CN114252262A - Helicopter main reducer propeller hub load simulation loading device considering balance static deadweight - Google Patents
Helicopter main reducer propeller hub load simulation loading device considering balance static deadweight Download PDFInfo
- Publication number
- CN114252262A CN114252262A CN202111501890.0A CN202111501890A CN114252262A CN 114252262 A CN114252262 A CN 114252262A CN 202111501890 A CN202111501890 A CN 202111501890A CN 114252262 A CN114252262 A CN 114252262A
- Authority
- CN
- China
- Prior art keywords
- assembly
- force
- loading
- bearing seat
- bearing
- 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.)
- Granted
Links
- 239000003638 chemical reducing agent Substances 0.000 title claims abstract description 50
- 238000004088 simulation Methods 0.000 title claims abstract description 37
- 230000003068 static effect Effects 0.000 title claims abstract description 17
- 238000010008 shearing Methods 0.000 claims abstract description 10
- 125000006850 spacer group Chemical group 0.000 claims description 12
- 229910000831 Steel Inorganic materials 0.000 claims description 6
- 238000002347 injection Methods 0.000 claims description 6
- 239000007924 injection Substances 0.000 claims description 6
- 239000010959 steel Substances 0.000 claims description 6
- 238000012360 testing method Methods 0.000 abstract description 25
- 238000013461 design Methods 0.000 abstract description 5
- 230000002159 abnormal effect Effects 0.000 abstract description 4
- 230000002411 adverse Effects 0.000 abstract description 3
- 238000006073 displacement reaction Methods 0.000 abstract description 3
- 230000000694 effects Effects 0.000 abstract description 3
- 238000000034 method Methods 0.000 abstract description 3
- 230000008569 process Effects 0.000 abstract description 2
- 239000000306 component Substances 0.000 description 9
- 238000005452 bending Methods 0.000 description 5
- 230000000712 assembly Effects 0.000 description 4
- 238000000429 assembly Methods 0.000 description 4
- 230000005540 biological transmission Effects 0.000 description 3
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 238000009661 fatigue test Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- 238000005096 rolling process Methods 0.000 description 2
- 238000012546 transfer Methods 0.000 description 2
- 206010034719 Personality change Diseases 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 229910052742 iron Inorganic materials 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000001228 spectrum Methods 0.000 description 1
Images
Classifications
-
- 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
- G01M13/027—Test-benches with force-applying means, e.g. loading of drive shafts along several directions
-
- 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
-
- 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
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention provides a helicopter main reducer propeller hub load simulation loading device considering balanced static deadweight, which can provide constant balance lift force during large axial displacement in static and dynamic states by adopting a force balance assembly combined by a pulley assembly and a tower-type force balancer, and ensures that the helicopter reducer is not subjected to downward abnormal axial force in the whole process; through the split design of the axial force and shearing force loading stress support arm and the rotor wing loading bearing seat, the requirements of the loading center positions of hubs of different main reducers can be met through the replacement of the stress support arm assembly. The whole set of device commonality is strong, simple structure, ingenious overcome the adverse effect of simulation loading device dead weight to main reducer, improved simulation loading device's commonality, improved the switching efficiency of different model test pieces.
Description
Technical Field
The invention belongs to the technical field of helicopter main reducer simulation tests, and particularly relates to a helicopter main reducer hub load simulation loading device considering balanced static deadweight.
Background
The helicopter main speed reduction transfers the rotating speed and the torque of an engine to accessories such as a main rotor, a tail rotor, a hydraulic pump, a generator and the like according to a certain transmission ratio, is a core component of the helicopter, and needs to be subjected to load simulation loading tests in the research, development and production stages. In actual operation of main speed reduction of the helicopter, besides torque loads of all shafting, a main rotor shaft also bears loads such as tension, shearing force, bending moment and the like from a rotor wing, and the loads are transmitted to a rotor wing supporting bearing, a transmission gear, a speed reducer shell and the like through the main rotor shaft, so that the service life of the bearing, gear meshing, deformation of the speed reducer shell and the like are all greatly influenced, and therefore load simulation loading of a hub of a main speed reducer of the helicopter is an important part of a test of the main speed reducer of the helicopter, and the simulation conformance of the hub of the main speed reducer of the helicopter to real working conditions is directly related to the success or failure of the simulation test.
