Turbofan-driven unmanned aerial vehicle ground auxiliary equipment

Abstract

The invention relates to turbofan-driven unmanned aerial vehicle ground auxiliary equipment which meets the actual requirements of supplying power to an unmanned aerial vehicle, providing high-speed large-air-volume cooling air flow for hot parts of the unmanned aerial vehicle and providing high-temperature large-air-volume air flow for heating starting of a power system of the unmanned aerial vehicle in a low-temperature environment. Comprising a casing, a turbofan engine and a power supply system, a transmission rotating shaft is arranged in the center of the turbofan engine, an air inlet cone, a fan blade disc, a supercharging blade disc, a turbine blade disc and a generator are sequentially and fixedly connected to the transmission rotating shaft, and the casing in the turbofan engine wraps part of the transmission rotating shaft, the supercharging blade disc, the turbine blade disc and the power supply system. An annular inner duct and an annular combustion area are formed between the turbofan engine outer casing and the turbofan engine inner casing, the turbofan engine is fixed to the auxiliary equipment casing through a rectification partition plate, a fuel pipeline extends into the combustion area from the outside of the casing, and a starting generator and a storage battery in the power supply system are connected with the power distribution management system. The power supply cable is connected with the power distribution management system and extends out of the casing.

Description

Technical Field

[0001] The present invention belongs to the field of unmanned aerial vehicles, and relates to a ground auxiliary equipment for unmanned aerial vehicles that uses a turbofan engine as a power source to drive the equipment, has high-pressure suction and high-pressure hot blowing, and ground power supply functions, and can be used for ground cooling or heating of unmanned aerial vehicles, and ground power supply. 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 electric drive auxiliary equipment 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 supplying power to UAVs, providing high-speed and high-volume cooling airflow for UAV thermal components, and providing high-temperature and high-volume airflow for heating and starting of UAV power systems in low-temperature environments. In conventional scenarios, it can self-generate electricity to power UAVs, provide high-speed and high-volume cooling airflow for UAV thermal components during ground tests, and provide high-temperature and high-volume airflow heating functions for UAV power systems in low-temperature environments.

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

[0006] A ground auxiliary device for a turbofan-driven unmanned aerial vehicle, comprising a casing 05 and a turbofan engine 10 and a power supply system 17 located in the casing 05. The center of the turbofan engine 10 is a transmission shaft 03. An air intake cone 02, a fan blade disk 01, a supercharger blade disk 11, a turbine blade disk 13 and a generator 06 are sequentially fixed to the transmission shaft 03. The inner casing 15 of the turbofan engine wraps part of the transmission shaft 03, the supercharger blade disk 11, the turbine blade disk 13 and the power supply system 17. The outer casing 14 of the turbofan engine and the inner casing of the turbofan engine An annular inner channel 32 and an annular combustion zone 12 are formed between 15, the turbofan engine 10 is fixed to the inner wall of the auxiliary equipment casing 05 through a circle of rectifying baffles 04, and a pipeline with a fuel inlet 16 extends from the outside of the casing 05 into the combustion zone 12. The starter generator 06 and the battery 07 inside the power supply system 17 are connected to the power distribution management system 08 through transmission cables 18, respectively. The power supply cable 09 is connected to the power distribution management system 08 and extends to the outside of the casing 05. 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 fan blades is 18 to 50, which are evenly distributed circumferentially on the fan disk 01. The number of rectifying baffles 04 is usually 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 turbofan engine 10 does not exceed 60% of the inner diameter of the auxiliary equipment casing 05.

[0008] The turbofan engine 10 may be a twin-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 working balance, the auxiliary equipment has a strong suction capacity for the air in front of the auxiliary equipment. 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 turbofan engine 10 can reach 500-600°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, and does not need to rely on a high-power power supply environment and large-scale power distribution control equipment. Therefore, it is portable and can be used in various scenarios that do not have high-power supply capabilities.

[0011] In scenarios where power supply is the main demand, the turbofan engine can operate in the most efficient working state, where the combustion efficiency is high, the fuel consumption per unit power and carbon emissions are also low. 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-drive shaft, 04-rectifier baffle, 05-casing, 06-generator, 07-battery, 08-power distribution management system, 09-power supply cable, 10-turbofan engine, 11-boost blade disk, 12-combustion zone, 13-turbine blade disk, 14-turbofan engine outer casing, 15-turbofan engine inner casing, 16-fuel inlet, 17-power supply system, 18-transmission 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 device for an unmanned aerial vehicle that uses a turbofan engine as a power source, has high-pressure suction and high-pressure hot air blowing, and ground power supply functions, and can be used for ground cooling or heating of the unmanned aerial vehicle, as well as ground power supply. Figure 1-3 As shown, the specific structure is as follows:

