Lightweight low altitude flying traffic vehicle

Abstract

The utility model discloses a kind of lightweight low-altitude flight traffic carriers, the utility model relates to low-altitude flight vehicle technical field.Lightweight low-altitude flight traffic carrier includes cockpit, the outside of cockpit is provided with flight mechanism, for generating lift and thrust, the flight mechanism includes: lift assembly, including fixedly installed in the fixed rod of cockpit bottom, the one end of the fixed rod swing installation has movable rod, when encountering transverse wind force, steering motor drives gear rotation, through the meshing transmission of gear and tooth ring, make guide tube rotate to the direction opposite with wind force;After guide tube is adjusted in place, drive motor drives transverse paddle rotation, generate with transverse wind force size matching, horizontally thrust opposite in direction, the thrust can directly offset the influence of transverse wind force to device, ensure that device keeps stable posture in hovering process, effectively solved the problem that traditional aircraft cannot resist transverse wind force when hovering.

Description

Technical Field

[0001] This utility model relates to the field of low-altitude flight vehicle technology, specifically a lightweight low-altitude flight transportation vehicle. Background Technology

[0002] Electric vertical takeoff and landing (eVTOL) aircraft are purely electric-powered aircraft capable of vertical takeoff and landing without a runway. Their primary energy source is lithium batteries, supplemented by clean technologies such as hydrogen energy. Their configurations include multi-rotor, compound-wing, and tiltrotor types, and they can be categorized into manned and unmanned types based on their operating modes, combining the flexibility of vertical takeoff and landing with the high endurance of fixed-wing aircraft. As a core carrier of the low-altitude economy, eVTOL, relying on breakthroughs in battery technology, distributed electric propulsion systems, and intelligent flight control, is mainly applied in urban commuting, emergency rescue, and logistics transportation.

[0003] The existing utility model patent with publication number CN220181084U discloses a lightweight manned multi-purpose rotorcraft, including a power unit, a tricycle safety seat, and a control cabin. The power unit includes several motor mounts, several propellers, and several motors. The motors are fixed to the motor mounts, and the propellers are fixed to the motors. The control cabin includes an irregularly shaped control cabin and arms. The arms are fixed around the irregularly shaped control cabin, and the motor mounts are fixed to the outside of the arms of the control cabin. The tricycle safety seat is detachably fixed to the bottom of the irregularly shaped control cabin. This utility model solves the problem that existing aircraft cannot simultaneously achieve low-altitude flight capability, maneuverability, equipment carrying capacity, and rapid transport capability. The aircraft can be used for target reconnaissance, flexible obstacle crossing, and material transport in complex low-altitude environments, improving the aircraft's maneuverability, safety, and stability, and providing a new type of mobile equipment for multi-domain mission deployment.

[0004] The aforementioned aircraft uses rotors to generate lift. During movement, the aircraft tilts as a whole by the difference in rotational speed between the front and rear rotors. The aircraft moves by the horizontal component of the lift generated by the rotors. In this way, the fuselage will tilt significantly during maneuvers such as emergency stops, affecting the pilot's comfort. At the same time, crosswinds will affect the hovering attitude during hovering, and the lift generated by the rotors remains in the vertical direction and cannot resist crosswinds. Summary of the Invention

[0005] To address the shortcomings of existing technologies, this utility model provides a lightweight low-altitude flight vehicle that solves the problems of aircraft tilting during movement affecting driving comfort and the inability to resist lateral wind forces during hovering.

[0006] To achieve the above objectives, this utility model provides the following technical solution: A lightweight low-altitude flight vehicle includes a cockpit, and a flight mechanism is disposed on the outside of the cockpit for generating lift and thrust. The flight mechanism includes: The lift assembly includes a fixed rod fixedly installed at the bottom of the cockpit, a movable rod movably installed at one end of the fixed rod, a limit bolt inserted at the connection between the movable rod and the fixed rod, a positioning tube sleeved on the outside of the movable rod, a mounting bracket fixedly installed at the end of the movable rod, a lift motor fixedly installed inside the mounting bracket, and a lift blade fixedly installed on the outside of the shaft of the lift motor. A movable component, positioned below the mounting bracket, is used to provide horizontal thrust.

