CN114235393A - Helicopter main reducer rotor torque static calibration method - Google Patents
Helicopter main reducer rotor torque static calibration method Download PDFInfo
- Publication number
- CN114235393A CN114235393A CN202111516363.7A CN202111516363A CN114235393A CN 114235393 A CN114235393 A CN 114235393A CN 202111516363 A CN202111516363 A CN 202111516363A CN 114235393 A CN114235393 A CN 114235393A
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- fixed
- adjusting nut
- rotor
- bolt
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
- G01M13/02—Gearings; Transmission mechanisms
- G01M13/025—Test-benches with rotational drive means and loading means; Load or drive simulation
-
- 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
Abstract
The invention belongs to the field of ground simulation tests of helicopter main reducers, and particularly relates to a static calibration method for the torque of a helicopter main reducer rotor, which is applied to test equipment with high power and high torque. According to the invention, the main speed reducer is fixed on the ground through bolts, the engine input shaft is fixed through the fixing support, the tail output shaft is fixed through the fixing support, the two torsion bars are arranged on the calibrated torquemeter, and the tension can be applied to one end of each torsion bar by adjusting the hexagonal adjusting nut, so that the adjustment strength of the hexagonal adjusting nut is controlled to change the tension. The function of the invention can meet the requirement of static calibration of the main reducer rotor torque, and the invention has the characteristics of simple operation and high reliability.
Description
Technical Field
The invention belongs to the field of ground simulation tests of helicopter main reducers, and particularly relates to a static calibration method for the torque of a helicopter main reducer rotor, which is applied to test equipment with high power and high torque.
Background
The helicopter main reducer (hereinafter referred to as main reducer) needs to load the torque of a main reducer rotor shaft when the main reducer is subjected to a factory test due to production requirements, the loading torque of the helicopter main reducer is usually measured by a dynamic torquer, and the torquer needs to be checked regularly according to the related requirements of mass measurement sequences.
Disclosure of Invention
The invention aims to provide a static calibration method for rotor torque of a main reducer of a helicopter, so as to realize calibration of a main reducer torquer in a static state.
The purpose of the invention is realized as follows:
a helicopter main reducer rotor torque static calibration method, the main reducer 1 includes the rotor shaft 4 engine input shaft 5 and the tail output shaft 9, the rotor shaft is installed with the rotor torquemeter 2; the main reducer is fixed on the ground through a bolt 8, and the engine input shaft 5 is fixed on the bracket 6 through a bolt 7; the tail output shaft 11 is fixed on the bracket 10 through a bolt 9; the rotor wing torquemeter 2 is fixed on a rotor wing shaft 4 through a bolt 3; the torsion bar 12 is connected with the rotor wing torquemeter 2 through a bolt 23, the left-handed fork lug 14 is connected with the torsion bar 12 through a hinge bolt 24, the hexagonal adjusting nut 15 is in threaded connection with the left-handed fork lug 14, and the right-handed fork lug 16 is in threaded connection with the hexagonal adjusting nut 15; the force sensor upper connecting piece 17 is connected with the right fork lug 16 through a bolt 25; the tension sensor 22 is in threaded connection with the upper connecting piece 17 of the force sensor; the lower connecting piece 18 of the force sensor is connected with the tension sensor 22 through threads; the fixed support 19 is connected with the lower connecting piece 18 of the force sensor through a bolt 21, the fixed support 19 is fixed on a fixed frame 20, and the method comprises the following steps: the main speed reducer is fixed on the ground through bolts, an engine input shaft is fixed through a fixing support, a tail output shaft is fixed through the fixing support, two torsion bars are installed on a calibrated torquemeter, tension can be applied to one end of each torsion bar through adjusting a hexagonal adjusting nut, and the adjustment force of the hexagonal adjusting nut is controlled to change the tension; through reading of a tension meter, the magnitude of the tension of the rod end of the two torsion bars is displayed as F1 and F2, the arm length of the torque bar is L, and the magnitude of the applied torque T is calculated as (F1+ F2) L; the hexagonal adjusting nut is characterized in that one end of the hexagonal adjusting nut is a left-handed thread, the other end of the hexagonal adjusting nut is a right-handed thread, the left-handed thread is connected with the left-handed fork lug, the right-handed thread is connected with the right-handed fork lug, when the hexagonal adjusting nut is rotated anticlockwise and is faced to the main part, anticlockwise torque is applied to the rotor torquer, and when the hexagonal adjusting nut is rotated clockwise and is faced to the main part, clockwise torque is applied to the rotor torquer.
