Oil-electricity hybrid unmanned aerial vehicle
By using a hybrid power system, combining fuel supply, power generation, and rectifier, the problems of low battery energy density and unreasonable mass distribution in rotary-wing UAVs have been solved, enabling UAVs to achieve ultra-long endurance and operating distance.
Patent Information
- Application Number
- CN202520143574.8
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-01-21
- Publication Date
- 2026-01-30
- Estimated Expiration
- 2035-01-21
AI Technical Summary
Existing rotary-wing drones suffer from low battery energy density and unreasonable mass distribution, resulting in short flight time and short range, making it impossible to achieve ultra-long flight time and ultra-long distance operations.
The system employs a hybrid oil-electricity approach, where fuel is supplied to a generator to produce electricity. The generator then converts the electricity into direct current through a rectifier to power the flight propulsion system, enabling the drone to fly.
It improves the power and endurance of drones, achieving ultra-long flight time and operating distance.
Smart Images
Figure CN223850851U_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The utility model relates to unmanned plane technical field, concretely relates to an oil -electric hybrid unmanned plane. BACKGROUND
[0002] With the development of society, the rotor unmanned plane has gradually applied to military, rescue, transportation, communication, surveying and mapping, aerial photography and so on many fields, and the importance of the rotor unmanned plane becomes particularly prominent. At present, various types of rotor unmanned planes have been widely used.
[0003] The existing rotor unmanned plane usually adopts battery power supply, and the energy density of the battery is usually between 0.1 and 0.5 kWh / kg. The theoretical energy density limit of the current common ternary power battery is only 350 Wh / kg, which leads to short flight time, short flight range and inability to work for a long time and across a large distance. In addition, the mass distribution of the existing rotor unmanned plane is unreasonable, which leads to uneven distribution of motor currents of the rotor unmanned plane. The greater the current of the motor of the rotor unmanned plane, the more the working efficiency of the motor decreases exponentially, and the useless power increases exponentially, so that the total power consumption of the rotor unmanned plane increases, and the flight time of the rotor unmanned plane is further shortened.
[0004] Therefore, the existing rotor unmanned plane cannot realize the operation demand of super-long flight time and super-long distance. UTILITY MODEL CONTENT
[0005] The utility model aims at providing an oil -electric hybrid unmanned plane to solve the above technical problems in the prior art. The preferred technical scheme in the plurality of technical schemes provided by the utility model can produce a plurality of technical effects. Details are described below.
[0006] To achieve the above-mentioned purpose, the utility model provides the following technical scheme:
[0007] The utility model provides an oil -electric hybrid unmanned plane, which comprises a supporting mechanism, an oil supply device, a power generation device, a rectifier device and a flight power device, wherein: the oil supply device, the power generation device, the rectifier device and the flight power device are all arranged on the supporting mechanism; the oil supply device is connected with the power generation device through an oil circuit, and the power generation device is electrically connected with the flight power device through the rectifier device.
[0008] Preferably, the oil -electric hybrid unmanned plane further comprises a power supply device, the power supply device is arranged on the supporting mechanism, the power supply device is electrically connected with the flight power device, and the power supply device is connected in parallel at the output end of the rectifier device.
[0009] Preferably, the oil-electric hybrid unmanned aerial vehicle comprises a flight control device, and the power generation device is electrically connected with the flight control device through the rectifier device, and the flight control device is used for controlling the flight power device.
[0010] Preferably, the support mechanism comprises a frame and a plurality of arms, wherein the arms are uniformly distributed on the frame in a circumferential direction, and the flight power devices are arranged on the arms.
[0011] Preferably, the oil supply device comprises an oil tank assembly arranged on an upper side of the frame and located at a middle position of the frame.
[0012] Preferably, the power generation device comprises a generator assembly arranged on a lower side of the frame and located close to a middle position of the frame.
[0013] Preferably, the frame is provided with a mounting cavity, and the flight control device and the rectifier device are arranged in the mounting cavity.
[0014] Preferably, the flight power device comprises a driving motor and a rotor, wherein the driving motor is arranged at an end of the arm away from the frame, and the rotor is drivingly connected with a driving end of the driving motor.
[0015] Preferably, the frame is a polygonal frame, and the number of the arms is matched with the polygonal frame, so that the gravity center of the oil-electric hybrid unmanned aerial vehicle coincides with the geometric center.
