CN110254730B - Generator installation device and aviation aircraft - Google Patents
Generator installation device and aviation aircraft Download PDFInfo
- Publication number
- CN110254730B CN110254730B CN201910604383.6A CN201910604383A CN110254730B CN 110254730 B CN110254730 B CN 110254730B CN 201910604383 A CN201910604383 A CN 201910604383A CN 110254730 B CN110254730 B CN 110254730B
- Authority
- CN
- China
- Prior art keywords
- flange
- generator
- output shaft
- connecting flange
- engine
- 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
- 238000009434 installation Methods 0.000 title abstract description 18
- 230000008878 coupling Effects 0.000 claims abstract description 63
- 238000010168 coupling process Methods 0.000 claims abstract description 63
- 238000005859 coupling reaction Methods 0.000 claims abstract description 63
- 238000007789 sealing Methods 0.000 claims description 12
- 230000007704 transition Effects 0.000 claims description 11
- 238000012423 maintenance Methods 0.000 abstract description 6
- 230000005611 electricity Effects 0.000 abstract description 5
- 230000005540 biological transmission Effects 0.000 abstract description 4
- 238000010586 diagram Methods 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004308 accommodation Effects 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/40—Arrangements for mounting power plants in aircraft
-
- 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
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
Abstract
The invention discloses a generator mounting device, which comprises a universal coupling, a first connecting flange and a second connecting flange, wherein the first connecting flange is used for being mounted on an output shaft of an engine, the second connecting flange is used for being mounted on an input shaft of a generator, a first flange plate at one end of the universal coupling is connected with the first connecting flange through a fastening bolt, and a second flange plate at the other end of the universal coupling is connected with the second connecting flange through a fastening bolt; the universal coupling is connected with the generator and the aircraft engine, the rotating speed of the output shaft of the engine can be synchronously transmitted to the input shaft of the generator, the generator is driven to generate electricity, the transmission efficiency is high, and the universal coupling has a relatively large application range to the coaxiality of two shafts connected with the universal coupling and the deviation of a deflection included angle, so that the installation and maintenance difficulty of the generator can be reduced, and the problem of reliability caused by low installation coaxiality precision between the output shaft of the engine and the input shaft of the generator can be solved. The invention also discloses an aviation aircraft comprising the generator mounting device.
Description
Technical Field
The invention relates to the technical field of connection of generators on aircrafts, in particular to a generator mounting device. In addition, the invention also relates to an aviation aircraft comprising the generator mounting device.
Background
Along with the increase of airborne electrical equipment of an aviation aircraft, the power consumption demand is gradually increased, and the self generated power of the original aviation engine cannot meet the demand of the airborne equipment, so that the electric quantity needs to be provided by additionally adding a generator set.
At present, two main modes are available for driving an additional generator on an aircraft, one mode is that the additional generator is driven to generate electricity through a belt wheel mechanism at a mounting position reserved at a propeller of an original aircraft engine, but the space at the mounting position is narrow, so that the power of the generator which can be arranged is insufficient to meet the use requirement; the other mode is that an output flange arranged at the tail end of the crankshaft of the original aero-engine is connected with a generator through a rigid coupling, so that the engine is driven to generate electricity, but the connection mode has high requirement on axial installation precision and high technical difficulty in installation and maintenance, and in addition, once axial deviation occurs in the operation process, the rigid coupling can be quickly damaged, and the reliability is low.
Therefore, the generator mounting device with low connection reliability and low mounting and maintenance difficulty is provided, and is a technical problem to be solved by the technical personnel in the field at present.
Disclosure of Invention
The invention aims to provide a generator mounting device which can reduce the difficulty in mounting and maintaining a generator and improve the connection reliability of the generator and an aircraft engine. Another object of the invention is to provide an aeronautical aircraft comprising a generator mounting device as described above.
In order to solve the technical problems, the invention provides a generator mounting device for an aircraft, which comprises a universal coupling, a first coupling flange and a second coupling flange, wherein the first coupling flange is used for being mounted on an output shaft of an engine, the second coupling flange is used for being mounted on an input shaft of a generator, a first flange plate at one end of the universal coupling is connected with the first coupling flange through a fastening bolt, and a second flange plate at the other end of the universal coupling is connected with the second coupling flange through a fastening bolt.
