to different partition frames; The diagonal braces are respectively connected to different long trusses; The diagonal braces are respectively connected to the long truss and the partition frame.

3. The motor arm according to claim 1, characterized in that, The battery module includes multiple individual battery cells; Each of the battery cells is stacked sequentially, and each battery cell has a mounting hole; The mounting holes of each of the battery cells are connected to form the mounting groove.

4. The motor arm according to any one of claims 1-3, characterized in that, The top of the skin is provided with a battery mounting port and a first cover for opening or closing the battery mounting port; The bottom of the skin is provided with a battery maintenance port and a second cover for opening or closing the battery maintenance port.

5. An aircraft, characterized in that, include: body; Wings, which are connected to the fuselage; The motor arm as described in any one of claims 1-4, wherein the motor arm is connected to the wing.

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