CN114955001B - Helicopter tail transmission system simulation experiment system - Google Patents
Helicopter tail transmission system simulation experiment system Download PDFInfo
- Publication number
- CN114955001B CN114955001B CN202210688429.9A CN202210688429A CN114955001B CN 114955001 B CN114955001 B CN 114955001B CN 202210688429 A CN202210688429 A CN 202210688429A CN 114955001 B CN114955001 B CN 114955001B
- Authority
- CN
- China
- Prior art keywords
- transmission shaft
- platform
- helicopter
- transmission
- unit
- 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.)
- Active
Links
- 230000005540 biological transmission Effects 0.000 title claims abstract description 151
- 238000004088 simulation Methods 0.000 title claims abstract description 33
- 238000002474 experimental method Methods 0.000 claims abstract description 12
- 239000003638 chemical reducing agent Substances 0.000 claims description 33
- 230000008878 coupling Effects 0.000 claims description 17
- 238000010168 coupling process Methods 0.000 claims description 17
- 238000005859 coupling reaction Methods 0.000 claims description 17
- 238000001514 detection method Methods 0.000 claims description 9
- 238000000034 method Methods 0.000 claims description 7
- 230000001133 acceleration Effects 0.000 claims description 6
- 230000008569 process Effects 0.000 claims description 6
- 238000006073 displacement reaction Methods 0.000 claims description 4
- 238000003475 lamination Methods 0.000 claims description 4
- 230000007246 mechanism Effects 0.000 abstract description 4
- 238000013461 design Methods 0.000 abstract description 3
- 230000009467 reduction Effects 0.000 description 10
- 238000010586 diagram Methods 0.000 description 8
- 238000005259 measurement Methods 0.000 description 3
- 239000006247 magnetic powder Substances 0.000 description 2
- 230000036544 posture Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000003745 diagnosis Methods 0.000 description 1
- 238000000605 extraction Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
Classifications
-
- 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
-
- 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
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The utility model provides a helicopter tail transmission system simulation experiment system, includes experiment platform and multi freedom platform, the experiment platform includes detecting element, tail transmission simulation unit and basic unit, basic unit is fixed to be set up in multi freedom platform, tail transmission simulation unit is used for simulating the tail transmission system of helicopter, detecting element is used for obtaining the parameter of experimental setting, multi freedom platform is used for simulating the different flight attitudes of helicopter. The invention discloses a simulation experiment system for a tail transmission system of a helicopter, the structural form of an experiment platform of the system is basically consistent with that of the tail transmission system of an actual helicopter, and the simulation experiment of the system can be used for well simulating the actual running states of the tail transmission system of the helicopter under different working conditions, so that experimental data are more approximate to the actual conditions, the analysis of the reasons of easy failure of the tail transmission system is facilitated, the dynamic performance of the helicopter is improved, and the design of the integral mechanism of the tail transmission system of the helicopter is optimized.
Description
Technical Field
The invention belongs to the technical field of helicopter tail transmission systems, and relates to a simulation experiment system of a helicopter tail transmission system.
Background
Helicopter is used as an important component in aircraft and plays an important role in the economic and social development of China. The tail transmission system of the helicopter has the characteristics of large span, high rotating speed and complex structure, and is the most frequent part for accidents, and the fault of the tail transmission system directly threatens the flight safety of the helicopter, so that the accidents occur.
In order to avoid the occurrence of flight accidents, a helicopter tail transmission system simulation experiment system is needed, and the system performs experiment analysis on the movement and stress conditions of each part of the tail transmission system when the tail transmission system works under different working conditions by simulating the transmission system of the helicopter tail, so that the reason that the tail transmission system is prone to failure is known, and the helicopter tail transmission system simulation experiment system has great significance in improving the dynamic performance of the helicopter and optimizing the structure of the tail transmission system of the helicopter.
Disclosure of Invention
In view of the above, the invention discloses a simulation experiment system for a tail transmission system of a helicopter, which comprises an experiment platform and a multi-degree-of-freedom platform, wherein the experiment platform comprises a detection unit, a tail transmission simulation unit and a basic unit, the basic unit is fixedly arranged on the multi-degree-of-freedom platform, the tail transmission simulation unit is used for simulating the tail transmission system of the helicopter, the detection unit is used for obtaining experimental set parameters, and the multi-degree-of-freedom platform is used for simulating different flight attitudes of the helicopter.
Further, the detection unit comprises a rotating speed and torque sensor, an eddy current sensor and an acceleration sensor; the rotational speed torque sensor is used for measuring rotational speed and torque generated in the experimental process, and the eddy current sensor and the acceleration sensor are used for measuring vibration generated in the experimental process.
