CN116698341A - high-Reynolds number single-screw aerodynamic force measurement test device and measurement method thereof - Google Patents
high-Reynolds number single-screw aerodynamic force measurement test device and measurement method thereof Download PDFInfo
- Publication number
- CN116698341A CN116698341A CN202310445059.0A CN202310445059A CN116698341A CN 116698341 A CN116698341 A CN 116698341A CN 202310445059 A CN202310445059 A CN 202310445059A CN 116698341 A CN116698341 A CN 116698341A
- Authority
- CN
- China
- Prior art keywords
- motor
- reynolds number
- torque sensor
- sleeve
- aerodynamic force
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000005259 measurement Methods 0.000 title claims abstract description 18
- 238000000691 measurement method Methods 0.000 title claims abstract description 5
- 238000000034 method Methods 0.000 claims abstract description 5
- 238000005452 bending Methods 0.000 claims abstract description 4
- 238000009434 installation Methods 0.000 claims description 9
- 238000007664 blowing Methods 0.000 claims description 3
- 238000004364 calculation method Methods 0.000 claims description 3
- 238000007789 sealing Methods 0.000 claims 1
- 230000008878 coupling Effects 0.000 description 4
- 238000010168 coupling process Methods 0.000 description 4
- 238000005859 coupling reaction Methods 0.000 description 4
- 238000004088 simulation Methods 0.000 description 4
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000011888 foil Substances 0.000 description 1
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Landscapes
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention discloses a high-Reynolds number single-propeller aerodynamic force measurement test device and a measurement method thereof, and belongs to the field of wind tunnel tests. Comprises a rotating shaft balance, an extension shaft body, a torque sensor, a turbine air motor, a motor mounting seat and a supporting rod. The propeller model is connected with a rotating shaft balance, the rotating shaft balance is connected with a torque sensor through an extension shaft, the torque sensor is connected with a turbine air motor, a strain gauge measures the bending moment of a blade of the propeller model, the rotating shaft balance measures the aerodynamic force of the propeller model, and the torque sensor monitors the torque of an output shaft of the turbine air motor. The measuring method comprises the following steps: the test device is arranged on a pressurized wind tunnel test section, and the density of a test flow field is increased by increasing the internal pressure of the wind tunnel by utilizing the pressurized wind tunnel, so that the test Reynolds number is increased, and the slipstream test of the high Reynolds number propeller aircraft is realized. The invention improves the accuracy of the wind tunnel test of the propeller model and reduces the test cost.
Description
Technical Field
The invention relates to the field of wind tunnel tests, in particular to a high Reynolds number single-screw aerodynamic force measurement test device and a measurement method thereof.
Background
In the wind tunnel test of the slip stream of the propeller aircraft, the Reynolds number is taken as one of key simulation parameters of the wind tunnel test, and the Reynolds number is too low to be an important reason for influencing the consistency of wind tunnel test data and real flight data, so that the wind tunnel test of the propeller aircraft with high Reynolds number is necessary. The mode of increasing the Reynolds number comprises two methods of increasing the test wind speed and increasing the model size, wherein the increasing the test wind speed is mainly used for simulating the Mach number of another simulation parameter of the wind tunnel test, is not suitable for collecting aerodynamic force of the propeller model in a high Reynolds number state, and the increasing of the model size can increase the test cost.
In a high Reynolds number propeller aircraft slipstream wind tunnel test, firstly, the aerodynamic force of an independent propeller model consistent with the full-aircraft model scaling is required to be measured and used for determining propeller simulation parameters. Due to the increase of the Reynolds number, the simulation parameters of the propeller are correspondingly changed, and the power and the torque of the required propeller driving device are larger. Therefore, a high reynolds number single-screw aerodynamic force measurement test device is needed to provide enough driving force for a screw model.
Disclosure of Invention
In order to solve the problems, the invention provides the high-Reynolds number single-screw aerodynamic force measurement test device, which solves the problem that the existing measurement test device provides insufficient driving force for a screw model, and has small influence on the screw model aerodynamic force due to the external dimension.
The technical scheme adopted by the invention is as follows: the utility model provides a high Reynolds number single screw aerodynamic force measurement test device, includes rotation axis balance, extension shaft sleeve, extension shaft body, torque sensor, motor sleeve, sensor adapter sleeve, turbine air motor, motor mount pad, branch and foil gage, the extension shaft body pass through the bearing and support in the inside of extension shaft sleeve, the rear end of extension shaft body pass through front coupling and torque sensor's front end connection, torque sensor be located the sensor adapter sleeve, torque sensor's rear end pass through rear coupling and turbine air motor's output shaft, extension shaft sleeve's tail end and sensor adapter sleeve's front end fixed connection, sensor adapter sleeve's tail end and motor sleeve's front end fixed connection, turbine air motor install on motor mount pad, motor sleeve's tail end and motor mount pad fixed connection, turbine air motor be located the airtight space that motor sleeve and motor mount pad formed, motor mount pad and branch fixed connection; the front end of the rotating shaft balance is fixedly connected with the propeller model, strain gauges are buried at the positions close to the blade root parts of the propeller model, and the inside of the center of the rotating shaft balance is radially positioned with the front end of the extension shaft body through a key and is fixedly connected with the front end of the extension shaft body through a bolt; the turbine air motor drives the torque sensor, the extension shaft body, the rotating shaft balance and the propeller model to synchronously rotate; the strain gauge measures the blade bending moment of the propeller model, the rotating shaft balance measures aerodynamic force of the propeller model, and the torque sensor monitors output shaft torque of the turbine air motor.
Further, the axes of the propeller model, the rotary shaft balance, the extension shaft body, the torque sensor and the turbine air motor are all positioned on the same axis.
Further, the output shafts of the extension shaft body, the front coupler, the torque sensor, the rear coupler and the turbine air motor are hollow structures, and the signal wires of the rotating shaft balance and the signal wires of the strain gauges sequentially penetrate through the internal cavities of the extension shaft body, the front coupler, the torque sensor, the rear coupler and the output shaft of the turbine air motor.
Further, the tail part of the turbine air motor is provided with a conductive slip ring.
Furthermore, a high-pressure air inlet pipeline installation space, an exhaust pipeline installation space and an equipment wiring installation space are reserved in the support rod.
Further, the upper plane of the motor sleeve is provided with a high-pressure air inlet interface and is connected with a high-pressure air inlet pipeline.
Furthermore, the rotating shaft balance, the extension shaft sleeve, the sensor connecting sleeve, the motor sleeve and the motor mounting seat are all provided with fairings.
The invention also aims to provide a high-Reynolds number single-screw aerodynamic force measuring method obtained by the high-Reynolds number single-screw aerodynamic force measuring test device, which improves the Reynolds number by increasing the pressure in a wind tunnel so as to increase the density of a flow field, and solves the problem of high test cost in the prior art, and comprises the following specific steps:
step one, after the wind tunnel is pressurized to a test preset pressure, acquiring initial readings of a rotating shaft balance of a propeller model under the same angle as a wind tunnel blowing test by a dynamic data acquisition system in a windless state;
step two, the wind tunnel is winded, high-pressure air supply is controlled to enable the propeller model to rotate to an initial rotating speed, wind tunnel wind speed is continuously increased to a test preset wind speed, and the high-pressure air supply is increased to enable the rotating speed of the propeller model to reach the test preset value;
and thirdly, after the wind tunnel flow field and the rotating speed feedback of the propeller model are stable, a dynamic data acquisition system acquires dynamic signals of a rotating shaft balance and a torque sensor and rotating speed signals of the propeller model, initial readings obtained in the first step are subtracted from rotating shaft balance data, aerodynamic data with the influence of the dead weight of the propeller model are obtained after calculation processing, and aerodynamic force of the propeller model in a high Reynolds number state is obtained after the dead weight of the propeller model is subtracted.
The invention has the beneficial effects and advantages that: the invention improves the accuracy of the wind tunnel test of the propeller model and reduces the test cost. The test device is arranged on a pressurized wind tunnel test section, and the density of a test flow field is increased by increasing the internal pressure of the wind tunnel by utilizing the pressurized wind tunnel, so that the test Reynolds number is increased, and the slipstream test of the high Reynolds number propeller aircraft is realized.
Drawings
FIG. 1 is a schematic diagram of a high Reynolds number single-screw aerodynamic force measurement test device of the present invention;
fig. 2 is a sectional structural view of fig. 1.
Wherein: 1. the propeller model comprises a propeller model 2, a rotating shaft balance 3, an extension shaft sleeve 4, an extension shaft body 5, a torque sensor 6, a front coupler 7, a motor sleeve 8, a sensor connecting sleeve 9, a turbine air motor 10, a rear coupler 11, a motor mounting seat 12 and a supporting rod.
