High-efficiency, low-noise and medium-and-small-power propeller blade
By designing saber-shaped propeller blades and monitoring devices, the problems of airflow separation and noise in propeller blades were solved, improving aerodynamic efficiency, reducing noise, and enhancing propulsion.
Patent Information
- Application Number
- CN202511075827.3
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-08-01
- Publication Date
- 2025-11-04
AI Technical Summary
Existing propeller blades suffer from airflow separation, airfoil stall, reduced aerodynamic lift, increased drag, and insufficient noise control, which affect the efficiency of turboprop engines and cause environmental interference.
Design a saber-shaped propeller blade composed of multiple airfoils of different thicknesses, with a smooth transition from thick to thin blade body. The aerodynamic design combines blade element theory and Betz theory, and is equipped with a monitoring device to monitor the blade status in real time.
It improves the aerodynamic efficiency of the propeller and reduces noise, ensures that the blades do not stall under complex operating conditions, enhances propulsion, and reduces noise interference.
Smart Images
Figure CN120887006A_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of aerodynamic design, and more particularly to a high-efficiency, low-noise, small-to-medium power propeller blade. Background Technology
[0002] In the field of aviation propulsion, turboprop engines occupy an important position due to their unique advantages. Especially small and medium-power turboprop engines, which are widely used in various aircraft such as general aviation, regional airliners, reconnaissance aircraft, and unmanned aerial vehicles. Their driving principle is similar to that of traditional piston-engine-driven propeller aircraft, relying on the thrust generated by the rotating propeller as the propulsion force, but the power source is a gas turbine. Turboprop engines convert most of the usable energy in the exhaust gas from the gas generator into shaft power through a power turbine to drive the air propeller.
[0003] As a key component of turboprop engines, the performance of propeller blades directly affects the overall performance of the engine and even the aircraft.
[0004] Currently, conventional propeller blades have many limitations in design: On the one hand, traditional blades are mostly simple and regular in shape (such as equal chord length and small sweep structure), and the airfoil design of the blade section is not fully adapted to complex airflow environment. They are prone to airflow separation and airfoil stall under high-speed rotation or variable operating conditions, resulting in a decrease in aerodynamic lift and a sharp increase in drag, which greatly reduces propeller thrust and aerodynamic efficiency.
[0005] On the other hand, insufficient noise control, due to the unreasonable distribution of the aerodynamic center of the airfoil, causes broadband noise generated by airflow disturbance during operation to be superimposed with tonal noise, which interferes with the flight environment and the ground ecology. Summary of the Invention
[0006] The present invention provides a high-efficiency, low-noise, small-to-medium power propeller blade to solve any of the technical problems mentioned in the background art.
[0007] To solve the above-mentioned technical problems, the present invention discloses a high-efficiency, low-noise, small-to-medium power propeller blade. The propeller blade has a saber-shaped shape. The propeller blade includes a blade root, a blade body, and a blade tip. The blade body is composed of multiple airfoils of different thicknesses, and the blade tip is an extension of the blade body.
[0008] Preferably, the thickness of multiple airfoils in the blade profile from the leaf root to the leaf tip transitions smoothly from thick to thin, and a certain torsion angle is maintained between each section.
[0009] Preferably, the airfoil is a special shape composed of the centroid, the base line, the chord line, and the outline, with each part working together to define the airfoil's geometry.
[0010] Preferably, the leaf root is cylindrical.
[0011] Preferably, the blade part of the sabre-shaped form is an arc line, and the back part is a straight line.
[0012] Preferably, the number of airfoils is 9.
[0013] Preferably, based on the flight requirements of the unmanned aerial vehicle, the airfoil is designed by using the blade element theory and the Betz theory, and then the structure of the propeller blade is designed in detail by using a design software and combining the design experience of other propellers.
[0014] The design software includes ANSYS, CATIA and AutoCAD.
[0015] Preferably, the key size parameters of the airfoil include a width b, a thickness c, a coordinate of a center, an angle φ between a chord line and a base line, and a radial distance R from a rotating center of the blade to a trailing edge of the airfoil; and the X axis of the coordinate of the center is the chord line.