The invention has the beneficial effects that: the function of the invention can meet the requirement of static calibration of the main reducer rotor torque, and the invention has the characteristics of simple operation and high reliability.
Drawings
FIG. 1 is a front view of the system of the present invention.
Fig. 2 is a top view of the system of the present invention.
Detailed Description
The invention is further described below with reference to the accompanying drawings.
The main speed reducer 1 comprises a rotor shaft 4, an engine input shaft 5 and a tail output shaft 9, wherein a rotor torque meter 2 is installed on the rotor shaft. The main reducer is fixed on the ground through a bolt 8, and the engine input shaft 5 is fixed on the bracket 6 through a bolt 7; the tail output shaft 11 is fixed on the bracket 10 through a bolt 9; the rotor torquer 2 is fixed on the rotor shaft 4 by a bolt 3.
The torsion bar 12 is connected with the rotor wing torquemeter 2 through a bolt 23, the left-handed fork lug 14 is connected with the torsion bar 12 through a hinge bolt 24, the hexagonal adjusting nut 15 is in threaded connection with the left-handed fork lug 14, and the right-handed fork lug 16 is in threaded connection with the hexagonal adjusting nut 15; the force sensor upper connecting piece 17 is connected with the right fork lug 16 through a bolt 25; the tension sensor 22 is in threaded connection with the upper connecting piece 17 of the force sensor; the lower connecting piece 18 of the force sensor is connected with the tension sensor 22 through threads; the fixed support 19 is connected with the lower connecting piece 18 of the force sensor through a bolt 21, and the fixed support 19 is fixed on a fixed frame 20.
The invention can realize the application of the rotor torque by screwing the hexagonal adjusting nut in a static state, and converts the rotor torque through the visual value and the force arm L of the tension sensor, thereby having the characteristics of convenient operation and high reliability.
Claims (1)
1. A static calibration method for rotor torque of a helicopter main reducer is characterized in that the main reducer (1) comprises a rotor shaft (4), an engine input shaft (5) and a tail output shaft (9), and a rotor torque meter (2) is mounted on the rotor shaft; the main speed reducer is fixed on the ground through a bolt (8), and the engine input shaft (5) is fixed on the bracket (6) through a bolt (7); the tail output shaft (11) is fixed on the bracket (10) through a bolt (9); the rotor wing torquemeter (2) is fixed on the rotor wing shaft (4) through a bolt (3); the torsion bar (12) is connected with the rotor wing torquemeter (2) through a bolt (23), the left-handed fork lug (14) is connected with the torsion bar (12) through a hinged bolt (24), the hexagonal adjusting nut (15) is in threaded connection with the left-handed fork lug (14), and the right-handed fork lug (16) is in threaded connection with the hexagonal adjusting nut (15); the upper connecting piece (17) of the force sensor is connected with the right fork lug (16) through a bolt (25); the tension sensor (22) is in threaded connection with the upper connecting piece (17) of the force sensor; the lower connecting piece (18) of the force sensor is connected with the tension sensor (22) through threads; fixing support (19) are connected with connecting piece (18) under the force sensor through bolt (21), and fixing support (19) are fixed in mount (20), its characterized in that includes the following step: the main speed reducer is fixed on the ground through bolts, an engine input shaft is fixed through a fixing support, a tail output shaft is fixed through the fixing support, two torsion bars are installed on a calibrated torquemeter, tension can be applied to one end of each torsion bar through adjusting a hexagonal adjusting nut, and the adjustment force of the hexagonal adjusting nut is controlled to change the tension; through reading of a tension meter, the magnitude of the tension of the rod end of the two torsion bars is displayed as F1 and F2, the arm length