At present, aiming at a helicopter main reducer propeller hub load simulation loading test, a method combining a static fatigue test and a dynamic working condition simulation test is generally adopted in the industry: the static fatigue test is mainly used for examining the strength of a rotor shaft of a main speed reducer of the helicopter; the dynamic working condition simulation test mainly examines the overall dynamic performance of the main speed reducer. The dynamic test of the helicopter main reducer can be carried out in a ground helicopter iron bird test which directly carries out a test with a rotor wing, wherein the main rotor wing shaft is subjected to loads such as rotor wing lift force, shear force, bending moment and the like, the consistency of the load condition and the actual flight working condition is high, but the cost is high. In the industry, a rolling bearing rotor loading bearing seat is mostly adopted to carry out analog loading on a rotor shaft at present, a rotor loading bearing seat rotating shaft is connected with a helicopter main reducing rotor shaft, and a static outer shell of the helicopter main reducing rotor shaft applies loads such as pulling force, shearing force, bending moment and the like through a hydraulic cylinder and other force loading devices. Generally, simulation test equipment requires a long design life, and due to the reason that a rotor shaft torque loading shaft of a helicopter main reducer penetrates through a shaft and the like, a rotor loading bearing seat adopts a large-diameter rolling bearing, so that the whole simulation loading device has a large mass, abnormal downward axial load can be applied to the rotor shaft of the main reducer in a non-running state, the rotor shaft of some helicopter main reducers has strict limitation on the downward axial load, and the abnormal downward axial load can cause damage to some structural members, so that the large self-weight influence of the loading device is considered to be overcome in the helicopter main reducer propeller hub load simulation loading test. In addition, the test function of the multi-type main reducer is often compatible on the helicopter main reducer test bed, hub centers and rotor shaft connection interfaces of reducers of different types are different, and the universality of the hub load simulation loading device needs to be improved in order to improve the quick switching of different test pieces.
Disclosure of Invention
The invention aims to solve the adverse effect of large dead weight of a loading device in a helicopter main reducer hub load simulation loading test, and provides a helicopter main reducer hub load simulation loading device considering balanced static dead weight.
A helicopter main reducer propeller hub load simulation loading device considering balance static deadweight comprises a rotor wing loading bearing seat assembly, a lift force loading assembly, a shear force loading assembly and a force balance assembly. The rotor wing loading bearing seat assembly comprises an output flange assembly, a tapered roller bearing, a bearing inner spacer ring, a bearing oil injection outer spacer ring, a bearing seat shell, a bearing seat rotating shaft, a rotor wing adapter flange and an axial force and shearing force loading stress support arm assembly. The rotor wing loading bearing seat assembly is supported by a pair of tapered roller bearings in a back-to-back combined mode, and the bearing inner spacer ring is matched with the bearing oil injection outer spacer ring to adjust the pretightening force. The rotor wing loading bearing seat assembly is provided with a bearing seat rotating shaft, the upper part of the bearing seat rotating shaft is connected with the output flange assembly through crowned teeth, and the lower part of the bearing seat rotating shaft is connected with the rotor wing adapter flange through end face teeth. The lift force loading assembly and the shear force loading assembly are connected with the bearing seat shell through the axial force and shear force loading stress support arm assembly. The force balancing assembly is connected with the shear loading assembly.
Further, the force balance assembly comprises a lifting pulley assembly, a steel wire rope and a tower-type force balancer assembly. The lifting pulley component is connected with the tower-type force balancer component through a steel wire rope.
