A hybrid propulsion device suitable for plateau environment
By incorporating battery insulation and propulsion components into the hybrid propulsion system of the UAV, the problem of sudden drop in battery power in high-altitude environments was solved, ensuring stable flight and sufficient thrust for the UAV in such environments.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- SHAANXI SILK ROAD AVIATION TECHNOLOGY CO LTD
- Filing Date
- 2025-09-25
- Publication Date
- 2026-07-21
AI Technical Summary
In high-altitude environments, the large temperature difference causes a sudden drop in battery power and an increase in internal resistance, affecting the drone's endurance and power output, and increasing the risk of loss of control. Existing technologies cannot effectively solve this problem.
A hybrid propulsion device for UAVs suitable for high-altitude environments was designed, comprising a battery insulation component and a power propulsion component. The battery is heated and kept at a constant temperature by heating wires, and lift and propulsion are provided by propellers to ensure stable flight of the UAV in the low-density air of high altitudes.
It effectively prevents battery performance degradation in low-temperature environments, ensures stable operation and sufficient thrust for drones in high-altitude environments, and solves the problem of insufficient power at high altitudes.
Smart Images
Figure CN224529039U_ABST
Abstract
Description
Technical Field
[0001] This utility model belongs to the field of unmanned aerial vehicle (UAV) technology, specifically a hybrid propulsion device for UAVs suitable for high-altitude environments. Background Technology
[0002] With the continuous maturation of theoretical systems related to UAVs, such as stator information technology, communication technology, and aircraft design, UAVs have experienced rapid development and improvement in recent years, and are widely used, especially in high-altitude environments for express delivery, disaster relief, surveying, and other fields. Shaanxi Province has a terrain characterized by high elevations in the north and south and low elevations in the middle, with diverse terrain types including plateaus, mountains, plains, and basins. Its complex geographical environment necessitates the use of hybrid propulsion systems to assist UAVs in flight and ensure flight safety.
[0003] In the existing technology, a propulsion device for unmanned aerial vehicle (UAV) with publication number CN118514903B is described. The amount of gas pumped out by the air pump controls the angle of the launch chamber reset. The volume of the buffer chamber is controlled by the telescopic sleeve. The air pump pumps out gas, and the gas expands in the buffer chamber. The remaining gas is discharged through the launch chamber, thereby enabling the encapsulation chamber to be launched with different initial velocities and launch angles. However, in general, the battery is installed and used directly for power supply. However, the temperature difference in high-altitude areas is large, and it is impossible to heat and maintain the temperature of the battery. This causes the battery capacity to drop sharply and the internal resistance to increase, which seriously affects the drone's endurance and power output. Low temperature can cause the battery to discharge incompletely or suddenly lose power, which increases the risk of the drone losing control during high-altitude flight. To address this, we provide a hybrid propulsion device for drones suitable for high-altitude environments. Utility Model Content
[0004] To address the shortcomings of existing technologies, solve the problem of heating and maintaining the temperature of the battery to ensure optimal battery performance in low-temperature environments, and ensure that the high-speed rotation of the propeller 806 generates lift and thrust for the UAV, thus ensuring that the UAV can maintain sufficient thrust and flight stability in the low-density air of high altitudes, a hybrid propulsion device for UAVs suitable for high-altitude environments is proposed.
[0005] The technical solution adopted by this utility model to solve its technical problem is: A hybrid propulsion system for unmanned aerial vehicles (UAVs) suitable for high-altitude environments includes: The mounting shell has mounting holes on both sides, a sealing groove on the front, and a protective groove at the top. A protective plate is threaded onto the inner wall of the protective groove, and a round hole is provided at the top of the protective plate.
[0006] Preferred options also include: A battery insulation component is installed inside a sealed groove to keep the battery warm.
[0007] Preferably, the battery insulation component includes: A sealing frame is slidably disposed inside a sealing groove. A circular groove is provided on one side of the sealing frame, and a travel groove is provided in the middle of the upper end of the sealing frame. A fixing plate is installed on the upper end of the sealing frame, and a storage battery is fixedly installed on the upper end of the fixing plate. A turntable is provided inside the circular groove.
[0008] Preferably, a rotating hole is provided on one side of the turntable, and a rotating rod is fixedly installed on the other side of the turntable. A bidirectional lead screw is fixedly installed at one end of the rotating rod, and one end of the bidirectional lead screw is set in the stroke groove through a bearing.
[0009] Preferably, the surface of the bidirectional lead screw is threadedly connected to a threaded block through a threaded hole. The threaded block is partially adapted to the stroke groove. A heating plate is bolted to the upper end of the threaded block, and a heating wire is provided inside the heating plate.
[0010] Preferred options also include: A propulsion assembly, which is installed inside a protective slot, is used for the forward thrust of the UAV.
[0011] Preferably, the propulsion assembly includes: A motor is bolted to the bottom of the protective groove. The output end of the motor is splined to a rotating rod. A rotating disk is fixedly installed at one end of the rotating rod, and the rotating disk is partially adapted to the circular hole.
[0012] Preferably, a transmission rod is fixedly installed at the upper end of the rotating disk, and a plurality of reinforcing rods are provided on the surface of the transmission rod, and a propeller is fixedly installed at the upper end of the transmission rod.
[0013] The beneficial effects of this utility model are: The battery insulation component of this invention uses an external power source to heat the heating plate via a heating wire. This heats the heating plate, which in turn rotates a turntable, causing a rotating rod to rotate. The rotating rod then rotates a bidirectional lead screw, which in turn moves a threaded block within a travel groove. This threaded block moves the heating plate, adjusting the distance between the heating plates and clamping them onto both sides of the battery. This process maintains a constant temperature for the battery, preventing it from becoming too cold and degrading or failing in high-altitude environments. It ensures the battery remains in optimal working condition in low-temperature conditions, guaranteeing the stable operation of the drone in high-altitude environments.
[0014] The power propulsion assembly of this invention uses an external power source connected to a motor to drive a rotating rod to rotate, which in turn drives a rotating disk to rotate. The rotating disk then drives a transmission rod to rotate, which in turn drives a propeller to rotate. The high-speed rotation of the propeller generates lift and thrust for the UAV, ensuring that the UAV can maintain sufficient thrust and flight stability in the low-density air of high altitudes. This solves the problem of insufficient power at high altitudes and adapts to special flight power requirements. Attached Figure Description
[0015] The accompanying drawings, which are included to provide a further understanding of the present invention and form part of this application, illustrate exemplary embodiments of the present invention and, together with the description thereof, serve to explain the present invention and do not constitute an undue limitation thereof. In the drawings: Figure 1 This is a perspective view of the present invention; Figure 2 This is an exploded view of the structure of this utility model; Figure 3 This is a three-dimensional view of the disassembled structure of the battery insulation component in this utility model; Figure 4 This is a utility model Figure 3 Enlarged view of the structure at point A in the middle; Figure 5 This is a three-dimensional view of the disassembled structure of the power propulsion component in this utility model.
[0016] Legend: 1. Mounting shell; 2. Mounting hole; 3. Sealing groove; 4. Protective groove; 5. Protective plate; 6. Round hole; 7. Battery insulation assembly; 701. Sealing frame; 702. Stroke groove; 703. Fixing plate; 704. Turntable; 705. Rotating rod; 706. Double-acting lead screw; 707. Threaded block; 708. Heating plate; 8. Power propulsion assembly; 801. Motor; 802. Rotating rod; 803. Rotating disk; 804. Transmission rod; 805. Reinforcing rod; 806. Propeller. Detailed Implementation
[0017] 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 skilled in the art without creative effort are within the protection scope of the present utility model.
[0018] Specific implementation examples are given below.
[0019] Example 1: Please see Figures 1 to 5 This utility model provides a hybrid propulsion device for unmanned aerial vehicles (UAVs) suitable for high-altitude environments, comprising: Mounting shell 1 has mounting holes 2 on both sides, a sealing groove 3 on the front, and a protective groove 4 at the top. A protective plate 5 is threaded onto the inner wall of the protective groove 4, and a round hole 6 is opened at the top of the protective plate 5. A battery insulation component 7 is installed inside the sealing groove 3 to insulate the battery. A power propulsion component 8 is installed inside the protective groove 4 to provide forward thrust for the UAV.
[0020] In this embodiment, the propulsion assembly 8 firstly generates lift and thrust for the UAV through the high-speed rotation of the propeller 806, ensuring that the UAV can maintain sufficient thrust and flight stability in the low-density air of the plateau, solving the problem of insufficient power at high altitudes and adapting to special flight power requirements; then, the battery insulation assembly 7 heats and maintains the temperature of the battery, preventing the battery from becoming too cold and degrading or failing in high-altitude environments, ensuring that the battery maintains its optimal working condition in low-temperature environments, and guaranteeing the stable operation of the UAV in the plateau environment.
[0021] Example 2: Based on Example 1, a battery insulation component 7 is further disclosed.
[0022] like Figure 1 , Figure 2 , Figure 3 and Figure 4 As shown, the battery insulation component 7 includes: A sealing frame 701 is slidably disposed inside the sealing groove 3. A circular groove is provided on one side of the sealing frame 701, and a stroke groove 702 is provided in the middle of the upper end of the sealing frame 701. A fixing plate 703 is installed on the upper end of the sealing frame 701, and a battery is fixedly installed on the upper end of the fixing plate 703. A turntable 704 is disposed inside the circular groove. A rotating hole is provided on one side of the turntable 704, and a rotating rod 705 is fixedly installed on the other side of the turntable 704. A double-acting screw 706 is fixedly installed on one end of the rotating rod 705. One end of the double-acting screw 706 is disposed in the stroke groove 702 through a bearing. A threaded block 707 is threadedly connected to the surface of the double-acting screw 706 through a threaded hole. The threaded block 707 is partially adapted to the stroke groove 702. A heating plate 708 is bolted to the upper end of the threaded block 707, and a heating wire is disposed inside the heating plate 708.
[0023] In this embodiment, the heating plate 708 is heated by an external power source connected to the heating wire. This heats up the turntable 704, causing the rotating rod 705 to rotate. The rotating rod 705 then drives the bidirectional lead screw 706 to rotate, which in turn moves the threaded block 707 within the travel groove 702. The threaded block 707 then moves the heating plate 708, adjusting the distance between the heating plates 708 and clamping them onto both sides of the battery. This heats and maintains a constant temperature for the battery, preventing it from becoming too cold and degrading or failing in high-altitude environments. This ensures the battery maintains optimal operating conditions in low-temperature environments and guarantees the stable operation of the UAV in high-altitude conditions.
[0024] Example 3: Based on Embodiment 1, the power propulsion component 8 is further disclosed.
[0025] like Figure 1 , Figure 2 and Figure 5 As shown, the propulsion assembly 8 includes: A motor 801 is bolted to the bottom of the protective groove 4. The output end of the motor 801 is splined to a rotating rod 802, which is made of alloy steel and nitrided. A rotating disk 803 is fixedly installed at one end of the rotating rod 802. The rotating disk 803 is made of aluminum alloy and has internal reinforcing ribs. The rotating disk 803 is partially fitted to the circular hole 6. A transmission rod 804 is fixedly installed at the upper end of the rotating disk 803. Multiple reinforcing rods 805 are provided on the surface of the transmission rod 804. A propeller 806 is fixedly installed at the upper end of the transmission rod 804. The propeller 806 adopts a plateau-specific airfoil, and the surface of the propeller hub of the propeller 806 is coated with an ice-repellent coating.
[0026] In this embodiment, the motor 801, powered by an external power source, drives the rotating rod 802 to rotate, which in turn drives the rotating disk 803 to rotate. The rotating disk 803 then drives the transmission rod 804 to rotate, which in turn drives the propeller 806 to rotate. The high-speed rotation of the propeller 806 generates lift and thrust for the UAV, ensuring that the UAV can maintain sufficient thrust and flight stability in the low-density air of high altitudes, solving the problem of insufficient power at high altitudes and adapting to special flight power requirements.
[0027] The foregoing has shown and described the basic principles, main features, and advantages of this utility model. Those skilled in the art should understand that this utility model is not limited to the above embodiments. The embodiments and descriptions in the specification are merely illustrative of the principles of this utility model. Various changes and modifications can be made to this utility model without departing from its spirit and scope, and all such changes and modifications fall within the scope of the claimed utility model.
Claims
1. A hybrid propulsion device for unmanned aerial vehicles (UAVs) suitable for high-altitude environments, characterized in that, include: Mounting shell (1), mounting holes (2) are provided on both sides of the mounting shell (1), a sealing groove (3) is provided on the front of the mounting shell (1), a protective groove (4) is provided at the upper end of the mounting shell (1), a protective plate (5) is installed on the inner side wall of the protective groove (4) by thread, and a round hole (6) is provided at the upper end of the protective plate (5).
2. The hybrid propulsion device for unmanned aerial vehicles (UAVs) suitable for high-altitude environments according to claim 1, characterized in that, Also includes: Battery insulation component (7) is installed inside the sealing groove (3) and is used to insulate the battery.
3. A hybrid propulsion device for unmanned aerial vehicles (UAVs) suitable for high-altitude environments according to claim 2, characterized in that, The battery insulation component (7) includes: A sealing frame (701) is slidably disposed inside the sealing groove (3). A circular groove is provided on one side of the sealing frame (701). A travel groove (702) is provided in the middle of the upper end of the sealing frame (701). A fixing plate (703) is installed on the upper end of the sealing frame (701). A storage battery is fixedly installed on the upper end of the fixing plate (703). A turntable (704) is provided inside the circular groove.
4. A hybrid propulsion device for unmanned aerial vehicles (UAVs) suitable for high-altitude environments according to claim 3, characterized in that: A rotating hole is provided on one side of the turntable (704), and a rotating rod (705) is fixedly installed on the other side of the turntable (704). A two-way lead screw (706) is fixedly installed at one end of the rotating rod (705), and one end of the two-way lead screw (706) is set in the stroke groove (702) through a bearing.
5. A hybrid propulsion device for unmanned aerial vehicles (UAVs) suitable for high-altitude environments according to claim 4, characterized in that: The surface of the bidirectional lead screw (706) is threadedly connected to a threaded block (707) through a threaded hole. The threaded block (707) is partially adapted to the stroke groove (702). A heating plate (708) is bolted to the upper end of the threaded block (707). A heating wire is provided inside the heating plate (708).
6. A hybrid propulsion device for unmanned aerial vehicles (UAVs) suitable for high-altitude environments according to claim 1, characterized in that, Also includes: A power propulsion assembly (8) is installed inside a protective groove (4) and is used for the forward thrust of the UAV.
7. A hybrid propulsion device for unmanned aerial vehicles (UAVs) suitable for high-altitude environments according to claim 6, characterized in that, The propulsion assembly (8) includes: A motor (801) is bolted to the bottom of the protective groove (4). The output end of the motor (801) is splined to a rotating rod (802). A rotating disk (803) is fixedly installed at one end of the rotating rod (802). The rotating disk (803) is partially adapted to the round hole (6).
8. A hybrid propulsion device for unmanned aerial vehicles (UAVs) suitable for high-altitude environments according to claim 7, characterized in that: A transmission rod (804) is fixedly installed on the upper end of the rotating disk (803), and a plurality of reinforcing rods (805) are provided on the surface of the transmission rod (804). A propeller (806) is fixedly installed on the upper end of the transmission rod (804).