of the torque bar is L, and the magnitude of the applied torque T is calculated as (F1+ F2) L; the hexagonal adjusting nut is characterized in that one end of the hexagonal adjusting nut is a left-handed thread, the other end of the hexagonal adjusting nut is a right-handed thread, the left-handed thread is connected with the left-handed fork lug, the right-handed thread is connected with the right-handed fork lug, when the hexagonal adjusting nut is rotated anticlockwise and is faced to the main part, anticlockwise torque is applied to the rotor torquer, and when the hexagonal adjusting nut is rotated clockwise and is faced to the main part, clockwise torque is applied to the rotor torquer.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111516363.7A CN114235393A (en) | 2021-12-09 | 2021-12-09 | Helicopter main reducer rotor torque static calibration method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111516363.7A CN114235393A (en) | 2021-12-09 | 2021-12-09 | Helicopter main reducer rotor torque static calibration method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114235393A true CN114235393A (en) | 2022-03-25 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111516363.7A Pending CN114235393A (en) | 2021-12-09 | 2021-12-09 | Helicopter main reducer rotor torque static calibration method |
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| Country | Link |
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| CN (1) | CN114235393A (en) |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201569540U (en) * | 2009-11-27 | 2010-09-01 | 中国直升机设计研究所 | Novel torque loading calibrating device |
| CN102829907A (en) * | 2012-08-17 | 2012-12-19 | 北京金风科创风电设备有限公司 | Torque measuring device and calibration method thereof |
| CN104155053A (en) * | 2014-08-18 | 2014-11-19 | 南通常测机电股份有限公司 | Hydraulic balance loading large torque static calibration device |
| CN204373844U (en) * | 2015-02-02 | 2015-06-03 | 北京菱动瑞创自动化技术有限公司 | A kind of torque sensor Intelligent Calibration device |
| CN204881971U (en) * | 2015-04-17 | 2015-12-16 | 成都理工大学 | Static test bench of maring of torque sensor |
| CN105675296A (en) * | 2016-01-13 | 2016-06-15 | 中国航空动力机械研究所 | Method for adjusting torque balance of multiple input shafts of main reducer |
| CN107764545A (en) * | 2017-09-25 | 2018-03-06 | 上海交通大学 | The Helicopter Main Reducer multi-function test stand of electric feedback |
| CN210741740U (en) * | 2019-06-03 | 2020-06-12 | 海卓(武汉)自动化科技有限公司 | Calibration device for torque sensor |
| 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 |
| CN112945548A (en) * | 2021-02-01 | 2021-06-11 | 中国兵器工业计算机应用技术研究所 | Running-in test and torque test device and method for coaxial double-propeller unmanned helicopter |
-
2021
- 2021-12-09 CN CN202111516363.7A patent/CN114235393A/en active Pending
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201569540U (en) * | 2009-11-27 | 2010-09-01 | 中国直升机设计研究所 | Novel torque loading calibrating device |
| CN102829907A (en) * | 2012-08-17 | 2012-12-19 | 北京金风科创风电设备有限公司 | Torque measuring device and calibration method thereof |
| CN104155053A (en) * | 2014-08-18 | 2014-11-19 | 南通常测机电股份有限公司 | Hydraulic balance loading large torque static calibration device |
| CN204373844U (en) * | 2015-02-02 | 2015-06-03 | 北京菱动瑞创自动化技术有限公司 | A kind of torque sensor Intelligent Calibration device |
| CN204881971U (en) * | 2015-04-17 | 2015-12-16 | 成都理工大学 | Static test bench of maring of torque sensor |
| CN105675296A (en) * | 2016-01-13 | 2016-06-15 | 中国航空动力机械研究所 | Method for adjusting torque balance of multiple input shafts of main reducer |
| CN107764545A (en) * | 2017-09-25 | 2018-03-06 | 上海交通大学 | The Helicopter Main Reducer multi-function test stand of electric feedback |
| CN210741740U (en) * | 2019-06-03 | 2020-06-12 | 海卓(武汉)自动化科技有限公司 | Calibration device for torque sensor |
| 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 |
| CN112945548A (en) * | 2021-02-01 | 2021-06-11 | 中国兵器工业计算机应用技术研究所 | Running-in test and torque test device and method for coaxial double-propeller unmanned helicopter |
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