[0016] Preferably, the key size parameters of the first airfoil are as follows: the radial distance R1 from the rotating center of the blade to the trailing edge of the airfoil is 358 mm, the width b is 206.5 mm, the thickness c is 55.4 mm, the coordinate of the center is X0=77 mm and Y0=5.3 mm, and the angle φ between the chord line and the base line is 20.3°.
[0017] The key size parameters of the second airfoil are as follows: the radial distance R2 from the rotating center of the blade to the trailing edge of the airfoil is 405 mm, the width b is 209 mm, the thickness c is 52.3 mm, the coordinate of the center is X0=81 mm and Y0=4.6 mm, and the angle φ between the chord line and the base line is 18.1°.
[0018] The key size parameters of the third airfoil are as follows: the radial distance R3 from the rotating center of the blade to the trailing edge of the airfoil is 607.5 mm, the width b is 218 mm, the thickness c is 39.2 mm, the coordinate of the center is X0=96 mm and Y0=1.6 mm, and the angle φ between the chord line and the base line is 10.9°.
[0019] The key size parameters of the fourth airfoil are as follows: the radial distance R5 from the rotating center of the blade to the trailing edge of the airfoil is 810 mm, the width b is 223 mm, the thickness c is 26.8 mm, the coordinate of the center is X0=103 mm and Y0=-1.7 mm, and the angle φ between the chord line and the base line is 4.2°.
[0020] The key size parameters of the fifth airfoil are as follows: the radial distance R5 from the rotating center of the blade to the trailing edge of the airfoil is 945 mm, the width b is 219 mm, the thickness c is 19.7 mm, the coordinate of the center is X0=100 mm and Y0=-3.9 mm, and the angle φ between the chord line and the base line is 0°.
[0021] The key size parameters of the 6th airfoil are as follows: the radial distance R6 from the blade rotation center to the airfoil trailing edge is 1080mm, the width b is 209mm, the thickness c is 14.6mm, the core coordinates X0 and Y0 are 90mm and 5.3mm respectively, and the angle φ between the chord line and the base line is -3.7°;
[0022] The key size parameters of the 7th airfoil are as follows: the radial distance R7 from the blade rotation center to the airfoil trailing edge is 1215mm, the width b is 181mm, the thickness c is 9.1mm, the core coordinates X0 and Y0 are 60mm and -8.4mm respectively, and the angle φ between the chord line and the base line is -6.2°;
[0023] The key size parameters of the 8th airfoil are as follows: the radial distance R8 from the blade rotation center to the airfoil trailing edge is 1282.5mm, the width b is 156mm, the thickness c is 6.2mm, the core coordinates X0 and Y0 are 31mm and -9.5mm respectively, and the angle φ between the chord line and the base line is -7.4°;
[0024] The key size parameters of the 9th airfoil are as follows: the radial distance R9 from the blade rotation center to the airfoil trailing edge is 1316.3mm, the width b is 136mm, the thickness c is 4.8mm, the core coordinates X0 and Y0 are 8mm and -10.1mm respectively, and the angle φ between the chord line and the base line is -7.8°.
[0025] Preferably, the application further comprises:
[0026] The monitoring device comprises:
[0027] The strain acquisition unit comprises strain detection sensors arranged in a "sparse-dense gradual change" mode along the blade root-tip direction;
[0028] The temperature acquisition unit comprises temperature detection sensors arranged in a "sparse-dense gradual change" mode along the blade root-tip direction;
[0029] The pressure acquisition unit comprises pressure detection sensors arranged in a "sparse-dense gradual change" mode along the blade root-tip direction;
[0030] The monitoring device is in communication connection with the intelligent monitoring device; the intelligent monitoring device comprises a deduction calibration module and an intelligent diagnosis decision module.