Further, the front end of the foundation unit is fixed on the platform with multiple degrees of freedom so that the foundation unit is in a cantilever structure.
Further, tail transmission analog unit includes actuating source, transmission shaft I, transmission shaft II, first reduction gear, transmission shaft III, second reduction gear and arresting gear, actuating source, transmission shaft I, transmission shaft II, first reduction gear, transmission shaft III, second reduction gear and arresting gear are by the front end of basic unit to tail end transmission complex setting in proper order in basic unit.
Further, at least two eddy current sensors are arranged on the base unit and respectively and correspondingly erected above the transmission shafts I and II to measure vibration of the transmission shafts and the base unit, and the displacement sensor is arranged on the base unit and used for measuring vibration of the base unit to compensate parameters obtained by the eddy current sensors; the rotating speed torque sensor is arranged on the basic unit and is positioned between the second speed reducer and the braking device, and the rotating speed torque sensor is provided with two end parts which are respectively and correspondingly connected with the second speed reducer and the braking device in a coaxial way.
Further, the transmission shaft I is provided with an input end and an output end, the transmission shaft II is provided with an input end and an output end, the input end of the transmission shaft I is connected with a driving source, the output end of the transmission shaft II is connected with a first speed reducer, and the output end of the transmission shaft I and the input end of the transmission shaft II are connected through a coupling to enable the transmission shaft I and the transmission shaft II to form a whole.
Further, the first speed reducer is provided with a pair of gear pairs with intersecting axes of 135 degrees, a driving shaft of each gear pair is coaxially connected with the output end of a transmission shaft II, and a driven shaft of each gear pair is coaxially connected with a transmission shaft III.
Further, the base unit further comprises a fixing frame for fixing the driving source and a support for supporting the transmission shaft II, and the fixing frame is arranged at the front end of the base unit; the support is arranged on the base unit and located at the position of the input end of the transmission shaft II, the base unit is of an L-shaped structure with a housing arranged outside, and the tail transmission simulation unit is arranged inside the housing.
Further, the connecting line of the braking device and the second speed reducer is perpendicular to the plane formed by the transmission shaft II and the transmission shaft III.
Further, the multi-degree-of-freedom platform is a six-degree-of-freedom parallel platform, the six-degree-of-freedom parallel platform comprises a movable platform, a fixed platform and six driving rods which are arranged at intervals along the circumferential direction of the platform, the movable platform and the fixed platform are connected through the driving rods, and the driving rods simulate different flight attitudes of a helicopter through driving the movable platform; the movable platform is fixedly provided with a supporting column, and the foundation unit is fixedly arranged on the supporting column.
The invention has the beneficial effects that:
The invention discloses a simulation experiment system for a tail transmission system of a helicopter, the structural form of an experiment platform of the system is basically consistent with that of the tail transmission system of an actual helicopter, and the simulation experiment of the system can be used for well simulating the actual running states of the tail transmission system of the helicopter under different working conditions, so that experimental data are more approximate to the actual conditions, the analysis of the reasons of easy failure of the tail transmission system is facilitated, the dynamic performance of the helicopter is improved, and the design of the integral mechanism of the tail transmission system of the helicopter is optimized.
Drawings
FIG. 1 is a schematic diagram of the structure of the present invention;
FIG. 2 is a schematic diagram of an experimental platform structure according to an embodiment of the present invention;
FIG. 3 is a schematic diagram of a connection structure between a driving source and a transmission shaft I according to an embodiment of the present invention;
FIG. 4 is a schematic diagram of a first speed reducer according to an embodiment of the present invention;
FIG. 5 is a schematic view of a multi-degree of freedom platform according to an embodiment of the present invention;
Detailed Description
FIG. 1 is a schematic diagram of the structure of the present invention; FIG. 2 is a schematic diagram of an experimental platform structure according to an embodiment of the present invention; FIG. 3 is a schematic diagram of a connection structure between a driving source and a transmission shaft I according to an embodiment of the present invention; FIG. 4 is a schematic diagram of a first speed reducer according to an embodiment of the present invention; FIG. 5 is a schematic view of a multi-degree of freedom platform according to an embodiment of the present invention;
as shown in the figure, the simulation experiment system for the tail transmission system of the helicopter comprises an experiment platform and a multi-degree-of-freedom platform, wherein the experiment platform comprises a detection unit, a tail transmission simulation unit and a foundation unit, the foundation unit is fixedly arranged on the multi-degree-of-freedom platform, the tail transmission simulation unit is used for simulating the tail transmission system of the helicopter, the detection unit is used for obtaining experimental set parameters, and the multi-degree-of-freedom platform is used for simulating different flight attitudes of the helicopter.