[0007] Preferably, the moving component includes a gear ring fixedly mounted on the bottom of the mounting frame, a guide tube movably mounted below the mounting frame, a steering motor fixedly mounted on the top of the guide tube, a gear fixedly mounted on the outer side of the steering motor's shaft, a pressure bearing fitted into the top of the guide tube, a connecting frame fixedly mounted inside the guide tube, a drive motor fixedly mounted inside the connecting frame, and transverse blades fixedly mounted on both sides of the drive motor.

[0008] Preferably, the bottom of the cockpit is provided with a frame structure for providing support during takeoff and landing, and the fixing rod is installed in an "X" shape at the bottom of the cockpit with the center of the cockpit as the reference.

[0009] Preferably, the movable rod and the fixed rod are rotatably connected, and the outer sides of the movable rod and the fixed rod are provided with grooves that match the threaded structure of the inner wall of the positioning tube. The mounting bracket is fixedly connected to the movable rod by means of insertion.

[0010] Preferably, the guide tube and the mounting bracket are rotatably connected, the top of the guide tube is provided with an annular protrusion, and the pressure bearing is located between the annular protrusion structure at the top of the guide tube and the mounting bracket.

[0011] Preferably, the steering motor is symmetrically installed on both sides of the guide tube, the gear and the gear ring mesh with each other, the transverse blades are fixedly installed at the front and rear ends of the drive motor, and the air outlet direction of the transverse blades is consistent. Beneficial effects

[0012] This invention provides a lightweight low-altitude flight vehicle. Compared with the prior art, it has the following advantages: (1) This lightweight low-altitude flight vehicle solves this problem through the independent operation and cooperation of the lift component and the moving component: the lift component focuses on providing vertical lift to maintain the overall height stability of the device and avoid the fuselage tilting due to lift adjustment; when movement is required, the moving component provides horizontal thrust independently. The steering motor in the moving component drives the gear to rotate, and the gear meshes with the gear ring to cause the guide tube to rotate, adjusting the orientation of the transverse blades. Subsequently, the drive motor drives the transverse blades to rotate to generate horizontal thrust, propelling the device to move. Throughout the movement process, the lift component does not need to change the lift direction, and the fuselage can achieve horizontal movement and emergency stop without tilting, effectively avoiding the impact of fuselage tilt on piloting comfort. At the same time, the cooperation between the lift component and the moving component ensures stability during movement.

[0013] (2) This lightweight low-altitude flight vehicle resists lateral wind force by flexibly adjusting the moving components during hovering: When hovering, the lift components continuously and stably output vertical lift to maintain the device's altitude; when encountering lateral wind force, the steering motor drives the gear to rotate, and through the meshing transmission of the gear and the gear ring, the guide tube rotates to the opposite direction of the wind force; after the guide tube is adjusted into place, the drive motor drives the lateral blades to rotate, generating a horizontal thrust that matches the magnitude of the lateral wind force and is opposite in direction. This thrust can directly offset the influence of the lateral wind force on the device, ensuring that the device maintains a stable attitude during hovering, effectively solving the problem that traditional aircraft cannot resist lateral wind force when hovering. Attached Figure Description

[0014] Figure 1 This is a schematic diagram of the overall structure of this utility model; Figure 2 This is a schematic diagram of the positioning tube installation structure of this utility model; Figure 3 This is a schematic diagram of the connection structure between the guide tube and the mounting bracket of this utility model; Figure 4 This is a schematic diagram of the transverse blade mounting structure of this utility model; In the diagram: 1. Cockpit; 2. Flight mechanism; 21. Lift assembly; 211. Fixed rod; 212. Movable rod; 213. Limit bolt; 214. Positioning tube; 215. Mounting bracket; 216. Lift motor; 217. Lift blade; 22. Moving assembly; 221. Gear ring; 222. Guide tube; 223. Steering motor; 224. Gear; 225. Pressure bearing; 226. Connecting frame; 227. Drive motor; 228. Transverse blade. Detailed Implementation

