CN110901951B - Multifunctional tail rotor test system - Google Patents
Multifunctional tail rotor test system Download PDFInfo
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- CN110901951B CN110901951B CN201911119255.9A CN201911119255A CN110901951B CN 110901951 B CN110901951 B CN 110901951B CN 201911119255 A CN201911119255 A CN 201911119255A CN 110901951 B CN110901951 B CN 110901951B
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- tail rotor
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- 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
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- Manufacturing & Machinery (AREA)
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- Aviation & Aerospace Engineering (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
- Force Measurement Appropriate To Specific Purposes (AREA)
Abstract
The invention relates to a multifunctional helicopter tail rotor test system, which comprises: the test bed comprises a test bed body, a three-phase asynchronous motor, a motor rotating speed control system, a propeller pitch control system, a gearbox, a ducted tail rotor transmission shaft, a ducted tail rotor, a conventional tail rotor transmission shaft, a conventional tail rotor, a force measuring rod system, a force measuring balance, a first torque sensor, a second torque sensor, a sound level meter, a wind speed and wind temperature measuring instrument and a data acquisition system. The invention can meet the test requirements of tail propellers with various structural forms, such as tail propellers with conventional structures, duct tail propellers and the like, can carry out various test items, such as performance tests, dynamic tests, noise researches, ground load measurement and the like, completely simulates a real machine to carry out tests, and has high consistency of boundary conditions and the working conditions of the tail propellers.
Description
Technical Field
The invention relates to the field of helicopter tests, in particular to a multifunctional tail rotor test system.
Background
The tail rotor is an important component of a helicopter lift system, is mainly used for balancing reactive torque during flight and is also a main component of an operation course. Compared with the ducted tail rotor, the five tail rotor forms can be collectively called as the tail rotor with the conventional structure. In the model development process, in order to determine the performance and efficiency of the tail rotor, a series of tests such as performance test, dynamics test, noise research, ground load measurement and the like need to be carried out on the tail rotor, and whether the design of the tail rotor meets the requirements or not is verified according to the test results.
At present, the existing similar test device in China is generally designed specifically only for the tail rotor with one structural form, the function of the test device is single, and only one or a few of the test items can be carried out.
Disclosure of Invention
The purpose of the invention is: the multifunctional tail rotor test system aims to solve the limitation of single function of the existing test device, can meet the test requirements of tail rotors with various structural forms such as conventional tail rotors and ducted tail rotors, and can perform various test items such as performance tests, dynamic tests, noise researches, ground load measurement and the like.
The technical scheme of the invention is as follows:
the utility model provides a multi-functional helicopter tail-rotor test system includes: the test bed comprises a test bed body 1, a three-phase asynchronous motor 2, a motor rotating speed control system 3, a propeller pitch control system 4, a gearbox 5, a duct tail rotor transmission shaft 6, a duct tail rotor 7, a conventional structure tail rotor transmission shaft 8, a conventional structure tail rotor 9, a force measuring rod system 10, a force measuring balance 11, a first torque sensor 12a, a second torque sensor 12b, a sound level meter 13, a wind speed and wind temperature measuring instrument 14 and a data acquisition system 15; the first torque sensor 12a and the second torque sensor 12b each have a function of measuring a rotational speed;
the three-phase asynchronous motor, the duct tail rotor 7 and the tail rotor 9 with the conventional structure are all fixed on the test bed body 1, and the duct tail rotor transmission shaft 6 and the tail rotor transmission shaft 8 with the conventional structure are both rotatably arranged on the test bed body 1; the output end of the three-phase asynchronous motor is connected with a gearbox, one end of the ducted tail rotor transmission shaft and one end of the tail rotor transmission shaft with the conventional structure are both connected with the gearbox, and the gearbox transmits torque to the ducted tail rotor transmission shaft and the tail rotor transmission shaft with the conventional structure; the other end of the culvert tail rotor transmission shaft is in power connection with the culvert tail rotor and transmits the torque to the culvert tail rotor, and the other end of the tail rotor transmission shaft in the conventional structure is in power connection with the tail rotor in the conventional structure and transmits the torque to the tail rotor in the conventional structure;
the force measuring rod system 10 is used for measuring the pulling force of the tail rotor;
the force measuring balance 11 is used for measuring the pulling force of the tail rotor with a conventional structure;
the first torque sensor 12a is used for measuring the torque and the rotating speed of the ducted tail rotor transmission shaft;
the second torque sensor 12b is used for measuring the torque and the rotating speed of the tail rotor transmission shaft with the conventional structure;
the ducted tail rotor transmission and the tail rotor of the conventional structure are both provided with a sound level meter 13 and a wind speed and wind temperature measuring instrument 14, and the measured noise level and the measured wind speed and wind temperature of the tail rotor are fed back to a data acquisition system 15;
the motor rotating speed control system 3 is used for controlling the rotating speed of the motor; the pitch control system 4 is used for controlling the pitch of the ducted tail rotor and the tail rotor with a conventional structure.
