A low altitude hovercraft

Abstract

This invention discloses a low-altitude hovering aircraft, comprising a fuselage, solar panels, an electromagnetic levitation module, a propellerless fluid propulsion system, and a sodium-ion battery pack. The fuselage integrates an intelligent flight control module, a positioning and tracking module, an ultrasonic anti-collision module, and a self-circulating charging module. The fuselage is an integrated, enclosed structure without wheels, wings, or propellers. The solar panels are mounted on the fuselage surface to convert solar energy into electrical energy for autonomous recharging. The electromagnetic levitation module is installed at the bottom of the fuselage to generate vertical levitation force. Through the design of the propellerless fluid propulsion system, there are no rotating blades or mechanically moving friction parts throughout the flight, eliminating wear and tear and reducing flight noise and fuselage vibration, achieving quiet low-altitude flight, complying with urban low-altitude noise control standards, and offering more environmentally friendly and stealthy operation.

Description

Technical Field

[0001] This invention relates to the field of civil low-altitude aircraft technology, specifically a low-altitude hovercraft. Background Technology

[0002] Aircraft are man-made machines that can take off from the ground, fly within the atmosphere or in space, and be controlled. Common types include rotorcraft, fixed-wing aircraft, flapping-wing aircraft, and vertical takeoff and landing aircraft, which are widely used in aerial photography, logistics transportation, emergency rescue, and other scenarios.

[0003] With the comprehensive development of the low-altitude economy, civilian short-haul low-altitude travel aircraft have become a core research and development direction for the industry, but existing similar products have multiple technical shortcomings: Firstly, in terms of energy and power, traditional power systems generally use traditional lithium batteries. The scarcity of raw materials leads to high costs, and lithium batteries have prominent risks of thermal runaway, fire and explosion, which cannot meet the mandatory safety standards for civil aircraft. In addition, the range mode is limited, only supporting external charging and lacking self-circulation charging and solar self-recharge functions, resulting in obvious range limitations. Secondly, in terms of power and drive, existing products all rely on wheels, wings, and propellers to achieve movement and flight, which are complex in structure, have high wind resistance, are easily damaged, and have poor practicality in civilian scenarios. Third, the design is not in line with the new national low-altitude airspace control regulations, making it impossible to complete the "one machine, one code" compliance certification, thus hindering its market-oriented implementation.

[0004] Therefore, in response to the aforementioned industry pain points, and to completely solve all the problems of existing technologies such as safety, cost, range, limited product variety, and insufficient compliance, and to fill the relevant technological gaps in the field of civilian low-altitude levitation travel equipment, this invention proposes a low-altitude levitation aircraft. Summary of the Invention

[0005] In view of the shortcomings of the prior art, the purpose of this invention is to provide a low-altitude hovering aircraft to solve the problems mentioned in the background art.

[0006] To achieve the above objectives, the present invention provides a low-altitude hovering aircraft in a specific embodiment, including an airframe, a solar panel, an electromagnetic levitation module, a propellerless fluid propulsion system, and a sodium-ion battery pack. The aircraft body integrates an intelligent flight control module, a positioning and tracking module, an ultrasonic anti-collision module, and a self-circulating charging module. The aircraft is an integrated enclosed fuselage without wheels, wings, or propellers. The solar panels are installed on the surface of the fuselage to convert solar energy into electrical energy and provide autonomous power replenishment. The electromagnetic levitation module is installed at the bottom of the machine body and is used to generate vertical levitation force; The sodium-ion battery pack is installed at the bottom of the machine body and is located at the center of gravity of the machine body; The ultrasonic anti-collision module includes a sensing probe, an electromagnetic buffer unit, and a near-range obstacle sensing and recognition module. By arranging a distributed ring-shaped electromagnetic buffer unit around the aircraft body and incorporating the near-range obstacle sensing and recognition module, it can detect buildings, walls, vehicles, and obstacles in advance. When an object is about to be touched, it automatically triggers electromagnetic magnetic attraction buffering, flexible deceleration, and lateral avoidance, thereby achieving no hard collision and protecting the safety of the aircraft structure and cabin personnel. This is suitable for low-altitude passage through dense urban buildings. The self-circulating charging module is electrically connected to the solar panel to form a self-sustaining system, which is used to recover flight / hovering kinetic energy and convert it into electrical energy. The intelligent flight control module is used to control the hovering, ascent, descent and flight attitude of the aircraft. Its output is connected in series with the sodium-ion battery pack, electromagnetic levitation module, ultrasonic anti-collision module and propellerless fluid propulsion system through wires. The aircraft has a built-in dual identification module that combines network and broadcast identification, and is connected to the national low-altitude intelligent network control system.