In this embodiment, the detection unit includes a rotational speed and torque sensor 15, an eddy current sensor 18, and an acceleration sensor 19; the rotational speed torque sensor is used for measuring rotational speed and torque generated in the experimental process, and the eddy current sensor and the acceleration sensor are used for measuring vibration generated in the experimental process. The rotating speed torque sensor and the eddy current sensor can obtain multi-parameter data under different running states, and are convenient for signal characteristic extraction analysis and fault diagnosis
In this embodiment, the front end of the base unit 1 is fixed to a platform with multiple degrees of freedom, so that the base unit has a cantilever structure.
In this embodiment, the tail transmission simulation unit includes driving source 2, transmission shaft i 4, transmission shaft ii 7, first reduction gear 9, transmission shaft iii 11, second reduction gear 13 and arresting gear 17, driving source 2, transmission shaft i 4, transmission shaft ii 7, first reduction gear 9, transmission shaft iii 11, second reduction gear 13 and arresting gear 17 are set up in the basic unit by the front end to the tail end of basic unit transmission fit in proper order. As shown in fig. 2, the driving source 2 outputs power, the transmission shaft i 4 and the transmission shaft ii 7 sequentially transmit power to the first speed reducer 9, the first speed reducer 9 transmits power to the second speed reducer 13 through the transmission shaft iii, and the second speed reducer 13 outputs power to the braking device 17, and at the same time, the braking device 17 works to simulate loads of the helicopter under different working conditions. In this embodiment, the driving source is a motor, the braking device is a magnetic powder brake, and the motor has the advantages of low price, simple structure and convenient operation compared with other driving devices, and the magnetic powder brake is adopted to simulate the load, so that stable torsion can be obtained, continuous sliding operation can be realized, noise is low, and heat capacity is large.
In this embodiment, the transmission shaft i 4 has an input end and an output end, the transmission shaft ii 7 has an input end and an output end, the input end of the transmission shaft i is connected to the driving source 2 through the coupling, the output end of the transmission shaft ii is connected to the first speed reducer, and the output end of the transmission shaft i is connected to the input end of the transmission shaft ii through the lamination coupling 5 to form a whole with the transmission shaft i. The transmission between the driving source and the first speed reducer adopts two sections, so that the reduction of rigidity of the transmission shaft caused by long span can be effectively avoided, and the vibration is enhanced.
In this embodiment, the rotational speed and torque sensor is installed in the base unit and located between the second speed reducer and the braking device to facilitate the measurement and collection of the torque and the rotational speed input to the braking device, the rotational speed and torque sensor has two ends, the two ends are respectively and correspondingly connected coaxially with the second speed reducer and the braking device, that is, the second speed reducer 13 is connected with one end of the rotational speed and torque sensor 15 through the quincuncial expansion sleeve type coupling 14, the braking device 17 is connected with the other end of the rotational speed and torque sensor 15 through the quincuncial expansion sleeve type coupling 16, and after the connection, the axes of the second speed reducer 13, the rotational speed and torque sensor 15 and the braking device 17 are on the same axis, so that the transmission is smoother.
In this embodiment, two eddy current sensors are provided, and the two eddy current sensors are mounted on the base unit 1 and respectively correspondingly mounted at positions above the transmission shafts i and ii to measure vibration of the transmission shafts and the base unit, as shown in fig. 2, a first eddy current sensor 18A is disposed at an input end of the transmission shaft i, and a second eddy current sensor 18B is disposed at an input end of the transmission shaft ii. The displacement sensor is arranged on the base unit and used for measuring vibration of the base unit so as to compensate parameters obtained by the eddy current sensor; the electric vortex sensor reflects the vibration condition of the shaft by collecting the displacement condition of the transmission shaft I and the transmission shaft II, and the electric vortex sensor is fixedly arranged on the base unit, and the vibration condition of the base unit can be obtained by the aid of the electric vortex sensor when the shaft vibrates, so that the electric vortex sensor actually measures the vibration of the transmission shaft and the base platform.
In this embodiment, the first reducer is provided with a pair of gear pairs with intersecting axes of 135 °, a driving shaft of the gear pair is coaxially connected with an output end of a transmission shaft ii, and a driven shaft of the gear pair is coaxially connected with a transmission shaft iii. As shown in fig. 4, the first speed reducer is composed of a pair of arc tooth bevel gear pairs 902 with intersecting axes of 135 degrees, the driving shafts and the driven shafts of the arc tooth bevel gear pairs are respectively supported by a pair of angular contact ball bearings 904, the driving shafts of the arc tooth bevel gear pairs are connected with a transmission shaft 7 through splines 905 and a laminated coupling 8, and the driven shafts of the arc tooth bevel gear pairs are connected with the transmission shaft 11 through splines 901 and a laminated coupling 10. The gear pair with 135-degree intersecting axis is used for changing the transmission direction, so that the structure of the invention is consistent with a helicopter tail transmission system.
In this embodiment, the base unit further includes a fixing frame for fixing the driving source and a support for supporting the transmission shaft ii. The fixed frame is arranged at the front end of the foundation unit, a connecting shaft 302 is arranged in the fixed frame, an output shaft of the driving source 2 is connected with the connecting shaft 302 through a quincuncial expansion sleeve type coupler 304, the connecting shaft is supported by a pair of angle contact ball bearings 303, and the connecting shaft 302 is fixedly connected with the transmission shaft 4 through a spline 301 so as to realize stable output of power. The support 6 is arranged at the basic unit and is positioned at the position of the input end of the transmission shaft II, a deep groove ball bearing is arranged on the upper portion of the support 6, the transmission shaft II is arranged through the deep groove ball bearing, and the support and the deep groove ball bearing are arranged to support the transmission shaft II so as to reduce the rigidity reduction of the transmission shaft and the vibration reinforcement of the transmission shaft caused by long-span transmission. The base unit is of an L-shaped structure with a housing outside, and the tail transmission simulation unit is arranged in the housing.
In this embodiment, the connection line between the braking device and the second speed reducer is perpendicular to the plane formed by the transmission shaft ii and the transmission shaft iii.
In this embodiment, the multi-degree-of-freedom platform is a six-degree-of-freedom parallel platform, and the six-degree-of-freedom parallel platform includes a movable platform 20, a fixed platform 23, and six driving rods 22 arranged at intervals along the circumferential direction of the platform, a support column 24 is fixedly mounted on the movable platform, and the base unit 1 is fixedly mounted on the support column 24; the movable platform is connected with the fixed platform through a driving rod, and the driving rod simulates different flight attitudes of the helicopter through driving the movable platform; the driving rod 22 is an electric cylinder, the driving rod has two ends along the length direction, the two ends are respectively and correspondingly connected to the bottom surface of the movable platform 20 and the top surface of the fixed platform 23 through the hook hinge 21, the six-degree-of-freedom parallel platform changes the length of the electric cylinder by controlling the output of different electric cylinders, so that the movable platform shows different postures to realize the working state of the experimental platform connected with the movable platform under the corresponding postures, the platform has six degrees of freedom, and the platform is a closed-loop mechanism driven in a parallel mode, and the six-degree-of-freedom parallel mechanism has the advantages of high rigidity, high precision, large load and the like. The output of each electric cylinder of the six-degree-of-freedom parallel platform can offset the influence of vibration generated by the experimental platform on the measurement of the sensor to a certain extent.
According to the structural design of the actual helicopter tail transmission system, the structural form of the helicopter tail transmission system simulation experiment system is basically consistent with that of the actual helicopter tail transmission system, and the actual running state of the helicopter tail transmission system can be well simulated by the simulation experiment conducted on the basis. According to the technical scheme, the quincuncial expansion sleeve type coupling and the lamination coupling are adopted to connect different shaft sections so as to facilitate disassembly and assembly of the device and transmission of larger moment, the lamination coupling is simple in structure and high in reliability, and the quincuncial expansion sleeve type coupling can absorb vibration of the driving source 2 and the output shaft of the second speed reducer to compensate radial, angular and axial deviation, so that the transmission condition of the tail transmission simulation unit is more similar to the actual condition; the invention adopts the paired angular contact ball bearings and the deep groove ball bearings to support the corresponding shaft sections, can bear radial load and axial load at the same time, ensures stable and reliable transmission, has higher limit rotating speeds of the two bearings, and can be more suitable for the working state of the high rotating speed of the experiment table.
In this embodiment, the data measurement and conversion techniques of each sensor are all the prior art, and are not described herein.
It should be noted that, in the description of the present specification, the terms "upper," "lower," "top," "bottom," "inner," "outer," "axial," "radial," "circumferential," and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, merely to facilitate description of the present invention and simplify the description, and do not indicate or imply that the devices or elements being referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present invention. In this embodiment, if no special description is provided, the connection, installation, etc. are all realized by a detachable fixed connection manner such as a bolt connection, which is the prior art, and will not be described here again
Finally, it is noted that the above embodiments are only for illustrating the technical solution of the present invention and not for limiting the same, and although the present invention has been described in detail with reference to the preferred embodiments, it should be understood by those skilled in the art that modifications and equivalents may be made thereto without departing from the spirit and scope of the technical solution of the present invention, which is intended to be covered by the scope of the claims of the present invention.
