Quick folding mechanism of eVTOL pontoon landing gear and water aircraft

Abstract

The present application belongs to the technical field of water eVTOL aircraft landing gear, and particularly relates to an eVTOL pontoon landing gear integrated quick folding mechanism and a water aircraft. The folding mechanism comprises a landing gear fixed base, a folding drive assembly, a synchronous link folding assembly, a landing gear main body and a locking and limiting assembly. The folding drive assembly drives the synchronous movement of the stacked link units. The landing gear main body is formed into a closed pontoon by relying on a rigid skeleton and wrapping a flexible skin. The pontoon inflation and deflation linkage system cooperates with the timing of the link retraction and extension. The locking and limiting assembly realizes work station locking and communicates with the aircraft flight control. The present application realizes the integration of the pontoon and the landing gear, has low aerodynamic resistance in the storage state, is stable and synchronous in retraction and extension, can adapt to amphibious landing conditions, and improves the endurance of the aircraft and the reliability of operation in complex water environments.

Description

Technical Field

[0001] This invention belongs to the field of landing gear technology for eVTOL seaplanes, specifically relating to an integrated quick-folding mechanism for eVTOL float landing gear and a seaplane. Background Technology

[0002] Current eVTOL (eVehicle-to-Land) aircraft generally adopt a split-structure design, where independent buoyancy floats and fixed / simple folding landing gear are arranged separately, which has many technical drawbacks. First, traditional floats are mostly fixed extended structures, with a large lateral windward area in flight, resulting in high aerodynamic drag and significantly increasing the aircraft's cruise energy consumption and reducing its range. Second, the split structure has a large number of components, complex piping and wiring, and a large overall weight, which does not meet the design requirements for lightweight aircraft. Third, conventional folding landing gear often uses multiple motors for independent drive and has a complex articulated structure, resulting in large multi-axis synchronization errors, stuttering during retraction and deployment, and attitude deviation. In addition, it has poor waterproof, corrosion-resistant, and water accumulation-resistant performance in waterborne operating environments, leading to a high failure rate. Fourth, the stability of the floats and landing gear in the deployed state is poor. Impact loads from water landing and uneven buoyancy loads on the water surface can easily lead to structural deformation. During high-speed flight, the extended structure is prone to airflow turbulence and resonance hazards. At the same time, the entire aircraft occupies a large space for parking, and has low convenience for transportation and storage. Summary of the Invention

[0003] To overcome the shortcomings of existing technologies, this invention provides an integrated quick-folding mechanism for eVTOL floats and landing gear, as well as a seaborne eVTOL aircraft with this integrated quick-folding mechanism. This addresses the technical pain points of existing separate designs for eVTOL floats and landing gear, such as high drag, structural redundancy, poor folding synchronization, and low reliability. The invention provides an integrated quick-folding mechanism for eVTOL floats and landing gear, achieving integrated buoyancy support, takeoff and landing support, and quick-folding storage, while also ensuring stability during takeoff and landing on water, low wind resistance during flight, lightweight structure, and high environmental adaptability.

[0004] One aspect of the present invention provides an integrated quick-folding mechanism for eVTOL float landing gear, including a landing gear fixing base, a folding drive assembly, a synchronous linkage folding assembly, a landing gear body, and a locking and limiting assembly; The landing gear mounting base is fixedly assembled to the bottom of the eVTOL fuselage; The folding drive assembly is located at the bottom of the landing gear mounting base; The lower end of the synchronous linkage folding assembly is hinged to the landing gear fixed base, and the upper end is hinged to the output end of the folding drive assembly; The main body of the landing gear is fixedly installed on the outer end of the synchronous link folding assembly; The locking and limiting components are located at the mating positions of the landing gear fixed base and the folding drive component, corresponding to the fully unfolded and fully folded storage positions of the mechanism, respectively.

[0005] Furthermore, this application also proposes that the folding drive assembly includes a linear drive motor, a vertical guide slide, and a sliding slider; The vertical guide slide is vertically fixed to the lower end face of the landing gear fixed base, and the sliding block is slidably sleeved on the outside of the vertical guide slide. The linear drive motor is fixedly installed at the bottom of the landing gear mounting base, and its telescopic output end is rigidly connected to the sliding block.

[0006] Furthermore, this application also proposes that the synchronous linkage folding assembly includes four layers of linkage units, which are stacked one on top of the other and share a sliding slider as the active drive end.

[0007] Furthermore, this application also proposes that the outer surface of the synchronous link folding assembly is covered with a flexible skin, and the landing gear body, the synchronous link folding assembly and the flexible skin constitute a float with a sealed cavity; The bottom of the flexible skin is equipped with a non-slip and wear-resistant take-off and landing support surface, and the sidewalls of the flexible skin are arc-shaped guide surfaces.