[0007] In one embodiment of this application, the aircraft is equipped with multiple sets of environmental sensors to collect data on altitude, external air pressure, wind speed and direction, and ambient temperature and humidity. Through the intelligent flight control module, the electromagnetic levitation module and the propellerless fluid propulsion system are intelligently linked to dynamically adjust the levitation lift, the aircraft's suspension gap, and the balance of the surrounding air pressure difference. It also automatically resists strong winds and airflow disturbances, achieving stable hovering and flight in all scenarios, including mountainous areas, urban areas, and rainy weather, and eliminating problems such as rollover, deviation, and loss of control.

[0008] In one embodiment of this application, the windward side of the fuselage integrates a frontal airflow kinetic energy recovery and power generation structure, which, together with a self-circulating charging module, enables the aircraft to autonomously recharge itself during flight. Furthermore, the fuselage integrates a global low-light and weak-light energy storage and replenishment module, which, together with a sodium-ion battery pack, forms an intelligent balanced management system. Combined with static solar energy replenishment, this multi-channel coordinated power supply significantly extends the flight range, reduces reliance on external charging, and enhances the practicality of low-altitude manned flight.

[0009] In one embodiment of this application, the propellerless fluid propulsion system adopts an ion electric field coupled airflow drive design. It uses a high-voltage electric field to ionize air to generate ions, and then uses electric field force to drive the ions to collide with neutral air molecules to form a directional airflow (ion wind). The electric field, ion motion and airflow field are strongly coupled to achieve airflow propulsion without mechanical moving parts.

[0010] In one embodiment of this application, the airframe integrates multiple sensors, including radar, high-definition vision, and three-dimensional terrain perception, to build a global environmental recognition capability. It can automatically identify obstacles such as high-voltage lines, trees, buildings, pedestrians, and vehicles, and autonomously plan low-altitude flight routes, automatically detour, and adjust speed limits. It supports one-click switching of multiple flight modes, adapting to various usage scenarios such as passenger commuting, low-altitude sightseeing, and stable cruising. Furthermore, through the design of a propellerless fluid propulsion system, there are no rotating blades or mechanical moving friction parts throughout the entire process, eliminating wear and tear and reducing flight noise and fuselage vibration, achieving quiet low-altitude flight, complying with urban low-altitude noise control standards, and making operation more environmentally friendly and more stealthy.

[0011] In one embodiment of this application, the sodium-ion battery pack uses a polymerizable non-flammable electrolyte, can operate in a wide temperature range of 40°C to 60°C, and can actively prevent battery thermal runaway. It does not burn or explode under extreme conditions, and has the advantages of low cost and high safety.

[0012] In one embodiment of this application, the fuselage adopts a wingless, angleless, and rounded streamlined shape, and is integrally molded from a lightweight, high-strength, corrosion-resistant composite material. It has the characteristics of being waterproof, dustproof, anti-aging, resistant to high and low temperatures, and resistant to long-term outdoor corrosion. In addition, it has strong structural integrity and impact resistance, which improves the service life of the whole aircraft and the flight safety factor.

[0013] In one embodiment of this application, the solar panel is a flexible solar panel, which fits the surface of the machine body better and is lighter in weight, thus achieving the purpose of reducing weight and wind resistance.

[0014] In one embodiment of this application, the sodium-ion battery pack adopts a flat and lightweight structure, which is perfectly embedded in the rounded body, does not occupy the passenger space, provides stable power supply and balanced power output, and ensures a smooth and turbulent flight throughout the hovering and flight process. The low-altitude hovering aircraft involved in this invention can be specifically implemented as various low-altitude hovering aircraft, hovering vehicles, hovering motorcycles, and other low-altitude manned or cargo-carrying hovering vehicle structures.