Claims (5)
1. A helicopter tail transmission system simulation experiment system is characterized in that: the device comprises an experiment platform and a multi-degree-of-freedom platform, wherein the experiment platform comprises a detection unit, a tail transmission simulation unit and a basic unit, the basic unit is fixedly arranged on the multi-degree-of-freedom platform, the tail transmission simulation unit is used for simulating a tail transmission system of a helicopter, the detection unit is used for obtaining experimental set parameters, and the multi-degree-of-freedom platform is used for simulating different flight attitudes of the helicopter;
The detection unit comprises a rotating speed and torque sensor, an eddy current sensor and an acceleration sensor; the rotating speed and torque sensor is used for measuring rotating speed and torque generated in the experimental process, and the eddy current sensor and the acceleration sensor are used for measuring vibration generated in the experimental process;
The front end of the foundation unit is fixed on the multi-degree-of-freedom platform to enable the foundation unit to be in a cantilever structure, the foundation unit is of an L-shaped structure with a housing arranged outside, and the tail transmission simulation unit is arranged inside the housing; the foundation unit comprises a fixing frame for fixing a driving source and a support for supporting a transmission shaft II, the fixing frame is arranged at the front end of the foundation unit, a connecting shaft is arranged in the fixing frame, an output shaft of the driving source is connected with the connecting shaft through a quincuncial expansion sleeve type coupling, the connecting shaft is supported by a pair of angle contact ball bearings, and the connecting shaft is connected with the transmission shaft I through a spline; the support is arranged on the basic unit and is positioned at the position of the input end of the transmission shaft II, a deep groove ball bearing is arranged at the upper part of the support, and the transmission shaft II penetrates through the deep groove ball bearing;
the tail transmission simulation unit comprises a driving source, a transmission shaft I, a transmission shaft II, a first speed reducer, a transmission shaft III, a second speed reducer and a braking device, wherein the driving source, the transmission shaft I, the transmission shaft II, the first speed reducer, the transmission shaft III, the second speed reducer and the braking device are sequentially arranged on the base unit in a transmission fit way from the front end to the tail end of the base unit;
The first speed reducer consists of a pair of arc tooth bevel gear pairs with 135-degree intersecting axes, the driving shafts and the driven shafts of the arc tooth bevel gear pairs are respectively supported by angular contact ball bearings, the driving shafts of the arc tooth bevel gear pairs are connected with a transmission shaft II through splines and a laminated coupling, and the driven shafts of the arc tooth bevel gear pairs are connected with a transmission shaft III through splines and the laminated coupling; the input end of the transmission shaft I is connected with a driving source through a coupling, the output end of the transmission shaft II is connected with a first speed reducer, and the output end of the transmission shaft I is connected with the input end of the transmission shaft II through a lamination coupling to form a whole with the transmission shaft I;
The rotating speed torque sensor is arranged on the basic unit and positioned between the second speed reducer and the braking device, the rotating speed torque sensor is provided with two end parts, the second speed reducer is connected with one end part of the torque rotating speed sensor through a quincuncial expansion sleeve type coupler, and the braking device is connected with the other end part of the torque rotating speed sensor through the quincuncial expansion sleeve type coupler.
2. The helicopter tail drive system simulation experiment system of claim 1, wherein: the electric vortex sensors are arranged on the foundation unit and respectively and correspondingly arranged at the positions above the transmission shafts I and II to measure the vibration of the transmission shafts and the foundation unit, and the displacement sensor is arranged on the foundation unit to measure the vibration of the foundation unit so as to compensate the parameters obtained by the electric vortex sensors; the rotating speed torque sensor is arranged on the basic unit and is positioned between the second speed reducer and the braking device, and the rotating speed torque sensor is provided with two end parts which are respectively and correspondingly connected with the second speed reducer and the braking device in a coaxial way.
3. The helicopter tail drive system simulation experiment system of claim 1, wherein: the transmission shaft I is provided with an input end and an output end, the transmission shaft II is provided with an input end and an output end, the input end of the transmission shaft I is connected with a driving source, the output end of the transmission shaft II is connected with a first speed reducer, and the output end of the transmission shaft I and the input end of the transmission shaft II are connected through a coupling to enable the transmission shaft I and the transmission shaft II to form a whole.
4. The helicopter tail drive system simulation experiment system of claim 1, wherein: the connecting line of the braking device and the second speed reducer is perpendicular to a plane formed by the transmission shaft II and the transmission shaft III.