Further, the test bed body 1 is of a truss structure. Preferably, the truss structure is constructed of steel and concrete.
Further, the gearbox is a speed increasing box.
Furthermore, the ducted tail rotor transmission shaft is arranged horizontally, and the tail rotor transmission shaft with the conventional structure is arranged vertically.
Further, the power of the three asynchronous machines 2 is 400kW.
Further, a first torque sensor 12a is connected in series with the ducted tail rotor drive shaft.
Further, a second torque sensor 12b is connected in series with the conventional tail rotor drive shaft.
Further, the force measuring bar system 10 adopts 6 series force sensors.
The invention can drag and control the rotation of the tail rotor, simulate the working state of the tail rotor of the helicopter in the flying process, and measure the parameters of the tail rotor such as the tension, the power, the noise level and the like. The invention can be used for performance tests, dynamic tests, noise researches, ground load measurement and other ground tests of duct tail rotors and tail rotors with conventional structures. The invention can carry out duct tail rotor test and conventional structure tail rotor test, uses real duct structure, front edge cone, upper vertical tail and fairing as test pieces, and the tail rotor is installed according to the installation posture, thereby completely simulating a real machine and having real test boundary conditions.
The invention has the advantages that: the invention can meet the test requirements of tail propellers with various structural forms, such as tail propellers with conventional structures, duct tail propellers and the like, can carry out various test items, such as performance tests, dynamic tests, noise researches, ground load measurement and the like, completely simulates a real machine to carry out tests, and has high consistency of boundary conditions and the working conditions of the tail propellers.
Drawings
FIG. 1 is a schematic diagram of the system architecture of the present invention;
FIG. 2 is a functional block diagram of the testing system of the present invention;
wherein: the test bed comprises a test bed body 1, three asynchronous motors 2, a gearbox 5, a duct-6 tail rotor transmission shaft 7, a duct-7 tail rotor, a conventional tail rotor transmission shaft 8, a conventional tail rotor with a conventional structure 9, a force measuring bar system 10, a force measuring balance 11, a first torque sensor 12a and a second torque sensor 12b.
Detailed Description
The present invention is described in further detail below.