Detailed Description
The invention is further illustrated by the following examples according to the drawings of the specification:
example 1
The high-Reynolds number single-propeller aerodynamic force measurement test device comprises a rotating shaft balance 2, an extension shaft sleeve 3, an extension shaft body 4, a torque sensor 5, a motor sleeve 7, a sensor connecting sleeve 8, a turbine air motor 9, a motor mounting seat 11, a supporting rod 12 and a strain gauge, wherein the extension shaft body 4 is supported in the extension shaft sleeve 3 through a bearing, the rear end of the extension shaft body 4 is connected with the front end of the torque sensor 5 through a front coupling 6, the torque sensor 5 is positioned in the sensor connecting sleeve 8, and the rear end of the torque sensor 5 is connected with an output shaft of the turbine air motor 9 through a rear coupling 10; the tail end of the extension shaft sleeve 3 is fixedly connected with the front end of the sensor connecting sleeve 8 through a screw, the tail end of the sensor connecting sleeve 8 is fixedly connected with the front end of the motor sleeve 7 through a screw, the turbine air motor 9 is mounted on the motor mounting seat 11 through a screw, the tail end of the motor sleeve 7 is fixedly connected with the motor mounting seat 11, the turbine air motor 9 is positioned in a closed space formed by the motor sleeve 7 and the motor mounting seat 11, and the motor mounting seat 11 is fixedly connected with the supporting rod 12; the propeller model 1 comprises blades, a front hub and a rear hub, and the blade roots are clamped by the front hub and the rear hub through screw fixation. The front end of the rotating shaft balance 2 is fixedly connected with the rear propeller hub, strain gauges are buried at the positions close to the blade root of the propeller model 1, and the inside of the center of the rotating shaft balance 2 is radially positioned with the front end of the extension shaft body 4 through a key and is fixedly connected with the front end of the extension shaft body 4 through a bolt; the turbine air motor 9 drives the torque sensor 5, the extension shaft body 4, the rotating shaft balance 2 and the propeller model 1 to synchronously rotate; the strain gauge measures the blade bending moment of the propeller model 1, the rotating shaft balance 2 measures the aerodynamic force of the propeller model 1, and the torque sensor 5 monitors the output shaft torque of the turbine air motor 9.
The axes of the propeller model 1, the rotating shaft balance 2, the extension shaft body 4, the torque sensor 5 and the turbine air motor 9 are all positioned on the same axis.
The output shafts of the extension shaft body 4, the front coupler 6, the torque sensor 5, the rear coupler 10 and the turbine air motor 9 are hollow structures, and the signal wire and the strain gauge signal wire of the rotating shaft balance 2 sequentially penetrate through the internal cavities of the extension shaft body 4, the front coupler 6, the torque sensor 5, the rear coupler 10 and the output shaft of the turbine air motor 9. The tail part of the turbine air motor 9 is provided with a conductive slip ring. The support rod 12 is internally reserved with a high-pressure air inlet pipeline installation space, an exhaust pipeline installation space and an equipment wiring installation space. The upper plane of the motor sleeve 7 is provided with a high-pressure air inlet interface and is connected with a high-pressure air inlet pipeline. The rotating shaft balance 2, the extension shaft sleeve 3, the sensor connecting sleeve 8, the motor sleeve 7 and the motor mounting seat 11 are all provided with fairings.
Example 2
The high-Reynolds number single-screw aerodynamic force measuring method obtained by the test equipment provided in the embodiment 1 obtains a screw test high-Reynolds number environment by increasing the pressure in a low-speed pressurizing wind tunnel and increasing the flow field density, and comprises the following steps:
step one, after the wind tunnel is pressurized to the preset test pressure, acquiring initial readings of a rotating shaft balance 2 of a propeller model 1 under the same angle as the wind tunnel blowing test by a dynamic data acquisition system in a windless state;
step two, the wind tunnel is winded, high-pressure air supply is controlled to enable the propeller model 1 to rotate to an initial rotating speed, wind tunnel wind speed is continuously increased to a test preset wind speed, and the high-pressure air supply is increased to enable the rotating speed of the propeller model 1 to reach the test preset value;
and thirdly, after the wind tunnel flow field and the rotating speed feedback of the propeller model 1 are stabilized, a dynamic data acquisition system acquires dynamic signals of the rotating shaft balance 2 and the torque sensor 5 and the rotating speed signal of the propeller model 1, initial readings obtained in the first step are subtracted from the rotating shaft balance 2 data, aerodynamic data with the self weight of the propeller model 1 are obtained after calculation processing, and aerodynamic force of the propeller model 1 in a high Reynolds number state is obtained after the self weight of the propeller model 1 is subtracted.
Claims (8)
1. The utility model provides a high Reynolds number single screw aerodynamic force measurement test device, includes rotation axis balance (2), extension axle sleeve (3), extension axle body (4), torque sensor (5), motor sleeve (7), sensor adapter sleeve (8), turbine air motor (9), motor mount pad (11), branch (12) and strain gauge, its characterized in that: the novel air turbine motor is characterized in that the extension shaft body (4) is supported in the extension shaft sleeve (3) through a bearing, the rear end of the extension shaft body (4) is connected with the front end of the torque sensor (5) through the front coupler (6), the torque sensor (5) is located in the sensor connecting sleeve (8), the rear end of the torque sensor (5) is connected with the output shaft of the turbine air motor (9) through the rear coupler (10), the tail end of the extension shaft sleeve (3) is fixedly connected with the front end of the sensor connecting sleeve (8), the tail end of the sensor connecting sleeve (8) is fixedly connected with the front end of the motor sleeve (7), the turbine air motor (9) is installed on the motor installing seat (11), the tail end of the motor sleeve (7) is fixedly connected with the motor installing seat (11), the turbine air motor (9) is located in a sealing space formed by the motor sleeve (7) and the motor installing seat (11), and the motor installing seat (12) is fixedly connected with the motor installing seat (12). The front end of the rotating shaft balance (2) is fixedly connected with the propeller model (1), a strain gauge is embedded at the blade root part close to the propeller model (1), and the inside of the center of the rotating shaft balance (2) is radially positioned with the front end of the extension shaft body (4) through a key and is fixedly connected with the front end of the extension shaft body (4) through a bolt; the turbine air motor (9) drives the torque sensor (5), the extension shaft body (4), the rotating shaft balance (2) and the propeller model (1) to synchronously rotate; the strain gauge measures the blade bending moment of the propeller model (1), the rotating shaft balance (2) measures aerodynamic force of the propeller model (1), and the torque sensor (5) monitors output shaft torque of the turbine air motor (9).
2. A high reynolds number single-screw aerodynamic force measurement test device as recited in claim 1, wherein: the screw propeller model (1), the rotary shaft balance (2), the extension shaft body (4), the torque sensor (5) and the axis of the turbine air motor (9) are all positioned on the same axis.
3. A high reynolds number single-screw aerodynamic force measurement test device as recited in claim 2, wherein: the output shafts of the extension shaft body (4), the front coupler (6), the torque sensor (5), the rear coupler (10) and the turbine air motor (9) are hollow structures, and the signal line of the rotating shaft balance (2) and the signal line of the strain gauge sequentially penetrate through the internal cavities of the extension shaft body (4), the front coupler (6), the torque sensor (5), the rear coupler (10) and the output shaft of the turbine air motor (9).
4. A high reynolds number single-screw aerodynamic force measurement test device as defined in claim 3, wherein: the tail part of the turbine air motor (9) is provided with an electric slip ring.
5. The high reynolds number single-screw aerodynamic force measurement test device of claim 4, wherein: the high-pressure air inlet pipeline installation space, the exhaust pipeline installation space and the equipment wiring installation space are reserved in the support rod (12).
6. The high reynolds number single-screw aerodynamic force measurement test device of claim 5, wherein: the upper plane of the motor sleeve (7) is provided with a high-pressure air inlet interface and is connected with a high-pressure air inlet pipeline.
7. A high reynolds number single-screw aerodynamic force measurement test device as defined in any of claims 1-6, wherein: the rotating shaft balance (2), the extension shaft sleeve (3), the sensor connecting sleeve (8), the motor sleeve (7) and the motor mounting seat (11) are all provided with fairings.