[0008] Furthermore, this application also proposes that the synchronous linkage folding assembly unfolds to form a rigid load-bearing frame, with the inner side of the flexible skin fitting against the outer side of the rigid load-bearing frame.

[0009] Furthermore, this application also proposes that it includes a float inflation / deflation linkage system, wherein the air path of the float inflation / deflation linkage system is connected to the sealed cavity, and its control timing is synchronously matched with the motion timing of the synchronous linkage folding assembly.

[0010] Furthermore, this application also proposes that the locking and limiting component is an electromagnetic pin-type locking structure, which is electrically connected to the aircraft flight control system.

[0011] Furthermore, this application also proposes that the linear drive motor is a waterproof ball screw linear motor, and the outer side of the motor body is covered with a waterproof sealing potting layer; The vertical guide slide is made of chrome-plated stainless steel, and the sliding slider is equipped with a self-lubricating wear-resistant bushing. The hinge joint of the synchronous linkage folding assembly has a pre-drainage gap.

[0012] Furthermore, this application also proposes that the landing gear mounting base is a one-piece machined structure of aviation aluminum alloy, with reserved standard mounting holes on the fuselage.

[0013] Furthermore, this application also proposes an integrated quick-folding mechanism for the fuselage and two sets of eVTOL float landing gear; Two sets of eVTOL float landing gear integrated quick-folding mechanisms are symmetrically arranged on both sides of the bottom of the fuselage, and each folding mechanism is an independent unit structure.

[0014] The present invention provides an eVTOL float landing gear integrated quick-folding mechanism and a seaplane, comprising a landing gear fixing base, a folding drive assembly, a synchronous linkage folding assembly, a landing gear body, and a locking and limiting assembly. The landing gear fixing base is fixedly mounted on the bottom of the eVTOL fuselage; the folding drive assembly is located at the bottom of the landing gear fixing base; the lower end of the synchronous linkage folding assembly is hinged to the landing gear fixing base, and the upper end is hinged to the output end of the folding drive assembly; the landing gear body is fixedly installed on the outer end of the synchronous linkage folding assembly; the locking and limiting assembly is located at the mating position between the landing gear fixing base and the folding drive assembly, corresponding to the fully deployed position and the fully folded storage position, respectively. By integrating the float and landing gear into one unit and adopting a synchronous linkage folding mechanism, rapid storage in flight is achieved to reduce the windward cross section, while ensuring structural rigidity and uniform load distribution during water landing. This effectively solves the problems of high aerodynamic drag, asynchronous movement, and unstable connection interface caused by traditional split designs, and has comprehensive advantages such as reducing flight energy consumption, improving operational reliability, and extending equipment service life. Attached Figure Description

[0015] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on the structures shown in these drawings without creative effort.

[0016] Figure 1 A schematic diagram showing the fully unfolded structure of the present invention; Figure 2 This invention represents Figure 1 Enlarged structural diagram at point A; Figure 3 A schematic diagram showing the folding drive assembly of the present invention; Figure 4 This is a schematic diagram illustrating the fully foldable and retractable structure of the present invention.

[0017] The symbols in the attached image are explained as follows: 1-Landing gear mounting base; 2-Folding drive assembly; 3-Synchronous linkage folding assembly; 4-Landing gear body; 5-Locking limit assembly; 21-Linear drive motor; 22- Slide the slider; 6- Flexible skin. Detailed Implementation

[0018] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present invention.

[0019] Please refer to Figures 1-4 This application proposes an eVTOL float landing gear integrated quick folding mechanism, including a landing gear fixing base 1, a folding drive assembly 2, a synchronous linkage folding assembly 3, a landing gear body 4, and a locking and limiting assembly 5; Landing gear mounting base 1 is fixedly mounted on the bottom of the eVTOL fuselage; The folding drive assembly 2 is located at the bottom of the landing gear mounting base 1; The lower end of the synchronous linkage folding assembly 3 is hinged to the landing gear fixed base 1, and the upper end is hinged to the output end of the folding drive assembly 2; The landing gear body 4 is fixedly installed on the outer end of the synchronous link folding assembly 3; The locking and limiting component 5 is located at the mating position between the landing gear fixed base 1 and the folding drive component 2, corresponding to the fully unfolded position and the fully folded storage position of the mechanism, respectively.

[0020] To facilitate understanding of the technical solution in this embodiment, some key terms involved are explained below: The eVTOL (eVTOL) float-landing gear integrated quick-folding mechanism is an integrated structure designed specifically for electric vertical takeoff and landing aircraft. It integrates the functions of floats and landing gear and has the ability to be quickly folded and deployed. It provides water takeoff and landing capabilities while achieving compact storage during flight or parking to optimize aerodynamic performance and space utilization.

[0021] The landing gear mounting base 1 is a structural component used to securely connect the entire folding mechanism to the bottom of the eVTOL aircraft fuselage. Its function is to provide a stable mounting interface and load-bearing support, ensuring the reliability of the mechanism under various operating conditions.

