Aircraft and vehicle
By designing a combined structure of battery module, bottom frame and support beam in the aircraft, the problem of excessive weight of the existing aircraft is solved, and the structural strength is increased and the weight is reduced, achieving the lightweight effect of the aircraft.
Patent Information
- Application Number
- CN202311622849.8
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2023-11-29
- Publication Date
- 2025-05-30
AI Technical Summary
Existing aircraft have challenges in reducing overall weight, especially in the connection structure of the battery module, which leads to a high weight of the aircraft, which is not conducive to lightweighting.
By designing an aircraft structure including a battery module, a bottom frame and a support beam, the battery module consists of a cover body, a pallet structure, a package body and a plurality of battery cell units. The pallet structure extends into the frame space of the bottom frame and abuts on the support beam, thereby improving the overall structural strength.
This design improves the overall structural strength after the battery module and the bottom frame are connected, so that the pallet structure can be made using a low-density material to reduce the overall weight of the aircraft and achieve the lightweight of the aircraft.
Smart Images
Figure CN120056662A_ABST
Abstract
Description
Technical Field
[0001] This application relates to the technical field of transportation, and particularly to an aircraft and a vehicle. Background Art
[0002] With the development of transportation technology, recently, aircraft such as flying cars have emerged. Aircraft have relatively strict requirements for weight and need to reduce the overall weight as much as possible to improve flight performance. In related technologies, some aircraft use battery modules such as power batteries to provide flight power.
[0003] Among them, on the basis that the aircraft body has sufficient strength, the battery module usually includes a box body with relatively high strength, and the side surface of the box body is used for mounted connection with the aircraft body to ensure the overall structural strength of the aircraft; however, this connection structure results in a relatively high weight of the aircraft, which is not conducive to the lightweight of the aircraft. Summary of the Invention
[0004] The main purpose of this application is to propose an aircraft to facilitate lightweight.
[0005] To achieve the above object, the aircraft proposed in this application includes a battery module, a bottom frame, and a support beam. The battery module includes a cover body, a tray structure, a package body, and a plurality of battery cell monomers. The cover body and the tray structure enclose to form a receiving cavity, the battery cell monomers are received in the receiving cavity, and the package body is arranged in the receiving cavity and encapsulates and fixes the battery cell monomers; the support beam is connected to the bottom frame, and the tray structure extends into the frame space of the bottom frame and abuts against the support beam.
[0006] Optionally, the aircraft further includes a bottom plate, and the plate surface of the bottom plate is connected to the side of the bottom frame facing away from the cover body; the bottom plate and the bottom frame enclose to form at least one receiving groove, and the support beam is arranged in the receiving groove; the tray structure includes a tray body, and the tray body and the cover body enclose to form the receiving cavity; the tray body extends into the receiving groove, the tray body is provided with a circumferential edge, and the circumferential edge is fixedly connected to the bottom frame to close the receiving groove by the tray body; the tray body is provided with a first pressure relief structure, and the bottom plate is provided with a second pressure relief structure.
[0007] Optionally, the support beam abuts against the plate surface of the bottom plate, the tray structure further includes a plurality of support bodies, the support bodies are arranged on the side of the tray body facing the receiving groove, the support bodies abut against the support beam, and the support bodies are arranged at intervals along the length direction of the support beam.
[0008] Optionally, the bottom frame includes a plurality of outer beams, and the plurality of outer beams are connected end to end in sequence; the bottom frame further includes a partition beam, and two ends of the partition beam are respectively connected to the outer beams, and two sides of the partition beam are respectively arranged at intervals with the corresponding outer beams; the partition beam, the outer beams and the bottom plate enclose to form the accommodation groove, and the ring edge abuts against the partition beam and the outer beams.
[0009] Optionally, the thickness direction of the partition beam and the thickness direction of the support beam are respectively perpendicular to the supporting plane of the tray structure, and the thickness of the partition beam is greater than the thickness of the support beam; a notch is arranged on a side of the partition beam facing away from the tray structure, the support beam passes through the notch, and two ends of the support beam are respectively connected to the corresponding outer beams.