Embodiment 1 provides a multi-functional helicopter tail-rotor test system, includes: the test bed comprises a test bed body 1, a three-phase asynchronous motor 2, a motor rotating speed control system 3, a propeller pitch control system 4, a gearbox 5, a duct tail rotor transmission shaft 6, a duct tail rotor 7, a conventional structure tail rotor transmission shaft 8, a conventional structure tail rotor 9, a force measuring rod system 10, a force measuring balance 11, a first torque sensor 12a, a second torque sensor 12b, a sound level meter 13, a wind speed and wind temperature measuring instrument 14 and a data acquisition system 15; the first torque sensor 12a and the second torque sensor 12b each have a function of measuring a rotational speed;
the three-phase asynchronous motor, the duct tail rotor 7 and the tail rotor 9 with the conventional structure are all fixed on the test bed body 1, and the duct tail rotor transmission shaft 6 and the tail rotor transmission shaft 8 with the conventional structure are both rotatably arranged on the test bed body 1; the output end of the three-phase asynchronous motor is connected with a gearbox, one end of the ducted tail rotor transmission shaft and one end of the tail rotor transmission shaft with the conventional structure are both connected with the gearbox, and the gearbox transmits torque to the ducted tail rotor transmission shaft and the tail rotor transmission shaft with the conventional structure; the other end of the culvert tail rotor transmission shaft is in power connection with the culvert tail rotor and transmits the torque to the culvert tail rotor, and the other end of the tail rotor transmission shaft in the conventional structure is in power connection with the tail rotor in the conventional structure and transmits the torque to the tail rotor in the conventional structure;
the force measuring rod system 10 is used for measuring the tension of the tail rotor;
the force measuring balance 11 is used for measuring the pulling force of the tail rotor with a conventional structure;
the first torque sensor 12a is used for measuring the torque and the rotating speed of the ducted tail rotor transmission shaft;
the second torque sensor 12b is used for measuring the torque and the rotating speed of the tail rotor transmission shaft with the conventional structure;
the ducted tail rotor transmission and the tail rotor of the conventional structure are both provided with a sound level meter 13 and a wind speed and wind temperature measuring instrument 14, and the measured noise level and the measured wind speed and wind temperature of the tail rotor are fed back to a data acquisition system 15;
the motor rotating speed control system 3 is used for controlling the rotating speed of the motor; the pitch control system 4 is used for controlling the transmission of the ducted tail rotor and the pitch of the tail rotor with a conventional structure.
The test bed body 1 is of a truss structure. The gearbox is a speed increasing box.
The duct tail rotor transmission shaft is arranged horizontally, and the tail rotor transmission shaft with a conventional structure is arranged vertically.
the three-phase asynchronous motor, the ducted tail rotor 7 and the tail rotor 9 with the conventional structure are all fixed on the test bed body 1, and the ducted tail rotor transmission shaft 6 and the tail rotor transmission shaft 8 with the conventional structure are both rotatably arranged on the test bed body 1; the output end of the three-phase asynchronous motor is connected with a gearbox, one end of the ducted tail rotor transmission shaft and one end of the tail rotor transmission shaft with the conventional structure are both connected with the gearbox, and the gearbox transmits torque to the ducted tail rotor transmission shaft and the tail rotor transmission shaft with the conventional structure; the other end of the culvert tail rotor transmission shaft is in power connection with the culvert tail rotor and transmits the torque to the culvert tail rotor, and the other end of the tail rotor transmission shaft in the conventional structure is in power connection with the tail rotor in the conventional structure and transmits the torque to the tail rotor in the conventional structure;
the force measuring rod system 10 is used for measuring the pulling force of the tail rotor;
the force measuring balance 11 is used for measuring the pulling force of the tail rotor with a conventional structure;
the first torque sensor 12a is used for measuring the torque and the rotating speed of the ducted tail rotor transmission shaft;
the second torque sensor 12b is used for measuring the torque and the rotating speed of the tail rotor transmission shaft with the conventional structure;
the ducted tail rotor transmission and the tail rotor of the conventional structure are both provided with a sound level meter 13 and a wind speed and wind temperature measuring instrument 14, and the measured noise level and the measured wind speed and wind temperature of the tail rotor are fed back to a data acquisition system 15;
the motor rotating speed control system 3 is used for controlling the rotating speed of the motor; the pitch control system 4 is used for controlling the pitch of the ducted tail rotor and the tail rotor with a conventional structure.
The test bed body 1 is of a truss structure. The truss structure is composed of steel bars and concrete.
The gearbox is a speed increasing box.
The duct tail rotor transmission shaft is arranged horizontally, and the tail rotor transmission shaft with a conventional structure is arranged vertically. The power of the three asynchronous machines 2 is 400kW.
A first torque sensor 12a is connected in series with the ducted tail rotor drive shaft.
A second torque sensor 12b is connected in series with the conventional configuration of the tail rotor drive shaft.
The load cell line 10 employs 6 series force sensors.
