CN209214916U - A kind of electric propeller system aeroperformance and efficiency synchronous measuring apparatus - Google Patents
A kind of electric propeller system aeroperformance and efficiency synchronous measuring apparatus Download PDFInfo
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- CN209214916U CN209214916U CN201822164033.6U CN201822164033U CN209214916U CN 209214916 U CN209214916 U CN 209214916U CN 201822164033 U CN201822164033 U CN 201822164033U CN 209214916 U CN209214916 U CN 209214916U
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Abstract
A kind of electric propeller system aeroperformance and efficiency synchronous measuring apparatus, motor, torque rotational speed meters and cantilever beam tension sensor are fixed on the base, torque rotational speed meters one end is sequentially connected the first transmission shaft, torque transmitting sliding sleeve and second driving shaft, and air propeller is fixed on second driving shaft and is located at test chamber direction of flow upstream；Baffle ring sleeve is fixed on second driving shaft for limiting to cantilever beam tension sensor；The torque rotational speed meters other end is fixedly connected with motor；Frequency converter is connected between motor and power meter；The data output end of torque rotational speed meters, power meter and cantilever beam tension sensor is connected with computer.Measurement method are as follows: rotated under wind speed setting by motor drive air propeller；Pulling force, axis torque, revolving speed and the output power of motor for measuring air propeller, are transferred to the aeroperformance that air propeller is calculated in computer, motor efficiency and electric propeller system effectiveness for data measured.
Description
Technical field
The utility model belongs to aviation electric propeller system aeroperformance and efficiency test technical field, more particularly to
A kind of electric propeller system aeroperformance and efficiency synchronous measuring apparatus.
Background technique
Propeller aeroplane is to use air propeller as the aircraft of dynamical system, has good low speed and plays drop characteristic,
Still in occupation of critical role in modern Aviation transport.For traditional propeller system using combustion engine powered, there is safety can
By the disadvantages of property is poor, structure is complicated, noise is big, and uses and have energy conservation and environmental protection, height by the propeller system of power of motor
The advantages that imitating low consumption and good comfort, now has become the preferred dynamical system of electric airplane.
Electric screw oar system mainly includes propeller and motor two large divisions, the aeroperformance and motor of propeller
Power out-put characteristic determine the superiority and inferiority of electric propeller system performance.Currently, can be with for independent propeller performance
Wind tunnel experiment carries out assessment, although propeller is also by motor drive during the test, motor here is only
Driving device when being only propeller performance test experiment, rather than the motor in electric screw oar system, and test
The data of acquisition are only the parameters such as aerodynamic force.Motor in electric screw oar system choose can by revolution speed of propeller,
The parameters such as required horsepower determine that in addition the efficiency of independent motor can also be tested by special testboard.
Currently, being divided into two kinds for the experiment of aviation electric screw oar system, the first is pneumatic for air propeller
The wind tunnel experiment of performance, second is the wind tunnel experiment for being directed to electric screw oar system, and two kinds of wind tunnel experiments are to be completely independent
It carries out.
For the wind tunnel experiment that the first is tested for air propeller aeroperformance, it is intended merely to assess
Design of Propeller scheme superiority and inferiority degree；For the wind tunnel experiment that second is tested for motor efficiency, only
The efficiency of motor can be measured.Although can be evaluated whether electric propeller by the aeroperformance of propeller and the efficiency of motor
System effectiveness, however can not be used to whether accurate evaluation propeller match with motor, the experimental situation furthermore tested twice, survey
The difference for trying equipment, by inevitably there are equipment errors and random error.Since experiment must be carried out independently in two times, lead
Experimental cost is caused to improve, efficiency reduces.Therefore, electronic spiral shell is evaluated only by propeller performance and the efficiency of motor
It is not rigorous for revolving oar system efficiency.
Utility model content
In view of the problems of the existing technology, the utility model provides a kind of electric propeller system aeroperformance and efficiency
Synchronous measuring apparatus only can obtain the pneumatic efficiency of propeller, generator efficiency and electronic by an experimentation simultaneously
Propeller system efficiency effectively prevents using independent experiment twice and existing every error, not only ensure that electric screw
The accuracy of oar system efficiency, and effectively increase conventional efficient.
To achieve the goals above, the utility model adopts the following technical solution: a kind of pneumatic property of electric propeller system
Energy and efficiency synchronous measuring apparatus, including pedestal, air propeller, motor, torque rotational speed meters, power meter and cantilever beam pulling force
Sensor；The pedestal is fixed in test chamber, the motor, torque rotational speed meters and cantilever beam tension sensor
It is fixedly mounted on pedestal, torque rotational speed meters one end is connected with the first transmission shaft by first shaft coupling, and the first transmission shaft passes through
Torque transmitting sliding sleeve is connected with second driving shaft, and the air propeller is fixedly mounted on second driving shaft, and air spiral
Paddle is located at the upstream of test chamber direction of flow；Fixing sleeve is equipped with baffle ring sleeve, the cantilever on the second driving shaft
Beam tension sensor is located between the baffle ring of baffle ring sleeve；The torque rotational speed meters other end passes through second shaft coupling and motor
Motor shaft be fixedly connected with；The power meter is connected with motor；The torque rotational speed meters, power meter and cantilever beam pull sensing
The data output end of device is connected with computer.
Frequency converter is connected between the power meter and motor, the motor, power meter and frequency converter composition are closed
Circuit is closed, is adjusted by revolving speed of the frequency converter to motor.
Bearing support block is installed between first transmission shaft and pedestal, by setting bearing support block to prevent
The malformation of first transmission shaft when rotated.
The longitudinal center line phase of first transmission shaft, second driving shaft, torque rotational speed meters, motor and test chamber
It is overlapped.
A kind of electric propeller system aeroperformance and efficiency method for synchronously measuring, using the electric propeller system
System aeroperformance and efficiency synchronous measuring apparatus, include the following steps:
Step 1: setting the wind speed in test chamber, the forward speed to simulated air propeller；
Step 2: starting motor is rotated by motor drive air propeller；
Step 3: the axis torque and revolving speed of air propeller are measured by torque rotational speed meters, passes through cantilever beam pull sensing
Device measures the pulling force of air propeller, by the output power of power meter measures motor, by the axis torque of air propeller, draws
Power and the output power data of rotary speed data and motor are transferred in computer；
Step 4: aeroperformance, motor efficiency and the electric screw of air propeller are calculated using computer
Oar system efficiency.
Change the revolving speed of motor by frequency converter, and then change the revolving speed of air propeller, realizes same wind speed and not
It is tested while with air propeller aeroperformance and electric propeller system effectiveness under revolving speed.
The aeroperformance of the air propeller is by the tension coefficient and torque coefficient of air propeller with tip-speed ratio
Change curve evaluated, the calculation formula of tension coefficient, torque coefficient and tip-speed ratio is
CT=2T/ ρ A (R ω)2
CM=2M/ ρ AR (R ω)2
λ=V/ ω R
In formula, CTFor tension coefficient, T is the pulling force of air propeller, and ρ is atmospheric density, A be air propeller windward
Area, R are the radius of turn of air propeller, and ω is the rotational angular velocity of air propeller, CMFor torque coefficient, M is air
The axis torque of propeller, λ are tip-speed ratio, and V is arrives stream wind speed.
The pneumatic efficiency η of the air propelleraCalculation formula be
ηa=TV/M ω
In formula, ηaFor the pneumatic efficiency of air propeller, T is the pulling force of air propeller, and V is arrives stream wind speed, and M is air
The axis torque of propeller, ω are the rotational angular velocity of air propeller.
The motor efficiency ηmCalculation formula be
ηm=M ω/PG
In formula, ηmFor motor efficiency, M is the axis torque of air propeller, and ω is the rotational angular velocity of air propeller,
PGFor the output power of motor.
The electric propeller system effectiveness ηtCalculation formula be
ηt=ηaηm
In formula, ηtFor electric propeller system effectiveness, ηaFor the pneumatic efficiency of air propeller, ηmFor motor efficiency.
The utility model has the beneficial effects that
The utility model compared with prior art, has given up dynamometry day used in existing propeller performance test
The complex components such as flat, conducting slip ring and speed probe, only evaluate spiral shell by cantilever beam tension sensor and revolving speed torquemeter
The parameters such as pulling force, torque and revolving speed needed for revolving paddle aeroperformance only can obtain propeller by an experimentation simultaneously
Pneumatic efficiency, generator efficiency and electric propeller system effectiveness, effectively prevent existing using independent experiment twice
Every error, not only ensure that the accuracy of electric propeller system effectiveness, and effectively increase conventional efficient.
Detailed description of the invention
Fig. 1 is that a kind of electric propeller system aeroperformance of the utility model and the structure of efficiency synchronous measuring apparatus are shown
It is intended to；
In figure, 1-pedestal, 2-air propellers, 3-motor, 4-torque rotational speed meters, 5-power meters, 6-frequency conversions
Device, 7-test chambers, the 8-the first transmission shaft, 9-second driving shafts, 10-first shaft couplings, 11-bearing support blocks,
12-computers, 13-cantilever beam tension sensors, 14-baffle ring sleeves, 15-torques transmit sliding sleeve, 16-second shaft couplings.
Specific embodiment
The utility model is described in further detail in the following with reference to the drawings and specific embodiments.
As shown in Figure 1, a kind of electric propeller system aeroperformance and efficiency synchronous measuring apparatus, including pedestal 1, air
Propeller 2, motor 3, torque rotational speed meters 4, power meter 5 and cantilever beam tension sensor 13；The pedestal 1 is fixed at wind
In hole test section 7, the motor 3, torque rotational speed meters 4 and cantilever beam tension sensor 13 are fixedly mounted on 1 on pedestal, torque
4 one end of rotational speed meters is connected with the first transmission shaft 8 by first shaft coupling 10, and the first transmission shaft 8 transmits sliding sleeve 15 by torque and connects
It is connected to second driving shaft 9, the air propeller 2 is fixedly mounted on second driving shaft 9, and air propeller 2 is located at wind-tunnel
The upstream of 7 direction of flow of test section；Fixing sleeve is equipped with baffle ring sleeve 14, the cantilever beam pulling force on the second driving shaft 9
Sensor 13 is located between the baffle ring of baffle ring sleeve 14；4 other end of torque rotational speed meters by second shaft coupling 16 with it is electronic
The motor shaft of machine 3 is fixedly connected with；The power meter 5 is connected with motor 3；The torque rotational speed meters 4, power meter 5 and cantilever beam
The data output end of tension sensor 13 is connected with computer 12.
Frequency converter 6, the motor 3, power meter 5 and frequency converter 6 are connected between the power meter 5 and motor 3
Closed circuit is constituted, is adjusted by revolving speed of the frequency converter 6 to motor 3.
Bearing support block 11 is installed between first transmission shaft 8 and pedestal 1, is used by setting bearing support block 11
To prevent the malformation of the first transmission shaft 8 when rotated.
First transmission shaft 8, second driving shaft 9, torque rotational speed meters 4, motor 3 and test chamber 7 axial direction in
Heart line coincides.
A kind of electric propeller system aeroperformance and efficiency method for synchronously measuring, using the electric propeller system
System aeroperformance and efficiency synchronous measuring apparatus, include the following steps:
Step 1: setting the wind speed in test chamber 7, the forward speed to simulated air propeller 2；
Step 2: starting motor 3 drives air propeller 2 to be rotated by motor 3；
Step 3: the axis torque and revolving speed of air propeller 2 are measured by torque rotational speed meters 4, is passed by cantilever beam pulling force
Sensor 13 measures the pulling force of air propeller 2, the output power of motor 3 is measured by power meter 5, by air propeller 2
The output power data of axis torque, pulling force and rotary speed data and motor 3 are transferred in computer 12；
Step 4: the aeroperformance of air propeller 2,3 efficiency of motor and electronic is calculated using computer 12
Propeller system efficiency.
By frequency converter 6 change motor 3 revolving speed, and then change air propeller 2 revolving speed, realize same wind speed and
It is tested while 2 aeroperformance of air propeller and electric propeller system effectiveness under different rotating speeds.
The aeroperformance of the air propeller 2 is by the tension coefficient and torque coefficient of air propeller 2 with sharp speed
The change curve of ratio is evaluated, and the calculation formula of tension coefficient, torque coefficient and tip-speed ratio is
CT=2T/ ρ A (R ω)2
CM=2M/ ρ AR (R ω)2
λ=V/ ω R
In formula, CTFor tension coefficient, T is the pulling force of air propeller 2, and ρ is atmospheric density, and A is meeting for air propeller 2
Wind area, R are the radius of turn of air propeller 2, and ω is the rotational angular velocity of air propeller 2, CMFor torque coefficient, M is
The axis torque of air propeller 2, λ are tip-speed ratio, and V is arrives stream wind speed.
The pneumatic efficiency η of the air propeller 2aCalculation formula be
ηa=TV/M ω
In formula, ηaFor the pneumatic efficiency of air propeller 2, T is the pulling force of air propeller 2, and V is arrives stream wind speed, and M is sky
The axis torque of gas propeller 2, ω are the rotational angular velocity of air propeller 2.
3 efficiency eta of motormCalculation formula be
ηm=M ω/PG
In formula, ηmFor 3 efficiency of motor, M is the axis torque of air propeller 2, and ω is the angle of rotation speed of air propeller 2
Degree, PGFor the output power of motor 3.
The electric propeller system effectiveness ηtCalculation formula be
ηt=ηaηm
In formula, ηtFor electric propeller system effectiveness, ηaFor the pneumatic efficiency of air propeller 2, ηmFor 3 efficiency of motor.
Scheme in embodiment is not the scope of patent protection to limit the utility model, all without departing from the utility model
Carried out by equivalence enforcement or change, be both contained in the scope of the patents of this case.
Claims (4)
1. a kind of electric propeller system aeroperformance and efficiency synchronous measuring apparatus, it is characterised in that: including pedestal, air spiral shell
Revolve paddle, motor, torque rotational speed meters, power meter and cantilever beam tension sensor；The pedestal is fixed at test chamber
In, the motor, torque rotational speed meters and cantilever beam tension sensor are fixedly mounted on pedestal, and torque rotational speed meters one end passes through
First shaft coupling is connected with the first transmission shaft, and the first transmission shaft transmits sliding sleeve by torque and is connected with second driving shaft, the sky
Gas propeller is fixedly mounted on second driving shaft, and air propeller is located at the upstream of test chamber direction of flow；Institute
It states fixing sleeve on second driving shaft and baffle ring sleeve is housed, the cantilever beam tension sensor is located between the baffle ring of baffle ring sleeve；
The torque rotational speed meters other end is fixedly connected with by the motor shaft of second shaft coupling and motor；The power meter and motor phase
Connection；The data output end of the torque rotational speed meters, power meter and cantilever beam tension sensor is connected with computer.
2. a kind of electric propeller system aeroperformance according to claim 1 and efficiency synchronous measuring apparatus, feature
It is: is connected with frequency converter between the power meter and motor, the motor, power meter and frequency converter constitutes closure electricity
Road is adjusted by revolving speed of the frequency converter to motor.
3. a kind of electric propeller system aeroperformance according to claim 1 and efficiency synchronous measuring apparatus, feature
It is: bearing support block is installed between first transmission shaft and pedestal, by setting bearing support block to prevent the
The malformation of one transmission shaft when rotated.
4. a kind of electric propeller system aeroperformance according to claim 1 and efficiency synchronous measuring apparatus, feature
Be: first transmission shaft, second driving shaft, torque rotational speed meters, motor and test chamber longitudinal center line be mutually overlapped
It closes.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822164033.6U CN209214916U (en) | 2018-12-21 | 2018-12-21 | A kind of electric propeller system aeroperformance and efficiency synchronous measuring apparatus |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822164033.6U CN209214916U (en) | 2018-12-21 | 2018-12-21 | A kind of electric propeller system aeroperformance and efficiency synchronous measuring apparatus |
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| Publication Number | Publication Date |
|---|---|
| CN209214916U true CN209214916U (en) | 2019-08-06 |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109556878A (en) * | 2018-12-21 | 2019-04-02 | 沈阳航空航天大学 | A kind of electric propeller system aeroperformance and efficiency synchronous measuring apparatus and method |
| CN113734465A (en) * | 2021-11-05 | 2021-12-03 | 中国航空工业集团公司沈阳空气动力研究所 | Test bed for measuring aerodynamic performance of variable pitch propeller |
| CN114563190A (en) * | 2022-02-28 | 2022-05-31 | 中检西部检测有限公司 | Propeller aircraft engine test system and test method |
| CN116465592A (en) * | 2023-04-10 | 2023-07-21 | 武汉理工大学 | Single-rotor unmanned aerial vehicle pneumatic characteristic testing device and method |
-
2018
- 2018-12-21 CN CN201822164033.6U patent/CN209214916U/en active Active
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109556878A (en) * | 2018-12-21 | 2019-04-02 | 沈阳航空航天大学 | A kind of electric propeller system aeroperformance and efficiency synchronous measuring apparatus and method |
| CN109556878B (en) * | 2018-12-21 | 2024-03-22 | 沈阳航空航天大学 | Synchronous measurement device and method for pneumatic performance and efficiency of electric propeller system |
| CN113734465A (en) * | 2021-11-05 | 2021-12-03 | 中国航空工业集团公司沈阳空气动力研究所 | Test bed for measuring aerodynamic performance of variable pitch propeller |
| CN114563190A (en) * | 2022-02-28 | 2022-05-31 | 中检西部检测有限公司 | Propeller aircraft engine test system and test method |
| CN114563190B (en) * | 2022-02-28 | 2024-03-08 | 中检西部检测有限公司 | Propeller aircraft engine test system and test method |
| CN116465592A (en) * | 2023-04-10 | 2023-07-21 | 武汉理工大学 | Single-rotor unmanned aerial vehicle pneumatic characteristic testing device and method |
| CN116465592B (en) * | 2023-04-10 | 2024-02-06 | 武汉理工大学 | Single-rotor unmanned aerial vehicle pneumatic characteristic testing device and method |
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