Preferably, the universal coupling is a double cross-axle universal coupling.
Preferably, the tail end of the engine output shaft is conical, the flange hole of the first coupling flange is a tapered hole matched with the tail end of the output shaft, and the first coupling flange is connected with the tail end of the engine output shaft in an interference fit manner.
Preferably, the tail end of the engine output shaft is provided with a threaded hole coaxial with the engine output shaft, the inner wall of the flange hole of the first connecting flange is provided with an annular boss, the engine output shaft further comprises a sealing bolt for fastening, a screw rod of the sealing bolt is in threaded matching connection with the tail end of the engine output shaft, and a nut of the sealing bolt abuts against the boss.
Preferably, the second coupling flange is splined to the generator input shaft.
Preferably, the generator input shaft is a spline shaft, and the second coupling flange is fixedly connected with a spline sleeve matched with the generator input shaft.
Preferably, a transition gasket for positioning is arranged between the first coupling flange and the first flange plate; circular steps are arranged on two sides of the transition gasket, one circular step is connected with the flange hole of the first flange plate in a matched mode, and the other circular step is connected with the flange hole of the first connecting flange in a matched mode.
The invention also provides an aircraft, which comprises an aircraft engine, a generator driven by the aircraft engine and the generator mounting device.
The invention provides a generator mounting device for an aviation aircraft, which comprises a universal coupling, a first connecting flange and a second connecting flange, wherein the first connecting flange is used for being mounted on an output shaft of an engine, the second connecting flange is used for being mounted on an input shaft of a generator, a first flange plate at one end of the universal coupling is connected with the first connecting flange through a fastening bolt, and a second flange plate at the other end of the universal coupling is connected with the second connecting flange through a fastening bolt.
The universal coupling is used for connecting the generator and the aero-engine, the rotating speed of the output shaft of the engine can be synchronously transmitted to the input shaft of the generator, the generator can be driven to generate electricity, the transmission efficiency is high, the universal coupling has a relatively large application range for coaxiality of two shafts connected with the universal coupling and deflection included angle deviation, the installation and maintenance difficulty of the generator can be reduced, the problem of reliability caused by low installation coaxiality precision between the output shaft of the engine and the input shaft of the generator can be solved, and in addition, the universal coupling is light in weight and more meets the requirement of weight reduction of an aero-product.
The aircraft provided by the invention comprises the generator mounting device, and the generator mounting device has the technical effects, so that the aircraft also has the same technical effects, and the details are not described herein.
Drawings
FIG. 1 is a schematic structural diagram of an embodiment of a generator mounting apparatus provided in the present invention;
FIG. 2 is a schematic structural diagram of one embodiment of a universal joint provided in the present invention;
FIG. 3 is a cross-sectional view of one embodiment of a universal joint provided by the present invention;
FIG. 4 is a schematic view of a conical surface connection of an output shaft of an engine in the generator mounting apparatus provided by the present invention;
fig. 5 is a mounting structure view of a transition washer in the generator mounting device provided by the invention.
The drawings are numbered as follows:
the universal joint comprises a universal joint body 1, an engine output shaft 2, a generator input shaft 3, a first connecting flange 4, a second connecting flange 5, a fastening bolt 6, a sealing bolt 7 and a transition gasket 8.
Detailed Description
The core of the invention is to provide a generator mounting device which can reduce the difficulty of mounting and maintaining a generator and improve the connection reliability of the generator and an aircraft engine. Another core of the invention is to provide an aeronautical vehicle comprising the generator mounting device.
In order that those skilled in the art will better understand the disclosure, the invention will be described in further detail with reference to the accompanying drawings and specific embodiments.
Referring to fig. 1 to 3, fig. 1 is a schematic structural diagram of a generator mounting apparatus according to an embodiment of the present invention; FIG. 2 is a schematic structural diagram of one embodiment of a universal joint provided in the present invention; FIG. 3 is a cross-sectional view of one embodiment of a universal joint provided by the present invention.
The generator mounting device provided by the specific embodiment of the invention mainly comprises a universal coupling 1, a first connecting flange 4 and a second connecting flange 5, wherein the first connecting flange 4 is used for being mounted on an engine output shaft 2 of an aircraft engine, the second connecting flange 5 is used for being mounted on a generator input shaft 3, a first flange plate at one end of the universal coupling 1 is fixedly connected with the first connecting flange 4, and a second flange plate at the other end of the universal coupling 1 is connected with the second connecting flange 5.
Specifically, the first flange plate and the first connecting flange 4 and the second flange plate and the second connecting flange 5 are preferably connected through the fastening bolts 6, so that the installation and the disassembly are simple and convenient, and the connection is firm and reliable.
Connect generator and aeroengine through universal joint 1, can transmit the rotational speed synchro of engine output shaft 2 for generator input shaft 3 and realize driving the generator electricity generation, high transmission efficiency, and because universal joint 1 is great relatively to the axiality of the diaxon that connects and the accommodation of deflection contained angle deviation, consequently can also reduce the installation of generator, the maintenance degree of difficulty, and can eliminate the reliability problem that the installation axiality precision is low to cause between engine output shaft 2 and the generator input shaft 3, in addition, because universal joint 1 is light in weight, more accord with the requirement that the aviation product subtracts the heavy.
The universal coupling 1 has various structural forms, and the application does not specifically limit the universal coupling; preferably, the double-cross-shaft type universal coupling 1 can be selected, and has the advantages of compact and reasonable structure, larger angle compensation capability, higher transmission efficiency, larger bearing capacity, stable carrying, low noise and convenient assembly, disassembly and maintenance.
It should be noted that the generator mounting device provided by the present invention is mainly used in an aircraft, and is used for connecting an aircraft engine and a generator, and of course, it may also be used for connecting two shafts that need to rotate synchronously on other machines, and the present application does not specifically limit this.
Referring to fig. 4, fig. 4 is a schematic view illustrating a conical surface connection of an output shaft of an engine in the generator mounting apparatus according to the present invention.
On the basis of the above specific embodiment, in the generator mounting device provided by the present invention, the first coupling flange 4 is mounted on the engine output shaft 2, the connection manner between the first coupling flange 4 and the engine output shaft 2 is various, and because the tail end of the engine output shaft 2 is generally conical, preferably, a flange hole of the first coupling flange 4 can be processed into a conical hole matched with the tail end of the engine output shaft 2, and the flange hole of the first coupling flange 4 is in conical surface fit and interference connection with the tail end of the engine output shaft 2 during connection, so that the engine output shaft 2 can drive the first coupling flange 4 to synchronously rotate during operation of the aircraft engine; the conical surface is connected and can be guaranteed first hookup flange 4 and engine output shaft 2's axiality, and the bell mouth can play the guide effect for the installation of first hookup flange 4 during the connection, makes first hookup flange 4 can overlap the tail end of engine output shaft 2 easily and adjusts the location well automatically, and the faying face is not fragile simultaneously, can install repeatedly and dismantle.
In order to further improve the connection reliability of the first connecting flange 4 and the engine output shaft 2, a sealing bolt 7 can be additionally arranged for fastening, specifically, a threaded hole can be processed at the tail end of the engine output shaft 2, the threaded hole is preferably coaxial with the engine output shaft 2, meanwhile, a boss is arranged on the inner wall of the flange hole of the first connecting flange 4, and the boss is preferably an annular boss coaxial with the flange hole, so as to ensure the structural strength; during installation, after the first connecting flange 4 is in taper connection with the tail end of the engine output shaft 2, a screw rod of the sealing bolt 7 penetrates through a flange hole of the first connecting flange 4, the end part of the screw rod is inserted into a threaded hole at the tail end of the engine output shaft 2, and then the sealing bolt 7 is screwed, so that the screw rod of the sealing bolt 7 is in matched connection with the threaded hole until a nut of the sealing bolt 7 is tightly abutted to a boss.
According to the generator mounting device provided by the invention, the second connecting flange 5 is mounted on the generator input shaft 3, the connection modes of the second connecting flange 5 and the generator output shaft are various, preferably, the second connecting flange 5 is in spline connection with the generator output shaft, the spline connection is uniform in stress and can transmit larger torque, and meanwhile, the second connecting flange 5 and the generator output shaft can axially slide in a certain range. Of course, the connection form between the second coupling flange 5 and the generator output shaft is not limited to this, and a flat key connection or the like may be employed.
Specifically, the generator input shaft 3 can be a spline shaft, in order to ensure the structural strength of the second coupling flange 5, the second coupling flange 5 is preferably connected with the generator input shaft 3 in a matching way through a spline housing, an internal spline matched with the generator output shaft is processed on the inner wall of the spline housing, the outer wall of the spline housing is matched with a flange hole of the second coupling flange 5, and the spline housing and the second coupling flange 5 can be specifically connected through bolts; of course, it is also possible to directly machine a spline groove matching with the output shaft of the generator on the flange hole of the second coupling flange 5, and it is also within the protection scope of the present invention.
Referring to fig. 5, fig. 5 is a structural view illustrating an installation structure of a transition washer in a generator installation apparatus according to the present invention.
On the basis of the above specific embodiments, in order to improve the installation coaxiality between the first coupling flange 4 and the universal coupling 1, a transition washer 8 may be disposed between the first coupling flange 4 and a first flange of the universal coupling 1 near one end of the aircraft engine for positioning, specifically, circular steps are disposed on both sides of the transition washer 8, an outer diameter of one circular step is matched with a flange hole of the first coupling flange 4, an outer diameter of the other circular step is matched with a flange hole of the first flange, when the generator mounting device is installed, one circular step sandwiched by the transition washer 8 is clamped into the flange hole of the first coupling flange 4, the other circular step is clamped into the flange hole of the first flange, and the coaxiality of the coupling member can be ensured by positioning the circular steps on both sides of the transition washer 8, so as to reduce the dynamic unbalance amount of the high-speed rotating member.
The specific implementation manner of the present invention further provides an aircraft including the above generator installation apparatus, the aircraft includes an aircraft engine and a generator driven by the aircraft engine, the generator is connected to the aircraft engine through the above generator installation apparatus, and the structure of other parts of the aircraft engine refers to the prior art and is not described herein again.
It is noted that, in the description of the present application, relational terms such as first and second, and the like are used solely to distinguish one entity from another entity without necessarily requiring or implying any actual such relationship or order between such entities.
In addition, the embodiments in the specification are described in a progressive manner, each embodiment focuses on differences from other embodiments, and similar parts among the embodiments are referred to each other. The device disclosed by the embodiment corresponds to the method disclosed by the embodiment, so that the description is simple, and the relevant part can be referred to the method part for description.
The generator mounting device and the aircraft provided by the invention are described in detail above. The principles and embodiments of the present invention are explained herein using specific examples, which are presented only to assist in understanding the method and its core concepts. It should be noted that, for those skilled in the art, without departing from the principle of the present invention, it is possible to make various improvements and modifications to the present invention, and those improvements and modifications also fall within the scope of the claims of the present invention.
Claims (6)
1. A generator mounting device is used for an aircraft, and is characterized by comprising a universal coupling (1), a first connecting flange (4) and a second connecting flange (5), wherein the first connecting flange (4) is used for being mounted on an output shaft (2) of an engine, the second connecting flange (5) is used for being mounted on an input shaft (3) of a generator, a first flange plate at one end of the universal coupling (1) is connected with the first connecting flange (4) through a fastening bolt (6), and a second flange plate at the other end of the universal coupling is connected with the second connecting flange (5) through a fastening bolt (6);
the tail end of the engine output shaft (2) is conical, a flange hole of the first connecting flange (4) is a conical hole matched with the tail end of the output shaft, and the first connecting flange (4) is in interference fit connection with the tail end of the engine output shaft (2);
the tail end of the engine output shaft (2) is provided with a threaded hole coaxial with the engine output shaft, an annular boss is arranged on the inner wall of a flange hole of the first connecting flange (4), the engine output shaft further comprises a sealing bolt (7) used for fastening, a screw rod of the sealing bolt (7) is in threaded matching connection with the tail end of the engine output shaft (2), and a nut of the sealing bolt (7) is abutted to the boss.
2. Generator mounting arrangement according to claim 1, wherein the universal coupling (1) is a double cross-axle universal coupling.
3. Generator mounting arrangement according to claim 1, wherein the second coupling flange (5) is splined to the generator input shaft (3).
4. Generator mounting arrangement according to claim 3, wherein the generator input shaft (3) is a splined shaft and wherein a splined sleeve matching the generator input shaft (3) is fixedly connected to the second coupling flange (5).
5. Generator mounting arrangement according to any one of claims 1-4, wherein a transition gasket (8) is provided between the first coupling flange (4) and the first flange for positioning; circular steps are arranged on two sides of the transition gasket (8), one circular step is connected with a flange hole of the first flange plate in a matched mode, and the other circular step is connected with a flange hole of the first connecting flange (4) in a matched mode.
6. An aircraft comprising an aircraft engine and a generator driven by the engine, characterised by comprising the generator mounting arrangement of any one of claims 1 to 5.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910604383.6A CN110254730B (en) | 2019-07-05 | 2019-07-05 | Generator installation device and aviation aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910604383.6A CN110254730B (en) | 2019-07-05 | 2019-07-05 | Generator installation device and aviation aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110254730A CN110254730A (en) | 2019-09-20 |
| CN110254730B true CN110254730B (en) | 2023-01-31 |
Family
ID=67924723
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910604383.6A Active CN110254730B (en) | 2019-07-05 | 2019-07-05 | Generator installation device and aviation aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110254730B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113503322A (en) * | 2021-09-13 | 2021-10-15 | 北京中航智科技有限公司 | Transmission system and transmission device |
Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB514634A (en) * | 1937-05-18 | 1939-11-14 | Air Equipment | Improvements in and relating to the mounting on an aircraft of accessory apparatus to be driven from the or a propelling engine |
| US5303681A (en) * | 1992-08-28 | 1994-04-19 | Cummins Engine Company, Inc. | Torsional tunable coupling for a diesel engine drive shaft |
| CN201443433U (en) * | 2009-07-08 | 2010-04-28 | 中国重汽集团济南动力有限公司 | Rear power takeoff device of engine |
| CN203865009U (en) * | 2014-03-21 | 2014-10-08 | 沈阳天之翼航空科技有限公司 | High-integration system of airborne electric generator |
| CN204376622U (en) * | 2014-12-10 | 2015-06-03 | 重庆智仁发电设备有限责任公司 | A kind of combined power generation device |
| CN104925261A (en) * | 2015-06-26 | 2015-09-23 | 周勤 | Unmanned aerial vehicle engine with power generation function |
| CN105186778A (en) * | 2015-08-27 | 2015-12-23 | 安庆市同博科技开发有限责任公司 | Total-power power generating device |
| CN205025969U (en) * | 2015-09-29 | 2016-02-10 | 三一重型能源装备有限公司 | Shaft coupling and aerogenerator for aerogenerator |
| CN105697906A (en) * | 2014-10-31 | 2016-06-22 | 爱默生过程管理调压器技术公司 | valve adapter connection assembly |
| CN105923169A (en) * | 2016-07-06 | 2016-09-07 | 西安交通大学 | Testing platform and testing method for power supply system of gasoline-electric hybrid unmanned aerial vehicle |
| WO2017022697A1 (en) * | 2015-07-31 | 2017-02-09 | Ntn株式会社 | Wheel bearing device with generator |
| CN106542100A (en) * | 2017-01-13 | 2017-03-29 | 必扬星环（北京）航空科技有限公司 | Unmanned Aerial Vehicle Powerplants |
| CN206452249U (en) * | 2017-02-24 | 2017-08-29 | 营口福泰科技有限责任公司 | Mobile charging stake or generating set engine and generator bindiny mechanism |
| CN108488258A (en) * | 2018-02-07 | 2018-09-04 | 北京航天控制仪器研究所 | A kind of actuator of novel on-vehicle taking force power generation system |
-
2019
- 2019-07-05 CN CN201910604383.6A patent/CN110254730B/en active Active
Patent Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB514634A (en) * | 1937-05-18 | 1939-11-14 | Air Equipment | Improvements in and relating to the mounting on an aircraft of accessory apparatus to be driven from the or a propelling engine |
| US5303681A (en) * | 1992-08-28 | 1994-04-19 | Cummins Engine Company, Inc. | Torsional tunable coupling for a diesel engine drive shaft |
| CN201443433U (en) * | 2009-07-08 | 2010-04-28 | 中国重汽集团济南动力有限公司 | Rear power takeoff device of engine |
| CN203865009U (en) * | 2014-03-21 | 2014-10-08 | 沈阳天之翼航空科技有限公司 | High-integration system of airborne electric generator |
| CN105697906A (en) * | 2014-10-31 | 2016-06-22 | 爱默生过程管理调压器技术公司 | valve adapter connection assembly |
| CN204376622U (en) * | 2014-12-10 | 2015-06-03 | 重庆智仁发电设备有限责任公司 | A kind of combined power generation device |
| CN104925261A (en) * | 2015-06-26 | 2015-09-23 | 周勤 | Unmanned aerial vehicle engine with power generation function |
| WO2017022697A1 (en) * | 2015-07-31 | 2017-02-09 | Ntn株式会社 | Wheel bearing device with generator |
| CN105186778A (en) * | 2015-08-27 | 2015-12-23 | 安庆市同博科技开发有限责任公司 | Total-power power generating device |
| CN205025969U (en) * | 2015-09-29 | 2016-02-10 | 三一重型能源装备有限公司 | Shaft coupling and aerogenerator for aerogenerator |
| CN105923169A (en) * | 2016-07-06 | 2016-09-07 | 西安交通大学 | Testing platform and testing method for power supply system of gasoline-electric hybrid unmanned aerial vehicle |
| CN106542100A (en) * | 2017-01-13 | 2017-03-29 | 必扬星环（北京）航空科技有限公司 | Unmanned Aerial Vehicle Powerplants |
| CN206452249U (en) * | 2017-02-24 | 2017-08-29 | 营口福泰科技有限责任公司 | Mobile charging stake or generating set engine and generator bindiny mechanism |
| CN108488258A (en) * | 2018-02-07 | 2018-09-04 | 北京航天控制仪器研究所 | A kind of actuator of novel on-vehicle taking force power generation system |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110254730A (en) | 2019-09-20 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US10934931B2 (en) | Integrated epicyclic gearbox and alternator | |
| CN107863873B (en) | High-speed synchronous permanent magnet coupler and installation method thereof | |
| CN110254730B (en) | Generator installation device and aviation aircraft | |
| US2516066A (en) | Rotor assembly | |
| EP4238873A1 (en) | Propeller transmission system for aviation power | |
| CN104385899A (en) | Hybrid power assembly device for new energy vehicle | |
| CN101951066B (en) | Power transmission device | |
| CN208297555U (en) | A kind of motor test electric machine support and its transmission main shaft | |
| CN101922519A (en) | Universal flexible multi-functional coupling | |
| CN208220895U (en) | A kind of oil pump for engine power takeoff | |
| CN106481736A (en) | Double motive power driving gear-boxes and freewheel clutch integrated | |
| CN203398928U (en) | Expansion bushing for drive motor of electric vehicle | |
| US2778565A (en) | Turbine and compressor coupling | |
| CN112436675B (en) | Double-generator structure of aircraft engine | |
| CN103401354A (en) | Expansion sleeve for electric vehicle drive motor | |
| CN212838329U (en) | A gear pump power transmission device | |
| CN104196956B (en) | A kind of flexible link of reasonable match system | |
| CN201860215U (en) | Power transmission device | |
| CN211106916U (en) | Central electric drive axle structure | |
| CN201779169U (en) | Universal flexible multifunctional coupling | |
| CN115642753B (en) | Reverse-through type coaxial three-support gear box high-speed rotor system | |
| CN219107276U (en) | Magnetic coupling with forward and reverse rotation function | |
| CN220416032U (en) | Connection structure of new forms of energy high-speed drive motor rack | |
| CN221764881U (en) | Gearbox test fixture | |
| CN111005946B (en) | Compact centering adjustable vibration isolation coupling |
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 |