8. A high reynolds number single-screw aerodynamic force measurement method obtained by a high reynolds number single-screw aerodynamic force measurement test device according to claim 7, wherein the reynolds number is increased by increasing the pressure in the wind tunnel to increase the flow field density, the method comprises the following steps:
step one, after the wind tunnel is pressurized to the preset test pressure, acquiring initial readings of a rotating shaft balance (2) of a propeller model (1) under the same angle as the wind tunnel blowing test by a dynamic data acquisition system in a windless state;
step two, the wind tunnel is winded, high-pressure air supply is controlled to enable the propeller model (1) to rotate to an initial rotating speed, wind tunnel wind speed is continuously increased to a test preset wind speed, and the high-pressure air supply is increased to enable the rotating speed of the propeller model (1) to reach the test preset value;
and thirdly, after the rotation speed feedback of the wind tunnel flow field and the propeller model (1) is stable, a dynamic data acquisition system acquires dynamic signals of the rotating shaft balance (2) and the torque sensor (5) and rotation speed signals of the propeller model (1), initial readings obtained in the first step are subtracted from the data of the rotating shaft balance (2), aerodynamic data with the influence of the dead weight of the propeller model (1) are obtained after calculation processing, and aerodynamic force of the propeller model (1) in a high Reynolds number state is obtained after the dead weight of the propeller model (1) is subtracted.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310445059.0A CN116698341A (en) | 2023-04-24 | 2023-04-24 | high-Reynolds number single-screw aerodynamic force measurement test device and measurement method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310445059.0A CN116698341A (en) | 2023-04-24 | 2023-04-24 | high-Reynolds number single-screw aerodynamic force measurement test device and measurement method thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116698341A true CN116698341A (en) | 2023-09-05 |
Family
ID=87834716
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310445059.0A Pending CN116698341A (en) | 2023-04-24 | 2023-04-24 | high-Reynolds number single-screw aerodynamic force measurement test device and measurement method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116698341A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117740307A (en) * | 2024-02-18 | 2024-03-22 | 中国空气动力研究与发展中心低速空气动力研究所 | Method for predicting performance of full-size rotor wing |
-
2023
- 2023-04-24 CN CN202310445059.0A patent/CN116698341A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117740307A (en) * | 2024-02-18 | 2024-03-22 | 中国空气动力研究与发展中心低速空气动力研究所 | Method for predicting performance of full-size rotor wing |
| CN117740307B (en) * | 2024-02-18 | 2024-05-14 | 中国空气动力研究与发展中心低速空气动力研究所 | Method for predicting performance of full-size rotor wing |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN201326511Y (en) | Signal acquisition device for independent pitch system of wind turbine | |
| CN116698341A (en) | high-Reynolds number single-screw aerodynamic force measurement test device and measurement method thereof | |
| CN109186922A (en) | A kind of wind tunnel test methods of helicopter co-axis double propeller hub model | |
| CN110779678A (en) | Test bed capable of synchronously measuring aerodynamic characteristics and acoustic characteristics of large-size propeller | |
| CN103443454A (en) | Wind turbine blade with air pressure sensors | |
| KR101038508B1 (en) | Device and method of wind tunnel testing | |
| CN109556878B (en) | Synchronous measurement device and method for pneumatic performance and efficiency of electric propeller system | |
| CN112504610A (en) | High-altitude propeller low-density wind tunnel test system and method | |
| CN110849575A (en) | Wind turbine complete machine aerodynamic force measuring system and method | |
| CN105021337A (en) | Propeller driving rotation force measuring apparatus and force measuring method | |
| CN115140323A (en) | Pneumatic characteristic testing device of tension torque decoupling type single rotor system | |
| CN113252286A (en) | Aircraft composite control wind tunnel semi-physical simulation test system | |
| CN110901951A (en) | Multifunctional tail rotor test system | |
| CN117073958B (en) | Open rotor engine rotor and stator blade high-speed wind tunnel test device | |
| CN201307004Y (en) | A helicopter airscrew propeller pitch angle dynamic calibration system | |
| CN116358757A (en) | Mechanical parameter testing device for electric propulsion system of electric propulsion aircraft | |
| CN209838604U (en) | Wind turbine blade stress-strain testing device based on rotating platform | |
| Schultz et al. | A parametric windtunnel test on rotorcraft aerodynamics and aeroacoustics (Helishape)—test procedures and representative results | |
| CN205592074U (en) | Long -range automatic measuring device of wind generating set mechanical load | |
| CN108691727B (en) | Wind turbine guide sleeve | |
| CN106560685A (en) | Airfoil-shaped dynamic aerodynamic characteristic test bench for horizontal-axis wind turbine | |
| CN112683189B (en) | Marine propeller blade dynamic strain measuring device based on FBG | |
| CN210375613U (en) | Wind tunnel test device for thrust measurement of oblique cutting nozzle of hypersonic vehicle | |
| CN219319442U (en) | Gyroscope speed measuring sensor calibration system of wind power variable pitch driver | |
| CN109724726B (en) | Turbocharger axial force testing system and testing method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |