CN110513217A - A UAV ducted fan power system - Google Patents

Abstract

The invention relates to a ducted fan power system for an unmanned aerial vehicle, including a hood, a fan rotor, a stator, a nose cone, a gasket, a motor and a tail cone; The total pressure of the gas flow increases and the velocity increases. After the air enters the stator, cut off the linear velocity of the airflow. The airflow is discharged from the tail at high speed to obtain thrust. By optimizing the blade parameters, the total pressure ratio is ≥1.08 times, and the isentropic efficiency is ≥85%. The system of the invention has high thrust-to-weight ratio, high efficiency and high reliability.

Description

A UAV ducted fan power system

technical field

The invention relates to a ducted fan power technology, in particular to a ducted fan power system, which belongs to the technical field of ducted fan power.

Background technique

The ducted fan power system relies on a lithium power supply or a DC power supply to drive a high-power brushless motor, and the brushless motor drives the fan to rotate at high speed. The fan draws in air and does work on it, increasing the total pressure and velocity of the airflow. After the air enters the stator, cut off the linear velocity of the airflow. The airflow is discharged from the tail at high speed to obtain thrust. The ducted fan power system has the characteristics of high efficiency, high thrust-to-weight ratio and low cost. As a power system, it has been widely used in the fields of drones and helicopters, and has an important impact on the performance of aircraft. Existing brushless motor ducted fans usually adopt a straight-wing blade design, which has low efficiency. The ducted fan is not designed for noise reduction and is very noisy. Therefore, the demand for greater take-off weight and high-quality UAV design cannot be met.

The aerodynamic shape and noise reduction design of the rotor and stator blades of the ducted fan are important key technologies in the design of the power system of the ducted fan.

The main technical difficulty in the aerodynamic design of ducted fan blades is to optimize the design of the geometric shape of the blade, the number of blades, the diameter of the duct, and the rotational speed to match the shaft power of the motor to obtain greater thrust and higher efficiency. . Analyzing the noise source and pressure field at the inlet and outlet of the fan, and optimizing the design of the noise reduction target for the shape and material structure of the inlet and outlet channels are the main technical difficulties in the aerodynamic noise reduction design of the fan. Therefore, the aerodynamic shape optimization and aerodynamic noise reduction design of ducted fans must rely on large-scale computational fluid dynamics numerical simulation software platform and high-performance computers for numerical calculations, combined with computational fluid dynamics technology, ground test technology, material technology and manufacturing technology. Ducted fan power system with excellent performance.

Contents of the invention

The problem solved by the technology of the present invention is: to overcome the insufficient thrust of the existing ducted fan power system, a high-power ducted fan power system is proposed, with a power ≥ 45kw, which meets the power design requirements of unmanned aerial vehicles in the range of Mach number 0.0-0.3 .

Technical solution of the present invention is:

A UAV ducted fan power system, including a hood, a fan rotor, a stator, a nose cone, a gasket, a motor and a tail cone;

The fan rotor, nose cone and stator are coaxially installed in the cylindrical hood; the fan rotor is connected to the stator, the head cone is fixed on the fan rotor and rotates synchronously with the fan rotor, the tail cone is connected to the rear of the stator, and the motor is set on the Inside the stator, it is used to drive the fan rotor to rotate, and the gasket for buffering and shock absorption is arranged between the motor and the stator;

The rotor blade has a twisted wide chord-swept aerodynamic shape, the chord length of the rotor blade gradually increases along the radial direction of the rotor blade, and the installation angle of the rotor blade gradually decreases along the radial direction of the rotor blade; the stator blade is a swept straight wing Aerodynamic shape, the chord length of the stator blade is fixed, and the installation angle of the stator blade gradually decreases along the radial direction of the stator blade.

Further, it also includes an L-shaped wire cover, the short straight arm of which is installed on the stator, and the long straight arm is connected to the head cover, and the wire cover is a closed body, and the wires for power supply to the motor are sequentially connected through the wire holes provided on the head cover. Into the long straight arm and the short straight arm, and finally into the motor to power the motor.

Further, the hood includes a rotor hood part and a stator hood part; the fan rotor corresponds to the rotor hood part, and the stator corresponds to the stator hood part; blind holes with the same diameter and the same depth are uniformly arranged on the inner wall of the rotor hood part; The rear edge of the stator head cover part is 60° serrated; there are multiple strip grooves evenly distributed on the surface of the tail cone.