Claims (7)
1. A multi-function helicopter tail rotor test system comprising: the test bed comprises a test bed body, a three-phase asynchronous motor, a motor rotating speed control system, a propeller pitch control system, a gearbox, a duct tail rotor transmission shaft, a duct tail rotor, a conventional structure tail rotor transmission shaft, a conventional structure tail rotor, a force measuring rod system, a force measuring balance, a first torque sensor, a second torque sensor, a sound level meter, a wind speed and wind temperature measuring instrument and a data acquisition system; the first torque sensor and the second torque sensor have the function of measuring the rotating speed;
the three-phase asynchronous motor, the ducted tail rotor and the tail rotor with the conventional structure are all fixed on the test bed body, and the ducted tail rotor transmission shaft and the tail rotor transmission shaft with the conventional structure are both rotatably arranged on the test bed body; the output end of the three-phase asynchronous motor is connected with a gearbox, one end of the ducted tail rotor transmission shaft and one end of the tail rotor transmission shaft with the conventional structure are both connected with the gearbox, and the gearbox transmits torque to the ducted tail rotor transmission shaft and the tail rotor transmission shaft with the conventional structure; the other end of the ducted tail rotor transmission shaft is in power connection with the ducted tail rotor to transmit torque to the ducted tail rotor, and the other end of the tail rotor transmission shaft in the conventional structure is in power connection with the tail rotor in the conventional structure to transmit the torque to the tail rotor in the conventional structure;
the force measuring rod is used for measuring the pulling force of the tail rotor; the force measuring balance is used for measuring the pulling force of the tail rotor with a conventional structure;
the first torque sensor is used for measuring the torque and the rotating speed of the ducted tail rotor transmission shaft; the second torque sensor is used for measuring the torque and the rotating speed of the tail rotor transmission shaft with the conventional structure;
the ducted tail rotor transmission and the tail rotor with the conventional structure are both provided with a sound level meter and a wind speed and wind temperature measuring instrument, and the measured noise level and the wind speed and wind temperature of the tail rotor are fed back to the data acquisition system;
the motor rotating speed control system is used for controlling the rotating speed of the motor; the propeller pitch control system is used for controlling the propeller pitch of the ducted tail rotor and the propeller pitch of the tail rotor with the conventional structure;
the second torque sensor is connected with the tail rotor transmission shaft in series;
the first torque sensor is connected in series with the ducted tail rotor transmission shaft.
2. The multifunctional helicopter tail rotor test system of claim 1, further comprising: the force measuring rod adopts 6 series force sensors.
3. The multifunctional helicopter tail rotor test system of claim 1, further comprising: the power of the three-phase asynchronous motor is 400kW.
4. The multi-function helicopter tail rotor test system of claim 1 further comprising: the duct tail rotor transmission shaft is arranged horizontally, and the tail rotor transmission shaft with a conventional structure is arranged vertically.
5. The multifunctional helicopter tail rotor test system of claim 1, further comprising: the test bed body is of a truss structure.
6. The multifunctional helicopter tail rotor test system of claim 1, further comprising: the gearbox is a speed increasing box.
7. The multi-function helicopter tail rotor testing system of claim 5, further comprising: the truss structure is composed of steel bars and concrete.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911119255.9A CN110901951B (en) | 2019-11-15 | 2019-11-15 | Multifunctional tail rotor test system |
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|---|---|---|---|
| CN201911119255.9A CN110901951B (en) | 2019-11-15 | 2019-11-15 | Multifunctional tail rotor test system |
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| CN110901951A CN110901951A (en) | 2020-03-24 |
| CN110901951B true CN110901951B (en) | 2023-01-13 |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111994301B (en) * | 2020-08-18 | 2022-03-22 | 常州华创航空科技有限公司 | Helicopter transmission system test device and system |
| CN111855201B (en) * | 2020-09-01 | 2022-03-22 | 常州华创航空科技有限公司 | Helicopter main reducer test bench |
| CN112407324B (en) * | 2020-11-03 | 2022-03-29 | 中国直升机设计研究所 | Helicopter tail rotor load measuring and mounting device |
| CN114919772B (en) * | 2022-06-02 | 2024-08-13 | 燕山大学 | Single rotor wing type unmanned helicopter rotating machinery fault simulation experiment table with tail rotor |
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