[0017] The entire auxiliary equipment is wrapped by the casing 05. The core component of the auxiliary equipment is the turbofan engine 10. The center of the turbofan engine 10 is a transmission shaft 03 with sufficiently high rigidity. The auxiliary equipment air intake cone 02, fan blade disk 01, boost blade disk 11, turbine blade disk 13 and generator 06 shafts are all fixed on the auxiliary equipment transmission shaft 03, so these 6 components can rotate together; the turbofan engine inner casing 15 wraps part of the transmission shaft 03, boost blade disk 11, turbine blade disk 13 and power supply system 17. Between the turbofan engine outer casing 14 and the turbofan engine inner casing 15 are the annular inner channel 32 and the annular combustion zone 12. The turbofan engine 10 is connected by a circle of rectifying baffles 04. Fixed on the auxiliary equipment casing 05, the fuel enters the combustion zone 12 through the fuel inlet 16 to participate in the combustion reaction; the generator 06, the battery 07, and the distribution management system 08 inside the power supply system 17 are connected through the transmission cable 18; 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 rectifier 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 turbofan engine 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 auxiliary equipment is started, the battery 07 provides the starting power for the generator 06, and the generator 06 drives the transmission shaft 03 to rotate, so that the fan blade disk 01 inhales the air outside the auxiliary equipment, and the fuel enters the turbofan combustion area 12 from the fuel inlet 16 to react with the air inhaled by the fan blade disk 01 to burn. The generated high-temperature airflow 22 drives the turbine blade disk 13 of the turbofan engine 10 along the auxiliary equipment inner channel 32 to drive the transmission shaft 03 to rotate, and then drives the intake cone 02, the fan blade disk 01, and the boost blade disk 11 to rotate. The rotating fan blade disk 01 draws a large amount of intake airflow 21 into the auxiliary equipment; at the same time, the transmission shaft 03 can drive the core of the generator 06 to rotate. A part of the sucked airflow enters the turbofan engine 10 and is supercharged by the rotating supercharger blade disk 11. The supercharged airflow enters the combustion zone 12 through the auxiliary equipment inner duct 32 to participate in the combustion. Due to the airflow supercharging, the combustion reaction is enhanced, and the high-temperature airflow 22 generated has a higher capacity, so there is a higher energy to drive the turbine blade disk to rotate and do work. Therefore, the speed of the auxiliary equipment increases, thereby sucking more intake airflow 21 into the auxiliary equipment until the working balance of the turbofan engine 10 is reached, and the speed no longer increases; at the same time, another part of the sucked airflow, the cold airflow 23, is combed by the rectifying baffle 04 and discharged from the auxiliary equipment through the auxiliary equipment outer duct 31. As the speed of the turbofan engine 10 increases, the generator 06 changes from the working mode to the power generation mode. The electric energy generated by the generator 06 is distributed according to actual needs through the power distribution management system 08 to charge the battery 07 and power the UAV electrical equipment through the power supply cable 09. The rotation speed of the auxiliary equipment shaft can be as high as 15000r / min. The use of large aspect ratio fan blades can achieve extremely strong suction capacity even with large fan diameter and high rotation speed.

[0019] The present invention has the following characteristics:

[0020] 1. Power source of auxiliary equipment: The turbofan engine is used as the power source to drive the auxiliary equipment fan to rotate at high speed to generate strong suction, so the size, air volume and total pressure of the auxiliary equipment can be very large. If the electric drive auxiliary equipment wants to achieve the same air volume and total pressure, it needs extremely high power input and large-scale power distribution equipment. Therefore, the auxiliary equipment 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 turbofan engines as power sources can also achieve high-speed hot air supply capacity. It is also limited by the problem of power supply. If the electric heating auxiliary equipment wants to provide hot air with the same air volume and temperature, the required electric power is even greater.

[0021] 2. The turbofan engine 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.

[0022] 3. 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.

[0023] 4. The present invention can not only be used to cool or heat UAV engines, but can also be applied to other equipment and spaces that require rapid heating or cooling.

[0024] 5. The use scenario of the auxiliary equipment of the present invention is not limited to the atmospheric environment with normal oxygen content. Since the turbofan engine that generates power can meet the operation requirements in the aviation environment, the auxiliary equipment can work in low temperature, low pressure or strong wind weather.

[0025] 6. The power supply system 17 does not have to be directly connected to the transmission shaft 03, and can also be arranged on the periphery of the turbofan engine through a transmission mechanism such as gears.

Claims

1. A turbofan-driven UAV ground auxiliary equipment, characterized by: The invention comprises a casing (05), a turbofan engine (10) and a power supply system (17) located in the casing (05), wherein the center of the turbofan engine (10) is a transmission shaft (03), an air intake cone (02), a fan blade disk (01), a supercharger blade disk (11), a turbine blade disk (13) and a generator (06) are sequentially fixed to the transmission shaft (03), an inner casing (15) of the turbofan engine wraps part of the transmission shaft (03), the supercharger blade disk (11), the turbine blade disk (13) and the power supply system (17), and an annular structure is formed between an outer casing (14) of the turbofan engine and an inner casing (15) of the turbofan engine. The invention discloses a turbofan engine (10) having an inner channel (32) and an annular combustion zone (12), wherein the turbofan engine (10) is fixed to the inner wall of the auxiliary equipment casing (05) through a circle of rectifying baffles (04), a pipeline with a fuel inlet (16) extends from the outside of the casing (05) into the combustion zone (12), a generator (06) and a battery (07) inside the power supply system (17) are connected to the power distribution management system (08) through a power transmission cable (18), a power supply cable (09) is connected to the power distribution management system (08) and extends to the outside of the casing (05), 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 turbofan-driven UAV ground support equipment according to claim 1, characterized in that: The number of fan blades is 18 to 50, and they are evenly distributed on the fan blade disk (01) in the circumferential direction.

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

4. The turbofan-driven UAV ground support equipment according to claim 1, characterized in that: The aspect ratio of the blades on the fan blade disk (01) is between 1.5 and 5.

5. The turbofan-driven UAV ground support equipment according to claim 1, characterized in that: The outer diameter of the turbofan engine (10) does not exceed 60% of the inner diameter of the casing (05).

6. The turbofan-driven UAV ground support equipment according to claim 1, characterized in that: The turbofan engine (10) is a twin-rotor, multi-stage turbocharging system or a single-shaft, single-stage turbocharging system.

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