[0022] The folding drive assembly 2 refers to the actuator responsible for providing power to drive the entire float landing gear mechanism in folding or unfolding motion. The assembly typically includes a power source and a transmission mechanism, enabling precise position control of the mechanism.

[0023] The synchronous linkage folding assembly 3 refers to a structure that achieves synchronous and coordinated movement of the landing gear body 4 through a series of linkage mechanisms. Under the action of driving force, the assembly can smoothly transition the landing gear body 4 from the unfolded state to the folded state, or vice versa, and ensure attitude stability during movement.

[0024] The landing gear body 4 refers to the structure that directly contacts the ground or water surface and provides support. In eVTOL applications on water, the synchronous linkage folding assembly 3, when unfolded, functions as a float in conjunction with its surface skin to provide buoyancy on the water surface.

[0025] The locking and limiting component 5 is a device used to lock the synchronous linkage folding component 3 in a predetermined position when the mechanism is fully extended or fully folded and stored, preventing accidental movement. This component ensures the structural stability and safety of the mechanism during flight or parking.

[0026] The fully extended position refers to the position where the synchronous linkage folding assembly 3 is in a fully extended state, ready for water surface take-off and landing operations or to provide water surface support.

[0027] A fully foldable storage station refers to a location where the synchronous linkage folding assembly 3 is in a fully retracted state to minimize space occupation and aerodynamic drag, facilitating flight, transportation, or storage.

[0028] This embodiment provides an integrated quick-folding mechanism for eVTOL float landing gear, the structural design of which aims to achieve efficient and stable take-off, landing and storage functions.

[0029] Specifically, the mechanism includes a landing gear mounting base 1, a folding drive assembly 2, a synchronous linkage folding assembly 3, a landing gear body 4, and a locking and limiting assembly 5. These components work together to form a complete folding system. For example, the landing gear mounting base 1 can be a simple metal plate or frame structure to provide a mounting interface; the folding drive assembly 2 can be a hydraulic cylinder or a pneumatic cylinder to provide linear or rotary motion; the synchronous linkage folding assembly 3 can be composed of multiple linkages connected by pins to realize the movement of the landing gear body 4; the landing gear body 4 can be a simple support rod or a box with buoyancy function; and the locking and limiting assembly 5 can be a mechanical latch or a simple limiting pin.

[0030] The landing gear mounting base 1 is designed to be fixedly assembled to the bottom of the eVTOL fuselage via the landing gear body 4. Its installation can employ conventional mechanical connection methods such as bolting, riveting, or welding to ensure a secure bond between the base and the fuselage. The base can be made of high-strength steel or composite materials to withstand the loads during takeoff and landing.

[0031] The folding drive assembly 2 is mounted on the bottom of the landing gear mounting base 1. The drive assembly can be a rotary motor with a gear transmission mechanism, or a lead screw drive mechanism whose output shaft or push rod can generate the required movement. The drive assembly is mounted at the bottom of the base to facilitate connection with the synchronous linkage folding assembly 3 and to provide driving force for the entire mechanism.

[0032] The lower end of the synchronous linkage folding assembly 3 is hinged to the landing gear fixed base 1, and the upper end is hinged to the output end of the folding drive assembly 2. This hinged connection allows the synchronous linkage folding assembly 3 to rotate or translate under the action of driving force. For example, the lower end can be connected to the lug on the fixed base by a pin, and the upper end can be connected to the push rod or rocker arm of the drive assembly by another pin.

[0033] The landing gear body 4 is fixedly mounted to the outer end of the synchronous link folding assembly 3. The connection between the landing gear body 4 and the synchronous link folding assembly 3 can be achieved by bolting, welding, or integral molding, ensuring a rigid connection between the two. The synchronous link folding assembly 3 provides support and buoyancy in its deployed state, and is stowed in a compact position in its folded state. For example, the synchronous link folding assembly 3 may be covered with a lightweight skin to provide some buoyancy.

[0034] The locking and limiting component 5 is positioned at the mating point between the landing gear fixed base 1 and the folding drive component 2, corresponding to the fully deployed and fully folded storage positions of the mechanism, respectively. The component's function is to provide mechanical locking or position restriction when the mechanism reaches the preset deployed or folded position. For example, a simple spring pin can be used; when the mechanism moves to the designated position, the spring pin automatically inserts into a hole on the fixed base or drive component, thereby achieving locking. When unlocking is required, the pin can be pulled out manually or electrically.