Further, the number of the rotor blades is 3-20, the diameter is 200-500mm, the ratio of the thickness of the rotor blade section airfoil to the chord length is 0.05-0.2, and the ratio of the section airfoil camber to the chord length is 0.03-0.06 .

Further, the number of the rotor blades is preferably 16, the diameter is preferably 300 mm, the ratio of the thickness of the airfoil section of the rotor blade to the chord length is preferably 0.15, and the ratio of the camber of the airfoil section to the chord length is preferably 0.054.

Further, the chord length and installation angle of the axial section position of the rotor blade are specifically:

When the distance between the axial section of the rotor blade and the rotating shaft of the fan rotor is 0, the chord length and installation angle of the axial section position are 68.3mm and 73.3° respectively;

When the distance between the axial section of the rotor blade and the rotating shaft of the fan rotor is 0.1R, the chord length and installation angle of the axial section position are 71.2mm and 70.2°, respectively, where R is the radius of the fan rotor;

When the distance between the axial section of the rotor blade and the rotating shaft of the fan rotor is 0.2R, the chord length and installation angle of the axial section are 72.2mm and 67.8° respectively;

When the distance between the axial section of the rotor blade and the rotating shaft of the fan rotor is 0.3R, the chord length and installation angle of the axial section are 73.1mm and 65.7° respectively;

When the distance between the axial section of the rotor blade and the rotating shaft of the fan rotor is 0.4R, the chord length and installation angle of the axial section are 73.5mm and 63.7° respectively;

When the distance between the axial section of the rotor blade and the rotating shaft of the fan rotor is 0.5R, the chord length and installation angle of the axial section are 75.7mm and 61° respectively;

When the distance between the axial section of the rotor blade and the rotating shaft of the fan rotor is 0.6R, the chord length and installation angle of the axial section are 79.7mm and 59.2° respectively;

When the distance between the axial section of the rotor blade and the rotating shaft of the fan rotor is 0.7R, the chord length and installation angle of the axial section position are 84.7mm and 57.1 respectively;

When the distance between the axial section of the rotor blade and the rotating shaft of the fan rotor is 0.8R, the chord length and installation angle of the axial section position are 90.8mm and 54.9° respectively;

When the distance between the axial section of the rotor blade and the rotating shaft of the fan rotor is 0.9R, the chord length and installation angle of the axial section position are 98.1mm and 52.6° respectively;

When the distance between the axial section of the rotor blade and the rotating shaft of the fan rotor is 1.0R, the chord length and installation angle of the axial section are 106.3mm and 50.6°, respectively.

Further, the number of stator blades is 20-40, the ratio of the section airfoil thickness to the chord length of the stator blade is 0.05-0.2, the ratio of the section airfoil camber to the chord length is 0.03-0.06; the stator diameter is 100-200mm.

Further, the number of stator blades is preferably 30, the ratio of the section airfoil thickness to the chord length of the stator blade is preferably 0.1, the ratio of the section airfoil camber to the chord length is preferably 0.05; the stator diameter is preferably 171 mm.

Further, the chord length and installation angle of the axial section position of the stator blade are specifically:

When the distance between the axial section of the stator blade and the central axis of the stator is 0, the chord length and installation angle of the axial section position are 50mm and 110° respectively;

When the distance between the axial section of the stator blade and the central axis of the stator is 0.1r, the chord length and installation angle of the axial section position are 50mm and 109° respectively, where r is the radius of the stator;

When the distance between the axial section of the stator blade and the central axis of the stator is 0.2r, the chord length and installation angle of the axial section position are 50mm and 108° respectively;

When the distance between the axial section of the stator blade and the central axis of the stator is 0.3r, the chord length and installation angle of the axial section position are 50mm and 107° respectively;

When the distance between the axial section of the stator blade and the central axis of the stator is 0.4r, the chord length and installation angle of the axial section are 50mm and 106°, respectively;

When the distance between the axial section of the stator blade and the central axis of the stator is 0.5r, the chord length and installation angle of the axial section position are 50mm and 106° respectively;

When the distance between the axial section of the stator blade and the central axis of the stator is 0.6r, the chord length and installation angle of the axial section position are 50mm and 105° respectively;

When the distance between the axial section of the stator blade and the central axis of the stator is 0.7r, the chord length and installation angle of the axial section are 50mm and 104°, respectively;

When the distance between the axial section of the stator blade and the central axis of the stator is 0.8r, the chord length and installation angle of the axial section position are 50mm and 103° respectively;

When the distance between the axial section of the stator blade and the central axis of the stator is 0.9r, the chord length and installation angle of the axial section position are 50mm and 102° respectively;

When the distance between the axial section of the stator blade and the central axis of the stator is 1.0r, the chord length and installation angle of the axial section are 50mm and 101°, respectively.

Further, the leading edge sweep angle of the stator blade is 15°-50°, preferably 45°.

Further, the total pressure ratio of the UAV ducted fan power system is ≥1.08 times, the total temperature ratio is ≥1.02, the isentropic efficiency is ≥85%, and the air flow rate is ≥6.0kg/s; when the maximum fan rotor speed is 9000rpm, the maximum Static thrust ≥ 60kg; motor shaft power greater than 45kw.

Advantage of the present invention compared with prior art:

(1) The present invention obtains the aerodynamic shape of the blade by adopting a wide chord-swept fan, high-lift airfoil and inclined stator blade design, and using CFD to calculate and optimize geometric parameters. Under the condition of brushless motor shaft power ≥ 45kw, the total pressure ratio and isentropic efficiency of the fan stage reach the maximum, and the ducted fan power system with a thrust ≥ 60kg is designed, and the isentropic efficiency is ≥ 85%. Compared with the existing electric ducted fan power system, the thrust of the present invention is greatly improved.

(2) The ducted fan power system of the present invention is applicable to the Mach number range of 0.0 to 0.3, which can meet the flight speed range of most low-speed drones. Compared with the coaxial power propeller thrust, the propulsion power system of the drone has obvious advantages. Advantage.

(3) The power system of the ducted fan of the present invention adopts a unique honeycomb structure and sawtooth structure to reduce noise, which can reduce noise by 10dB compared with the original ducted fan.

Description of drawings

Fig. 1 is one of the dimension schematic diagrams of the ducted fan power system in the embodiment of the present invention;

Fig. 2 is the second schematic diagram of the size of the ducted fan power system in the embodiment of the present invention;

Fig. 3 is one of the structural schematic diagrams of the ducted fan power system in the embodiment of the present invention;

Fig. 4 is the second structural diagram of the ducted fan power system in the embodiment of the present invention;

Fig. 5 is the third schematic diagram of the structure of the ducted fan power system in the embodiment of the present invention;

Fig. 6 is the fourth schematic diagram of the structure of the ducted fan power system in the embodiment of the present invention;

Fig. 7 is one of the schematic cross-sectional views of the fan blade of the present invention;

Fig. 8 is the second schematic cross-sectional view of the fan blade of the present invention;

Fig. 9 is one of the schematic cross-sectional views of the stator blade of the present invention;

Fig. 10 is the second schematic cross-sectional view of the stator blade of the present invention;

Fig. 11 is the third schematic cross-sectional view of the stator blade of the present invention;

Fig. 12 is a schematic diagram of comparison between the system of the present invention and propellers of the same power.

Detailed ways

The invention proposes a high-efficiency, low-noise and high-thrust unmanned aerial vehicle ducted fan power system. Using computational fluid dynamics technology to optimize the aerodynamic shape of the blades of the ducted fan, a ducted fan blade with a thrust ≥ 60kg and an isentropic efficiency ≥ 85% is obtained. It also optimized the structure of the fan inlet and outlet, and proposed a honeycomb structure inlet and sawtooth structure noise-reducing tail nozzle, as well as a grooved tail cone scheme. Compared with products of the same type, the aerodynamic noise of the invention can be reduced by 10dB.

