CN110901951A - A multifunctional tail rotor test system - Google Patents
A multifunctional tail rotor test system Download PDFInfo
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- CN110901951A CN110901951A CN201911119255.9A CN201911119255A CN110901951A CN 110901951 A CN110901951 A CN 110901951A CN 201911119255 A CN201911119255 A CN 201911119255A CN 110901951 A CN110901951 A CN 110901951A
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- 238000012360 testing method Methods 0.000 title claims abstract description 66
- 230000005540 biological transmission Effects 0.000 claims description 64
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- 238000005259 measurement Methods 0.000 abstract description 5
- 238000011056 performance test Methods 0.000 abstract description 5
- 238000011160 research Methods 0.000 abstract description 5
- 238000010586 diagram Methods 0.000 description 2
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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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Abstract
本发明涉及一种多功能直升机尾桨试验系统，包括：试验台体、三相异步电机、电机转速控制系统、桨距控制系统、变速箱、涵道尾桨传动轴、涵道尾桨、常规结构尾桨传动轴、常规结构尾桨、测力杆系、测力天平、第一扭矩传感器、第二扭矩传感器、声级计、风速风温测量仪和数据采集系统。本发明可满足常规结构尾桨和涵道尾桨等多种结构形式尾桨的试验要求，可进行性能试验、动力学试验、噪声研究、地面载荷测量等多种试验项目，完全模拟真机进行试验，边界条件与尾桨工况一致性高。
The invention relates to a multifunctional helicopter tail rotor test system, comprising: a test bed body, a three-phase asynchronous motor, a motor speed control system, a pitch control system, a gearbox, a ducted tail rotor drive shaft, a ducted tail rotor, a conventional Structural tail rotor drive shaft, conventional structural tail rotor, force measuring rod system, force measuring balance, first torque sensor, second torque sensor, sound level meter, wind speed and temperature measuring instrument and data acquisition system. The invention can meet the test requirements of various structural types of tail rotors such as conventional structure tail rotor and ducted tail rotor, and can carry out various test items such as performance test, dynamic test, noise research, ground load measurement, etc., completely simulating the real machine. In the test, the boundary conditions are highly consistent with the tail rotor operating conditions.
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. The tail rotor is divided into a seesaw type, a universal joint type, a hinge type, a bearingless type, a scissor type, a duct tail rotor and the like from the structural form, and compared with the duct tail rotor, the former 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:
a multifunctional helicopter tail rotor test system is provided, comprising: 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 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 duct 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 400 kW.
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 configuration of the tailrotor 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, the tail rotor is installed according to the installation posture, completely simulates a real machine, and the test boundary condition is real.
The invention has the advantages that: the invention can meet the test requirements of tail rotors with various structural forms such as tail rotors with conventional structures, duct tail rotors 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 tail rotor working conditions.
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 12 b.
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 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 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 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 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 400 kW.
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 (9)
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 ducted tail rotor transmission shaft, a ducted tail rotor, a conventional structure tail rotor transmission shaft, a conventional structure tail rotor, a force measuring rod system 10, a force measuring balance, a first torque sensor, a second torque sensor, a sound level meter, a wind speed and wind temperature measuring instrument 14 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 duct tail rotor and the tail rotor with the conventional structure are all fixed on the test bed body, and the duct tail rotor transmission shaft and the tail rotor transmission shaft with the conventional structure are all 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 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 is used for measuring the tension 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 tail rotor with the conventional structure.
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: and the second torque sensor is connected with the tail rotor transmission shaft in series in a conventional structure.
4. The multifunctional helicopter tail rotor test system of claim 1, further comprising: the first torque sensor is connected in series with the ducted tail rotor transmission shaft.
5. The multifunctional helicopter tail rotor test system of claim 1, further comprising: the power of the three asynchronous motors is 400 kW.
6. The multifunctional 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.
7. The multifunctional helicopter tail rotor test system of claim 1, further comprising: the test bed body is of a truss structure.
8. The multifunctional helicopter tail rotor test system of claim 1, further comprising: the gearbox is a speed increasing box.
9. The multifunctional helicopter tail rotor testing system of claim 7, 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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| 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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| CN110901951A true CN110901951A (en) | 2020-03-24 |
| CN110901951B CN110901951B (en) | 2023-01-13 |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN111855201A (en) * | 2020-09-01 | 2020-10-30 | 常州华创航空科技有限公司 | Helicopter main reducer test bench |
| CN111994301A (en) * | 2020-08-18 | 2020-11-27 | 常州华创航空科技有限公司 | Helicopter transmission system test device and system |
| CN112407324A (en) * | 2020-11-03 | 2021-02-26 | 中国直升机设计研究所 | Helicopter tail rotor load measuring and mounting device |
| CN114919772A (en) * | 2022-06-02 | 2022-08-19 | 燕山大学 | Rotating mechanical fault simulation experiment table for single-rotor unmanned helicopter with tail rotor |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111994301A (en) * | 2020-08-18 | 2020-11-27 | 常州华创航空科技有限公司 | Helicopter transmission system test device and system |
| 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 |
| CN111855201A (en) * | 2020-09-01 | 2020-10-30 | 常州华创航空科技有限公司 | Helicopter main reducer test bench |
| 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 |
| CN112407324A (en) * | 2020-11-03 | 2021-02-26 | 中国直升机设计研究所 | Helicopter tail rotor load measuring and mounting device |
| 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 |
| CN114919772A (en) * | 2022-06-02 | 2022-08-19 | 燕山大学 | Rotating mechanical fault simulation experiment table for single-rotor unmanned helicopter with tail rotor |
| 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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