[0035] Therefore, the eVTOL float landing gear integrated quick-folding mechanism of this embodiment effectively solves the problems of high aerodynamic drag, high energy consumption, complex structure, and excessive weight caused by traditional split structures by integrating the functions of the float and landing gear into one design and adopting a synchronous linkage folding mechanism. The mechanism can achieve compact storage in flight, significantly reducing the lateral windward area, thereby reducing aerodynamic drag and optimizing the aircraft's cruise energy consumption and range. At the same time, the integrated design reduces the number of parts and piping, contributing to the aircraft's lightweight design. Its synchronous linkage folding assembly 3 ensures the smoothness and synchronization of the deployment and folding process, avoiding multi-axis synchronization errors, deployment / folding jams, and attitude deviations. Furthermore, the locking and limiting assembly 5 enhances the overall stability of the mechanism by locking it at the deployment and folding positions, effectively coping with water landing impact loads and water surface buoyancy loads, and reducing the risk of airflow turbulence and resonance during high-speed flight. The mechanism's quick-folding and storage characteristics also significantly reduce the space occupied during parking, improving the convenience of transportation and storage.

[0036] This application further proposes the specific structure of the folding drive assembly 2, which includes a linear drive motor 21, a vertical guide slide bar, and a sliding slider 22.

[0037] The linear drive motor 21 is an actuator capable of directly generating linear motion without the need for an additional rotary-to-linear conversion device, thus simplifying the drive chain. Its working principle typically involves converting electrical energy into linear mechanical energy through electromagnetic action to achieve push-pull or reciprocating motion. For example, it can be a motor with a built-in lead screw or ball screw mechanism, where the motor rotation drives the nut of the lead screw or ball screw to perform linear displacement, or it can directly drive the mover to move linearly along the stator via electromagnetic force. The linear drive motor 21 is fixedly mounted on the bottom of the landing gear mounting base 1, and its telescopic output end is rigidly connected to the sliding block 22, thereby directly transmitting the linear driving force of the motor to the sliding block 22.

[0038] The vertical guide rod is vertically fixed to the lower end face of the landing gear base 1, serving as a constraint on the motion trajectory of the sliding slider 22. The guide rod is typically a rod or guide rail with high rigidity and wear resistance. Its function is to ensure that the sliding slider 22 can move precisely in a predetermined vertical direction when driven by force, effectively suppressing lateral sway and deflection, thereby ensuring the motion accuracy and stability of the entire folding mechanism.

[0039] The sliding slider 22 is slidably sleeved on the outside of the vertical guide rod and is a key component connecting the output end of the linear drive motor 21 and the synchronous linkage folding assembly 3. The sliding slider 22 typically contains a sliding bearing, ball bearing, or guide bushing to reduce friction with the vertical guide rod and ensure smooth movement. Through the precise sliding of the sliding slider 22 on the vertical guide rod, the linear displacement generated by the linear drive motor 21 is stably and reliably transmitted to the synchronous linkage folding assembly 3, serving as its active drive end.

[0040] Through the above technical solution, the folding drive assembly 2 is concretized into a structure consisting of a linear drive motor 21, a vertical guide slide bar, and a sliding slider 22, achieving precise linear drive of the synchronous linkage folding assembly 3. The linear drive motor 21 directly provides linear displacement, avoiding complex transmission mechanisms and making the entire drive system more compact and efficient. The vertical guide slide bar provides a stable vertical motion trajectory for the sliding slider 22, effectively preventing swaying and jittering during movement, ensuring the motion accuracy and reliability of the folding mechanism. As an intermediate link in force transmission, the sliding slider 22 smoothly transmits the driving force of the motor to the synchronous linkage folding assembly 3, thereby ensuring the smoothness and synchronization of the landing gear during folding and unfolding. This design not only solves the problems of insufficient accuracy and complex structure that may exist in traditional drive methods, but also improves the overall integration, response speed, and operational stability of the mechanism, providing a solid foundation for the rapid and reliable folding of the eVTOL float landing gear.

[0041] This application further proposes a synchronous linkage folding assembly 3, which includes four layers of linkage units, arranged in a stacked manner, and sharing a sliding slider 22 as the active drive end.

[0042] Specifically, the synchronous linkage folding assembly 3 does not employ a single parallel four-bar structure, but rather consists of four independent linkage units. Each linkage unit is connected by rods and hinges, ensuring the stability of the landing gear body 4 during retraction and extension. These four linkage units are not arranged side-by-side, but rather stacked vertically. By tightly integrating the multi-layered linkage structure, a more robust box-shaped or truss-shaped structure is formed, effectively distributing and transferring loads. Simultaneously, the sliding slider 22 in the aforementioned folding drive assembly 2, acting as the motion input end, simultaneously drives these four linkage units to move synchronously. Through its own linear displacement, the sliding slider 22 drives the upper hinge points of all stacked linkage units to move synchronously, thereby achieving the coordinated folding or unfolding of the entire synchronous linkage folding assembly 3.

[0043] Through the above technical solution, the synchronous linkage folding assembly 3 is designed as a four-layer linkage unit stacked vertically, sharing a common sliding slider 22 as the active drive end, which significantly enhances the structural rigidity and load-bearing capacity of the entire folding mechanism. This multi-layer stacked structure can effectively resist bending and torsional loads from different directions, ensuring that the landing gear maintains excellent structural stability when subjected to the eVTOL's own weight, takeoff and landing impacts, and complex stresses during water landing, avoiding deformation or swaying problems that may occur with a single linkage structure. At the same time, sharing the sliding slider 22 as the active drive end ensures that the movement of the four-layer linkage unit is highly synchronized and coordinated, simplifies drive control, and improves the smoothness and reliability of the mechanism's operation, thereby effectively improving the overall safety and service life of the eVTOL float landing gear.

[0044] This application further proposes that the outer surface of the synchronous link folding assembly 3 is covered with a flexible skin 6, and the landing gear body 4, the synchronous link folding assembly 3 and the flexible skin 6 constitute a float with a sealed cavity; the bottom of the flexible skin 6 is provided with an anti-slip and wear-resistant take-off and landing support surface, and the side wall of the flexible skin 6 is an arc-shaped guide surface.

[0045] Specifically, the outer surface of the synchronous link folding assembly 3 is covered with a flexible skin 6, forming a float with a sealed cavity. The flexible skin 6 is the core component for realizing the float's function, and its material is typically a high-molecular material with good waterproofness, wear resistance, tear resistance, and a certain degree of elasticity, such as polyurethane-coated fabric, neoprene rubber, or PVC composite material. The flexible skin 6 seals the outer surface of the synchronous link folding assembly 3, forming one or more independent sealed cavities. When the cavity is inflated, a float structure with sufficient buoyancy is formed. This flexible design not only provides buoyancy but also provides a certain degree of cushioning upon contact with the water surface, reducing the impact on the aircraft.

[0046] The bottom of the flexible skin 6 is provided with an anti-slip and wear-resistant take-off and landing support surface. The support surface is the area of ​​the flexible skin 6 in contact with the ground or water surface, and its design aims to enhance the wear resistance of the bottom of the flexible skin 6 to cope with the friction and impact of various complex ground surfaces. The support surface can be achieved by embedding high-strength fibers in the flexible skin 6 material, increasing surface texture, or coating with a wear-resistant coating, to ensure reliability and durability under frequent take-off and landing operations.

[0047] The flexible skin 6 has arc-shaped guide surfaces on its sidewalls. This arc-shaped guide surface design primarily considers the interaction between the eVTOL and water during gliding or takeoff and landing. By employing a streamlined arc design, water resistance is effectively reduced, water splash is minimized, thereby improving the efficiency and stability of gliding on the water and reducing energy consumption. This design is similar to the shape of a ship's hull or the floats of a seaplane, aiming to optimize hydrodynamic performance.

[0048] Through the aforementioned technical solution, the landing gear body 4, the synchronous linkage folding assembly 3, and the externally covering flexible skin 6 together constitute a float with a sealed cavity, providing the necessary buoyancy support and cushioning capacity for eVTOL takeoff and landing on water, effectively solving the problems of insufficient buoyancy and high impact force of traditional landing gear when operating on water. Simultaneously, the anti-slip and wear-resistant takeoff and landing support surface at the bottom of the flexible skin 6 enhances the landing gear's grip and durability during land takeoff and landing, effectively extending its service life. Furthermore, the arc-shaped guide surface design of the flexible skin 6's sidewalls significantly reduces the eVTOL's fluid resistance during water taxiing, improving water maneuverability and energy utilization. Overall, the structure enables the eVTOL float-landing gear integrated mechanism to efficiently and safely adapt to both land and water takeoff and landing environments, greatly expanding the aircraft's application scenarios and mission capabilities.

[0049] This application further proposes that the aforementioned synchronous link folding assembly 3 unfolds to form a rigid load-bearing frame, and the inner side of the flexible skin 6 is fitted with the outer side of the rigid load-bearing frame.

[0050] Specifically, the rigid load-bearing frame is a structural support component inside the pontoon, and its main function is to provide structural stiffness, load-bearing capacity and shape stability.

[0051] Through the above technical solutions, the rigid load-bearing frame provides solid internal support for the flexible skin 6, significantly enhancing the overall structural strength and deformation resistance of the pontoon. This ensures that takeoff and landing loads can be efficiently and reliably transferred from the pontoon to the folding mechanism and fuselage, avoiding structural failure that might occur if the flexible skin 6 were to bear the load alone. Simultaneously, the close fit between the inner side of the flexible skin 6 and the outer side of the rigid load-bearing frame allows the pontoon to maintain a stable geometric shape when subjected to external impacts or internal inflation pressure, effectively dispersing stress and thus improving the reliability and durability of the pontoon during takeoff and landing, mooring, and in complex environments.

[0052] This application further proposes the above-mentioned eVTOL float landing gear integrated quick folding mechanism, which also includes a float inflation / deflation linkage system. The air passage of the float inflation / deflation linkage system is connected to the sealed cavity, and its control timing is synchronously matched with the motion timing of the synchronous linkage folding assembly 3.

[0053] Specifically, the float inflation / deflation linkage system is an integrated pneumatic control unit whose main function is to precisely control the inflation and deflation process of the sealed cavity inside the float according to preset logic or received instructions. The system typically consists of one or more air pumps (or connected to an external high-pressure air source), a series of solenoid valves, pressure sensors, and a microcontroller. The air pumps are responsible for injecting gas into the sealed cavity to achieve inflation, the solenoid valves control the gas inlet and outlet paths, and the pressure sensors monitor the air pressure inside the cavity in real time and feed the data back to the microcontroller. The microcontroller coordinates the operation of the entire system based on this information and the preset program. The system is designed to ensure that the float can quickly and accurately adjust its internal pressure and volume under different operating conditions.

[0054] The air passage of the float inflation / deflation linkage system is connected to the sealed cavity, meaning that the system establishes a reliable connection with the sealed cavity inside the landing gear body 4 through dedicated air passage pipes. These air passage pipes are typically made of pressure-resistant and corrosion-resistant flexible or rigid materials, and are tightly connected to the air inlet and outlet ports on the flexible skin 6 through sealed joints to ensure that no gas leakage occurs during inflation / deflation. This connection method is the foundation for realizing the float inflation / deflation function, providing a physical channel for the efficient flow of gas between the inflation / deflation linkage system and the sealed cavity.

[0055] Furthermore, the control timing of the float inflation / deflation linkage system is synchronized with the motion timing of the synchronous linkage folding assembly 3. This means that the inflation or deflation of the float is not independent, but closely coordinated with the mechanical folding or unfolding process of the landing gear. For example, when the aircraft is preparing to land on the water, the synchronous linkage folding assembly 3 begins to unfold, and the float inflation / deflation linkage system synchronously starts the inflation program, ensuring that the float reaches the preset inflation state when the landing gear is fully unfolded, providing sufficient buoyancy. Conversely, when the landing gear needs to be folded and stored, the inflation / deflation linkage system synchronously starts the deflation program, ensuring that the float is deflated before or during the retraction of the synchronous linkage folding assembly 3, thereby reducing the volume and rigidity of the float and avoiding interference with the folding mechanism. This synchronized control logic is typically implemented by the aircraft's flight control system or a dedicated landing gear control unit, which monitors the motion state of the synchronous linkage folding assembly 3 through sensors and sends corresponding control commands to the inflation / deflation linkage system.

[0056] Through the above technical solution, this application can effectively solve the adaptability problem of the pontoon under different operating conditions. During takeoff and landing on the water surface, the pontoon inflation linkage system ensures that the pontoon is rapidly inflated when the landing gear is deployed, providing sufficient buoyancy support and structural rigidity, thereby ensuring the stability and safety of the eVTOL during mooring and takeoff and landing on the water surface. When the landing gear is folded and stored, the pontoon inflation and deflation linkage system simultaneously deflates the pontoon, reducing the volume of the flexible skin 6 and lowering the internal pressure. This not only significantly reduces the driving load of the synchronous linkage folding assembly 3 during the folding process, avoiding folding interference or mechanism damage that may be caused by excessive pontoon rigidity, but also improves the operating efficiency and reliability of the folding mechanism. At the same time, the smaller volume of the deflated pontoon facilitates the compact storage of the landing gear, effectively saving fuselage space. In addition, this intelligent synchronous control also reduces wear on the flexible skin 6 and related seals, helping to extend the service life of the entire system and improving the system's automation and intelligence level.

[0057] This application further proposes that the locking and limiting component 5 is an electromagnetic pin-type locking structure and is electrically connected to the aircraft flight control system.

[0058] Specifically, the electromagnetic pin-type locking mechanism is a mechanism that uses electromagnetic force to drive a pin for locking and unlocking. Its core components typically include an electromagnetic coil, a movable iron core (or plunger), and a pin. When the electromagnetic coil is energized, it generates a magnetic field that attracts the movable iron core, thereby causing the pin to extend or retract, thus locking or unlocking the landing gear folding mechanism. This structure offers advantages such as fast response, precise control, and compact design. The pin is usually made of high-strength materials to ensure it can withstand the loads generated by the landing gear during takeoff, landing, or flight when locked. To improve reliability, a fail-safe mechanism that automatically locks or unlocks upon power loss can be designed, for example, through spring preload.

[0059] Simultaneously, the electrical connection with the aircraft's flight control system refers to the establishment of a communication and control relationship between the electromagnetic pin-type locking structure of the locking limit assembly 5 and the eVTOL flight control system via electrical circuits. This connection typically includes power lines, control signal lines, and status feedback lines. The flight control system can send commands to the locking limit assembly 5 to control it to perform locking or unlocking operations based on flight mode, takeoff and landing commands, or fault diagnosis results. The locking limit assembly 5 can also provide real-time feedback of its own locking / unlocking status (e.g., by detecting the pin position through a built-in limit switch or Hall sensor) to the flight control system for status monitoring, logic judgment, and safety interlocking.