[0016] Preferably, the polygonal frame is a hexagonal frame comprising six support corners, and the number of the flight power devices is six, and the six flight power devices are arranged on the six support corners, respectively.
[0017] The oil-electric hybrid unmanned aerial vehicle provided by the utility model has at least the following beneficial effects:
[0018] The oil-electric hybrid unmanned aerial vehicle comprises a support mechanism, an oil supply device, a power generation device, a rectifier device and a flight power device, and the oil supply device, the power generation device, the rectifier device and the flight power device are arranged on the support mechanism.
[0019] The oil supply device is connected with the power generation device through an oil path, the power generation device is electrically connected with the flight power device through the rectifier device, and the oil supply device provides fuel for the power generation device through the oil path during flight, the power generation device generates power by taking fuel as raw material, then the rectifier device converts the alternating current generated by the power generation device into direct current and supplies to the flight power device, thereby realizing flight.
[0020] The utility model discloses a support mechanism, oil supply device, power generation device, rectifier device and flight power device cooperate with each other, realize flight by adopting oil electricity hybrid mode, compared with the prior art ternary power battery driven mode, not only power is sufficient, but also has super long duration and super long operation distance. BRIEF DESCRIPTION OF DRAWINGS
[0021] In order to more clearly illustrate the technical scheme in the embodiment of the utility model or prior art, the following will be briefly introduced to the drawing needed to be used in the embodiment or prior art description, obviously, the drawing in the following description only some embodiments of the utility model, for ordinary skilled person in the art, under the premise of not paying creative labor, can also obtain other drawings according to these drawings.
[0022] Figure 1 It is the structural schematic diagram of the utility model;
[0023] Figure 2 It is the bottom view schematic diagram of the utility model;
[0024] Figure 3 It is the top view schematic diagram of the utility model;
[0025] Figure 4 It is the front view schematic diagram of the utility model;
[0026] Figure 5 It is the A part of the utility model enlarged view.
[0027] Reference signs
[0028] 1, support mechanism;2, oil supply device;21, oil tank assembly;11, rack;12, arm;13, landing gear;3, power generation device;31, generator assembly;4, rectifier device;5, flight power device;51, drive motor;52, rotor;6, power supply device;7, flight control device. DETAILED DESCRIPTION
[0029] In order to make the purpose, technical scheme and advantages of the utility model more clear, the technical scheme of the utility model will be described in detail below. Obviously, the described embodiments are only part of the embodiments of the utility model, not all. Based on the embodiments in the utility model, all other embodiments obtained by those skilled in the art without creative labor belong to the scope protected by the utility model.
[0030] Embodiment 1:
[0031] The utility model provides a kind of oil-electric hybrid unmanned aerial vehicle, reference Figures 1 to 5 As shown, the oil-electric hybrid unmanned aerial vehicle includes support mechanism 1, oil supply device 2, power generation device 3, rectifier device 4 and flight power device 5.
[0032] Oil supply device 2, power generation device 3, rectifier device 4 and flight power device 5 are all arranged on support mechanism 1;Oil supply device 2 is connected with power generation device 3 by oil circuit, and power generation device 3 is electrically connected with flight power device 5 by rectifier device 4.
[0033] When flying, oil supply device 2 provides fuel to power generation device 3 through oil circuit, and power generation device 3 operates, to convert the heat energy of fuel into mechanical energy, and then convert the mechanical energy into electrical energy, then, rectifier device 4 converts the alternating current generated by power generation device 3 into direct current, and supplies to flight power device 5, and flight power device 5 acts, to realize the flight of the oil-electric hybrid unmanned aerial vehicle.
[0034] Because the energy density of fuel is about 12kWh / kg, and the theoretical maximum efficiency of engine is about 36%, and the actual efficiency is about 20%, which means that 2.4kWh of electrical energy can be generated per kilogram of fuel. The energy density of battery is usually between 0.1 and 0.5kWh / kg, for example, the theoretical limit of unit mass energy density of the widely used high-energy-density ternary power battery is 350Wh / kG;Therefore, the electrical energy stored by the battery is much lower than the electrical energy generated by the fuel under the same mass.