[0031] Compared with the prior art, the application has the following beneficial effects:
[0032] The technical scheme of the present application is a horse sword type swept blade, the root of the blade is close to a circle, the profile of the blade from the blade root to the blade tip is composed of multiple advanced airfoils similar to the wing, the thickness is smoothly transitioned from thick to thin, and a certain torsion angle is maintained between each section, so that the airfoil will not stall during the operation of the blade, and a larger aerodynamic lift and a smaller aerodynamic resistance are generated, the horse sword type sweep of the overall shape of the blade is generated by designing the constantly changing aerodynamic center of the airfoil, so that the noise of the blade during operation is smaller than that of other shaped blades, thereby improving the pulling force and aerodynamic efficiency of the propeller itself.
[0033] The propeller of the present application has high efficiency, low noise and high lift coefficient. BRIEF DESCRIPTION OF DRAWINGS
[0034] In order to more clearly illustrate the technical solutions in the present application or prior art, the following will briefly introduce the drawings needed to be used in the embodiments or prior art description. Obviously, the drawings in the following description are some embodiments of the present application, and other drawings can be obtained by those skilled in the art without creative labor.
[0035] Figure 1 The blade profile of the present application is shown in the figure.
[0036] Figure 2 The blade profile of the present application is shown in the figure.
[0037] In the figure: 1, blade root; 2, blade body; 3, airfoil; 4, blade tip; 5, center of profile; 6, base line; 7, chord line; 8, contour line. DETAILED DESCRIPTION
[0038] In order to make the purpose, technical scheme and advantages of the present application more clear, the technical scheme in the present application will be described clearly and completely in combination with the drawings in the present application. Obviously, the described embodiments are some embodiments of the present application, not all embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor belong to the scope of protection of the present application.
[0039] The present application provides a high-efficiency, low-noise small and medium power propeller blade, as shown in Figure 1 , Figure 2 , comprising:
[0040] The propeller blade is in the shape of a horse sword; the propeller blade comprises a blade root 1, a blade body 2 and a blade tip 4; the blade body 2 is composed of multiple airfoils 3 with different thicknesses, and the blade tip 4 is obtained by extending the blade body 2.
[0041] Preferably, the thickness of the plurality of airfoils 3 of the blade profile 2 from the blade root 1 to the blade tip 4 smoothly transitions from thick to thin, maintaining a twist angle between each section.
[0042] Preferably, the airfoil 3 is specially shaped by a camber line 5, a base line 6, a chord line 7 and a profile line 8, which cooperatively define the geometry of the airfoil 3.
[0043] Preferably, the blade root 1 is cylindrical, the blade edge is arc-shaped and the blade back is straight.
[0044] Preferably, the number of the airfoils 3 is 9.
[0045] Preferably, based on the flight requirements of the unmanned aerial vehicle, the airfoil 3 is designed by using the blade element theory and the Betz theory, and then designed in detail by using a design software and combining the design experience of other propeller models to obtain the structure of the propeller blade.
[0046] The design software includes ANSYS, CATIA and AutoCAD.
[0047] Preferably, the key size parameters of the airfoil 3 include a width b, a thickness c, a camber line 5 coordinate, an angle φ between the chord line 7 and the base line 6, and a radial distance R from the blade rotation center to the trailing edge of the airfoil 3; the X axis of the camber line 5 coordinate is the chord line.
[0048] Preferably, the key size parameters of the first airfoil are as follows: the radial distance R1 from the blade rotation center to the trailing edge of the airfoil is 358 mm, the width b is 206.5 mm, the thickness c is 55.4 mm, the camber line coordinate X0 is 77 mm, the camber line coordinate Y0 is 5.3 mm, and the angle φ between the chord line and the base line is 20.3°.
[0049] The key size parameters of the second airfoil are as follows: the radial distance R2 from the blade rotation center to the trailing edge of the airfoil is 405 mm, the width b is 209 mm, the thickness c is 52.3 mm, the camber line coordinate X0 is 81 mm, the camber line coordinate Y0 is 4.6 mm, and the angle φ between the chord line and the base line is 18.1°.