The invention has the beneficial effects that:
by adopting the force balancing component combining the pulley component and the tower-type force balancer, constant balancing lift force can be provided during large axial displacement in a static state and a dynamic state, and the helicopter speed reducer is prevented from being subjected to downward abnormal axial force in the whole process; through the split design of the axial force and shearing force loading stressed support arm and the rotor wing loading bearing seat, the requirements of different main speed reducers on the loading center positions of the hubs can be met through the replacement of the stressed support arm. The whole set of device commonality is strong, simple structure, ingenious overcome the adverse effect of simulation loading device dead weight to main reducer, improved simulation loading device's commonality, improved the switching efficiency of different model test pieces.
Drawings
FIG. 1 is a schematic structural view of the present invention;
fig. 2 is a schematic view of the structure of the present invention in a plan view.
Detailed Description
The invention is further described below with reference to the accompanying drawings.
Fig. 1 is a schematic structural diagram of a helicopter main reducer hub load simulation loading device in consideration of a balanced static self-weight in a preferred embodiment of the invention, which mainly comprises a rotor loading bearing seat assembly 10, a lift loading assembly 20, a shear loading assembly 30 and a force balancing assembly 40. The rotor wing loading bearing seat assembly 10 mainly comprises an output flange assembly 11, a tapered roller bearing 12, a bearing inner spacer ring 13, a bearing oil injection outer spacer ring 14, a bearing seat shell 15, a bearing seat rotating shaft 16, a rotor wing adapter flange 17 and an axial force and shearing force loading stress support arm assembly 18; wherein the lift force loading component 20 and the shear force loading component 30 are servo hydraulic cylinder loaders; the force balance assembly 40 is composed of a lift pulley assembly 41, a steel wire rope 42 and a tower type force balancer assembly 43.
The rotor wing loading bearing seat assembly 10 is supported by a pair of tapered roller bearings 12 in a back-to-back combined mode, the bearing inner spacer ring 13 is matched with the bearing oil injection outer spacer ring 14 to adjust the pre-tightening force, the bearing group can bear combined loads such as large axial force, radial force, bending moment and the like, the installation and allocation are simple, the bearing capacity is extremely strong, and the rotor wing loading bearing seat assembly is suitable for the working condition of low-speed large load of a rotor wing shaft of a helicopter main reducer; the upper part of a bearing block rotating shaft 16 of the rotor wing loading bearing block assembly 10 is connected with the output flange assembly 11 through crowned teeth, so that the transmission of large rotor wing loading torque can be realized, the deviation of the rated coaxiality 4' of the torque loading shaft and the rotor wing loading bearing block assembly 10 can be realized, the structure is simple, the installation is convenient, the compensation amount is large, and the device is suitable for large attitude change caused by pull rod deformation and temperature after the rotor wing shaft of a helicopter main reducer operates; the lower part of a bearing block rotating shaft 16 of the rotor loading bearing block assembly 10 is connected with a rotor adapter flange 17 through end face teeth, the rotor adapter flange 17 is connected with a rotor shaft of a main speed reducer, and the rotor adapter flange 17 is replaced to realize connection with main speed reducers of helicopters of different models; the bearing block rotating shaft 16 has a larger inner diameter, so that space is reserved for an inner rotor shaft of the main reducer of the double-rotor helicopter, and the universality of the device is improved.
The lift loading assembly 20 and the shear loading assembly 30 are connected with the bearing seat housing 15 through the axial force and shear force loading force bearing arm assembly 18. The lift force loading assembly 20 and the shear force loading assembly 30 can be replaced according to the change of the A point of the rotor loading center on the helicopter main reducer test piece and the change of the simulated loading load, and the test requirements of different models of tests are met. The 4 groups of lift cylinders integrally combine to provide a rotor wing lift force simulation load, and the lift force loading assemblies symmetrically arranged at 180 degrees can realize the rotor wing bending moment simulation load by applying different lift force loads; the action axis of the shear loading assembly passes through a loading center point A and provides the front and side shear force simulation loads of the rotor wing. The lift force loading assembly 20 and the shear force loading assembly 30 are controlled by a hydraulic servo control system, and can be loaded according to a specific main reducer hub load spectrum of the helicopter.