[0035] The utility model cooperates oil supply device 2, power generation device 3 and rectifier device 4, adopts oil-electric hybrid mode, compared with current ternary power battery, not only power is sufficient, but also can effectively improve endurance.
[0036] Embodiment 2:
[0037] Embodiment 2 is based on embodiment 1:
[0038] As Figures 1 to 5As shown, the oil-electric hybrid unmanned aerial vehicle further comprises a power supply device 6, which is arranged on the support mechanism 1 and is electrically connected with the flight power device 5, and is arranged in parallel at the output end of the rectifier device 4.
[0039] The power supply device 6 is essentially an independent battery, which is used after the oil-electric hybrid unmanned aerial vehicle is started and the power generation device 3 is stopped, and participates in the take-off and landing process of the oil-electric hybrid unmanned aerial vehicle.
[0040] As an optional implementation, the oil-electric hybrid unmanned aerial vehicle comprises a flight control device 7, the power generation device 3 is electrically connected with the flight control device 7 through the rectifier device 4, and the flight control device 7 is used for controlling the flight power device 5 to ensure normal flight of the oil-electric hybrid unmanned aerial vehicle.
[0041] As an optional implementation, the support mechanism 1 comprises a frame 11 and an arm 12.
[0042] The frame 11 is a frame structure, the arm 12 is arranged on the frame 11, the number of the arms 12 is arranged to be multiple, all the arms 12 are uniformly distributed on the frame 11 in a circumferential direction, the number of the flight power devices 5 is the same as that of the arms 12, and the flight power devices 5 are arranged on the corresponding arms 12.
[0043] The oil-electric hybrid unmanned aerial vehicle is a multi-wing unmanned aerial vehicle, and in actual use, a plurality of types are formed according to the number.
[0044] In addition, the distribution of mass is particularly important when the unmanned aerial vehicle is sailing, a reasonable layout can make the unmanned aerial vehicle sail more stably, and the efficiency of the motor of the unmanned aerial vehicle will be reduced with the increase of current, so that the total power of the motor is high if the layout is unreasonable, therefore, a reasonable layout can also reduce the energy consumption generated when the unmanned aerial vehicle sails.
[0045] The oil-electric hybrid unmanned aerial vehicle is a multi-wing unmanned aerial vehicle, and in actual use, a plurality of types are formed according to the number.
[0046] As an optional implementation, the oil supply device 2 comprises an oil tank assembly 21, which is arranged on the upper side of the frame 11 and is located at the middle position of the frame 11, and the centrally arranged oil tank assembly 21 makes the stress more balanced.
[0047] As an optional implementation, the power generation device 3 comprises a generator assembly 31, which is arranged on the lower side of the frame 11 and is located at a position close to the middle of the frame 11; in this way, the generator assembly 31 close to the middle position is located below the oil tank assembly 21, so that the fuel can smoothly enter the generator assembly 31, and the reliability of fuel supply is ensured.
[0048] As an optional implementation, the rack 11 is provided with a mounting cavity, and the flight control device 7 and the rectifier device 4 are arranged in the mounting cavity, so that the flight control device 7 and the rectifier device 4 can be effectively protected.
[0049] As an optional implementation, the flight power device 5 comprises a driving motor 51 and a rotor 52, the driving motor 51 is arranged at the end of the arm 12 away from the rack 11, and the rotor 52 is drivingly connected to the driving end of the driving motor 51.
[0050] During flight, the power generation device 3 provides direct current to the driving motor 51 through the rectifier device 4, the driving motor 51 works to drive the rotor 52 to rotate, thereby realizing flight.
[0051] As an optional implementation, the rack 11 is provided as a polygonal rack, the number of arms 12 is matched with the polygonal rack 11, and the gravity center of the oil-electric hybrid unmanned aerial vehicle coincides with the geometric center.
[0052] In this way, the oil-electric hybrid unmanned aerial vehicle can obtain better stability and lower energy consumption.
[0053] As an optional implementation, the polygonal rack 11 is provided as a hexagonal rack 11, the hexagonal rack 11 is provided as a hexagon with six support corners, the number of flight power devices 5 is six, and the six flight power devices 5 are arranged on the six support corners, respectively, and the oil-electric hybrid unmanned aerial vehicle is a six-wing unmanned aerial vehicle.
[0054] The bottom side of the hexagonal rack 11 is provided with three landing gears 13 uniformly distributed in the circumferential direction, the three landing gears 13 are arranged at intervals in the circumferential direction and are arranged at the bottom side of the corresponding support corners, the landing gear 13 comprises a landing leg and a reinforcing rod, the reinforcing rod is arranged obliquely, and the two ends of the reinforcing rod are connected to the rack 11 and the corresponding landing leg, respectively.
[0055] In the description of the present application, it should be understood that the terms "upper", "lower", "inner", "outer", "top", "bottom" and the like indicate the orientation or positional relationship shown in the drawings, and are only for the purpose of facilitating the description of the present application and simplifying the description, and do not indicate or imply that the indicated device or element must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present application.
[0056] In addition, the terms "first", "second" are only for the purpose of description, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first", "second" can explicitly or implicitly include at least one of the features. In the description of the present application, the meaning of "a plurality of", "several" is at least two, for example, two, three, etc., unless otherwise explicitly specified.
[0057] In this application, unless otherwise clearly specified and limited, the terms "mounting", "connection", "connecting", "fixing" and the like should be understood in a broad sense, for example, can be fixed connection, can also be detachable connection, or integral; can be directly connected, or indirectly connected through an intermediate medium, can be the internal communication of two elements or the interaction relationship of two elements, unless otherwise clearly limited. For those skilled in the art, the specific meaning of the above terms in this application can be understood according to the specific circumstances.
[0058] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited to this. Any person skilled in the art can easily think of changes or replacements within the technical range disclosed by the present application, which should be covered within the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.
Claims
1. An oil-electric hybrid drone, characterized in that, The oil-electric hybrid unmanned aerial vehicle comprises a supporting mechanism, an oil supply device, a power generation device, a rectifying device and a flight power device, wherein: The oil supply device, the power generation device, the rectifying device and the flight power device are arranged on the supporting mechanism; the oil supply device is connected with the power generation device through an oil path; the power generation device is electrically connected with the flight power device through the rectifying device.
2. The hybrid-electric unmanned aerial vehicle of claim 1, wherein, The oil-electric hybrid unmanned aerial vehicle further comprises a power supply device, which is arranged on the supporting mechanism and is electrically connected with the flight power device, and is arranged in parallel at the output end of the rectifying device.
3. The hybrid electric-oil unmanned aerial vehicle according to claim 1, wherein, The oil-electric hybrid unmanned aerial vehicle comprises a flight control device, the power generation device is electrically connected with the flight control device through the rectifying device, and the flight control device is used for controlling the flight power device.
4. The hybrid electric-oil unmanned aerial vehicle according to claim 3, wherein, The supporting mechanism comprises a frame and arms, wherein: The number of the arms is multiple, and all the arms are uniformly distributed on the frame in a circumferential direction; The number of the flight power devices is the same as that of the arms, and the flight power devices are arranged on the corresponding arms.
5. The hybrid-electric unmanned aerial vehicle of claim 4, wherein, The oil supply device comprises an oil tank assembly, which is arranged on the upper side of the frame and is located at the middle position of the frame.
6. The hybrid electric-oil drone of claim 4, wherein, The power generation device comprises a power generator assembly, which is arranged on the lower side of the frame and is located at the position close to the middle of the frame.
7. The hybrid electric-oil drone of claim 4, wherein, The frame is provided with a mounting cavity, and the flight control device and the rectifying device are arranged in the mounting cavity.
8. The hybrid electric-oil drone of claim 4, wherein, The flight power device comprises a driving motor and a rotor, wherein: The driving motor is arranged at the end position of the arm away from the frame; The rotor is drivingly connected with the driving end of the driving motor.
9. The hybrid-electric unmanned aerial vehicle of claim 4, wherein, The frame is arranged as a polygonal frame, and the number of the arms is adapted to the polygonal frame, so that the gravity center of the oil-electric hybrid unmanned aerial vehicle coincides with the geometric center.
10. The hybrid-electric unmanned aerial vehicle of claim 9, wherein, The polygonal frame is arranged as a hexagonal frame, the number of the flight power devices is six, and the six flight power devices are arranged on the six supporting corners, respectively; The bottom side of the hexagonal frame is provided with three landing gears which are spaced apart in a circumferential direction and are arranged at the bottom side of the corresponding supporting corners.