5. The helicopter tail drive system simulation experiment system of claim 1, wherein: the multi-degree-of-freedom platform is a six-degree-of-freedom parallel platform, the six-degree-of-freedom parallel platform comprises a movable platform, a fixed platform and six driving rods which are arranged at intervals along the circumferential direction of the platform, the movable platform and the fixed platform are connected through the driving rods, and the driving rods simulate different flight attitudes of a helicopter by driving the movable platform; the movable platform is fixedly provided with a supporting column, and the foundation unit is fixedly arranged on the supporting column.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210688429.9A CN114955001B (en) | 2022-06-17 | 2022-06-17 | Helicopter tail transmission system simulation experiment system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210688429.9A CN114955001B (en) | 2022-06-17 | 2022-06-17 | Helicopter tail transmission system simulation experiment system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114955001A CN114955001A (en) | 2022-08-30 |
| CN114955001B true CN114955001B (en) | 2024-05-31 |
Family
ID=82963531
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210688429.9A Active CN114955001B (en) | 2022-06-17 | 2022-06-17 | Helicopter tail transmission system simulation experiment system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114955001B (en) |
Citations (28)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2028591C1 (en) * | 1990-07-02 | 1995-02-09 | Московский вертолетный завод им.М.Л.Миля | Stand for member dynamic tests |
| EP1080353A1 (en) * | 1998-05-16 | 2001-03-07 | ZF Luftfahrttechnik GmbH | Stress test rig for helicopter transmissions |
| US6360616B1 (en) * | 2000-10-13 | 2002-03-26 | Donald R. Halliday | Automated diagnosis and monitoring system, equipment, and method |
| KR20030092603A (en) * | 2002-05-30 | 2003-12-06 | 주식회사 동서종합기계 | a tester for helicopter's trans mission |
| KR20090039563A (en) * | 2007-10-18 | 2009-04-22 | 한국항공우주연구원 | Helicopter tail rotor test rig |
| CN101614615A (en) * | 2009-07-03 | 2009-12-30 | 中国航空动力机械研究所 | Simulative loader of tail reducer of helicopter |
| CN201494625U (en) * | 2009-09-17 | 2010-06-02 | 中国航空动力机械研究所 | Foldable-type oblique-tail transmission shaft device |
| CN102269654A (en) * | 2011-05-10 | 2011-12-07 | 重庆大学 | Water lubricated bearing and transmission system comprehensive performance testing platform |
| JP2012093323A (en) * | 2010-10-29 | 2012-05-17 | Ntn Corp | Testing device of bearing around crank of engine |
| CN103076175A (en) * | 2013-01-10 | 2013-05-01 | 哈尔滨东安发动机（集团）有限公司 | Bearing test method for tail transmission shaft of helicopter |
| CN103558016A (en) * | 2013-10-25 | 2014-02-05 | 中国航空动力机械研究所 | Testing rack and all-condition sealing testing device |
| CN103863576A (en) * | 2013-12-26 | 2014-06-18 | 吉林大学 | Unmanned helicopter performance testing platform |
| CN203939932U (en) * | 2014-06-23 | 2014-11-12 | 深圳市高士通科技有限公司 | The T-shaped secondary gear reducing transmission structure of depopulated helicopter |
| CN104502093A (en) * | 2014-12-19 | 2015-04-08 | 湖南科技大学 | Fault simulation experiment device for helicopter tail transmission system |
| CN104502094A (en) * | 2014-12-19 | 2015-04-08 | 湖南科技大学 | Fault simulation device for helicopter main transmission system |
| CN104943868A (en) * | 2015-07-15 | 2015-09-30 | 合肥工业大学 | Transmission system device of light unmanned helicopter |
| CN204740140U (en) * | 2015-07-06 | 2015-11-04 | 安徽精科检测技术有限公司 | High -speed rotation test platform of transaxle |
| CN105067234A (en) * | 2015-07-17 | 2015-11-18 | 安阳工学院 | High speed electric main shaft comprehensive experiment platform and experiment method |
| CN105716762A (en) * | 2016-03-25 | 2016-06-29 | 哈尔滨飞机工业集团有限责任公司 | Helicopter tail transmission shaft torque testing system |
| CN206756452U (en) * | 2017-01-15 | 2017-12-15 | 吉林大学 | A kind of industrial robot power unit reliability test bench |
| CN108168875A (en) * | 2017-12-01 | 2018-06-15 | 中国直升机设计研究所 | A kind of Helicopter Tail Drive System system fault-injection testing stand |
