Hybrid-power cannon-launched unmanned aerial vehicle

Abstract

The utility model relates to a hybrid power cannon-launched unmanned aerial vehicle which comprises an unmanned aerial vehicle body, a power assembly and a transmission assembly, the unmanned aerial vehicle body is provided with an engine compartment, the power assembly and the transmission assembly are arranged in the engine compartment, and the power assembly comprises an energy storage battery, a fuel oil engine and a starter-generator. The transmission assembly comprises a driving wheel, a driven wheel and a speed-changing gear box, the energy storage battery is electrically connected with the starter-generator, and the starter-generator is in transmission connection with the fuel engine and used for starting the fuel engine, generating electric energy under driving of the fuel engine when the fuel engine works and outputting the electric energy to the energy storage battery. The driving wheel is in power connection with the starter-generator and the fuel engine, the driven wheel is in transmission connection with the driving wheel, the driven wheel is connected with an input shaft of the speed-changing gear box, and an output shaft of the speed-changing gear box is connected with a rotor wing of the cannon-launch unmanned aerial vehicle. The power output state can be adjusted according to all states of the unmanned aerial vehicle from launching to cruising, energy loss is reduced, and the fuel oil utilization rate is improved.

Description

Technical Field

[0001] The utility model belongs to the technical field of unmanned aerial vehicles, and in particular relates to a hybrid power cannon-launched unmanned aerial vehicle. Background Art

[0002] Commonly used drones are mostly powered by pure electric or pure fuel engines. Pure electric engines are easy to control and have high stability, but their endurance is poor. Pure fuel engines have high requirements for oxygen concentration and poor response control sensitivity, making them difficult to apply to high altitude and high speed areas and areas that require precise positioning or stabilization of the aircraft. In the case of drone takeoff weight restrictions, it is necessary to improve fuel utilization and increase range.

[0003] However, for artillery-fired UAVs, when switching to fuel engines, the cross-sectional space of the engine compartment is limited and it is impossible to install market-standard engine components. When the engine installation space is limited, the engine structure needs to be adjusted.

[0004] In summary, there is an urgent need to provide a hybrid power gun-launched UAV that can adjust the power output state according to the various states from UAV launch to cruising, reduce energy loss, and improve fuel utilization. Utility Model Content

[0005] The utility model aims to provide a hybrid power gun-launched UAV which can adjust the power output state according to various states from the launch to the cruising of the UAV, reduce the loss of energy and improve the fuel utilization rate.

[0006] The above-mentioned purpose is achieved through the following technical scheme: a hybrid power artillery-fired UAV, comprising a UAV body, a power assembly and a transmission assembly, the UAV body is provided with an engine compartment, the power assembly and the transmission assembly are arranged in the engine compartment, the power assembly comprises an energy storage battery, a fuel engine and an inspiration motor, the transmission assembly comprises a driving wheel, a driven wheel and a gear transmission, the energy storage battery is electrically connected to the inspiration motor, the inspiration motor is transmission-connected to the fuel engine, and is used to start the fuel engine and generate electrical energy under the drive of the fuel engine when the fuel engine is working and output it to the energy storage battery, the driving wheel is power-connected to the inspiration motor and the fuel engine, the driven wheel is transmission-connected to the driving wheel, the driven wheel is connected to the input shaft of the gear transmission, and the output shaft of the gear transmission is connected to the rotor of the artillery-fired UAV.

[0007] The utility model adjusts the engine assembly as a whole to suit the installation space requirements of the artillery-launched UAV. When the engine output position is limited, a transmission assembly is added to the engine output shaft to adjust the output direction of the engine, thereby simplifying the structure of the mechanical transmission device of the UAV and improving the reliability of the UAV.