[0015] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0016] Please see Figure 1-4 This utility model provides a technical solution: a lightweight low-altitude flight vehicle includes a cockpit 1, and a flight mechanism 2 is provided on the outside of the cockpit 1 for generating lift and thrust. The flight mechanism 2 includes a lift assembly 21, including a fixed rod 211 fixedly installed at the bottom of the cockpit 1, a movable rod 212 movably installed at one end of the fixed rod 211, a limit bolt 213 inserted at the connection between the movable rod 212 and the fixed rod 211, a positioning tube 214 sleeved on the outside of the movable rod 212, and a mounting bracket 215 fixedly installed at the end of the movable rod 212. A lift motor 216 is fixedly installed inside the mounting bracket 215. A lift blade 217 is fixedly installed on the outside of the shaft of the lift motor 216. A frame structure for providing support during takeoff and landing is provided at the bottom of the cockpit 1. The fixed rod 211 is installed in an "X" shape at the bottom of the cockpit 1 with the center of the cockpit 1 as the reference. The movable rod 212 and the fixed rod 211 are rotatably connected. The outer sides of the movable rod 212 and the fixed rod 211 are provided with grooves that match the threaded structure of the inner wall of the positioning tube 214. The mounting bracket 215 is fixedly connected to the movable rod 212 by interlocking.

[0017] Specifically, the bottom of the cockpit 1 integrates the power supply and flight control system, which are used to coordinate the speed of each motor and the power supply of the motor. The fixed rod 211 can limit the position of the bottom end of the movable rod 212. After loosening the limit bolt 213, the movable rod 212 can rotate from the horizontal state to the vertical state, so as to reduce the footprint of the aircraft when not in use. When the movable rod 212 is in the horizontal state, the fixed rod 211 and the movable rod 212 can be connected by the threaded structure on the inner wall of the positioning tube 214, and its rotation angle is limited. The lift motor 216 can drive the lift blade 217 to rotate, providing lift for the aircraft and assisting the moving component 22 in providing a certain horizontal component when the cockpit 1 is slightly tilted.

[0018] A movable component 22, positioned below the mounting bracket 215, provides horizontal thrust. The movable component 22 includes a gear ring 221 fixedly mounted to the bottom of the mounting bracket 215. A guide tube 222 is movably mounted below the mounting bracket 215. A steering motor 223 is fixedly mounted on the top of the guide tube 222. A gear 224 is fixedly mounted on the outer side of the shaft of the steering motor 223. A pressure bearing 225 is fitted onto the top of the guide tube 222. A connecting bracket 226 is fixedly mounted inside the guide tube 222. A drive motor is fixedly mounted inside the connecting bracket 226. The drive motor 227 has horizontal blades 228 fixedly installed on both sides. The guide tube 222 and the mounting bracket 215 are rotatably connected. The top of the guide tube 222 is provided with a ring-shaped protrusion. The pressure bearing 225 is located between the ring-shaped protrusion structure at the top of the guide tube 222 and the mounting bracket 215. The steering motor 223 is symmetrically installed on both sides of the guide tube 222. The gear 224 and the gear ring 221 mesh with each other. The horizontal blades 228 are fixedly installed at the front and rear ends of the drive motor 227, and the air outlet direction of the horizontal blades 228 is consistent.

[0019] Specifically, since the steering motor 223 is fixedly connected to the guide tube 222, when the steering motor 223 drives the gear 224 to rotate, the gear 224 will drive the guide tube 222 to rotate because it meshes with the gear ring 221, thereby adjusting the orientation of the tubular structure at the bottom of the guide tube 222 and adjusting the orientation of the drive motor 227 inside the guide tube 222. The drive motor 227 is a dual-axis motor, which drives the horizontal blades 228 on both sides to rotate to generate horizontal thrust, so as to facilitate the movement and turning of the aircraft.

[0020] Specifically, the lifting motor 216 is model 23HS45-4204D, the steering motor 223 is model KH39800, and the drive motor 227 is model CK48HB16FF01. In addition, all contents not described in detail in this specification are existing technologies known to those skilled in the art.

[0021] During operation, the lift assembly 21 operates first, and the lift motor 216 drives the lift blades 217 to rotate, generating vertical lift and lifting the cockpit 1 and the overall structure off the ground. During this process, the frame structure at the bottom of the cockpit 1 plays a role in take-off and landing support. The fixed rods 211 in the flight mechanism 2 are distributed in an "X" shape with the center of the cockpit 1 as the reference, providing stable support for the movable rods 212. The movable rods 212 and the fixed rods 211 are kept in a horizontal fixed state by the limit bolts 213 and the positioning tubes 214, ensuring the overall structural stability of the lift assembly 21. When horizontal movement is required, the moving component 22 starts working, and the steering motor 223 drives the gear 224 to rotate. Since the gear 224 meshes with the gear ring 221 fixed to the bottom of the mounting bracket 215, it drives the guide tube 222 to rotate around the mounting bracket 215. The pressure bearing 225 at the top of the guide tube 222 reduces friction during rotation, allowing the guide tube 222 to be precisely adjusted in orientation. After the guide tube 222 is adjusted to its correct position, the drive motor 227 fixed to its internal connecting bracket 226 starts, driving the transverse blades 228 at both ends to rotate, generating horizontal thrust. The device moves in the designated direction; if a turn is required, the device can be turned by adjusting the orientation of the guide tubes 222 in different moving components 22 and the thrust of the transverse blades 228; when the device needs to hover, the lift component 21 maintains stable lift, and the moving component 22 adjusts the thrust according to the ambient wind conditions to counteract the interference of transverse wind; when the device lands, the lift component 21 gradually reduces the lift, and the bottom frame structure of the cockpit 1 contacts the ground to complete the take-off and landing; when idle, the limit bolts 213 can be loosened to rotate the movable rod 212 from the horizontal state to the vertical state to reduce the footprint of the device.

[0022] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such process, method, article, or apparatus.

[0023] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A lightweight low-altitude flight vehicle, characterized in that: The system includes a cockpit (1), and a flight mechanism (2) is provided on the outside of the cockpit (1) for generating lift and thrust. The flight mechanism (2) includes: The lift assembly (21) includes a fixed rod (211) fixedly installed at the bottom of the cockpit (1). A movable rod (212) is movably installed at one end of the fixed rod (211). A limit bolt (213) is inserted at the connection between the movable rod (212) and the fixed rod (211). A positioning tube (214) is sleeved on the outside of the movable rod (212). A mounting bracket (215) is fixedly installed at the end of the movable rod (212). A lift motor (216) is fixedly installed inside the mounting bracket (215). A lift blade (217) is fixedly installed on the outside of the shaft of the lift motor (216). A movable component (22) is positioned below the mounting bracket (215) to provide horizontal thrust.

2. A lightweight low-altitude flight vehicle according to claim 1, characterized in that: The moving component (22) includes a gear ring (221) fixedly mounted on the bottom of the mounting frame (215). A guide tube (222) is movably mounted below the mounting frame (215). A steering motor (223) is fixedly mounted on the top of the guide tube (222). A gear (224) is fixedly mounted on the outside of the shaft of the steering motor (223). A pressure bearing (225) is fitted on the top of the guide tube (222). A connecting frame (226) is fixedly mounted inside the guide tube (222). A drive motor (227) is fixedly mounted inside the connecting frame (226). Transverse blades (228) are fixedly mounted on both sides of the drive motor (227).

3. A lightweight low-altitude flight vehicle according to claim 1, characterized in that: The bottom of the cockpit (1) is provided with a frame structure for providing support during takeoff and landing, and the fixing rod (211) is installed in an "X" shape at the bottom of the cockpit (1) with the center of the cockpit (1) as the reference.

4. A lightweight low-altitude flight vehicle according to claim 1, characterized in that: The movable rod (212) and the fixed rod (211) are rotatably connected. The outer sides of the movable rod (212) and the fixed rod (211) are provided with grooves that match the threaded structure of the inner wall of the positioning tube (214). The mounting bracket (215) is fixedly connected to the movable rod (212) by inserting it through.

5. A lightweight low-altitude flight vehicle according to claim 2, characterized in that: The guide tube (222) and the mounting bracket (215) are rotatably connected. The top of the guide tube (222) is provided with an annular protrusion. The pressure bearing (225) is located between the annular protrusion structure at the top of the guide tube (222) and the mounting bracket (215).

6. A lightweight low-altitude flight vehicle according to claim 2, characterized in that: The steering motor (223) is symmetrically installed on both sides of the guide tube (222), the gear (224) meshes with the gear ring (221), the transverse blade (228) is fixedly installed at the front and rear ends of the drive motor (227), and the air outlet direction of the transverse blade (228) is consistent.

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