[0050] The key size parameters of the third airfoil are as follows: the radial distance R3 from the blade rotation center to the trailing edge of the airfoil is 607.5 mm, the width b is 218 mm, the thickness c is 39.2 mm, the camber line coordinate X0 is 96 mm, the camber line coordinate Y0 is 1.6 mm, and the angle φ between the chord line and the base line is 10.9°.
[0051] The key size parameters of the 4th airfoil are as follows: the radial distance R5 from the blade rotation center to the airfoil trailing edge is 810mm, the width b is 223mm, the thickness c is 26.8mm, the coordinate X0 of the cam is 103mm, the coordinate Y0 of the cam is -1.7mm, and the angle φ between the chord line and the base line is 4.2°;
[0052] The key size parameters of the 5th airfoil are as follows: the radial distance R5 from the blade rotation center to the airfoil trailing edge is 945mm, the width b is 219mm, the thickness c is 19.7mm, the coordinate X0 of the cam is 100mm, the coordinate Y0 of the cam is -3.9mm, and the angle φ between the chord line and the base line is 0°;
[0053] The key size parameters of the 6th airfoil are as follows: the radial distance R6 from the blade rotation center to the airfoil trailing edge is 1080mm, the width b is 209mm, the thickness c is 14.6mm, the coordinate X0 of the cam is 90mm, the coordinate Y0 of the cam is 5.3mm, and the angle φ between the chord line and the base line is -3.7°;
[0054] The key size parameters of the 7th airfoil are as follows: the radial distance R7 from the blade rotation center to the airfoil trailing edge is 1215mm, the width b is 181mm, the thickness c is 9.1mm, the coordinate X0 of the cam is 60mm, the coordinate Y0 of the cam is -8.4mm, and the angle φ between the chord line and the base line is -6.2°;
[0055] The key size parameters of the 8th airfoil are as follows: the radial distance R8 from the blade rotation center to the airfoil trailing edge is 1282.5mm, the width b is 156mm, the thickness c is 6.2mm, the coordinate X0 of the cam is 31mm, the coordinate Y0 of the cam is -9.5mm, and the angle φ between the chord line and the base line is -7.4°;
[0056] The key size parameters of the 9th airfoil are as follows: the radial distance R9 from the blade rotation center to the airfoil trailing edge is 1316.3mm, the width b is 136mm, the thickness c is 4.8mm, the coordinate X0 of the cam is 8mm, the coordinate Y0 of the cam is -10.1mm, and the angle φ between the chord line and the base line is -7.8°.
[0057] The following table is the airfoil data table of an embodiment of the present application.
[0058] Airfoil data table
[0059] 1 2 3 4 5 6 7 8 9 R 358 405 607.5 810 945 1080 1215 1282.5 1316.3 b 206.5 209 218 223 219 209 181 156 136 φ 20.3° 18.1° 10.9° 4.2° 0° -3.7° -6.2° -7.4° -7.8° C 55.4 52.3 39.2 26.8 19.7 14.6 9.1 6.2 4.8 X0 77 81 96 103 100 90 60 31 8 [Y0] 5.3 4.6 1.6 -1.7 -3.9 -6.2 -8.4 -9.5 -10.1
[0060] The purpose of the present application is to improve the working efficiency of the propeller, reduce the noise of the propeller, design the propeller blade based on the advanced aircraft airfoil, reduce the inflow velocity of the airfoil in the region, and make the aircraft fly faster and more fuel-efficient.
[0061] Because the aerodynamic load borne by the blade in work is very complex: the propeller needs to bear the centrifugal force load, centrifugal bending moment load, aerodynamic force lift load, aerodynamic resistance load and aerodynamic bending moment load of air power on the blade in the whole process of take-off, climbing, cruising, falling and ground sliding, therefore, if high efficiency and low noise are achieved, repeated iteration calculation is needed.
[0062] The beneficial effects of the above technical solution are:
[0063] The technical solution of the present application is a horse sword type swept-back blade, the blade root is close to a circular shape, the blade body 2 profile from the blade root 1 to the blade tip 4 is composed of multiple advanced airfoils similar to the wing shape, the thickness is smoothly transitioned from thick to thin, and a certain torsion angle is maintained between each section, so that the airfoil will not stall in the working process of the blade, and a larger aerodynamic lift and a smaller aerodynamic resistance are generated, the horse sword type sweep is generated in the overall shape of the blade by designing the continuously changing aerodynamic center of the airfoil, so that the noise of the blade in work is smaller than that of other shape blades, thereby improving the pulling force and aerodynamic efficiency of the propeller itself.
[0064] The propeller of the present application has high efficiency, low noise and high lift coefficient.
[0065] Embodiment 2, based on embodiment 1, further comprises:
[0066] The monitoring device comprises:
[0067] The strain acquisition unit comprises strain detection sensors arranged along the blade root 1-blade tip 4 according to the "sparse and dense gradual change";
[0068] The temperature acquisition unit comprises temperature detection sensors arranged along the blade root 1-blade tip 4 according to the "sparse and dense gradual change";
[0069] The pressure acquisition unit comprises pressure detection sensors arranged along the blade root 1-blade tip 4 according to the "sparse and dense gradual change";
[0070] The monitoring device is in communication connection with the intelligent monitoring device; the intelligent monitoring device comprises a reasoning calibration module and an intelligent diagnosis decision module.
[0071] Preferably, the reasoning calibration module comprises:
[0072] The deduction unit is in communication connection with the monitoring device, receives the pressure distribution data, combines the real-time flight attitude information obtained from the unmanned aerial vehicle flight control system, and calculates the actual angle of attack and Mach number of the blade in real time through an aerodynamic inversion algorithm based on the blade element theory; the "improved blade element-momentum theory fusion algorithm" (tail flow contraction factor is introduced for correction) is used to calculate the actual angle of attack (detection range -10°+15°, accuracy ±0.5°) and Mach number (detection range 0 to 0.5, accuracy ±0.01) in real time, and the inversion error is reduced by 30% compared with the traditional blade element theory;
[0073] The calibration unit is in communication connection with the deduction unit, and when the deviation between the actual angle of attack and Mach number obtained by inversion and the calculated value of the theoretical aerodynamic model is greater than 10%, the corresponding correction coefficient of the working condition is automatically called to dynamically calibrate the detection threshold, so that the detection error of the aerodynamic efficiency of the blade in the complex maneuvering process is less than or equal to 3%; and the "task priority weight" (such as the calibration accuracy weight is increased when an emergency task occurs) is introduced in the calibration process;
[0074] The intelligent diagnosis decision module comprises:
[0075] The edge intelligent reasoning unit adopts an unmanned aerial vehicle special-purpose heterogeneous processing chip with a power consumption of less than or equal to 0.5 W, is in communication with the deduction and calibration module and the unmanned aerial vehicle flight control system respectively, receives the strain, temperature and pressure data and the flight control system state information, constructs a "multi-dimensional fault feature matrix" (containing strain gradient, temperature change rate, pressure fluctuation amplitude, motor speed fluctuation and other characteristic parameters), adopts a "vibration-strain" fusion noise reduction algorithm (combined with wavelet threshold noise reduction and strain signal baseline correction, wherein the threshold self-adaptive adjustment factor is positively correlated with the vibration frequency) for the unmanned aerial vehicle 100-500 Hz high-frequency vibration environment, so that the crack recognition accuracy is improved from 0.3 mm to 0.2 mm, and the abnormal vibration misjudgment rate is less than or equal to 1% when the acceleration is greater than or equal to 0.6 g;
[0076] The maintenance scheme generation unit is in electrical connection with the edge intelligent reasoning unit, adopts a "fault-maintenance knowledge graph" (containing more than 500 historical fault cases and corresponding solutions), and encrypts the fault type (including crack, abnormal vibration, aerodynamic efficiency attenuation, etc.), fault position and severity obtained by diagnosis through the unmanned aerial vehicle data transmission link (using a 2.4 GHz frequency band, transmission rate is greater than or equal to 1 Mbps) to the ground station, so that the ground station can generate a maintenance scheme report containing spare part model recommendation (matching blade model and unmanned aerial vehicle model) and replacement cycle suggestion (according to fault severity and flight task requirements).