[0008] During the application process, during the launch preparation stage of the UAV, the energy storage battery provides electric energy to operate the inspiration motor instead of the fuel engine output, that is, the energy storage battery provides electric energy to drive the inspiration motor, the inspiration motor drives the driving wheel to move, the power is transmitted to the driving driven wheel, and is output to the rotor of the cannon-launched UAV after passing through the gear transmission to prepare for launch; during the launch stage of the UAV, the energy storage battery provides electric energy to drive the inspiration motor, the inspiration motor works and starts the fuel engine, and at the same time, the inspiration motor still drives the driving wheel to move, and the power is output to the rotor of the cannon-launched UAV; during the climbing stage of the UAV, the fuel engine drives the driving wheel to move, the power is transmitted to the driving driven wheel, and is output to the rotor of the cannon-launched UAV after passing through the gear transmission to provide power for climbing, and the inspiration motor also drives the driving wheel to move to provide auxiliary power; during the cruising stage of the UAV, the fuel engine drives the inspiration motor to work, and the inspiration motor generates electric energy at idle speed or overflow kinetic energy state and outputs it to the energy storage battery for energy storage. During the cruising phase of the drone, when the energy storage battery is fully charged, the fuel engine can be shut down according to the range conditions, and only the energy storage battery can be used to provide electricity to operate the inspiration motor instead of the fuel engine output, thereby further improving fuel utilization.

[0009] The utility model can adjust the power output state according to various states of the UAV from launching to cruising, reduce energy loss and improve fuel utilization.

[0010] A further technical solution is that the rotating shaft of the fuel engine, the rotating shaft of the induction motor and the rotating shaft of the driving wheel are coaxially arranged.

[0011] A further technical solution is that the induction motor is arranged on the upper part of the fuel engine, the driving wheel is arranged on the upper part of the induction motor, the gear box is arranged on one side of the fuel engine, the driven wheel is arranged on the upper part of the gear box, the output shaft of the gear box is arranged horizontally, and the input shaft of the gear box is arranged vertically. In this way, the engine assembly is adjusted as a whole to meet the installation space requirements of the gun-launched UAV. The output direction of the engine is adjusted, the structure of the mechanical transmission device of the UAV is simplified, and the reliability of the UAV is improved.

[0012] A further technical solution is that the fuel engine is provided with an air inlet and an exhaust pipe, and the exhaust pipe is arranged horizontally and below the gear transmission.

[0013] A further technical solution is that the driving wheel and the driven wheel are connected via a transmission belt.

[0014] A further technical solution is that the gun-launched UAV also includes a controller, which is used to control the power output of the inspiration motor, or start the fuel engine, or control the input current to the energy storage battery pack when the inspiration motor is in a power generation state. In a specific application process, the controller includes a central control circuit, a motor drive module, and a rectifier output circuit, and the above circuits are prior art.

[0015] A further technical solution is that the fuel engine is provided with a heat sink, the engine compartment is provided with heat dissipation holes, and the heat sink penetrates the heat dissipation holes. Such an arrangement is beneficial to the heat dissipation of the fuel engine.

[0016] A further technical solution is that the heat sink is made of thermally conductive silicone.

[0017] Compared with the prior art, the utility model adjusts the engine assembly as a whole to suit the required form of the gun-launched UAV, with a simple structure and simple control. When the engine output position is limited, the transmission assembly is added to the engine output shaft to adjust the engine output direction, simplify the structure of the mechanical transmission device of the UAV, and improve the reliability of the UAV. At the same time, the electric drive and oil-driven direct drive are integrated, and the power output state can be adjusted according to the various states of the UAV from launch to cruising, reducing energy loss, improving fuel utilization, and improving the endurance and effective load capacity of the UAV. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] The accompanying drawings constituting a part of the present invention are used to provide a further understanding of the present invention. The illustrative embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation on the present invention.

[0019] Figure 1 This is a schematic structural diagram of a gun-launched UAV according to one embodiment of the utility model;

[0020] Figure 2 The utility model is a schematic diagram of the connection structure of the power assembly and the transmission assembly involved in one embodiment.

[0021] In the figure:

[0022] 1Energy storage battery 2Fuel engine 3Initiator motor 4Drive wheel

[0023] 5 transmission belt 6 driven wheel 7 gear box 8 output shaft

[0024] 9 UAV body 10 engine compartment 11 rotor 12 air intake

[0025] 13 Exhaust pipe DETAILED DESCRIPTION

[0026] The present invention is described in detail below in conjunction with the accompanying drawings. The description in this section is only exemplary and explanatory and should not have any limiting effect on the scope of protection of the present invention. In addition, those skilled in the art can make corresponding combinations of the features in the embodiments and in different embodiments of the present invention according to the description of this document.

[0027] The utility model embodiments are as follows, referring to Figure 1 and Figure 2 A hybrid power gun-launched UAV comprises a UAV body 9, a power assembly and a transmission assembly, wherein the UAV body 9 is provided with an engine compartment 10, wherein the power assembly and the transmission assembly are arranged in the engine compartment 10, wherein the power assembly comprises an energy storage battery 1, a fuel engine 2 and an inspiration motor 3, wherein the transmission assembly comprises a driving wheel 4, a driven wheel 6 and a gear transmission case 7, wherein the energy storage battery 1 is electrically connected to the inspiration motor 3, wherein the inspiration motor 3 is transmission-connected to the fuel engine 2 for starting the fuel engine 2 and generating electric energy under the drive of the fuel engine 2 when the fuel engine 2 is working and outputting the electric energy to the energy storage battery 1, wherein the driving wheel 4 is power-connected to the inspiration motor 3 and the fuel engine 2, wherein the driven wheel 6 is transmission-connected to the driving wheel 4, wherein the driven wheel 6 is connected to the input shaft of the gear transmission case 7, and wherein the output shaft 8 of the gear transmission case 7 is connected to the rotor 11 of the gun-launched UAV.

[0028] The utility model adjusts the engine assembly as a whole to suit the installation space requirements of the artillery-launched UAV. When the engine output position is limited, a transmission assembly is added to the engine output shaft 8 to adjust the output direction of the engine, thereby simplifying the structure of the mechanical transmission device of the UAV and improving the reliability of the UAV.

[0029] During the application process, in the UAV launch preparation stage, the energy storage battery 1 provides electric energy to make the inspiration motor 3 operate instead of the fuel engine 2 output, that is, the energy storage battery 1 provides electric energy to drive the inspiration motor 3, the inspiration motor 3 drives the driving wheel 4 to move, the power is transmitted to the driving driven wheel 6, and is output to the rotor 11 of the cannon-launched UAV after passing through the gear box 7, so as to prepare for the launch; in the UAV launch stage, the energy storage battery 1 provides electric energy to drive the inspiration motor 3, the inspiration motor 3 works and starts the fuel engine 2, and at the same time, the inspiration motor 3 still drives the driving wheel 4 to move, and the power is output to the rotor 11 of the cannon-launched UAV; in the UAV climbing stage, the fuel engine 2 drives the driving wheel 4 to move, the power is transmitted to the driving driven wheel 6, and is output to the rotor 11 of the cannon-launched UAV after passing through the gear box 7, providing power for climbing, and the inspiration motor 3 also drives the driving wheel 4 to move, providing auxiliary power; in the UAV cruising stage, the fuel engine 2 drives the inspiration motor 3 to work, and the inspiration motor 3 generates electric energy at idle speed or overflow kinetic energy state and outputs it to the energy storage battery 1 for energy storage. During the cruising phase of the UAV, when the energy storage battery 1 is fully charged, the fuel engine 2 can be shut down according to the range conditions, and only the energy storage battery 1 is used to provide electricity to operate the inspiration motor 3 instead of the fuel engine 2 output, thereby further improving fuel utilization.

[0030] The utility model can adjust the power output state according to various states of the UAV from launching to cruising, reduce energy loss and improve fuel utilization.

[0031] Based on the above embodiment, in another embodiment of the utility model, as Figure 2 The rotating shaft of the fuel engine 2, the rotating shaft of the induction motor 3 and the rotating shaft of the driving wheel 4 are coaxially arranged.

[0032] Based on the above embodiment, in another embodiment of the utility model, as Figure 2 The induction motor 3 is arranged on the upper part of the fuel engine 2, the driving wheel 4 is arranged on the upper part of the induction motor 3, the gear box 7 is arranged on one side of the fuel engine 2, the driven wheel 6 is arranged on the upper part of the gear box 7, the output shaft 8 of the gear box 7 is arranged horizontally, and the input shaft of the gear box 7 is arranged vertically. In this way, the engine assembly is adjusted as a whole to meet the installation space requirements of the gun-launched UAV. The output direction of the engine is adjusted, the structure of the mechanical transmission device of the UAV is simplified, and the reliability of the UAV is improved.

[0033] Based on the above embodiment, in another embodiment of the utility model, as Figure 2 The fuel engine 2 is provided with an air intake 12 and an exhaust pipe 13 , and the exhaust pipe 13 is arranged horizontally and below the gear transmission case 7 .