| CN109708883A (en) * | 2019-03-05 | 2019-05-03 | 合肥工业大学 | A kind of electrically driven (operated) duty testing device of empennage of helicopter and control method |
| CN111879511A (en) * | 2020-08-14 | 2020-11-03 | 湘潭科达电工专用成套设备有限责任公司 | Helicopter middle and tail speed reducer comprehensive test bed |
| CN111999056A (en) * | 2020-07-31 | 2020-11-27 | 中南大学 | Multifunctional experiment table for simulating helicopter tail transmission vibration |
| 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 |
| CN113483060A (en) * | 2021-07-07 | 2021-10-08 | 重庆大学 | Torque-dividing gear transmission speed reducer for main speed reducer of coaxial helicopter |
| CN113551910A (en) * | 2021-08-27 | 2021-10-26 | 中浙高铁轴承有限公司 | Helicopter rotor system matched bearing testing machine and method |
| CN216050691U (en) * | 2020-12-15 | 2022-03-15 | 中国人民解放军总参谋部第六十研究所 | Multichannel coordinated loading electric feedback type unmanned helicopter transmission test system |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2831664B1 (en) * | 2001-10-29 | 2004-07-30 | Eurocopter France | TEST BENCH FOR TESTING A POWER TRANSMISSION DEVICE AND TEST SYSTEM COMPRISING SUCH A TEST BENCH PROVIDED WITH A POWER TRANSMISSION DEVICE |
| US11040785B2 (en) * | 2018-04-16 | 2021-06-22 | Bell Helicopter Textron Inc. | Devices and methods to verify tail rotor cross-head positioning |
-
2022
- 2022-06-17 CN CN202210688429.9A patent/CN114955001B/en active Active
Patent Citations (28)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2028591C1 (en) * | 1990-07-02 | 1995-02-09 | Московский вертолетный завод им.М.Л.Миля | Stand for member dynamic tests |
| EP1080353A1 (en) * | 1998-05-16 | 2001-03-07 | ZF Luftfahrttechnik GmbH | Stress test rig for helicopter transmissions |
| US6360616B1 (en) * | 2000-10-13 | 2002-03-26 | Donald R. Halliday | Automated diagnosis and monitoring system, equipment, and method |
| KR20030092603A (en) * | 2002-05-30 | 2003-12-06 | 주식회사 동서종합기계 | a tester for helicopter's trans mission |
| KR20090039563A (en) * | 2007-10-18 | 2009-04-22 | 한국항공우주연구원 | Helicopter tail rotor test rig |
| CN101614615A (en) * | 2009-07-03 | 2009-12-30 | 中国航空动力机械研究所 | Simulative loader of tail reducer of helicopter |
| CN201494625U (en) * | 2009-09-17 | 2010-06-02 | 中国航空动力机械研究所 | Foldable-type oblique-tail transmission shaft device |
| JP2012093323A (en) * | 2010-10-29 | 2012-05-17 | Ntn Corp | Testing device of bearing around crank of engine |
| CN102269654A (en) * | 2011-05-10 | 2011-12-07 | 重庆大学 | Water lubricated bearing and transmission system comprehensive performance testing platform |
| CN103076175A (en) * | 2013-01-10 | 2013-05-01 | 哈尔滨东安发动机（集团）有限公司 | Bearing test method for tail transmission shaft of helicopter |
| CN103558016A (en) * | 2013-10-25 | 2014-02-05 | 中国航空动力机械研究所 | Testing rack and all-condition sealing testing device |
| CN103863576A (en) * | 2013-12-26 | 2014-06-18 | 吉林大学 | Unmanned helicopter performance testing platform |
| CN203939932U (en) * | 2014-06-23 | 2014-11-12 | 深圳市高士通科技有限公司 | The T-shaped secondary gear reducing transmission structure of depopulated helicopter |
| CN104502094A (en) * | 2014-12-19 | 2015-04-08 | 湖南科技大学 | Fault simulation device for helicopter main transmission system |
| CN104502093A (en) * | 2014-12-19 | 2015-04-08 | 湖南科技大学 | Fault simulation experiment device for helicopter tail transmission system |
| CN204740140U (en) * | 2015-07-06 | 2015-11-04 | 安徽精科检测技术有限公司 | High -speed rotation test platform of transaxle |
| CN104943868A (en) * | 2015-07-15 | 2015-09-30 | 合肥工业大学 | Transmission system device of light unmanned helicopter |
| CN105067234A (en) * | 2015-07-17 | 2015-11-18 | 安阳工学院 | High speed electric main shaft comprehensive experiment platform and experiment method |
| CN105716762A (en) * | 2016-03-25 | 2016-06-29 | 哈尔滨飞机工业集团有限责任公司 | Helicopter tail transmission shaft torque testing system |
| CN206756452U (en) * | 2017-01-15 | 2017-12-15 | 吉林大学 | A kind of industrial robot power unit reliability test bench |