[0077] The above-mentioned scheme has the beneficial effects that:
[0078] Through the working condition self-adaptation of the inference calibration module, the aerodynamic efficiency detection error is ≤3% under complex maneuvers such as canyon shuttle and sudden stop hovering, which is 2-3 times higher than that of the traditional scheme (error 8%-12%), ensuring the flight stability of tasks such as inspection and logistics.
[0079] The fusion denoising algorithm makes the crack recognition accuracy reach 0.2mm, and the structure damage is warned 3-5 flight cycles in advance, reducing the risk of sudden propeller breakage of the unmanned aerial vehicle (fault prediction accuracy ≥95%).
[0080] A closed loop of "detection-diagnosis-repair" is constructed, and the ground station repair scheme generation time is ≤10s, the spare parts replacement cycle is shortened, and the operation and maintenance efficiency is improved.
[0081] Strain, temperature, and pressure detection are deeply coordinated with aerodynamic inversion and fault diagnosis to realize "structure health-aerodynamic performance" linkage monitoring (such as abnormal temperature rise → predicting structure thermal fatigue → calibrating aerodynamic threshold).
[0082] Algorithm-hardware collaborative optimization: FPGA of heterogeneous chips accelerates fault reasoning (processing time ≤50ms), and ARM core is responsible for communication and decision-making, solving the contradiction between "limited computing power" and "complex tasks" of the unmanned aerial vehicle, and providing an innovative paradigm for intelligent detection of small aviation equipment.
[0083] Finally, it should be noted that: the above examples are only used to illustrate the technical solutions of the present application, and not to limit them; although the present application has been described in detail with reference to the foregoing examples, those skilled in the art should understand that they can still modify the technical solutions recorded in the foregoing examples, or make equivalent replacements for part of the technical features; and these modifications or replacements do not make the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present application.
[0084] The technical solutions of the embodiments of the present application.
[0085] The technical solutions of the embodiments of the present application.
[0086] The technical solutions of the embodiments of the present application.
Claims
1. A high-efficiency, low-noise, small-to-medium power propeller blade, characterized in that, The propeller blade has a saber-shaped shape; the propeller blade includes a blade root (1), a blade body (2), and a blade tip (4); the blade body (2) is composed of multiple airfoils (3) of different thicknesses, and the blade tip (4) is an extension of the blade body (2).
2. The high-efficiency, low-noise, small-to-medium power propeller blade according to claim 1, characterized in that, The thickness of the multiple airfoils (3) in the cross section of the leaf body (2) from the leaf root (1) to the leaf tip (4) smoothly transitions from thick to thin, and a certain torsion angle is maintained between each cross section.
3. The high-efficiency, low-noise, small-to-medium power propeller blade according to claim 1, characterized in that, The airfoil (3) is a special shape composed of the centroid (5), the base line (6), the chord line (7), and the outline (8). The parts work together to define the geometry of the airfoil (3).
4. The high-efficiency, low-noise, small-to-medium power propeller blade according to claim 1, characterized in that, The leaf root (1) is cylindrical.
5. The high-efficiency, low-noise, small-to-medium power propeller blade according to claim 1, characterized in that, The blade of the saber-shaped blade is curved, while the back of the blade is straight.
6. The high-efficiency, low-noise, small-to-medium power propeller blade according to claim 1, characterized in that, There are 9 airfoils (3).
7. The high-efficiency, low-noise, small-to-medium power propeller blade according to claim 1, characterized in that, Based on the requirements of unmanned aerial vehicle flight, the aerodynamic design is carried out using the blade element theory and Betz theory. Then, through design software and combined with the design experience of other propeller models, a detailed design is carried out to obtain the structural shape of the propeller blades. The design software includes ANSYLS, CATIA, and AutoCAD.
8. The high-efficiency, low-noise, small-to-medium power propeller blade according to claim 1, characterized in that, The key dimensional parameters of the airfoil (3) include: width b, thickness c, centroid (5) coordinates, angle φ between the chord line (7) and the base line (6), and radial distance R from the blade rotation center to the trailing edge of the airfoil (3); the X-axis of the centroid (5) coordinates is the chord line.
9. A high-efficiency, low-noise, small-to-medium power propeller blade according to claim 8, characterized in that, The key dimensional parameters of the first airfoil are as follows: the radial distance R1 from the blade rotation center to the airfoil trailing edge is 358 mm, the width b is 206.5 mm, the thickness c is 55.4 mm, the centroid coordinates X0 is 77 mm, Y0 is 5.3 mm, and the angle φ between the chord and the base line is 20.3°. The key dimensional parameters of the second airfoil are as follows: the radial distance R2 from the blade rotation center to the airfoil trailing edge is 405mm, the width b is 209mm, the thickness c is 52.3mm, the centroid coordinates X0 is 81mm, Y0 is 4.6mm, and the angle φ between the chord line and the base line is 18.1°. The key dimensional parameters of the third airfoil are as follows: the radial distance R3 from the blade rotation center to the airfoil trailing edge is 607.5 mm, the width b is 218 mm, the thickness c is 39.2 mm, the centroid coordinates X0 is 96 mm, Y0 is 1.6 mm, and the angle φ between the chord and the base line is 10.9°. The key dimensional parameters of the fourth airfoil are as follows: the radial distance R5 from the blade rotation center to the airfoil trailing edge is 810mm, the width b is 223mm, the thickness c is 26.8mm, the centroid coordinates X0 is 103mm, Y0 is -1.7mm, and the angle φ between the chord and the base line is 4.2°. The key dimensional parameters of the fifth airfoil are as follows: the radial distance R5 from the blade rotation center to the airfoil trailing edge is 945mm, the width b is 219mm, the thickness c is 19.7mm, the centroid coordinates X0 is 100mm, Y0 is -3.9mm, and the angle φ between the chord and the base line is 0°. The key dimensional parameters of the 6th airfoil are as follows: the radial distance R6 from the blade rotation center to the airfoil trailing edge is 1080mm, the width b is 209mm, the thickness c is 14.6mm, the centroid coordinates X0 is 90mm, Y0 is 5.3mm, and the angle φ between the chord and the base line is -3.7°. The key dimensional parameters of the 7th airfoil are as follows: the radial distance R7 from the blade rotation center to the airfoil trailing edge is 1215mm, the width b is 181mm, the thickness c is 9.1mm, the centroid coordinates X0 is 60mm, Y0 is -8.4mm, and the angle φ between the chord and the base line is -6.2°. The key dimensional parameters of the 8th airfoil are as follows: the radial distance R8 from the blade rotation center to the airfoil trailing edge is 1282.5mm, the width b is 156mm, the thickness c is 6.2mm, the centroid coordinates X0 is 31mm, Y0 is -9.5mm, and the angle φ between the chord and the base line is -7.4°. The key dimensional parameters of the 9th airfoil are as follows: the radial distance R9 from the blade rotation center to the airfoil trailing edge is 1316.3 mm, the width b is 136 mm, the thickness c is 4.8 mm, the centroid coordinates X0 is 8 mm, Y0 is -10.1 mm, and the angle φ between the chord and the base line is -7.8°.
10. A high-efficiency, low-noise, small-to-medium power propeller blade according to claim 1, characterized in that, Also includes: Monitoring device, the monitoring device comprising: Strain acquisition unit: includes strain detection sensors arranged in a "gradually varying density" pattern along the leaf root (1) to the leaf tip (4); Temperature acquisition unit: includes temperature detection sensors arranged in a "gradually changing density" pattern along the leaf root (1) to the leaf tip (4); Pressure acquisition unit: includes pressure detection sensors arranged in a "gradually varying density" pattern along the leaf root (1) to the leaf tip (4); The monitoring device is communicatively connected to the intelligent monitoring device; the intelligent monitoring device includes: a simulation calibration module and an intelligent diagnostic decision module.