[0015] The advantages of this invention compared to existing technologies are: (1) Through the design of the propellerless fluid propulsion system, there are no rotating blades or mechanical moving friction parts throughout the entire process, which eliminates wear and life reduction while reducing flight noise and fuselage vibration, achieving quiet low-altitude flight, meeting urban low-altitude noise control standards, and making operation more environmentally friendly and more stealthy.

[0016] (2) The fuselage adopts a wingless, angleless, and rounded streamlined shape, and the whole is made of lightweight, high-strength composite anti-corrosion material in one piece. It has the characteristics of being waterproof, dustproof, anti-aging, resistant to high and low temperatures, and long-term corrosion resistant outdoors. In addition, the structure is strong and impact resistant, which improves the service life of the whole aircraft and the flight safety factor.

[0017] (3) Through the intelligent linkage between the intelligent flight control module and the electromagnetic suspension module and the propellerless fluid propulsion system, the suspension lift, the suspension gap of the aircraft and the balance of the air pressure difference are dynamically adjusted, and the strong wind and airflow disturbance are automatically resisted, so as to achieve stable hovering and flight in all scenarios such as mountainous areas, urban areas and rainy days, and eliminate the problems of rollover, deviation and loss of control. Attached Figure Description

[0018] 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 these drawings without creative effort.

[0019] Figure 1 The three-dimensional body of the magnetic levitation vehicle of a low-altitude levitation aircraft in this invention. Figure 1 ; Figure 2 The three-dimensional body of the magnetic levitation vehicle of a low-altitude levitation aircraft in this invention. Figure 2 ; Figure 3 The three-dimensional fuselage of a magnetic levitation aircraft, a low-altitude levitation vehicle, is described in this invention. Figure 1 ; Figure 4 The three-dimensional fuselage of a magnetic levitation aircraft, a low-altitude levitation vehicle, is described in this invention. Figure 2 ; Figure 5 The three-dimensional body of a magnetic levitation motorcycle, a low-altitude levitating aircraft, is described in this invention. Figure 1 ; Figure 6 The three-dimensional body of a magnetic levitation motorcycle, a low-altitude levitating aircraft, is described in this invention. Figure 2 ; Figure 7 This is a flowchart illustrating the working principle of a low-altitude hovering aircraft according to the present invention. Figure 8 This is a flowchart illustrating a collision avoidance strategy for a low-altitude hovering aircraft according to the present invention.

[0020] Explanation of reference numerals in the attached diagram: 1. Body; 2. Solar panel; 3. Electromagnetic levitation module; 5. Power generation mechanism; 6. Ultrasonic anti-collision module; 8. Sodium-ion battery pack; 9. Propellerless fluid propulsion system. Detailed Implementation

[0021] 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 some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0022] like Figures 1 to 8 As shown: Airframe 1 adopts an integrated enclosed fuselage design. Its core function is to integrate all functional modules, ensure structural strength, and provide a stable installation benchmark for each component. At the same time, it avoids interference from the external environment (such as dust, water vapor, and airflow disturbance) on the internal modules, ensuring the operational stability of the aircraft in complex low-altitude environments.

[0023] The intelligent flight control module is the "brain" of the entire aircraft. It is integrated inside the fuselage 1 and serves as the control center for all functional modules. Its output is connected in series with the sodium-ion battery pack 8, the electromagnetic levitation module 3, the ultrasonic anti-collision module 6, and the propellerless fluid propulsion system 9 through wires, forming a closed-loop control logic of "command output - execution feedback - dynamic adjustment".

[0024] The intelligent flight control module receives signals from various sensors in real time, processes them, and outputs precise control commands to regulate the operating status of each module, ensuring that all actions of the aircraft, such as hovering, ascent and descent, flight attitude, collision avoidance, and recharging, are coordinated and consistent.

[0025] The electromagnetic levitation module 3 is installed at the bottom of the fuselage 1. Its core function is to generate vertical levitation force, enabling the aircraft to detach from the ground / contact surface and achieve contactless levitation, laying the foundation for subsequent flight.

[0026] When needed, the intelligent flight control module issues a levitation start command, and the sodium-ion battery pack 8 supplies power to the electromagnetic levitation module 3. A stable current is passed through the electromagnetic coil inside the module, generating a strong magnetic field. This magnetic field interacts with the magnetic medium of the ground / contact surface (or the induced magnetic field generated through electromagnetic induction). According to the attraction principle of electromagnetic levitation (EMS) technology, the module generates gravity, overcoming the aircraft's own weight (the total weight of the fuselage 1, all modules, and the battery pack), causing the aircraft to slowly detach from the contact surface and achieve initial levitation. Then, the gap sensor built into the electromagnetic levitation module 3 (not separately labeled, integrated inside the module) collects the levitation gap data between the aircraft and the ground / contact surface in real time (usually controlled within a preset safety range). Furthermore, the system controls the aircraft's flight altitude within urban areas to a maximum of 120 meters (which is within the legal flight altitude range for urban areas). This facilitates subsequent civil aviation registration with a unique code and airspace network verification. After the data is fed back to the intelligent flight control module, the module uses a PID control algorithm to adjust the current flowing through the electromagnetic coil in real time, thereby regulating the magnetic field strength. This ensures that the levitation force and the aircraft's gravity remain in dynamic balance. When ascent is required, the flight control module issues a lift enhancement command, increasing the current flowing through the coil. This further enhances the magnetic field force, making it greater than the aircraft's gravity, thus propelling the aircraft vertically upward. When descent is required, the flight control module reduces the current flowing through the coil, weakening the magnetic field force to less than the aircraft's gravity. The aircraft then descends slowly and vertically until it reaches the preset altitude or lands.

[0027] Once the aircraft achieves stable hovering, the intelligent flight control module sends propulsion commands to the propellerless fluid propulsion system 9 based on the preset flight trajectory or real-time control instructions. The sodium-ion battery pack 8 powers the system, and the system activates its internal fluid drive device (such as a high-pressure pump and air jet mechanism). The propellerless fluid propulsion system 9 draws air (or other fluid) into the system through its internal drive device, pressurizes it, and then ejects it through a specially shaped guide channel. Utilizing the Coanda effect, the ejected fluid adheres to the curved surface of the guide channel, forming a stable fluid jet. According to Newton's third law, the reaction force generated by the fluid jet is the horizontal propulsion of the aircraft. The intelligent flight control module adjusts the direction and intensity of the fluid jet from the propellerless fluid propulsion system 9 to achieve horizontal flight, turning, and speed regulation of the aircraft. The entire process requires no rotating parts, achieving silent and stable flight, suitable for low-altitude close-range flight scenarios.

[0028] The sodium-ion battery pack 8 is installed at the bottom of the fuselage 1, located at its center of gravity. Its flat, lightweight design further reduces the overall weight of the fuselage and lowers the center of gravity, enhancing the aircraft's levitation stability in conjunction with the electromagnetic levitation module 3 and preventing issues such as center of gravity shift or tilting during flight. Simultaneously, the battery pack uses a polymerizable non-flammable electrolyte, exhibiting a wide operating temperature range of 40℃ to 60℃, adapting to extreme environments such as high temperatures and extreme cold, significantly improving the aircraft's environmental adaptability. Furthermore, the sodium-ion battery pack 8 employs a high-capacity energy storage design, achieving an energy conversion efficiency of over 97% and a cycle life exceeding 15,000 cycles. It can store sufficient electrical energy to provide stable power support for all functional modules of the aircraft (intelligent flight control module, electromagnetic levitation module 3, propellerless fluid propulsion system 9, ultrasonic anti-collision module 6, positioning and tracking module, dual identification module, self-circulating charging module, radar, high-definition vision, and various sensors for 3D terrain perception). Its output voltage and current are regulated by the intelligent flight control module to adapt to the power requirements of different modules. For example, the electromagnetic levitation module 3 requires a large current to start up, and the flight control module adjusts the battery pack to output the corresponding current to ensure that the module starts up normally; while the positioning and tracking module and the dual identification module require a stable small current power supply, and the battery pack continuously outputs low-power energy to ensure their all-weather operation.

[0029] The sodium-ion battery pack 8, together with the flexible solar panel 2, the self-circulating charging module, and the oncoming airflow energy recovery power generation mechanism 5, forms a "triple energy replenishment" system. It also incorporates a battery management system (BMS) responsible for the charging and discharging management and status monitoring of the battery pack, preventing overcharging, over-discharging, and overheating, thus extending battery life. Specifically, the BMS monitors the battery pack's state of charge (SOC), temperature, and voltage in real time. When the battery temperature exceeds a wide temperature range of 40°C to 60°C or the charge level is above 85%, it automatically adjusts the charging and discharging strategy to ensure safe battery operation. When the battery charge falls below a preset threshold, the energy replenishment mechanism is automatically triggered, charging the battery simultaneously or individually through the flexible solar panel 2, the self-circulating charging module, and the oncoming airflow energy recovery power generation mechanism 5.

[0030] Because the solar panel 2 is installed on the surface of the fuselage 1 and adopts a high-efficiency photoelectric conversion design, it can receive sunlight to the maximum extent. Then, through the internal photoelectric conversion element, the solar energy is converted into direct current. After rectification and voltage regulation, it is transmitted to the sodium-ion battery pack 8 to charge the battery pack. At the same time, the solar panel 2 is linked with the battery pack's BMS. When the battery pack is fully charged, it automatically stops charging to avoid overcharging and damaging the battery. When there is insufficient sunlight (such as on cloudy days or at night), the solar panel 2 stops supplementing energy, and the battery pack supplies power to the system alone to ensure the normal operation of the aircraft.

[0031] The self-circulating charging module is also integrated inside the fuselage 1. Its core function is to recover the excess kinetic energy generated during the flight and hovering of the aircraft and convert it into electrical energy, so as to realize the recycling of energy.

[0032] During operation, solar panel 2 is mainly responsible for "active energy replenishment," relying on external sunlight for continuous energy replenishment; the self-circulating charging module is mainly responsible for "passive energy replenishment," relying on the kinetic energy generated by the aircraft's own operation for cyclical energy replenishment; and the oncoming airflow energy recovery and power generation mechanism 5 is mainly responsible for "flight airflow energy replenishment," relying on the oncoming airflow during flight to achieve charging while flying. The three complement each other and work together—when there is sufficient sunlight and the aircraft is flying, the three replenish energy synchronously to quickly charge the battery pack; when there is insufficient sunlight but the aircraft is flying, the self-circulating charging module and the oncoming airflow energy recovery and power generation mechanism 5 work synchronously to ensure continuous energy replenishment; when the aircraft is stationary and there is sunlight, only flexible solar panel 2 replenishes energy; when the aircraft is stationary and there is no sunlight, all energy replenishment modules stop working, and the battery pack supplies power alone, maximizing the aircraft's endurance and meeting the needs of long-term low-altitude flight.

[0033] Multiple sensors, including radar, high-definition vision, and 3D terrain perception, work together to achieve all-around, blind-spot-free environmental and obstacle recognition: Radar sensors emit electromagnetic waves to detect the position, distance, and speed of obstacles at a distance, making them suitable for obstacle recognition in complex weather conditions (such as fog and rain); high-definition vision sensors collect images of the surrounding environment and, through image recognition algorithms, accurately identify the specific types of nearby obstacles such as pedestrians, vehicles, and buildings; 3D terrain perception sensors collect terrain data in real time, identifying terrain changes such as ground protrusions and depressions, and, combined with data from radar and high-definition vision sensors, accurately identify small obstacles such as high-voltage lines and trees. All identified obstacle information and terrain data are transmitted in real time to the intelligent flight control module, providing support for flight path planning and collision avoidance decisions.

[0034] The intelligent flight control module combines obstacle information and terrain data fed back by the all-domain environmental recognition sensor with the preset flight destination. Through path planning algorithm, it autonomously plans the optimal low-altitude flight route to avoid all obstacles. During flight, if the sensor detects a new obstacle (such as a pedestrian or vehicle that suddenly appears), the flight control module immediately replans the route and controls the propellerless fluid propulsion system 9 and the electromagnetic levitation module 3 to work together to achieve automatic detour. At the same time, it automatically adjusts the speed limit according to the distance and type of the obstacle (such as reducing the flight speed when approaching pedestrians or vehicles to improve safety).

[0035] The ultrasonic anti-collision module 6 is integrated inside the fuselage 1 and consists of three parts: a sensing probe, an electromagnetic buffer unit, and a near-field obstacle sensing and recognition module. As a supplement to the all-area environmental recognition, it is mainly responsible for the accurate detection of near-field obstacles and emergency collision avoidance. The sensing probes are evenly distributed in different positions of the fuselage 1 and emit ultrasonic signals in real time. The ultrasonic signals propagate around at a frequency of about 40kHz. When they encounter an obstacle during propagation, the ultrasonic signals are reflected to form echo signals. After receiving the echo signals, the sensing probes transmit them to the near-field obstacle sensing and recognition module. The module calculates the distance between the aircraft and the obstacle and feeds back the distance data and obstacle location information to the intelligent flight control module in real time. When the distance between the detected obstacle and the aircraft is less than the preset safety threshold, a "danger warning" signal is immediately sent to the flight control module. After receiving the "danger warning" signal, the intelligent flight control module immediately activates the collision avoidance response strategy.

[0036] Active obstacle avoidance: The flight control module quickly adjusts the jet direction and propulsion intensity of the propellerless fluid propulsion system 9 and the levitation height of the electromagnetic levitation module 3 based on the location and distance data of the obstacle, so as to guide the aircraft to avoid the obstacle in a safe direction (such as deflecting to the left / right, ascending / descending) until it is far away from the obstacle and resumes normal flight. If the obstacle is too close, the flight control module will immediately stop propulsion and control the aircraft to maintain a levitated state to avoid continuing to approach the obstacle.

[0037] Passive buffering: In the event of a sudden collision (such as the sudden appearance of an obstacle that cannot be actively avoided in time), the electromagnetic buffer unit is activated immediately. By generating a reverse electromagnetic force, it forms a buffer barrier to offset the impact force of the collision, reduce the damage to the airframe 1 and internal modules, and protect the obstacle (such as preventing injury to people or fragile items). After the collision, the flight control module will automatically detect the operating status of each module. If no fault occurs, it can continue to operate normally. If a fault occurs, it will immediately control the aircraft to land.

[0038] The network-based and broadcast-based dual identification modules are integrated inside the aircraft body 1. This is the core interface for the aircraft to access the national low-altitude intelligent network control system. Upon leaving the factory, the dual identification modules are programmed with a unique identification code (bound to the aircraft's product model and serial number). This code corresponds to the user's real-name registration information (including owner identity information, intended use, etc., in accordance with the "Requirements for Real-Name Registration and Activation of Civil Unmanned Aerial Vehicles"), and is simultaneously entered into the national low-altitude intelligent network control system. The two work together to ensure the stability and compliance of the access. After the user completes real-name registration, the identification code is bound to the real-name information, achieving "one code per aircraft, verifiable by real name," ensuring that every aircraft can be accurately controlled and preventing unauthorized or illegal flights. The positioning and tracing module integrates a high-precision positioning chip (such as GPS + BeiDou dual-mode positioning). The system collects real-time location data of the aircraft, including latitude, longitude, altitude, flight speed, and flight direction. This data, combined with the operating commands from the intelligent flight control module, generates complete flight trajectory data. This data is uploaded in real-time to the National Low-Altitude Intelligent Networked Control System via a dual-identification module, and simultaneously stored locally, enabling full traceability of the flight trajectory. Control departments can query the aircraft's historical flight trajectory, current location, and operational status through the system, while users can also query their own aircraft's flight records via their terminals. If the aircraft violates regulations (such as entering a no-fly zone), the control system will issue a no-fly order through the dual-identification module. Upon receiving the order, the intelligent flight control module will immediately control the aircraft to stop flying, land smoothly, and upload the violation information. If the aircraft is lost, it can be quickly located using the real-time positioning function of the positioning and tracing module.

[0039] The low-altitude hovering aircraft involved in this invention can be specifically implemented as various low-altitude hovering aircraft, hovering vehicles, hovering motorcycles, and other low-altitude passenger or cargo hovering vehicle structures. Among them, the hovering aircraft is suitable for medium- and long-distance low-altitude flight, the hovering vehicle is suitable for short-distance travel for multiple family members, and the hovering motorcycle is suitable for lightweight single-person transportation. All of them are equipped with intelligent balance flight control and automatic collision avoidance systems, ensuring stable and safe operation. Moreover, the overall production cost of the three categories is controlled within 100,000 yuan.

[0040] It should be noted that the control method in the embodiments of this application can be automatically controlled by a controller. The control method of the controller can be implemented by simple programming by those skilled in the art, which is common knowledge in the field. Furthermore, this application is mainly used to protect mechanical structures, so the control method and circuit connection will not be explained in detail here.

[0041] Obviously, the above-described embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention. Thus, if these modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention also intends to include these modifications and variations.

Claims

1. A low-altitude hovercraft, characterized in that, It includes the body (1), solar panel (2), electromagnetic levitation module (3), propellerless fluid propulsion system (9) and sodium-ion battery pack (8). The body (1) integrates an intelligent flight control module, a positioning and tracking module, an ultrasonic anti-collision module (6), and a self-circulating charging module. The body (1) is an integrated closed fuselage without wheels, wings, or propellers. The solar panel (2) is installed on the surface of the body (1) to convert solar energy into electrical energy and to provide autonomous power replenishment. The electromagnetic levitation module (3) is installed at the bottom of the body (1) to generate vertical levitation force; The sodium-ion battery pack (8) is installed at the bottom of the body (1) and is located at the center of gravity of the body (1); The ultrasonic anti-collision module (6) includes a sensing probe, an electromagnetic buffer unit, and a near-range obstacle sensing and recognition module. The self-circulating charging module is electrically connected to the solar panel (2) to form a self-sustaining system, which is used to recover flight / hovering kinetic energy and convert it into electrical energy; The intelligent flight control module is used to control the hovering, lifting and lowering and flight attitude of the aircraft (1). Its output end is connected in series with the sodium-ion battery pack (8), the electromagnetic levitation module (3), the ultrasonic anti-collision module (6) and the propellerless fluid propulsion system (9) through wires. The aircraft (1) has a built-in network and broadcast dual identification module and is connected to the national low-altitude intelligent network control system.

2. The low-altitude hovering aircraft according to claim 1, characterized in that, The body (1) is equipped with multiple sets of environmental sensors for collecting data on altitude, external air pressure, wind speed and direction, and ambient temperature and humidity.

3. A low-altitude hovercraft according to claim 2, characterized in that, The windward side of the fuselage integrates a windward airflow kinetic energy recovery and power generation mechanism (5), which, together with a self-circulating charging module, enables the fuselage (1) to autonomously circulate and charge itself during flight.

4. A low-altitude hovering aircraft according to claim 2, characterized in that, The propellerless fluid propulsion system (9) adopts an increased ion electric field coupling airflow drive design. It uses a high-voltage electric field to ionize air to generate ions, and then uses electric field force to drive the ions to collide with neutral air molecules to form a directional airflow (ion wind). It also allows the electric field, ion motion and airflow field to be strongly coupled to achieve airflow propulsion without mechanical moving parts.

5. A low-altitude hovercraft according to claim 1, characterized in that, The body (1) integrates multiple sensors such as radar, high-definition vision, and three-dimensional terrain perception to build a full-domain environmental recognition capability. It can automatically identify obstacles such as high-voltage lines, trees, buildings, pedestrians, and vehicles, and autonomously plan low-altitude flight routes, automatically detour, and adjust speed limits.

6. A low-altitude hovering aircraft according to claim 4, characterized in that, The sodium-ion battery pack (8) uses a polymerizable non-flammable electrolyte and has the characteristic of operating in a wide temperature range of 40°C to 60°C.

7. A low-altitude hovercraft according to claim 1, characterized in that, The body (1) adopts a wingless, angleless, and rounded streamlined shape, and is integrally molded with lightweight, high-strength composite anti-corrosion material.

8. A low-altitude hovercraft according to claim 1, characterized in that, The solar panel (2) is a flexible solar panel (2), which fits the surface of the body (1) better.

9. A low-altitude hovercraft according to claim 1, characterized in that, The sodium-ion battery pack (8) adopts a flat and lightweight structure.

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