Unmanned aerial vehicle ground auxiliary equipment driven by eddy current

Abstract

The invention relates to eddy-current-driven unmanned aerial vehicle ground auxiliary equipment which has the functions of high-pressure suction, high-pressure hot air blowing and ground power supply and can be used for ground cooling or heating of an unmanned aerial vehicle and ground power supply. Comprising a casing, an air inlet cone, a fan blade disc, a pressurizing blade disc and a motor which share the same rotating shaft, and a turbine blade disc and a generator which share the other rotating shaft; the turbocharging blade disc, the motor, the storage battery, the power distribution management system, the generator and the turbine blade disc are wrapped by the eddy current system inner casing; the motor, the storage battery and the generator are respectively connected with the power distribution management system, and the power supply cable is connected with the power distribution management system and extends out of the auxiliary equipment through the hollow rectification partition plate; an annular inner duct and an annular combustion area are formed between the eddy current system outer casing and the eddy current system inner casing, the eddy current system is fixed on the auxiliary equipment casing, and a fuel inlet pipeline extending out of the auxiliary equipment is arranged at the combustion area.

Description

Technical Field

[0001] The present invention belongs to the field of unmanned aerial vehicles, and in particular relates to a vortex-electric driven unmanned aerial vehicle ground auxiliary equipment. Background Art

[0002] Before taking off or during ground testing, the drone needs to directly power the electrical equipment on the aircraft through ground equipment. At the same time, during the ground testing, some heating equipment of the drone needs to be cooled on the ground through high-speed airflow to achieve normal operation. At the same time, in a low-temperature environment, the drone power unit needs to be heated by hot airflow to reach the starting temperature that meets the normal start of the drone. In both cases, if sufficient cooling wind speed and air volume are required, or high-temperature and high-speed airflow is required, huge energy input is required. At this time, if an electric drive fan or electric heating equipment is used, large-sized, high-power density motors and high-power electric heating equipment are required, and the power supply demand of the drone itself also needs to be met by additional power supply equipment. Large-sized, high-power motors and high-power electric heating equipment require very high-power current input and huge supporting current control equipment. However, most of the above scenarios do not have sufficient current supply capacity or distribution cabinet space.

[0003] Therefore, an unmanned aerial vehicle ground auxiliary equipment that has its own power supply capability, large wind volume and high wind speed suction, and high-temperature hot air flow heating function has extremely high practical value. Summary of the invention

[0004] The purpose of the present invention is to meet the actual needs of powering a UAV, providing a high-speed and high-volume cooling airflow for UAV thermal components, and providing a high-temperature and high-volume airflow for heating and starting the UAV power system in a low-temperature environment.

[0005] The present invention is achieved by the following technical solutions:

[0006] A turboelectric driven unmanned aerial vehicle ground auxiliary equipment, comprising a casing 05 and a turboelectric system 10 wrapped therein, wherein an air intake cone 02, a fan blade disk 01, a supercharger blade disk 11, a motor 06, a battery 09, a power distribution management system 07, a generator 03 and a turbine blade disk 13 wrapped in the casing 05 are arranged in sequence, wherein the air intake cone 02, the fan blade disk 01, the supercharger blade disk 11 and the motor 06 share the same rotating shaft, and the turbine blade disk 13 and the generator 03 share another rotating shaft; the casing 15 in the turboelectric system wraps the supercharger blade disk 11, the motor 06, the battery 09, the power distribution management system 07, the transmission cable 08, the generator 03 and Turbine blade disk 13; motor 06, battery 09, generator 03 are respectively connected to the distribution management system 07 through transmission cable 08, power supply cable 17 is connected to the distribution management system 07 and extends to the outside of the auxiliary equipment through the hollow rectifying baffle 04; an annular inner channel 32 and an annular combustion zone 12 are formed between the outer casing 14 of the turbo-electric system and the inner casing 15 of the turbo-electric system, the turbo-electric system 10 is fixed to the auxiliary equipment casing 05 through a circle of rectifying baffles 04, a pipeline extending to the outside of the auxiliary equipment is provided at the combustion zone 12, a fuel inlet 16 is provided at the end of the pipeline, and the outer diameter of the blades on the fan blade disk 01 is smaller than the inner diameter of the casing 05.

[0007] The number of the fan blades is 18 to 50, which are evenly distributed circumferentially on the fan disk 01; the number of the rectifying baffles 04 is 10 to 30, which are evenly distributed circumferentially; the aspect ratio of the blades on the fan disk 01 is between 1.5 and 5; the outer diameter of the vortex electric system 10 does not exceed 60% of the inner diameter of the auxiliary equipment casing 05.

[0008] The turbo-electric system 10 may be a dual-rotor, multi-stage turbine and supercharging system, and is not limited to a single-shaft, single-stage turbocharging system.

[0009] The invention has the function of self-generating power supply, and at the same time has the functions of suction and hot air blowing with high total pressure and large air volume. After reaching stable operation, the fan has a strong suction capacity for the air in front of the fan. The suction and exhaust capacity of auxiliary equipment of different specifications is different. After calculation, the auxiliary equipment with a diameter of 1.5 meters has a total pressure of 50000Pa and an air volume of 230m 3 / s, the temperature of the high-temperature airflow 23 at the outlet of the vortex electric system 10 can reach 400-600°C, and the average temperature of the mixed airflow 22 and the high-temperature airflow 23 at the outlet of the auxiliary equipment is 100-200°C.

[0010] At the same time, the energy source of the auxiliary equipment of the present invention is fossil fuel, which does not need to rely on high-power power supply environment and large-scale power distribution control equipment, so it is portable and can be used in various scenarios that do not have high-power supply capabilities. At the same time, the power distribution management system can distribute power or power in the battery to the outside of the auxiliary equipment system to power other devices in need.

[0011] In scenarios where power supply is the main demand, the turboelectric system can operate in the most efficient working state, with high combustion efficiency, low fuel consumption per unit power and low carbon emissions. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] Figure 1 is an axonometric view of the present invention;

[0013] Figure 2 It is a structural diagram of the present invention;

[0014] Figure 3 yes Figure 2 AA view of the .

[0015] In the figure, 01-fan blade disk, 02-intake cone, 03-generator, 04-rectifier baffle, 05-casing, 06-motor, 07-power distribution management system, 08-transmission cable, 09-battery, 10-turboelectric system, 11-boost blade disk, 12-combustion zone, 13-turbine blade disk, 14-turboelectric system outer casing, 15-turboelectric system inner casing, 16-fuel inlet, 17-power supply cable, 21-intake airflow, 22-high temperature airflow, 23-cold airflow, 31-outer duct, 32-inner duct. DETAILED DESCRIPTION

[0016] The present invention relates to a ground auxiliary equipment for unmanned aerial vehicles (UAVs) which adopts an eddy-electric system as a power source and has high-voltage suction, high-voltage hot blowing and ground power supply functions, and can be used for ground cooling or heating of UAVs, as well as ground power supply.

[0017] like Figure 1-3As shown, the specific structure of the present invention is as follows: the entire auxiliary equipment is wrapped by the auxiliary equipment casing 05, the core component is the turboelectric system 10, the air intake cone 02, the fan blade disk 01, the supercharger blade disk 11 and the motor 06 share the same rotating shaft, and the turbine blade disk 13 and the generator 03 share another rotating shaft; the turboelectric system inner casing 15 wraps the supercharger blade disk 11, the motor 06, the power distribution management system 07, the transmission cable 08, the battery 09, the generator 03 and the turbine blade disk 13; the motor 06, the power distribution management system 07, the battery 09 and the generator 03 are connected by the transmission cable 08, and the power supply cable 17 extends to the outside of the auxiliary equipment through the hollow rectifier partition 04; the turboelectric system outer casing Between 14 and the inner casing 15 of the vortex-electric system are an annular inner channel 32 and an annular combustion zone 12. The vortex-electric system 10 is fixed on the auxiliary equipment casing 05 through a circle of rectifying baffles 04, and the fuel enters the combustion zone 12 through the fuel inlet 16 to participate in the combustion reaction; the top of the blade on the fan blade disk 01 is close to the auxiliary equipment casing 05; the number of fan blades is 18 to 50 and is evenly distributed circumferentially on the fan blade disk 01, and the number of rectifying baffles 04 is usually 10 to 30 and is evenly distributed circumferentially; the aspect ratio of the blades on the fan blade disk 01 is between 1.5 and 5; the outer diameter of the vortex-electric system 10 does not exceed 60% of the inner diameter of the auxiliary equipment casing 05; the outer diameter of the blades on the fan blade disk 01 is slightly smaller than the inner diameter of the auxiliary equipment casing 05.

[0018] The specific working method is as follows: when the turbo-electric system 10 in the auxiliary equipment starts to start, the motor 06 uses the electric energy in the battery 09 to drive the auxiliary equipment fan blade disk 01 to rotate and inhale the intake airflow 21. A part of the intake airflow 21 enters the turbo-electric system 10, and is pressurized by the turbo-electric system's booster blade disk 11, and the fuel entering the turbo-electric combustion zone 12 from the fuel inlet 16 undergoes a combustion reaction. Due to the airflow pressurization, the combustion reaction is enhanced, and the high-temperature airflow 22 generated along the inner channel 32 drives the turbine blade disk 13 of the turbo-electric system 10 to rotate. The turbine blade disk 13 drives the shaft of the generator 03 to rotate and generate electricity. The generated electric energy can enter the power distribution management system 07 through the transmission cable 08, and the electric energy is distributed according to the power demand of the motor 06, the power supply demand of the drone, and the power loss of the battery 09. The electric energy entering the motor 06 drives the motor 06 to drive the fan blade disk 01 to rotate, thereby sucking more intake airflow 21 into the auxiliary equipment, and the speed of the fan shaft can be as high as 15000r / min. As the airflow increases, the combustion reaction produces more high-temperature airflow 22, which has higher energy to drive the turbine blade disk 13 to rotate and do work. After reaching the design speed of the generator, the speed no longer increases; at the same time, the other part of the sucked airflow 23 is combed by the rectifying baffle 04 and discharged from the auxiliary equipment through the outer duct 31. The surplus electric energy produced by the generator 03 can be used to charge the battery 09, and can also be used to power the UAV's electrical equipment through the power supply cable 17. The use of large aspect ratio fan blades can achieve extremely strong suction capacity even with a large fan diameter and high speed.

[0019] The present invention has the following characteristics:

[0020] 1. Power source: The vortex electric system is used as the power source to drive the fan to rotate at high speed to generate strong suction, so the fan size, air volume and total pressure can be very large. If the electric drive fan wants to achieve the same air volume and total pressure, it needs extremely high power input and large-scale power distribution equipment. Therefore, the device in the present invention can be used in a variety of scenarios without relying on power supply capacity. At the same time, the use of the vortex electric system as the power source can also achieve high-speed hot air supply capacity, which is also limited by the power supply problem. If the electric hot air blower wants to provide the same air volume and temperature of hot air, the required electric power is even greater.

[0021] 2. Compared with conventional axial-flow engines, the turbo-electric system eliminates the middle rotating shaft, so the structural strength requirements are relatively low, the processing complexity is reduced, and the cost has certain advantages. At the same time, the addition of a power distribution management system can be used to flexibly adjust the fan speed according to needs. By flexibly adjusting the input motor current, the engine is ensured to work under the most efficient conditions. At this time, the fuel consumption is the lowest, so it will save fuel relatively.

[0022] 3. The present invention can not only be used for cooling or heating UAV components, but can also be applied to other equipment and spaces that require rapid heating or cooling.

[0023] 4. Due to its power generation, storage and distribution functions, the device in the present invention can supply power to other devices outside the device, not limited to the drone system, so it is also equivalent to a portable generator or portable power source.

[0024] 5. The turbo-electric system used in the present invention can be a dual-rotor, multi-stage turbocharging system, and is not limited to a single-shaft, single-stage turbocharging system. Moreover, the fuel is not limited to liquid fuels such as gasoline, kerosene, and diesel, but can also be gaseous fuels such as hydrogen and natural gas.

[0025] 6. The use scenario of the device of the present invention is not limited to the atmospheric environment with normal oxygen content. Since the vortex electric system that generates power can meet the operation requirements in the aviation environment, the device can operate in low temperature, low pressure or strong wind weather.

Claims

1. A vortex-electric driven UAV ground auxiliary equipment, characterized by: The invention comprises a casing (05) and a turboelectric system (10) enclosed therein, wherein an air intake cone (02), a fan blade disk (01), a supercharger blade disk (11), a motor (06), a battery (09), a power distribution management system (07), a generator (03) and a turbine blade disk (13) enclosed in the casing (05) are arranged in sequence, wherein the air intake cone (02), the fan blade disk (01), the supercharger blade disk (11) and the motor (06) share the same rotating shaft, and the turbine blade disk (13) and the generator (03) share another rotating shaft; and the casing (15) in the turboelectric system encloses the supercharger blade disk (11), the motor (06), the battery (09), the power distribution management system (07), the generator (03) and the turbine blade disk (13); The motor (06), the storage battery (09), and the generator (03) are respectively connected to the power distribution management system (07) through a transmission cable (08); the power supply cable (17) is connected to the power distribution management system (07) and extends to the outside of the auxiliary equipment through a hollow rectifying baffle (04); an annular inner channel (32) and an annular combustion zone (12) are formed between the outer casing (14) of the turbo-electric system and the inner casing (15) of the turbo-electric system; the turbo-electric system (10) is fixed to the casing (05) of the auxiliary equipment through a circle of rectifying baffles (04); a pipeline extending to the outside of the auxiliary equipment is provided at the combustion zone (12); a fuel inlet (16) is provided at the end of the pipeline; and the outer diameter of the blades on the fan blade disk (01) is smaller than the inner diameter of the casing (05).

2. The vortex-electric driven UAV ground auxiliary equipment according to claim 1 is characterized in that: The number of the fan blades is 18 to 50, and they are evenly distributed on the fan blade disk (01) in the circumferential direction.

3. The vortex-electric driven UAV ground auxiliary equipment according to claim 1 is characterized by: The number of the rectifying baffles (04) is 10 to 30 and they are evenly distributed in the circumferential direction.

4. The vortex-electric driven UAV ground auxiliary equipment according to claim 1 is characterized by: The aspect ratio of the blades on the fan blade disk (01) is between 1.5 and 5.

5. The vortex-electric driven UAV ground auxiliary equipment according to claim 1 is characterized by: The outer diameter of the eddy-electric system (10) does not exceed 60% of the inner diameter of the casing (05).

6. The vortex-electric driven UAV ground auxiliary equipment according to claim 1 is characterized by: The turbo-electric system (10) is a twin-rotor, multi-stage turbo-charging system or a single-shaft, single-stage turbo-charging system.

Images