A distributed electric aircraft capable of fast battery replacement

Abstract

The utility model discloses a kind of distributed electric aircrafts of quick battery replacement;It is related to new energy unmanned aerial vehicle technical field, multiple electric propellers are distributedly arranged on wing, multiple local skins are detachably connected on wing, mounting seat for erecting battery is equipped on local skin, mounting seat includes upper support plate and lower support plate, upper support plate is fixedly connected on wing rib, lower support plate is used to carry battery, shear fork telescopic structure is equipped between upper support plate and lower support plate;Lower support plate is fixedly connected with local skin;When local skin is fixed on wing rib, battery is clamped between upper support plate and lower support plate, and in working position;Upper support plate is also provided with connecting notch, and battery is connected to motor output power supply through connecting notch;The mounting seat design of detachable local skin and shear fork telescopic structure cooperation of the present application realizes the quick clamping positioning and power connection of battery on wing main structure, solves the technical problem that traditional battery replacement needs to disassemble fuselage component, operation is complex, has the advantages of improving battery replacement efficiency, simplifying operation process and guaranteeing structural stability.

Description

Technical Field

[0001] This utility model relates to the field of new energy unmanned aerial vehicle (UAV) technology, and in particular to a distributed electric aircraft with fast battery swapping capability. Background Technology

[0002] With the development of aviation technology, distributed electric aircraft with multiple energy sources are gradually coming into the public eye, and the integration of electric propulsion systems with turbine systems is gradually becoming a new development trend.

[0003] Distributed electric aircraft construct a distributed power system by distributing multiple small electric thrusters along the wing section. This system includes propellers, motors, and batteries. The motors and batteries are housed within the wing and fixed to the main wing structure. The motors drive the propellers to provide power. (See attached diagram.) Figure 1 This design, which uses electricity as its power source, allows the aircraft to produce almost no carbon emissions during flight, significantly reducing greenhouse gas emissions. At the same time, the noise level of the electric propulsion system is much lower than that of traditional aircraft engines, which can significantly reduce noise pollution and is highly in line with the development demands of green aviation in modern society.

[0004] However, the charging time for electric aircraft is much longer than the refueling time for traditional fuel-powered aircraft, which significantly reduces the aircraft's energy replenishment efficiency. Therefore, how to improve the transport energy replenishment efficiency of aircraft while maintaining their performance has become one of the urgent problems to be solved for electric transport aircraft. Utility Model Content

[0005] To improve the refueling efficiency of aircraft, this application provides a distributed electric aircraft with rapid battery swapping capability.

[0006] This application provides a distributed electric aircraft with rapid battery swapping capability, employing the following technical solution:

[0007] A distributed electric aircraft with rapid battery swapping features multiple electric thrusters distributed along its wings. Multiple detachable partial skins are attached to the wings, each with a mounting base for a battery. Each mounting base includes an upper support plate and a lower support plate. The upper support plate is fixedly connected to the wing rib, while the lower support plate carries the battery. A scissor-telescopic structure connects the upper and lower support plates. The lower support plate is fixedly connected to the partial skins. When the partial skins are fixed to the wing ribs, the battery is held between the upper and lower support plates and is in a working position. The upper support plate also has a connection slot through which the battery supplies power to the motors.

[0008] Optionally, the scissor-type telescopic structure consists of multiple intersecting links; the links are connected by pins to form a telescopic frame structure. This scissor-type telescopic structure is connected between the upper and lower support plates via fixed supports.

[0009] Optionally, the inner sides of both the upper support plate and the lower support plate are provided with grooves for battery insertion, and heat dissipation holes are also provided on the upper support plate and the lower support plate.

[0010] Optionally, the upper support plate, lower support plate, and partial skin are all connected to the wing ribs via connecting beams; both ends of the connecting beams are fixedly connected to the wing ribs with screws, and the upper support plate, lower support plate, and partial skin are detachably connected to the connecting beams with bolts.

[0011] As can be seen from the above, the distributed electric aircraft with rapid battery swapping and its scissor telescopic structure and mounting base assembly provided in this application, through the mounting base design that combines detachable partial skin with scissor telescopic structure, achieves rapid clamping and positioning of the battery on the main wing structure and power connection, solving the technical problem of traditional battery replacement requiring disassembly of fuselage parts and complex operation, and has the advantages of improving battery swapping efficiency, simplifying operation process and ensuring structural stability. Attached Figure Description

[0012] Figure 1 This is a schematic diagram of the wing and internal motor layout of a distributed electric aircraft;

[0013] Figure 2 This is a detailed diagram of the battery mounting location in this application;

[0014] Figure 3 This is an overall structural diagram of the battery installation structure in a distributed electric aircraft with fast battery swapping capability, as described in this application.

[0015] Figure 4 yes Figure 2 The overall structure diagram after some parts of the structure have been hidden;

[0016] Figure 5 This is a schematic diagram of the battery swapping process in this application.

[0017] Explanation of reference numerals in the attached figures:

[0018] 1. Wing ribs; 2. Upper support plate; 21. Connecting slot; 3. Lower support plate; 4. Scissor telescopic structure; 5. Fixed support; 6. Battery; 7. Partial skin; 8. Connecting beam; 9. Heat dissipation holes. Detailed Implementation

[0019] The following is in conjunction with the appendix Figure 1-5 This application will be described in further detail.

[0020] In existing technologies, with the development of aviation technology, distributed electric aircraft with multiple energy sources have gradually become a research hotspot. These aircraft construct their power system by distributing multiple small electric propulsion units along the wings, with the motors and batteries fixed inside the main wing structure. While this design offers advantages in terms of environmental friendliness and low noise, the battery charging time is much longer than traditional refueling time, resulting in low aircraft refueling efficiency. Especially in high-frequency transportation scenarios, the long charging time severely restricts the aircraft's operational efficiency.

[0021] To address the aforementioned issues and the core pain point of low refueling efficiency in electric aircraft, it was found that the traditional fixed battery mounting method (6) leads to difficulties in battery replacement. Analysis revealed that if the battery mounting structure and the wing skin section (7) could be integrated into a detachable module, rapid, complete battery replacement could be achieved. Further considering the integrity of the wing structure, modular assembly and disassembly must be implemented while maintaining aerodynamic shape. Therefore, it is proposed to integrate the battery mounting structure and the skin section (7) into a replaceable unit, and to achieve rapid positioning and fixation of the battery (6) through an adjustable support structure.

[0022] Therefore, this application proposes a wing with multiple electric thrusters distributed on it, and multiple partial skins 7 detachably connected to the wing. Each partial skin 7 has a mounting base for a battery 6. The mounting base includes an upper support plate 2 and a lower support plate 3. The upper support plate 2 is fixedly connected to the wing rib 1, and the lower support plate 3 carries the battery 6. A scissor telescopic structure 4 is provided between the two. The lower support plate 3 is fixedly connected to the partial skins 7. When the partial skins 7 are fixed to the wing rib, the battery 6 is clamped between the upper and lower support plates 3 in a working position. The upper support plate 2 has a connecting slot 21 for the battery 6 to output power to the motor.

[0023] The detachable partial skin 7 refers to the mechanical connection between the partial skin 7 and the wing rib 1, which allows for separation and fixation. Specifically, bolts and locating pins can be used to ensure the aerodynamic shape is maintained before and after assembly / disassembly. The upper support plate 2 of the mounting base is the load-bearing structure fixed to the wing rib 1, and can be made of aluminum alloy profiles to provide a mounting reference surface for the battery 6. The scissor telescopic structure 4 is a telescopic mechanism composed of cross links, which can be made of stainless steel hinged links. The distance between the upper and lower support plates 3 can be changed by adjusting the link angle. The connecting slot 21 is the conductive interface area on the upper support plate 2, which can be formed by copper alloy inserts to create a sliding contact surface, enabling rapid connection between the battery 6 and the motor circuit.

[0024] Specifically, when battery 6 needs to be replaced, the partial skin 7, which integrates the lower support plate 3 and battery 6, is removed by disassembling the connector between the partial skin 7 and the wing rib 1. When the partial skin 7 unit is installed, the scissor-type telescopic structure 4 automatically adjusts the distance between the upper and lower support plates 3, ensuring that battery 6 is precisely embedded in the groove of the upper support plate 2. The electrodes of battery 6 form physical contact with the onboard circuitry through the connecting slot 21, completing power transmission. The rigid connection between the partial skin 7 and the wing rib ensures the stability of the battery 6 module during flight, and the self-locking characteristic of the scissor structure prevents displacement caused by vibration.

[0025] Compared to existing technologies, the traditional solution fixes battery 6 inside the wing cavity, requiring the disassembly of numerous structural components for replacement. This solution, through the integrated design of the partial skin 7 and the battery 6 mounting base, enables the complete replacement of the battery 6 module, reducing operation time to 30% of the original solution. Simultaneously, the scissor-lift structure, while ensuring support rigidity, allows for millimeter-level assembly tolerances in battery 6 installation, improving replacement reliability. The modular design ensures that a single battery 6 failure does not affect the overall system, and specific partial skin 7 units can be replaced during maintenance.

[0026] Through the above technical solutions, this application achieves rapid battery replacement, with a single battery replacement time controlled within five minutes, significantly reducing aircraft ground dwell time. The modular design decouples the battery 6 maintenance unit from the wing aerodynamic shape, ensuring structural strength while avoiding the impact of frequent disassembly and assembly on the sealing of the local skin 7. The adaptive adjustment function of the scissor structure reduces assembly precision requirements and improves the fault tolerance of the replacement operation. The sliding contact design of the connecting slot 21 ensures reliable power transmission and avoids poor contact caused by wear of the connectors.

[0027] This application further proposes a scissor telescopic structure consisting of multiple intersecting links connected by pins to form a telescopic frame structure. The scissor telescopic structure 4 is connected between the upper support plate 2 and the lower support plate 3 by a fixed support 5.

[0028] The scissor-type telescopic structure refers to a telescopic mechanism composed of two or more sets of cross-arranged connecting rods. Specifically, it can be implemented using connecting rods made of aluminum alloy or carbon fiber connected by hinge points. Its function is to adjust the spacing between the support plates by unfolding and retracting the connecting rods. The fixed support 5 is the mounting base used to connect the scissor structure and the support plates. Specifically, it can be a metal block with positioning holes, fixed to the inner surfaces of the upper support plate 2 and the lower support plate 3 by bolts. Its function is to provide a stable support point for the scissor structure and transfer loads.

[0029] Specifically, when battery 6 needs to be replaced, the scissor lift telescopic structure 4 moves the lower support plate 3 vertically via the cross motion of the connecting rod, expanding the clamping space between the lower support plate 3 and the upper support plate 2. At this time, battery 6 can be removed or installed. After the battery replacement is completed, the scissor lift structure retracts the connecting rod to reset the lower support plate 3, re-clamping battery 6 in the predetermined working position. The fixed support 5 ensures the stability of the connection between the scissor lift structure and the support plate through bolt connection, preventing the structure from loosening due to vibration.

[0030] Compared to existing technologies, traditional battery 6 mounting structures often employ fixed brackets, requiring the disassembly of multiple connecting components when replacing battery 6. This solution, however, utilizes a retractable scissor structure to enable rapid adjustment of the support plate spacing, significantly simplifying the battery 6 installation and removal process. Furthermore, the modular design of the fixed support 5 allows for independent maintenance and replacement of the scissor structure, reducing maintenance costs.

[0031] Through the above technical solution, this application achieves rapid installation and removal of the battery 6 from the partial wing skin 7. The switching of the battery 6's clamping state is directly controlled by the telescopic movement of the scissor structure, avoiding the cumbersome operation of disassembling large sections of skin or support plates required in traditional methods, and effectively improving the energy replenishment efficiency of electric aircraft. At the same time, the rigid support characteristics of the scissor structure ensure the stability of the battery 6 during flight, preventing loosening of the connection due to turbulence.

[0032] This application further proposes that the inner sides of both the upper support plate 2 and the lower support plate 3 are provided with grooves for inserting the battery 6, and the upper support plate 2 and the lower support plate 3 are also provided with heat dissipation holes 9.

[0033] Through the above technical solution, this application can reduce the time of manual intervention during the installation of battery 6, and avoid the need for downtime maintenance due to overheating of battery 6, thereby improving the reliability of continuous operation of electric aircraft.

[0034] This application further proposes that the upper support plate 2, the lower support plate 3, and the partial skin 7 are all connected to the wing rib 1 via a connecting beam 8; both ends of the connecting beam 8 are fixedly connected to the wing rib 1 by screws, and the upper support plate 2, the lower support plate 3, and the partial skin 7 are detachably connected to the connecting beam 8 by bolts.

[0035] The connecting beam 8 is a structural component used to support the upper support plate 2, lower support plate 3, and partial skin 7. It can be made of aluminum alloy or carbon fiber composite material and arranged laterally or longitudinally to form a support frame. Its function is to provide stable intermediate support for the battery 6 mounting base and the partial skin 7, avoiding the difficulties in disassembly and assembly caused by a direct rigid connection to the wing main structure. The screw-fixed connection refers to the fastening method between the connecting beam 8 and the wing rib 1, which can be achieved using countersunk screws or flange bolts. Its function is to ensure a rigid connection between the connecting beam 8 and the wing rib 1, maintaining the overall structural stability. The bolt-detachable connection refers to the installation method of the upper support plate 2, lower support plate 3, and partial skin 7 to the connecting beam 8, which can be achieved using threaded fasteners with pre-embedded nuts. Its function is to enable quick disassembly and assembly of the battery 6 mounting base and partial skin 7, facilitating battery 6 replacement or component maintenance.

[0036] Specifically, the connecting beam 8 is pre-fixed to a predetermined position on the wing rib 1, forming a modular installation interface. The upper support plate 2, lower support plate 3, and partial skin 7 are bolted to the corresponding holes on the connecting beam 8. After the battery 6 is installed, the partial skin 7 covers the exterior and forms a complete aerodynamic shape with the large-area fixed skin of the wing. When the battery 6 needs to be replaced, only the bolts between the partial skin 7 and the lower support plate 3 need to be removed to remove the battery 6 from the mounting base, while the connecting beam 8 remains fixed to the wing rib 1. This design allows the battery 6 to be replaced without damaging the main wing structure, while reducing the impact of disassembly and assembly operations on aerodynamic performance.

[0037] Compared to existing technologies, the battery 6 mounting structure of current electric aircraft is typically fixed to the wing rib 1 by direct welding or riveting, resulting in the need to disassemble numerous structural components and a lengthy process for battery 6 replacement. This solution uses a connecting beam 8 as an intermediate transition structure, forming an independent module between the battery 6 mounting base and the partial skin 7. This significantly shortens the disassembly and assembly steps while ensuring structural strength. Furthermore, the pre-fixed design of the connecting beam 8 avoids wear on the wing rib 1 caused by repeated disassembly and assembly, extending the equipment's service life.

[0038] Through the above technical solution, this application achieves rapid separation of the battery 6 mounting base from the partial skin 7, enabling battery 6 replacement operations to be performed without disassembling the main wing structure, effectively shortening the refueling time of the electric aircraft. The modular design of the connecting beam 8 reduces maintenance complexity while maintaining the integrity of the wing's aerodynamic shape, avoiding the risk of structural deformation caused by frequent disassembly and reassembly.

[0039] The above are all preferred embodiments of this application, and are not intended to limit the scope of protection of this application. Therefore, all equivalent changes made in accordance with the structure, shape and principle of this application should be covered within the scope of protection of this application.

Claims

1. A distributed electric aircraft capable of rapid battery swapping, comprising multiple electric thrusters distributed along its wings, characterized in that: The wing has multiple detachable partial skins, each with a mounting base for mounting batteries. Each mounting base includes an upper support plate and a lower support plate. The upper support plate is fixedly connected to the wing rib, and the lower support plate carries the battery. A scissor-telescopic structure connects the upper and lower support plates. The lower support plate is fixedly connected to the partial skins. When the partial skins are fixed to the wing rib, the battery is held between the upper and lower support plates and is in the working position. The upper support plate also has a connection slot through which the battery outputs power to the motor.

2. The distributed electric aircraft with rapid battery swapping capability according to claim 1, characterized in that: The scissor lift telescopic structure consists of multiple intersecting links; the links are connected by pins to form a telescopic frame structure, and the scissor lift telescopic structure is connected between the upper support plate and the lower support plate by fixed supports.

3. A distributed electric aircraft with rapid battery swapping capability according to claim 1, characterized in that: The upper support plate and the lower support plate both have grooves on their inner sides for inserting batteries, and heat dissipation holes are also provided on the upper support plate and the lower support plate.

4. A distributed electric aircraft with rapid battery swapping capability according to claim 1, characterized in that: The upper support plate, lower support plate, and partial skin are all connected to the wing ribs via connecting beams; both ends of the connecting beams are fixedly connected to the wing ribs with screws, and the upper support plate, lower support plate, and partial skin are detachably connected to the connecting beams with bolts.

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