As shown in Figures 1 to 6, the present invention proposes a UAV ducted fan power system, including a hood 1, a fan rotor 2, a stator 3, a nose cone 4, a gasket 6, a motor 7 and a tail cone 10;

A fan rotor 2, a nose cone 4 and a stator 3 are coaxially installed in a cylindrical hood 1; the fan rotor 2 is connected to the stator 3, the nose cone 4 is fixed on the fan rotor 2 and rotates synchronously with the fan rotor 2, and the tail cone 10 is connected to the rear of the stator 3, the motor 7 is arranged inside the stator 3, and is used to drive the fan rotor 2 to rotate, and the gasket 6 for buffering and shock absorption is arranged between the motor 7 and the stator 3;

The rotor blade 8 has a twisted wide chord-swept aerodynamic shape, the chord length of the rotor blade 8 gradually increases along the radial direction of the rotor blade 8, and the installation angle of the rotor blade 8 gradually decreases along the radial direction of the rotor blade 8; 5 is the aerodynamic shape of a swept straight wing, the chord length of the stator blade 5 is fixed, and the installation angle of the stator blade 5 gradually becomes smaller along the radial direction of the stator blade 5 .

Further, the power system of the present invention also includes an L-shaped wire cover 9, the short straight arm of which is installed on the stator 3, and the long straight arm is connected to the head cover 1, and the wire cover 9 is a closed body, which supplies power to the motor 7 The wire enters the long straight arm and the short straight arm successively from the wire hole provided on the headshield 1, and finally enters the motor 7 to supply power for the motor.

Further, the above-mentioned hood 1 includes a rotor hood part and a stator hood part; the fan rotor 2 corresponds to the rotor hood part, and the stator 3 corresponds to the stator hood part; The blind hole and the honeycomb hole can reduce the low-frequency vibration of the noise, thereby reducing the noise of the air inlet; the rear edge of the stator cover part is serrated, and the large vortex shedding at the tail of the nozzle is broken through the serrated shape to break it into pieces vortex, thereby reducing the noise of the tail nozzle; the surface of the tail cone 10 is evenly distributed with a plurality of strip grooves, the optimized strip grooves can not only aerodynamically rectify the tail nozzle, but also cool the motor, and the heat passes through The slots diffuse into the airflow while also reducing the tailpipe's airflow separation causing thrust decay.

The important part of the ducted fan of the rotor blade directly determines the thrust, efficiency and pressure ratio of the entire ducted fan. The design of fan blades is very complicated, and requires the use of computational aided modeling technology, computational fluid dynamics numerical simulation technology, and high-performance parallel computing technology. After a large number of selection, numerical simulation calculations, and repeated iterations, a solution that meets the design indicators can be obtained.

As shown in Figures 3 to 6, the number of rotor blades 8 is 3 to 20, and the diameter is 200 to 500mm. The ratio is 0.03-0.06.

The number of rotor blades 8 is preferably 16, the diameter is preferably 300 mm, the ratio of the thickness of the airfoil section of the rotor blade 8 to the chord length is preferably 0.15, and the ratio of the camber of the airfoil section to the chord length is preferably 0.054.

Specifically, the twisted special-shaped rotor blade is cut along the axial direction to describe the configuration of the special-shaped rotor blade more clearly, as shown in FIGS. 7-8 .

The chord length and installation angle of the axial section position of the rotor blade 8 are specifically:

When the distance between the axial section of the rotor blade 8 and the rotating shaft of the fan rotor is 0, the chord length and installation angle of the axial section are 68.3mm and 73.3° respectively;

When the distance between the axial section of the rotor blade 8 and the rotating shaft of the fan rotor is 0.1R, the chord length and installation angle of the axial section are 71.2mm and 70.2°, respectively, where R is the radius of the fan rotor 2;

When the distance between the axial section of the rotor blade 8 and the rotating shaft of the fan rotor is 0.2R, the chord length and installation angle of the axial section are 72.2mm and 67.8° respectively;

When the distance between the axial section of the rotor blade 8 and the rotating shaft of the fan rotor is 0.3R, the chord length and installation angle of the axial section are 73.1mm and 65.7° respectively;

When the distance between the axial section of the rotor blade 8 and the rotating shaft of the fan rotor is 0.4R, the chord length and installation angle of the axial section are 73.5mm and 63.7° respectively;

When the distance between the axial section of the rotor blade 8 and the rotating shaft of the fan rotor is 0.5R, the chord length and installation angle of the axial section are 75.7mm and 61° respectively;

When the distance between the axial section of the rotor blade 8 and the rotating shaft of the fan rotor is 0.6R, the chord length and installation angle of the axial section are 79.7mm and 59.2° respectively;

When the distance between the axial section of the rotor blade 8 and the rotating shaft of the fan rotor is 0.7R, the chord length and installation angle of the axial section are 84.7 mm and 57.1 respectively;

When the distance between the axial section of the rotor blade 8 and the rotating shaft of the fan rotor is 0.8R, the chord length and installation angle of the axial section are 90.8mm and 54.9° respectively;

When the distance between the axial section of the rotor blade 8 and the rotating shaft of the fan rotor is 0.9R, the chord length and installation angle of the axial section are 98.1mm and 52.6° respectively;

When the distance between the axial section of the rotor blade 8 and the rotating shaft of the fan rotor is 1.0R, the chord length and installation angle of the axial section are 106.3mm and 50.6°, respectively.

After the fan inhales the airflow, it does work on it, so that the total pressure increases by 1.01-1.1 times, and the airflow velocity increases to Ma=0.3-0.8. The air flow must pass through the stator to eliminate its linear velocity, and ensure that the air flow angle is ≤5° along the horizontal jet under the condition that the air flow does not separate in the boundary layer of the stator, and the total pressure recovery coefficient is required to be ≥0.99. Therefore, stator design is one of the key technologies in ducted fan design.

As shown in Figures 9 to 11, the number of stator blades 5 is 20 to 40, the ratio of the section airfoil thickness to the chord length of the stator blade 5 is 0.05 to 0.2, and the ratio of the section airfoil camber to the chord length is 0.03 to 0.06; The diameter is 100-200mm.

The number of the stator blades 5 is preferably 30, the ratio of the section airfoil thickness to the chord length of the stator blade 5 is preferably 0.1, the ratio of the section airfoil camber to the chord length is preferably 0.05; the diameter of the stator 3 is preferably 171mm.

Specifically, the stator blade is cut along the axial direction to describe the configuration of the stator blade more clearly, as shown in FIGS. 9-11 .

The chord length and installation angle of the axial section position of the stator blade 5 are specifically:

When the distance between the axial section of the stator blade 5 and the central axis of the stator is 0, the chord length and installation angle of the axial section are 50mm and 110° respectively;

When the distance between the axial section of the stator blade 5 and the central axis of the stator is 0.1r, the chord length and installation angle of the axial section position are 50mm and 109° respectively, where r is the radius of the stator 3;

When the distance between the axial section of the stator blade 5 and the central axis of the stator is 0.2r, the chord length and installation angle of the axial section position are 50mm and 108° respectively;

When the distance between the axial section of the stator blade 5 and the central axis of the stator is 0.3r, the chord length and installation angle of the axial section are 50mm and 107°, respectively;

When the distance between the axial section of the stator blade 5 and the central axis of the stator is 0.4r, the chord length and installation angle of the axial section are 50mm and 106° respectively;

When the distance between the axial section of the stator blade 5 and the central axis of the stator is 0.5r, the chord length and installation angle of the axial section position are 50mm and 106° respectively;

When the distance between the axial section of the stator blade 5 and the central axis of the stator is 0.6r, the chord length and installation angle of the axial section position are 50mm and 105° respectively;

When the distance between the axial section of the stator blade 5 and the central axis of the stator is 0.7r, the chord length and installation angle of the axial section position are 50mm and 104° respectively;

When the distance between the axial section of the stator blade 5 and the central axis of the stator is 0.8r, the chord length and installation angle of the axial section are 50mm and 103° respectively;

When the distance between the axial section of the stator blade 5 and the central axis of the stator is 0.9r, the chord length and installation angle of the axial section are 50mm and 102° respectively;

When the distance between the axial section of the stator blade 5 and the central axis of the stator is 1.0r, the chord length and installation angle of the axial section are 50 mm and 101°, respectively.

The leading edge sweep angle of the stator blade 5 is 15°-50°, preferably 45°.

The airflow angle of the present invention is less than or equal to 5°, the airflow does not separate in the boundary layer of the stator, and the total pressure recovery coefficient is more than or equal to 0.99.