The force balance assembly 40 is composed of a lift pulley assembly 41, a steel wire rope 42 and a tower-type force balancer assembly 43, the lift pulley assembly 41 can multiply and amplify the constant tension provided by the tower-type force balancer assembly 43, as shown in the form of fig. 1, if the tower-type force balancer assembly 43 is set to be 200kg tension, finally, each force balance assembly 40 provides 800kg tension for the rotor loading bearing seat assembly 10, if the tower-type force balancer assemblies 43 at 4 positions are uniformly distributed in fig. 2, the force balance assemblies 40 provide 3200kg tension for the rotor loading bearing seat assembly 10, and different arrangement modes and tension settings of the force balance assemblies 40 can be set according to the dead weight of a helicopter main reducer propeller load simulation loading device and the arrangement condition of an actual test bed. The tower force balancer assembly 43 can maintain a constant balancing tension over a range of the telescopic length of the wire rope 42.
In conclusion, the invention provides a helicopter main reducer hub load simulation loading device considering balanced static deadweight, which can balance the deadweight of the simulation loading device under static and dynamic conditions, thereby ensuring safe and reliable hub load simulation loading of a helicopter main reducer test piece on a test bed; the split design of the axial force and shearing force loading stressed support arm and the design of the rotor wing adapter flange improve the universality and the use convenience of the propeller hub load simulation loading.
The helicopter main reducer propeller hub load simulation loading device considering the balance static deadweight adopts a pair of tapered rollers used in combination to load a bearing seat, a bearing seat rotor can be connected with main reducers of different models through a transfer flange, and the bearing seat rotor has a larger inner diameter and can meet the test connection requirement of the main reducer with double rotors; the axial force and shearing force loading stressed support arm and the rotor wing loading bearing seat are designed into two bodies, and the requirements of the loading center positions of hubs of different main reducers can be met by replacing the stressed support arm; force balancing components are evenly distributed on an axial force and shearing force loading stress support arm of the helicopter main reducer propeller hub load simulation loading device, the components adopt pulley components and tower type force balancer combinations, the pulling force of the tower type force balancer can be amplified according to different pulley combinations, the self weight of the helicopter main reducer propeller hub load simulation loading device is balanced in a large force range, and in addition, the characteristic that the force is constant in a large telescopic stroke of the tower type force balancer is utilized, when the main reducer is subjected to large axial pulling force to generate large axial displacement, constant balanced lifting force can still be provided.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (2)
1. A helicopter main reducer propeller hub load simulation loading device considering balance static deadweight is characterized by comprising a rotor wing loading bearing seat assembly (10), a lift force loading assembly (20), a shear force loading assembly (30) and a force balance assembly (40). The rotor wing loading bearing seat assembly (10) comprises an output flange assembly (11), a tapered roller bearing (12), a bearing inner spacer ring (13), a bearing oil injection outer spacer ring (14), a bearing seat shell (15), a bearing seat rotating shaft (16), a rotor wing adapter flange (17) and an axial force and shearing force loading stress support arm assembly (18). The rotor wing loading bearing seat assembly (10) is supported by a pair of tapered roller bearings (12) in a back-to-back combined mode, and an inner spacer ring (13) of the bearing is matched with an outer spacer ring (14) of oil injection of the bearing to adjust pretightening force. The rotor wing loading bearing seat assembly (10) is provided with a bearing seat rotating shaft (16), the upper part of the bearing seat rotating shaft (16) is connected with the output flange assembly (11) through a crowned tooth, and the lower part of the bearing seat rotating shaft (16) is connected with a rotor wing adapter flange (17) through an end face tooth. The lift force loading assembly (20) and the shear force loading assembly (30) are connected with the bearing seat shell (15) through the axial force and shear force loading stress support arm assembly (18). The force balancing assembly (40) is connected to the shear loading assembly (30).
2. The helicopter main reducer hub load simulation loading device considering the balanced static dead weight according to claim 1, wherein the force balance assembly (40) comprises a lift pulley assembly (41), a steel wire rope (42) and a tower type force balancer assembly (43). The lifting pulley component (41) is connected with the tower-type force balancer component (43) through a steel wire rope (42).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111501890.0A CN114252262B (en) | 2021-12-09 | 2021-12-09 | Helicopter main reducer hub load simulation loading device considering balanced static dead weight |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111501890.0A CN114252262B (en) | 2021-12-09 | 2021-12-09 | Helicopter main reducer hub load simulation loading device considering balanced static dead weight |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114252262A true CN114252262A (en) | 2022-03-29 |
| CN114252262B CN114252262B (en) | 2023-12-08 |
Family
ID=80794435
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111501890.0A Active CN114252262B (en) | 2021-12-09 | 2021-12-09 | Helicopter main reducer hub load simulation loading device considering balanced static dead weight |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114252262B (en) |
Citations (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4089211A (en) * | 1976-11-01 | 1978-05-16 | United Technologies Corporation | Elastomeric bearing test machine |
| WO2003091099A2 (en) * | 2002-04-25 | 2003-11-06 | Airscooter Corporation | Rotorcraft |
| 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 |
| US20100284794A1 (en) * | 2007-08-02 | 2010-11-11 | Florida Turbine Technologies, Inc. | Low pressure turbine rotor disk |
| JP2013052853A (en) * | 2011-08-31 | 2013-03-21 | Ntc Ltd | Main rotor maintenance equipment |
| RU2611480C1 (en) * | 2016-01-26 | 2017-02-22 | Дмитрий Сергеевич Дуров | Multi-screw unmanned rotorcraft |
| CN107436237A (en) * | 2017-06-05 | 2017-12-05 | 上海交通大学 | A kind of helicopter hub center non-torque loading simulator |
| CN107672786A (en) * | 2017-11-02 | 2018-02-09 | 中国科学院、水利部成都山地灾害与环境研究所 | The aircraft and its change flying method of a kind of fixed-wing and rotor change |
| CN207570917U (en) * | 2017-12-01 | 2018-07-03 | 中国直升机设计研究所 | Main hub branch brachiostrophosis load testing machine |
| WO2019154067A1 (en) * | 2018-02-11 | 2019-08-15 | 桂艳春 | Active main rotor blade vertical take-off and landing aircraft |
| CN110803296A (en) * | 2019-10-15 | 2020-02-18 | 中国直升机设计研究所 | Helicopter full-mechanical static test lift force system dummy |
| CN110987424A (en) * | 2019-12-30 | 2020-04-10 | 中国船舶重工集团公司第七0三研究所 | Hollow floating rotary supporting device |
| CN112683528A (en) * | 2020-12-15 | 2021-04-20 | 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 and method |
| CN112722321A (en) * | 2020-12-25 | 2021-04-30 | 中国船舶重工集团公司第七0三研究所 | Intelligent loading method for airplane high-voltage direct-current generator |
| CN113533085A (en) * | 2021-07-01 | 2021-10-22 | 中国航发湖南动力机械研究所 | Helicopter main reducer rotor shaft load loading simulation device |
-
2021
- 2021-12-09 CN CN202111501890.0A patent/CN114252262B/en active Active
Patent Citations (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4089211A (en) * | 1976-11-01 | 1978-05-16 | United Technologies Corporation | Elastomeric bearing test machine |
| WO2003091099A2 (en) * | 2002-04-25 | 2003-11-06 | Airscooter Corporation | Rotorcraft |
| US20100284794A1 (en) * | 2007-08-02 | 2010-11-11 | Florida Turbine Technologies, Inc. | Low pressure turbine rotor disk |
| 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 |
| JP2013052853A (en) * | 2011-08-31 | 2013-03-21 | Ntc Ltd | Main rotor maintenance equipment |
| RU2611480C1 (en) * | 2016-01-26 | 2017-02-22 | Дмитрий Сергеевич Дуров | Multi-screw unmanned rotorcraft |
| CN107436237A (en) * | 2017-06-05 | 2017-12-05 | 上海交通大学 | A kind of helicopter hub center non-torque loading simulator |
| CN107672786A (en) * | 2017-11-02 | 2018-02-09 | 中国科学院、水利部成都山地灾害与环境研究所 | The aircraft and its change flying method of a kind of fixed-wing and rotor change |
| CN207570917U (en) * | 2017-12-01 | 2018-07-03 | 中国直升机设计研究所 | Main hub branch brachiostrophosis load testing machine |
| WO2019154067A1 (en) * | 2018-02-11 | 2019-08-15 | 桂艳春 | Active main rotor blade vertical take-off and landing aircraft |
| CN110803296A (en) * | 2019-10-15 | 2020-02-18 | 中国直升机设计研究所 | Helicopter full-mechanical static test lift force system dummy |
| CN110987424A (en) * | 2019-12-30 | 2020-04-10 | 中国船舶重工集团公司第七0三研究所 | Hollow floating rotary supporting device |
| CN112683528A (en) * | 2020-12-15 | 2021-04-20 | 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 and method |
| CN112722321A (en) * | 2020-12-25 | 2021-04-30 | 中国船舶重工集团公司第七0三研究所 | Intelligent loading method for airplane high-voltage direct-current generator |
| CN113533085A (en) * | 2021-07-01 | 2021-10-22 | 中国航发湖南动力机械研究所 | Helicopter main reducer rotor shaft load loading simulation device |
Non-Patent Citations (3)
| Title |
|---|
| KIM, SH 等: "Numerical Simulation of Cavitation Phenomena for Hybrid Contra-Rotating Shaft Propellers", JOURNAL OF PHYSICS: CONFERENCE SERIES * |
| 谢寒冰: "主旋翼轴高周疲劳寿命研究", 中国优秀硕士学位论文全文数据库, no. 7 * |
| 韩东;张勇刚;黄东盛;: "变直径旋翼直升机飞行性能研究", 南京航空航天大学学报, no. 02 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114252262B (en) | 2023-12-08 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN100485345C (en) | Apparatus for testing fatigue strength of axial hinge bearing of helicopter | |
| CN113533085B (en) | Helicopter main reducer rotor shaft load loading simulation device | |
| CN205593747U (en) | Helicopter main reducer rotor loading device based on hydraulic pressure loading | |
| CN105545612B (en) | Large-scale Wind Turbines and its blade installation structure | |
| CN110641735A (en) | Fatigue test loading device for tail rotor hub journal shaft sleeve assembly | |
| CN102822519A (en) | Wind turbine | |
| WO2019219160A1 (en) | A modular drive system, a load unit and a test bench comprising said modular drive system | |
| CN205280360U (en) | Bearing testing machine | |
| CN113803216B (en) | Wind generating set | |
| CN114252262B (en) | Helicopter main reducer hub load simulation loading device considering balanced static dead weight | |
| CN109030000B (en) | High-speed large-load horizontal sliding bearing performance test bed | |
| CN104389746B (en) | The impeller and wind power generating set of wind power generating set | |
| CN111879511B (en) | Comprehensive test bed for tail speed reducer in helicopter | |
| CN115979652B (en) | GTF engine high-speed flexible rotor system dynamic characteristic test device | |
| CN206256937U (en) | Bearing support structure and aero-engine | |
| CN212363647U (en) | Helicopter middle and tail speed reducer comprehensive test bed | |
| CN205483563U (en) | Single -point supports joint bearing performance test machine | |
| CN209802668U (en) | Gear drive fan engine low pressure rotor system model test ware | |
| CN203374745U (en) | Pure torsion bar device | |
| CN210661313U (en) | Wheel-side speed reducer of drive axle of loader | |
| CN117871093A (en) | Helicopter main reducer propeller hub load simulation loading device | |
| CN115165597B (en) | High-pressure turbine shaft strength test device | |
| CN219964752U (en) | Transmission fixed knot constructs and mixer | |
| CN216131349U (en) | Multi-split parallel transmission structure of gear box | |
| CN221350528U (en) | Water lubrication bearing performance test bed |
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 |