[0010] Optionally, a seat is arranged on a side of the cover body facing away from the tray structure, and a surface of the cover body abuts against the seat.
[0011] Optionally, two spaced-apart limiting beams are arranged on a side of the cover body facing away from the tray structure, and part of the seat is arranged between the two limiting beams, and a side surface of the limiting beam is used for abutting against the seat.
[0012] Optionally, a cooling structure is further arranged in the accommodation cavity, and the cooling structure is used for cooling the battery cell monomers; the cooling structure is arranged in the accommodation cavity, the cooling structure is arranged beside the battery cell monomers, and the encapsulation body encapsulates and fixes the cooling structure and the battery cell monomers.
[0013] Optionally, an extending direction of the cooling structure is parallel to the supporting plane of the tray structure, the cooling structure includes at least one bending section, and the encapsulation body is fixedly connected to the bending section.
[0014] Optionally, at least two spaced-apart cooling structures are arranged in the accommodation cavity, an arrangement direction of the cooling structures is parallel to the supporting plane of the tray structure, and the battery cell monomers are correspondingly arranged in intervals between two adjacent cooling structures; and / or, a supporting plate and a plurality of vertical plates are further arranged in the accommodation cavity, and the vertical plates are arranged on the supporting plate at intervals; the vertical plates are arranged beside the battery cell monomers, and the encapsulation body encapsulates and fixes the cooling structures, the vertical plates and the battery cell monomers.
[0015] Optionally, at least part of the tray structure is made of plastic; and / or, a material density of the tray structure is less than a material density of the cover body.
[0016] The present application further provides a transportation vehicle, which includes a road vehicle and the above-mentioned aircraft, and the aircraft is detachably mounted on the road vehicle.
[0017] The technical solution of the present application sets the aircraft to include a battery module, a bottom frame, and a support beam. The battery module includes a cover body, a tray structure, a package body, and a plurality of battery cell monomers. The cover body and the tray structure enclose to form a receiving cavity, the battery cell monomers are accommodated in the receiving cavity, and the package body is arranged in the receiving cavity and encapsulates and fixes the battery cell monomers; the support beam is connected to the bottom frame, the tray structure extends into the frame space of the bottom frame and abuts against the support beam; the package body fixes the battery cell monomers, which can improve the overall structural strength of the battery module; the tray structure abuts against the support beam connected to the bottom frame, which can improve the overall structural strength after the battery module is connected to the bottom frame; the improvement of the overall structural strength of the battery module and the overall structural strength after the battery module is connected to the bottom frame is conducive to using materials with lower density to manufacture the tray structure and ensuring the overall structural strength of the aircraft, which is conducive to the lightweight of the aircraft. Description of the Drawings
[0018] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the following will briefly introduce the drawings required for use in the description of the embodiments or the prior art. Obviously, the drawings in the following description are only some embodiments of the present application. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on the structures shown in these drawings.
[0019] Figure 1 It is a partial structural schematic diagram of an embodiment of the aircraft of the present application.
[0020] Figure 2 It is a partial structural explosion diagram of an embodiment of the aircraft of the present application.
[0021] Figure 3 It is another partial structural schematic diagram of an embodiment of the aircraft of the present application.
[0022] Figure 4 It is Figure 3 The cross-sectional view at A-A in
[0023] Figure 5 It is Figure 4 The partial enlarged view at C in
[0024] Figure 6 It is Figure 3 The cross-sectional view at B-B in
[0025] Figure 7 It is another partial structural schematic diagram of an embodiment of the aircraft of the present application.
[0026] Figure 8 It is a structural schematic diagram of an embodiment of the vehicle of the present application.
[0027] The realization of the purpose of this application, its functional features and advantages will be further described in conjunction with the embodiments with reference to the accompanying drawings. Detailed implementation manners
[0028] Next, the technical solutions in the embodiments of this application will be clearly and completely described with reference to the accompanying drawings in the embodiments of this application. Obviously, the described embodiments are only a part of the embodiments of this application, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments in this application without making creative efforts belong to the scope of protection of this application.
[0029] It should be noted that if there are directional indications (such as up, down, left, right, front, back...) involved in the embodiments of this application, then such directional indications are only used to explain the relative positional relationship and movement conditions between components in a specific posture. If this specific posture changes, then such directional indications will also change accordingly.
[0030] In addition, if there are descriptions such as "first", "second", etc. involved in the embodiments of this application, then such descriptions of "first", "second", etc. are only for descriptive purposes and cannot be understood as indicating or implying their relative importance or implicitly indicating the quantity of the indicated technical features. Thus, the features defined with "first" and "second" may explicitly or implicitly include at least one of such features. In addition, if "and / or" or "and / or" appears throughout the text, its meaning includes three parallel scenarios. Taking "A and / or B" as an example, it includes scenario A, or scenario B, or the scenario where A and B are satisfied simultaneously. In addition, the technical solutions between various embodiments can be combined with each other, but it must be based on the fact that those of ordinary skill in the art can implement them. When the combination of technical solutions is contradictory or cannot be implemented, it should be considered that such a combination of technical solutions does not exist and is not within the scope of protection required by this application.
[0031] With the development of transportation technology, recently, flying cars, a type of aircraft, have emerged. Aircraft have relatively strict requirements for weight and need to reduce the overall weight as much as possible to improve flight capabilities. In related technologies, some aircraft use battery modules such as power batteries to provide flight power.
[0032] Among them, on the basis that the airframe of the aircraft has sufficient strength, the battery module usually includes a box with relatively high strength, and the side of the box is used for mounted connection with the airframe of the aircraft to ensure the overall structural strength of the aircraft; however, this connection structure results in a relatively high weight of the aircraft, which is not conducive to the lightweight of the aircraft.
[0033] Therefore, this application proposes an aircraft to facilitate lightweight.
[0034] Refer toFigure 1 and Figure 2 In an embodiment of the present application, the aircraft 1000 includes a battery module 1100, a bottom frame 1200, and a support beam 1300. Among them, the aircraft 1000 may further include a rotor assembly and a corresponding drive motor, and the battery module 1100 may be electrically connected to the drive motor of the rotor assembly to provide power. Among them, the aircraft 1000 may be configured as a flying car or the like. The battery module 1100 includes a cover 1110, a tray structure 1120, a package 1130, and a plurality of battery cells 1140; the cover 1110 and the tray structure 1120 enclose a receiving cavity, which can be understood as the outer edge of the cover 1110 abuts against the outer edge of the tray structure 1120 to form the receiving cavity.
[0035] The battery cells 1140 are accommodated in the receiving cavity, and the package 1130 is disposed in the receiving cavity and encapsulates and fixes the battery cells 1140. Among them, the package 1130 may be formed by potting. It can be understood that after all the battery cells 1140 are arranged in place, potting is performed to form the above-mentioned package 1130. Among them, after the cover 1110 and the tray structure 1120 enclose a receiving cavity, potting can be performed by reserving an injection port in structures such as the cover 1110; potting can also be performed using the tray structure 1120 and a corresponding mold, and this embodiment does not limit this.
[0036] The support beam 1300 is connected to the bottom frame 1200, for example, by welding or plugging. The tray structure 1120 extends into the frame space of the bottom frame 1200 and abuts against the support beam 1300, so that the support beam 1300 can bear the weight of the battery module 1100.
[0037] In this embodiment, the package 1130 fixes the battery cells 1140, which can improve the overall structural strength of the battery module 1100; the tray structure 1120 abuts against the support beam 1300 connected to the bottom frame 1200, which can improve the overall structural strength after the battery module 1100 is connected to the bottom frame 1200; the improvement of the overall structural strength of the battery module 1100 and the overall structural strength after the battery module 1100 is connected to the bottom frame 1200 is conducive to using materials with a lower density to manufacture the tray structure 1120 and ensuring the overall structural strength of the aircraft 1000, which is conducive to the lightweight of the aircraft 1000.
[0038] In some embodiments, at least part of the tray structure 1120 is made of plastic to reduce the overall weight of the aircraft and achieve the lightweight of the aircraft 1000; at the same time, the cover 1110 can be made of aluminum material, so that the material density of the tray structure 1120 is less than the material density of the cover 1110.
[0039] In some embodiments, the single battery cell 1140 may be configured as a cylindrical battery cell to reduce the internal expansion force of the battery module 1100 and improve the overall structural strength and durability of the battery module 1100. Of course, the single battery cell 1140 may also be configured as a square shell battery cell or a soft-pack battery cell, and this embodiment does not limit this. In addition, the body frame may also be configured to have a carrying compartment for carrying passengers or goods.
[0040] In some embodiments, referring to Figure 1 and Figure 2 , the aircraft 1000 further includes a bottom plate 1400. The plate surface of the bottom plate 1400 is connected to the side of the bottom frame 1200 facing away from the cover 1110. For example, the plate surface of the bottom plate 1400 is connected to the bottom side of the bottom frame 1200 in the figure. Among them, the bottom frame 1200 can be made of steel to improve the structural strength of the aircraft 1000; the bottom plate 1400 can be made of materials such as steel or aluminum. The bottom plate 1400 can be fixedly connected to the bottom frame 1200 by means of welding, riveting, etc. Referring to Figure 2 , the bottom plate 1400 and the bottom frame 1200 enclose at least one receiving groove 1401, and the support beam 1300 is arranged in the receiving groove 1401. The tray structure 1120 includes a tray body 1121. The tray body 1121 and the cover 1110 enclose a receiving cavity; it can be understood that the outer edge of the cover 1110 abuts against the outer edge of the tray body 1121 to form this receiving cavity. Among them, the tray body 1121 can be made of a material with a density lower than a preset value, such as plastic, to reduce the overall weight of the aircraft 1000. The tray body 1121 extends into the receiving groove 1401. The tray body 1121 is provided with a ring edge 1122, and the ring edge 1122 is fixedly connected to the bottom frame 1200 to close the receiving groove 1401 by the tray body 1121; it can be understood that part of the battery module 1100 extends into the receiving groove 1401 and closes the receiving groove 1401. The tray body 1121 is provided with a first pressure relief structure, and the bottom plate 1400 is provided with a second pressure relief structure. Among them, at least one of the first pressure relief structure and the second pressure relief structure can be configured as an explosion-proof valve. Or, a through hole can be provided in the tray body 1121, and a diaphragm such as a nylon plate is covered on the through hole to form the first pressure relief structure.
[0041] In this embodiment, the receiving groove 1401 formed by the bottom plate 1400 and the bottom frame 1200 can replace the lower box body of the battery module 1100 in the related art (the lower box body in the related art is usually made of aluminum material). It can be understood that this embodiment integrates the battery module 1100 and the bottom frame 1200, which is beneficial to reducing the overall weight of the aircraft 1000 and making the aircraft 1000 lightweight.
[0042] It can be understood that when the tray body 1121 and the cover body 1110 enclose to form a receiving cavity, the battery cell unit 1140 inside may form a high pressure in the receiving cavity due to thermal runaway. At this time, when the battery cell unit 1140 in the receiving cavity undergoes thermal runaway, the first pressure relief structure can discharge substances such as high-temperature ejecta into the receiving groove 1401 between the tray body 1121 and the bottom plate 1400, reducing the risk of damage to the aircraft 1000. If there are a large amount of substances such as high-temperature ejecta discharged from the battery cell unit 1140 in the receiving cavity, resulting in an increase in the internal pressure of the receiving groove 1401, the second pressure relief structure can be opened under pressure for excretion, which is beneficial to further reducing the risk of damage to the aircraft 1000.
[0043] In some embodiments, the encapsulation body 1130 extends to the bottom plate 1400, and the first pressure relief structure is arranged in one-to-one correspondence with the battery cell unit 1140, so that each battery cell unit 1140 has an independent excretion channel, which is beneficial to reducing the risk of the damaged battery cell unit 1140 due to thermal runaway damaging other battery cell units 1140.
[0044] In some embodiments, a seat may be provided on the side of the cover body 1110 facing away from the tray structure 1120, and the surface of the cover body 1110 abuts against the seat. In this embodiment, the seat can be carried on the battery module 1100 with relatively high structural strength and the connection structure between the battery module 1100 and the bottom frame 1200, which is beneficial to reducing the supporting members of the seat and beneficial to lightening the weight of the aircraft 1000. Among them, with reference to Figure 1 and Figure 2 , two spaced-apart limiting beams 1500 may be provided on the side of the cover body 1110 facing away from the tray structure 1120, and part of the seat is arranged between the two limiting beams 1500. The side surfaces of the limiting beams 1500 are used to abut against the seat to improve the connection stability of the seat. In addition, the limiting beams 1500 are also beneficial to improving the overall structural strength of the cover body 1110 and the battery module 1100, beneficial to using materials with a lower density to manufacture the tray structure 1120 and ensuring the overall structural strength of the aircraft 1000, and beneficial to the lightening of the aircraft 1000.
[0045] In some embodiments, with reference to Figure 1, one side of the bottom plate 1400 has an extension section 1410, and the extension section 1410 extends out of the cross beam 1230 along the arrangement direction of the cross beam 1230, so that it can be used for the occupant to place feet or can be used to place other objects. One side of the cover body 1110 forms a convex part 1111, and the convex part 1111 protrudes in the direction away from the tray structure 1120, so that other components of the battery module 1100 can be accommodated inside the convex part 1111, improving the space utilization rate of the aircraft 1000. The limiting beam 1500 is arranged beside the convex part 1111, and the convex part 1111 and the extension section 1410 are arranged opposite to each other, thereby further improving the space utilization rate of the aircraft 1000.
[0046] In some embodiments, referring to Figure 2 , a cooling structure 1150 is further provided in the accommodation cavity, and the cooling structure 1150 is used to cool the battery cell monomers 1140 to reduce the risk of thermal runaway of the battery cell monomers 1140. The cooling structure 1150 is arranged in the accommodation cavity, the cooling structure 1150 is arranged beside the battery cell monomers 1140, and the encapsulation body 1130 encapsulates and fixes the cooling structure 1150 and the battery cell monomers 1140. In this embodiment, the cooling structure 1150 can serve as the skeleton structure of the encapsulation body 1130, improving the overall structural strength of the battery module 1100, and allowing other structures such as the tray structure 1120 to be prepared with lighter or lower density materials, which is beneficial to the lightweight of the aircraft 1000.
[0047] In some embodiments, referring to Figure 2 , the extending direction of the cooling structure 1150 is parallel to the supporting plane of the tray structure 1120, the cooling structure 1150 includes at least one bending section 1151, and the encapsulation body 1130 is fixedly connected to the bending section 1151. Among them, the cooling structure 1150 can be set as a serpentine cooling pipe, so that the cooling structure 1150 includes a plurality of bending sections 1151. In this embodiment, the cooling structure 1150 including at least one bending section 1151 can further improve the overall structural strength of the battery module 1100 through the encapsulation and fixation of the encapsulation body 1130, and allows other structures such as the tray structure 1120 to be prepared with lighter or lower density materials, which is more beneficial to the lightweight of the aircraft 1000. In addition, the cooling structure 1150 including at least one bending section 1151 can also increase the contact area with the battery cell monomers 1140, which is beneficial to further reducing the risk of thermal runaway of the battery cell monomers 1140.
[0048] In some embodiments, referring to Figure 2, at least two cooling structures 1150 arranged at intervals are provided in the accommodating cavity. The arrangement direction of the cooling structures 1150 is parallel to the supporting plane of the tray structure 1120, and the battery cell monomers 1140 are correspondingly arranged in the intervals between two adjacent cooling structures 1150. In this embodiment, at least two cooling structures 1150 arranged at intervals can further improve the overall structural strength of the battery module 1100 through the encapsulation and fixation of the encapsulation body 1130, and can allow other structures such as the tray structure 1120 to be prepared with lighter or lower-density materials, which is more conducive to the lightweight of the aircraft 1000. In addition, at least two cooling structures 1150 arranged at intervals can also increase the overall contact area with the battery cell monomers 1140, which is beneficial to further reducing the risk of thermal runaway of the battery cell monomers 1140.
[0049] In some embodiments, referring to Figure 2 , a supporting plate 1161 and a plurality of vertical plates 1162 are further provided in the accommodating cavity. The vertical plates 1162 are arranged at intervals on the supporting plate 1161; the vertical plates 1162 are arranged beside the battery cell monomers 1140, and the encapsulation body 1130 encapsulates and fixes the cooling structures 1150, the vertical plates 1162 and the battery cell monomers 1140. The supporting plate 1161 and the vertical plates 1162 can support the battery cell monomers 1140. During the process of forming the encapsulation body 1130 by means such as glue injection, it is beneficial to reduce the risk of the battery cell monomers 1140 being skewed and squeezing each other, and is beneficial to reducing the risk of thermal runaway of the battery cell monomers 1140 due to mutual extrusion. Among them, the supporting plate 1161 and the vertical plates 1162 can be made of materials such as aerogel or plastic respectively. The supporting plate 1161 can also be bonded to the tray body 1121 before loading the battery cell monomers 1140 to improve the position stability. In addition, an adhesive layer can be formed on the side surface of the vertical plate 1162 to improve the supporting stability of the battery cell monomers 1140 by bonding the battery cell monomers 1140.
[0050] In some embodiments, referring to Figure 3 and Figure 4 , the supporting beam 1300 abuts against the plate surface of the bottom plate 1400, so that the supporting beam 1300, the bottom frame 1200 and the bottom plate 1400 can form a new groove at the bottom of the accommodating groove 1401. In this embodiment, if some of the battery cell monomers 1140 experience thermal runaway, the groove formed by the supporting beam 1300, the bottom frame 1200 and the bottom plate 1400 can collect the discharge products, reduce the distribution range of the discharge products, and reduce the subsequent cleaning difficulty. Among them, the groove formed by the supporting beam 1300, the bottom frame 1200 and the bottom plate 1400 can correspond to a plurality of first pressure relief structures, which can be understood as the discharge products of the plurality of first pressure relief structures being discharged into one of the above grooves.
[0051] Referring to Figure 4 andFigure 5 In addition, the tray structure 1120 further includes a plurality of support bodies 1123. The support bodies 1123 can be configured as columns; the support bodies 1123 can be made of plastic, or the support bodies 1123 can be integrally formed with the tray body 1121. The support bodies 1123 are disposed on the side of the tray body 1121 facing the receiving groove 1401, and the support bodies 1123 are in contact with the support beams 1300, so as to bear the weight of the battery module 1100. The support bodies 1123 are arranged at intervals along the length direction of the support beams 1300 to improve the load uniformity of the battery module 1100. In addition, when a large amount of substances are discharged from the battery cell 1140 through the first pressure relief structure, these substances can overflow the support beams 1300 and flow from the intervals between the support beams 1300 to the second pressure relief structure, which is beneficial to reducing the number of the second pressure relief structures on the bottom plate 1400, beneficial to reducing the overall manufacturing cost and improving the overall structural strength of the bottom plate 1400.
[0052] In some embodiments, the support body 1123 is provided with through holes, and the aircraft 1000 further includes fasteners; the fasteners pass through the through holes, and both ends of the fasteners are fixedly connected to the tray body 1121 and the support beams 1300 respectively; wherein, the fasteners can be configured as rivets, screws, bolts, etc. The encapsulation body 1130 extends to the fasteners, and the encapsulation body 1130 is fixedly connected to the fasteners. The fasteners passing through the through holes of the support body 1123 are beneficial to improving the structural strength of the support body 1123 and reducing the risk of the support body 1123 being skewed and broken. The encapsulation body 1130 being fixedly connected to the fasteners is beneficial to reducing the risk of the fasteners becoming loose and improving the connection stability between the battery module 1100 and the support beams 1300.
[0053] In some embodiments, the bottom frame 1200 includes a plurality of outer beams, and the plurality of outer beams are sequentially connected end to end; Figure 6 and Figure 7 in some embodiments, two of the outer beams can be configured as side beams 1220, and two of the outer beams can be configured as cross beams 1230; wherein, the extending direction of the cross beam 1230 is transverse to the extending direction of the side beam 1220. The cross beam 1230 is correspondingly connected to the side beam 1220, so as to enclose the above-mentioned receiving groove 1401 with the bottom plate 1400, that is, the partition beam 1210, the outer beam and the bottom plate 1400 enclose the receiving groove 1401. In addition, the bottom frame 1200 may further include a partition beam 1210, and both ends of the partition beam 1210 are respectively connected to the outer beams, for example, by welding or riveting; both sides of the partition beam 1210 are respectively spaced apart from the corresponding outer beams, for example, Figure 7 both sides of the partition beam 1210 in Figure 2, a sealing ring can be provided on one side of the circumferential edge 1122 of the tray structure 1120 facing the partition beam 1210 to improve the sealing performance when the battery module 1100 encloses the receiving groove 1401.
[0054] In addition, referring to Figure 2 , the cover body 1110 can also be provided with another circumferential edge to facilitate the connection between the cover body 1110 and the circumferential edge 1122 of the tray structure 1120. Among them, another sealing ring can be provided between the circumferential edge of the cover body 1110 and the circumferential edge 1122 of the tray structure 1120 to improve the sealing performance of the accommodating cavity formed by enclosing the cover body 1110 and the tray structure 1120. At this time, fasteners such as bolts and rivets can be used to sequentially pass through the circumferential edge of the cover body 1110, the circumferential edge 1122 and the corresponding sealing ring, so as to fix the cover body 1110, the tray body 1121 and the bottom frame 1200.
[0055] Referring to Figure 7 , in some embodiments, the thickness direction of the partition beam 1210 and the thickness direction of the support beam 1300 are respectively perpendicular to the supporting plane of the tray structure 1120, and the thickness of the partition beam 1210 is greater than the thickness of the support beam 1300; a notch 1211 is provided on one side of the partition beam 1210 facing away from the tray structure 1120, and the support beam 1300 passes through the notch 1211, and both ends of the support beam 1300 are respectively connected to the corresponding outer beams, for example, both ends of the support beam 1300 are respectively connected to the side beam 1220 in the figure. The structural form in which the support beam 1300 passes through the notch 1211 can improve the integrity of the support beam 1300, thereby further improving the overall structural strength after the battery module 1100 is connected to the bottom frame 1200, which is beneficial to manufacturing structures such as the tray structure 1120 with materials of lower density and ensuring the overall structural strength of the aircraft 1000, and is beneficial to the lightweight of the aircraft 1000.
[0056] In some embodiments, the aircraft 1000 may include a plurality of support beams 1300, and the support beams 1300 are arranged at intervals; correspondingly, a plurality of notches 1211 may be provided on one side of the partition beam 1210 facing away from the tray structure 1120. In this embodiment, the plurality of support beams 1300 are beneficial to further improving the load balance of the battery module 1100, and are also beneficial to improving the overall structural strength after the battery module 1100 is connected to the bottom frame 1200, which is beneficial to manufacturing structures such as the tray structure 1120 with materials of lower density and ensuring the overall structural strength of the aircraft 1000, and is beneficial to the lightweight of the aircraft 1000.
[0057] The present application also provides a means of transportation, which includes a road vehicle 2000 and the above-mentioned aircraft 1000. The aircraft 1000 is detachably mounted on the road vehicle 2000. Among them, the aircraft 1000 can fly away from the road vehicle 2000, and the aircraft 1000 can also be parked on the road vehicle 2000 for transportation by the road vehicle 2000.
[0058] It can be understood that for the specific structure of the aircraft 1000, reference may be made to the above-mentioned embodiments. Since this means of transportation adopts all the technical solutions of all the embodiments of the above-mentioned aircraft 1000, it at least has all the beneficial effects brought by the technical solutions of the above-mentioned embodiments, which will not be elaborated here one by one.
[0059] The above are only the preferred embodiments of the present application, and do not limit the patent scope of the present application. Any equivalent structural transformation made under the technical concept of the present application by using the content of the specification and drawings of the present application, or any direct / indirect application in other related technical fields is included in the patent protection scope of the present application.
Claims
1. An aircraft, characterized in that, the aircraft includes a battery module, a bottom frame and a support beam. The battery module includes a cover body, a tray structure, a package body and a plurality of battery cell monomers. The cover body and the tray structure enclose a receiving cavity. The battery cell monomers are received in the receiving cavity. The package body is disposed in the receiving cavity and encapsulates and fixes the battery cell monomers; the support beam is connected to the bottom frame, and the tray structure extends into the frame space of the bottom frame and abuts against the support beam.
2. The aircraft according to claim 1, characterized in that, the aircraft further includes a bottom plate, and a plate surface of the bottom plate is connected to a side of the bottom frame facing away from the cover body; at least one receiving groove is formed by enclosing the bottom plate and the bottom frame, and the support beam is disposed in the receiving groove; the tray structure includes a tray body, and the tray body and the cover body enclose the receiving cavity; the tray body extends into the receiving groove, and the tray body is provided with a circumferential edge, and the circumferential edge is fixedly connected to the bottom frame to close the receiving groove by the tray body; a first pressure relief structure is provided on the tray body, and a second pressure relief structure is provided on the bottom plate.
3. The aircraft according to claim 2, characterized in that, the support beam abuts against the plate surface of the bottom plate, and the tray structure further includes a plurality of support bodies. The support bodies are disposed on a side of the tray body facing the receiving groove, and the support bodies abut against the support beam. The support bodies are arranged at intervals along the length direction of the support beam.
4. The aircraft according to claim 2, characterized in that, the bottom frame includes a plurality of outer beams, and the plurality of outer beams are connected end to end in sequence; the bottom frame further includes a partition beam, and two ends of the partition beam are respectively connected to the outer beams, and two sides of the partition beam are respectively spaced from the corresponding outer beams; the partition beam, the outer beam and the bottom plate enclose the receiving groove, and the circumferential edge abuts against the partition beam and the outer beam.
5. The aircraft according to claim 4, characterized in that, the thickness direction of the partition beam and the thickness direction of the support beam are respectively perpendicular to the supporting plane of the tray structure, and the thickness of the partition beam is greater than the thickness of the support beam; a notch is provided on a side of the partition beam facing away from the tray structure, and the support beam passes through the notch, and two ends of the support beam are respectively connected to the corresponding outer beams.
6. The aircraft according to any one of claims 1 to 5, characterized in that, a seat is provided on a side of the cover body facing away from the tray structure, and a surface of the cover body abuts against the seat.
7. The aircraft according to claim 6, characterized in that, two spaced-apart limiting beams are provided on a side of the cover body facing away from the tray structure, and part of the seat is disposed between the two limiting beams, and a side surface of the limiting beam is used to abut against the seat.
8. The aircraft according to any one of claims 1 to 5, characterized in that, A cooling structure is further provided in the accommodation cavity, and the cooling structure is used to cool the battery cell unit; the cooling structure is arranged in the accommodation cavity, beside the battery cell unit, and the encapsulation body encapsulates and fixes the cooling structure and the battery cell unit.
9. The aircraft according to claim 8, characterized in that the extending direction of the cooling structure is parallel to the supporting plane of the tray structure, the cooling structure includes at least one bending section, and the encapsulation body is fixedly connected to the bending section.
10. The aircraft according to claim 8, characterized in that at least two cooling structures arranged at intervals are provided in the accommodation cavity, the arrangement direction of the cooling structures is parallel to the supporting plane of the tray structure, and the battery cell unit is correspondingly arranged in the interval between two adjacent cooling structures; and / or a supporting plate and a plurality of vertical plates are further provided in the accommodation cavity, and the vertical plates are arranged on the supporting plate at intervals; the vertical plates are arranged beside the battery cell unit, and the encapsulation body encapsulates and fixes the cooling structure, the vertical plates and the battery cell unit.
11. The aircraft according to any one of claims 1 to 5, characterized in that at least part of the tray structure is made of plastic; and / or the material density of the tray structure is less than the material density of the cover body.
12. A vehicle, characterized in that the vehicle includes a road vehicle and the aircraft according to any one of claims 1 to 11, and the aircraft is detachably mounted on the road vehicle.