The total pressure ratio of the ducted fan power system of the unmanned aerial vehicle of the present invention is ≥1.08 times, the total temperature ratio is ≥1.02, the isentropic efficiency is ≥85%, and the air flow rate is ≥6.0kg/s; when the maximum speed of the fan rotor 2 is 9000rpm, the ground is the largest The static thrust is more than or equal to 60kg; the shaft power of the motor 7 is greater than 45kw. Compared with propellers of the same power, the present invention has obvious advantages in thrust when Ma≥0.1, as shown in FIG. 12 .

Parts not described in detail in the present invention belong to the common knowledge of those skilled in the art.

Claims (11)

1. A UAV ducted fan power system is characterized in that: comprise hood (1), fan rotor (2), stator (3), nose cone (4), gasket (6), motor (7) ) and tail cone (10); A fan rotor (2), nose cone (4) and stator (3) are installed coaxially inside the cylindrical hood (1); the fan rotor (2) is connected to the stator (3), and the nose cone (4) is fixed on The fan rotor (2) rotates synchronously with the fan rotor (2), the tail cone (10) is connected to the rear of the stator (3), and the motor (7) is arranged inside the stator (3) to drive the fan rotor (2) Rotate, the spacer (6) that is used for cushioning shock absorption is arranged between motor (7) and stator (3); The rotor blade (8) has a twisted wide chord-swept aerodynamic shape, the chord length of the rotor blade (8) gradually increases along the radial direction of the rotor blade (8), and the installation angle of the rotor blade (8) is along the direction of the rotor blade (8). ) gradually becomes smaller in the radial direction; the stator blade (5) has a swept-back straight wing aerodynamic shape, the chord length of the stator blade (5) is fixed, and the installation angle of the stator blade (5) gradually changes along the radial direction of the stator blade (5) Small. 2. A ducted fan power system for unmanned aerial vehicle according to claim 1, characterized in that: it also includes an L-shaped wire cover (9), its short straight arm is installed on the stator (3), and its length is straight. The arms are connected to the head cover (1), and the wire cover (9) is a closed body, and the wires for powering the motor (7) enter the long straight arm and the short straight arm in turn from the wire hole provided on the head cover (1), and finally enter the The motor (7) supplies power to the motor. 3. A kind of UAV ducted fan power system according to claim 1 or 2, characterized in that: the hood (1) includes a rotor hood part and a stator hood part; the fan rotor (2) corresponds to the rotor head The cover part, the stator (3) corresponds to the stator cover part; blind holes with the same diameter and the same depth are uniformly arranged on the inner wall of the rotor cover part; the rear edge of the stator cover part is 60° serrated; the tail cone (10) A plurality of strip grooves are evenly distributed on the surface. 4. A UAV ducted fan power system according to claim 2, characterized in that: the number of the rotor blades (8) is 3-20, the diameter is 200-500mm, and the rotor blades (8) The ratio of section airfoil thickness to chord length is 0.05-0.2, and the ratio of section airfoil camber to chord length is 0.03-0.06. 5. A kind of unmanned aerial vehicle ducted fan power system according to claim 4, is characterized in that: the quantity of described rotor blade (8) is preferably 16, and diameter is preferably 300mm, and rotor blade (8) section wing The ratio of profile thickness to chord length is preferably 0.15, and the ratio of section airfoil camber to chord length is preferably 0.054. 6. A kind of unmanned aerial vehicle ducted fan power system according to claim 4 or 5, is characterized in that: the chord length and installation angle of rotor blade (8) axial section position are specifically: When the distance between the axial section of the rotor blade (8) and the rotating shaft of the fan rotor is 0, the chord length and installation angle of the axial section are 68.3mm and 73.3° respectively; When the distance between the axial section of the rotor blade (8) and the rotating shaft of the fan rotor is 0.1R, the chord length and installation angle of the axial section position are 71.2mm and 70.2° respectively, where R is the fan rotor (2) radius; When the distance between the axial section of the rotor blade (8) and the rotating shaft of the fan rotor is 0.2R, the chord length and installation angle of the axial section are 72.2mm and 67.8° respectively; When the distance between the axial section of the rotor blade (8) and the rotating shaft of the fan rotor is 0.3R, the chord length and installation angle of the axial section are 73.1mm and 65.7° respectively; When the distance between the axial section of the rotor blade (8) and the rotating shaft of the fan rotor is 0.4R, the chord length and installation angle of the axial section are 73.5mm and 63.7° respectively; When the distance between the axial section of the rotor blade (8) and the rotating shaft of the fan rotor is 0.5R, the chord length and installation angle of the axial section are 75.7mm and 61° respectively; When the distance between the axial section of the rotor blade (8) and the rotating shaft of the fan rotor is 0.6R, the chord length and installation angle of the axial section are 79.7mm and 59.2° respectively; When the distance between the axial section of the rotor blade (8) and the rotating shaft of the fan rotor is 0.7R, the chord length and installation angle of the axial section are 84.7mm and 57.1 respectively; When the distance between the axial section of the rotor blade (8) and the rotating shaft of the fan rotor is 0.8R, the chord length and installation angle of the axial section are 90.8mm and 54.9° respectively; When the distance between the axial section of the rotor blade (8) and the rotating shaft of the fan rotor is 0.9R, the chord length and installation angle of the axial section are 98.1mm and 52.6° respectively; When the distance between the axial section of the rotor blade (8) and the rotating shaft of the fan rotor is 1.0R, the chord length and installation angle of the axial section are 106.3mm and 50.6° respectively. 7. A kind of UAV ducted fan power system according to claim 2, characterized in that: the number of the stator blades (5) is 20 to 40, and the thickness of the section airfoil of the stator blades (5) and the chord length The ratio is 0.05-0.2, the ratio of the camber of the section airfoil to the chord length is 0.03-0.06; the diameter of the stator (3) is 100-200mm. 8. A kind of unmanned aerial vehicle ducted fan power system according to claim 7, is characterized in that: described stator blade (5) quantity is preferably 30, and the ratio of stator blade (5) section airfoil thickness and chord length It is preferably 0.1, and the ratio of the camber of the section airfoil to the chord length is preferably 0.05; the diameter of the stator (3) is preferably 171 mm. 9. The power system of a UAV ducted fan according to claim 7 or 8, characterized in that: the chord length and installation angle of the axial section position of the stator blade (5) are specifically: When the distance between the axial section of the stator blade (5) and the central axis of the stator is 0, the chord length and installation angle of the axial section are 50mm and 110° respectively; When the distance between the axial section of the stator blade (5) and the central axis of the stator is 0.1r, the chord length and installation angle of the axial section position are 50mm and 109° respectively, where r is the radius of the stator (3); When the distance between the axial section of the stator blade (5) and the central axis of the stator is 0.2r, the chord length and installation angle of the axial section are 50mm and 108° respectively; When the distance between the axial section of the stator blade (5) and the central axis of the stator is 0.3r, the chord length and installation angle of the axial section are 50mm and 107°, respectively; When the distance between the axial section of the stator blade (5) and the central axis of the stator is 0.4r, the chord length and installation angle of the axial section are 50mm and 106° respectively; When the distance between the axial section of the stator blade (5) and the central axis of the stator is 0.5r, the chord length and installation angle of the axial section are 50mm and 106° respectively; When the distance between the axial section of the stator blade (5) and the central axis of the stator is 0.6r, the chord length and installation angle of the axial section position are 50mm and 105° respectively; When the distance between the axial section of the stator blade (5) and the central axis of the stator is 0.7r, the chord length and installation angle of the axial section are 50mm and 104° respectively; When the distance between the axial section of the stator blade (5) and the central axis of the stator is 0.8r, the chord length and installation angle of the axial section are 50mm and 103° respectively; When the distance between the axial section of the stator blade (5) and the central axis of the stator is 0.9r, the chord length and installation angle of the axial section are 50mm and 102° respectively; When the distance between the axial section of the stator blade (5) and the central axis of the stator is 1.0r, the chord length and installation angle of the axial section are 50mm and 101° respectively. 10. A UAV ducted fan power system according to claim 7 or 8, characterized in that: the leading edge sweep angle of the stator blade (5) is 15°-50°, preferably 45°. 11. A UAV ducted fan power system according to claim 1 or 2, characterized in that: the total pressure ratio of the UAV ducted fan power system is ≥1.08 times, the total temperature ratio is ≥1.02, and isentropic Efficiency ≥ 85%, air flow ≥ 6.0kg/s; when the maximum rotational speed of the fan rotor (2) is 9000rpm, the maximum ground static thrust ≥ 60kg; the shaft power of the motor (7) is greater than 45kw.