[0060] By employing the aforementioned technical solution, the locking and limiting component 5 is designed as an electromagnetic pin-type locking structure and electrically connected to the aircraft's flight control system. This application significantly improves the safety, reliability, and automation level of the eVTOL float landing gear integrated quick-folding mechanism. The electromagnetic pin-type locking structure, with its rapid response and precise control characteristics, ensures that the landing gear can be quickly and reliably locked in its fully deployed and fully folded positions, effectively preventing safety risks caused by accidental unlocking during flight or takeoff and landing. Simultaneously, its electrical connection to the aircraft's flight control system allows the pilot or autopilot system to monitor the locking status in real time and precisely control the locking mechanism's actions according to flight mission requirements. For example, before takeoff, the flight control system can automatically detect whether the landing gear is fully locked in the deployed position; during flight, it can ensure that the landing gear remains folded and locked; before landing, the flight control system can instruct the landing gear to unlock and deploy. This deep integration not only improves operational convenience and automation, but more importantly, through the intelligent judgment and interlocking mechanism of the flight control system, it effectively avoids accidental landing gear retraction or extension caused by human error or system malfunction, thereby greatly enhancing the flight safety of eVTOL. Furthermore, the electromagnetic pin-type locking structure typically has a long service life and low maintenance requirements, further improving the overall reliability of the mechanism.

[0061] In some embodiments described above in this application, a folding drive assembly 2, consisting of a linear drive motor 21, a vertical guide slide, and a sliding block 22, is proposed to drive the folding and unfolding of the float landing gear. However, considering that the working environment of the eVTOL float landing gear may involve water surface takeoff and landing or high humidity environments, the hinge joints of the traditional drive motor, guide slide, sliding block 22, and synchronous linkage folding assembly 3 are prone to moisture erosion, corrosion, and wear during long-term use, thereby affecting the reliability, service life, and motion accuracy of the mechanism, and even leading to functional failure.

[0062] In response, this application further proposes optimizations to the aforementioned folding drive assembly 2 and synchronous linkage folding assembly 3, specifically including: The linear drive motor 21 is designed as a waterproof ball screw linear motor, with its main body covered by a waterproof sealing potting layer. A waterproof ball screw linear motor is an actuator that efficiently converts rotary motion into linear motion, and its internal ball screw structure features high precision and efficiency. The emphasis on the "waterproof" design and external waterproof sealing potting layer indicates that special waterproofing measures have been taken in the design and manufacturing of the motor. The waterproof sealing potting layer typically uses high-molecular polymer materials, such as epoxy resin or silicone. Its dense protective layer effectively isolates external moisture, humidity, and dust, preventing water vapor from entering the motor and causing short circuits, corrosion, or mechanical failures. This significantly improves the motor's durability and reliability in harsh environments such as humid, wet, or even temporarily submerged conditions.

[0063] The vertical guide slide is made of chrome-plated stainless steel. Stainless steel itself has good corrosion resistance, while the chrome layer applied to its surface through electroplating further enhances the surface hardness, wear resistance, and corrosion resistance in corrosive environments such as salt spray and humidity. This ensures that the vertical guide slide is not prone to rust or wear during long-term use in water or high humidity, providing a stable and low-friction guiding path for the sliding block 22, and guaranteeing the long-term reliable operation of the mechanism.

[0064] The sliding slider 22 is internally fitted with a self-lubricating wear-resistant bushing. The bushing is typically made of composite materials (such as PTFE, POM, UHMW-PE, etc.) or metal-based materials containing solid lubricants. It can release lubricant itself during friction or has an extremely low coefficient of friction, thereby significantly reducing the frictional resistance between the sliding slider 22 and the vertical guide rod, and reducing wear. This self-lubricating characteristic avoids the problem of traditional lubricants being washed away by water, ensuring that the sliding slider 22 can maintain smooth and stable sliding motion in water or humid environments without external oil supply, extending the service life of the component and reducing maintenance requirements.

[0065] Furthermore, the hinge joint of the synchronous linkage folding assembly 3 is equipped with drainage gaps. These drainage gaps are tiny gaps, holes, or channels intentionally left or formed in the structural design. Their function is to allow water to drain naturally when it enters the hinge joint, preventing water from accumulating inside. This effectively prevents corrosion, freezing (in low-temperature environments), or movement sluggishness caused by water film resistance in critical components such as internal bearings and pins due to long-term water accumulation, ensuring that the synchronous linkage folding assembly 3 can maintain flexible and precise folding movement even in humid or water-filled environments.

[0066] Through the above technical solutions, a waterproof ball screw linear motor is adopted, and its main body is covered with a waterproof sealing and potting layer, effectively isolating the motor from moisture corrosion and ensuring the stable operation and long service life of the linear drive motor 21 in humid or water-filled environments. The chrome-plated stainless steel vertical guide rod significantly improves its corrosion resistance and surface hardness. Combined with the self-lubricating wear-resistant bushing embedded inside the sliding slider 22, frictional resistance is greatly reduced, wear is minimized, and the sliding slider 22 can still move smoothly and accurately along the guide rod in harsh environments, avoiding jamming and corrosion. Furthermore, the hinge joint of the synchronous linkage folding assembly 3 has a pre-reserved drainage gap, effectively preventing water accumulation inside the joint, thereby avoiding corrosion and movement obstruction of internal components and ensuring the reliability and smoothness of the entire folding mechanism under water take-off and landing or high humidity conditions. These improvements collectively enhance the adaptability, reliability, and maintenance convenience of the eVTOL float landing gear integrated quick-folding mechanism in complex environments.

[0067] The above description is merely a preferred embodiment of the present invention and does not limit the patent scope of the present invention. Any equivalent structural transformations made using the contents of the present invention's specification and drawings under the inventive concept of the present invention, or direct / indirect applications in other related technical fields, are included within the patent protection scope of the present invention.

Claims

1. A quick-folding mechanism for an eVTOL float landing gear, characterized in that, It includes a landing gear mounting base, a folding drive assembly, a synchronous linkage folding assembly, the landing gear body, and a locking and limiting assembly; The landing gear mounting base is fixedly assembled to the bottom of the eVTOL fuselage; The folding drive assembly is located at the bottom of the landing gear mounting base; The lower end of the synchronous linkage folding assembly is hinged to the landing gear fixed base, and the upper end is hinged to the output end of the folding drive assembly; The landing gear body is fixedly installed on the outer end of the synchronous link folding assembly; The locking and limiting components are located at the mating positions of the landing gear fixing base and the folding drive component, respectively corresponding to the fully unfolded and fully folded storage positions of the mechanism.

2. The eVTOL float landing gear integrated quick-folding mechanism according to claim 1, characterized in that, The folding drive assembly includes a linear drive motor, a vertical guide slide rod, and a sliding slider; the vertical guide slide rod is vertically fixedly connected to the lower end face of the landing gear mounting base, and the sliding slider is slidably sleeved on the outside of the vertical guide slide rod; the linear drive motor is fixedly installed at the bottom of the landing gear mounting base, and its telescopic output end is rigidly fixedly connected to the sliding slider.

3. The eVTOL float landing gear integrated quick-folding mechanism according to claim 2, characterized in that, The synchronous linkage folding assembly includes four layers of linkage units, which are stacked one on top of the other and share the sliding slider as the active drive end.

4. The eVTOL float landing gear integrated quick-folding mechanism according to claim 1, characterized in that, The outer surface of the synchronous link folding assembly is covered with a flexible skin. The landing gear body, the synchronous link folding assembly, and the flexible skin constitute a float with a sealed cavity. The bottom of the flexible skin is provided with an anti-slip and wear-resistant takeoff and landing support surface, and the sidewall of the flexible skin is an arc-shaped guide surface.

5. The eVTOL float landing gear integrated quick-folding mechanism according to claim 4, characterized in that, The folding assembly of the synchronous link unfolds to form a rigid load-bearing frame, and the inner side of the flexible skin fits into the outer side of the rigid load-bearing frame.

6. The eVTOL float landing gear integrated quick-folding mechanism according to claim 4, characterized in that, It also includes a float inflation / deflation linkage system, the air path of which is connected to the sealed cavity, and its control timing is synchronized with the movement timing of the synchronous linkage folding assembly.

7. The eVTOL float landing gear integrated quick-folding mechanism according to claim 1, characterized in that, The locking and limiting component is an electromagnetic pin-type locking structure, which is electrically connected to the aircraft's flight control system.

8. The eVTOL float landing gear integrated quick-folding mechanism according to claim 2, characterized in that, The linear drive motor is covered with a waterproof sealing layer; the sliding slider is fitted with a self-lubricating wear-resistant bushing; and the hinge joint of the synchronous connecting rod folding assembly is reserved with a drainage gap.

9. The eVTOL float landing gear integrated quick-folding mechanism according to claim 1, characterized in that, The landing gear mounting base is a one-piece aluminum alloy structure with pre-drilled standard mounting holes on the fuselage.

10. A seaplane, characterized in that, It includes the fuselage and two sets of eVTOL float landing gear integrated quick-folding mechanisms as described in claim 1; the two sets of eVTOL float landing gear integrated quick-folding mechanisms are symmetrically arranged on both sides of the bottom of the fuselage, and each set of folding mechanisms is an independent unit structure.

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