[0034] Based on the above embodiment, in another embodiment of the utility model, as Figure 2 The driving wheel 4 is connected to the driven wheel 6 through a transmission belt 5.

[0035] On the basis of the above embodiment, in another embodiment of the utility model, the gun-launched UAV further includes a controller, which is used to control the output power of the inspiration motor 3, or start the fuel engine 2, or control the input current to the energy storage battery 1 when the inspiration motor 3 is in the power generation state. In the specific application process, the controller includes a central control circuit, a motor drive module and a rectifier output circuit, and the above circuit is the prior art.

[0036] Based on the above embodiment, in another embodiment of the utility model, the fuel engine 2 is provided with a heat sink, the engine compartment 10 is provided with a heat dissipation hole, and the heat sink penetrates the heat dissipation hole. Such an arrangement is beneficial to the heat dissipation of the fuel engine 2.

[0037] Based on the above embodiment, in another embodiment of the utility model, the heat sink is made of thermally conductive silicone.

[0038] Compared with the prior art, the utility model adjusts the engine assembly as a whole to suit the required form of the gun-launched UAV, has a simple structure and simple control, and when the engine output position is limited, by adding a transmission assembly to the engine output shaft 8, the output direction of the engine is adjusted, the structure of the mechanical transmission device of the UAV is simplified, and the reliability of the UAV is improved. At the same time, the electric drive and oil-driven direct drive are integrated, and the power output state can be adjusted according to the various states of the UAV from launch to cruising, which reduces energy loss, improves fuel utilization, and improves the endurance and effective load capacity of the UAV.

[0039] The above is only a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the principle of the present invention. These improvements and modifications should also be regarded as the protection scope of the present invention.

Claims

1. A hybrid power gun-launched UAV, comprising a UAV body, a power assembly and a transmission assembly, wherein the UAV body is provided with an engine compartment, the power assembly and the transmission assembly are arranged in the engine compartment, and characterized in that: The power component includes an energy storage battery, a fuel engine and an inspiration motor, and the transmission component includes a driving wheel, a driven wheel and a gear transmission. The energy storage battery is electrically connected to the inspiration motor, and the inspiration motor is transmission-connected to the fuel engine for starting the fuel engine and generating electrical energy driven by the fuel engine when the fuel engine is working and outputting it to the energy storage battery. The driving wheel is power-connected to the inspiration motor and the fuel engine, and the driven wheel is transmission-connected to the driving wheel. The driven wheel is connected to the input shaft of the gear transmission, and the output shaft of the gear transmission is connected to the rotor of the gun-launched UAV.

2. The hybrid gun-launched UAV according to claim 1, characterized in that: The rotating shaft of the fuel engine, the rotating shaft of the induction motor and the rotating shaft of the driving wheel are coaxially arranged.

3. The hybrid gun-launched UAV according to claim 2, characterized in that: The induction motor is arranged on the upper part of the fuel engine, the driving wheel is arranged on the upper part of the induction motor, the gear transmission is arranged on one side of the fuel engine, the driven wheel is arranged on the upper part of the gear transmission, the output shaft of the gear transmission is arranged horizontally, and the input shaft of the gear transmission is arranged vertically.

4. The hybrid gun-launched UAV according to claim 3, characterized in that: The fuel engine is provided with an air inlet and an exhaust pipe, and the exhaust pipe is arranged horizontally and below the gear transmission box.

5. The hybrid gun-launched UAV according to any one of claims 1 to 4, characterized in that: The driving wheel and the driven wheel are connected via a transmission belt.

6. The hybrid gun-launched UAV according to any one of claims 1 to 4, characterized in that: The gun-launched UAV also includes a controller, which is used to control the power output of the inspiration motor, or start the fuel engine, or control the input current to the energy storage battery pack when the inspiration motor is in a power generation state.

7. The hybrid gun-launched UAV according to claim 6, characterized in that: The fuel engine is provided with a heat sink, the engine compartment is provided with a heat dissipation hole, and the heat sink passes through the heat dissipation hole.

8. The hybrid gun-launched UAV according to claim 7, characterized in that: The heat sink is made of thermally conductive silica gel.

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