| CN108168875A (en) * | 2017-12-01 | 2018-06-15 | 中国直升机设计研究所 | A kind of Helicopter Tail Drive System system fault-injection testing stand |
| CN109708883A (en) * | 2019-03-05 | 2019-05-03 | 合肥工业大学 | A kind of electrically driven (operated) duty testing device of empennage of helicopter and control method |
| CN111999056A (en) * | 2020-07-31 | 2020-11-27 | 中南大学 | Multifunctional experiment table for simulating helicopter tail transmission vibration |
| CN111879511A (en) * | 2020-08-14 | 2020-11-03 | 湘潭科达电工专用成套设备有限责任公司 | Helicopter middle and tail speed reducer comprehensive test bed |
| 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 |
| CN216050691U (en) * | 2020-12-15 | 2022-03-15 | 中国人民解放军总参谋部第六十研究所 | Multichannel coordinated loading electric feedback type unmanned helicopter transmission test system |
| CN113483060A (en) * | 2021-07-07 | 2021-10-08 | 重庆大学 | Torque-dividing gear transmission speed reducer for main speed reducer of coaxial helicopter |
| CN113551910A (en) * | 2021-08-27 | 2021-10-26 | 中浙高铁轴承有限公司 | Helicopter rotor system matched bearing testing machine and method |
Non-Patent Citations (4)
| Title |
|---|
| 基于TEAMS的直升机传动***测试性建模分析;袁志文;赵云;金小强;李新民;中国科技信息;20211231(第005期);第24-26页 * |
| 直升机传动***花键连接轴的动力失稳;康丽霞;曹义华;梅庆;;北京航空航天大学学报;20100615(第06期);第645-649页 * |
| 直升机电动尾桨技术发展与展望;建志旭;唐兴中;陈国军;张润泽;陈义;付裕;直升机技术;20211231(第003期);第58-64页 * |
| 虚拟原型实验仿真技术及应用;唐倩, 易树平, 詹捷;重庆大学学报(自然科学版);20010930(第05期);第11-13页 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114955001A (en) | 2022-08-30 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102269654B (en) | Water lubricated bearing and transmission system comprehensive performance testing platform | |
| CN110510148B (en) | Rotor wing test bed of large-load unmanned helicopter | |
| CN206242048U (en) | A kind of small-sized six-freedom parallel motion platform | |
| CN107719696B (en) | Dynamic characteristic synchronous testing device of axial compact type aircraft propeller | |
| CN102095541B (en) | Experiment table for studying friction mechanism of precision ball screw pair | |
| CN102156047B (en) | Loading simulation device for test bed of wind turbine | |
| CN109632249B (en) | Wing type high-speed wind tunnel dynamic test device | |
| CN110919688A (en) | Mechanical arm joint | |
| CN101719700B (en) | Moment motor driving shafting module for inner frame of airborne photoelectric platform | |
| CN106908238B (en) | Hydraulic integrated transmission system test system and test device thereof | |
| CN101539476B (en) | Aerocraft steering engine non-rubber deviation load torque following mechanism | |
| CN103335838B (en) | Misalign spline vibration abrasion contrast experiment device | |
| CN110844113B (en) | Rigid coaxial dual-rotor test bed capable of simultaneously measuring upper rotor load and lower rotor load | |
| CN103353399A (en) | Mechanical performance testing table for piston engine | |
| CN105181333A (en) | Helicopter tail rotor system supporting combination joint bearing test machine | |
| CN111207923B (en) | Test bed for transmission device of cross dual-rotor unmanned helicopter | |
| CN105856188B (en) | Portable Flexible Building Structures detect robot | |
| CN114955001B (en) | Helicopter tail transmission system simulation experiment system | |
| CN109828207B (en) | Three-degree-of-freedom spherical motor gesture and moment detection bench and detection method | |
| CN201885839U (en) | Precise ball-screw pair friction mechanism research experiment table | |
| CN102700524A (en) | Automobile with semi-automatic error correction braking system with inward rotating solenoid valve having fixed rotation angle | |
| CN107505132B (en) | Bidirectional tiltable double-gear box closed loop torsion loading test bed | |
| CN201285334Y (en) | Measurement instrument for detecting dynamic friction torque of bearing | |
| CN211841989U (en) | Cooperative robot joint module with torque sensor | |
| CN111452083B (en) | Integrated joint type driving and controlling module with force/position detection function |
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 | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |