CN211711095U - Helicopter tail transmission shaft device - Google Patents
Helicopter tail transmission shaft device Download PDFInfo
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- CN211711095U CN211711095U CN201922136816.8U CN201922136816U CN211711095U CN 211711095 U CN211711095 U CN 211711095U CN 201922136816 U CN201922136816 U CN 201922136816U CN 211711095 U CN211711095 U CN 211711095U
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- tail shaft
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- 230000005540 biological transmission Effects 0.000 title claims abstract description 50
- 230000008878 coupling Effects 0.000 claims abstract description 39
- 238000010168 coupling process Methods 0.000 claims abstract description 39
- 238000005859 coupling reaction Methods 0.000 claims abstract description 39
- 238000013016 damping Methods 0.000 claims description 34
- 239000002184 metal Substances 0.000 claims description 30
- 238000006073 displacement reaction Methods 0.000 description 13
- 238000012423 maintenance Methods 0.000 description 4
- 239000000463 material Substances 0.000 description 4
- 238000009434 installation Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 230000000149 penetrating effect Effects 0.000 description 2
- 229920002635 polyurethane Polymers 0.000 description 2
- 239000004814 polyurethane Substances 0.000 description 2
- 238000000926 separation method Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 1
- 210000001503 joint Anatomy 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000032258 transport Effects 0.000 description 1
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Abstract
The utility model provides a helicopter tail transmission shaft device, which structurally comprises a front diaphragm coupling (1), a front connecting piece (2), a front tail shaft (3), a front bearing seat component (4), a spline pair, a rear bearing seat component (7), a rear tail shaft (8), a rear connecting piece (9), a rear diaphragm coupling (10) and a spline flange (11); the front diaphragm coupling (1) is connected with one end of a front tail shaft (3) through a front connecting piece (2), the other end of the front tail shaft (3) is connected with one end of a rear tail shaft (8) through a spline pair, the other end of the rear tail shaft (8) is connected with one end of a rear diaphragm coupling (10) through a rear connecting piece (9), the other end of the rear diaphragm coupling (10) is connected with a spline flange (11), a front bearing seat assembly (4) is installed on the front tail shaft (3), and a rear bearing seat assembly (7) is installed on the rear tail shaft (8). The utility model provides a problem that difficulty was maintained in the dismouting of helicopter tail transmission shaft system.
Description
Technical Field
The utility model relates to a helicopter tail transmission shaft device belongs to helicopter tail transmission shaft transmission technical field.
Background
The tail transmission shaft system for the helicopter is mainly of a slender shaft structure, and the angular displacement compensation amount and the axial displacement compensation amount of the tail transmission shaft are generally required to be increased as much as possible so as to reduce the assembly precision requirement on the whole helicopter and further reduce the vibration level of the tail transmission shaft and the whole helicopter; meanwhile, the tail transmission shaft system needs to adopt a flexible supporting structure as much as possible so as to compensate the installation error of the tail transmission shaft and reduce the vibration level of the tail transmission shaft; and most helicopter tail transmission shaft systems all adopt the integral type, and the structure size is great, and the dismouting is maintained the difficulty, and the transportation is inconvenient.
SUMMERY OF THE UTILITY MODEL
The utility model provides a helicopter tail transmission shaft device, its purpose aims at solving current helicopter tail transmission shaft system and adopts integral type structure, dismouting maintenance difficulty's problem.
The technical solution of the utility model is as follows: a helicopter tail transmission shaft device structurally comprises a front diaphragm coupling 1, a front connecting piece 2, a front tail shaft 3, a front bearing seat assembly 4, a spline pair, a rear bearing seat assembly 7, a rear tail shaft 8, a rear connecting piece 9, a rear diaphragm coupling 10 and a spline flange 11; wherein, preceding diaphragm coupling 1 is connected with the one end of preceding tailshaft 3 through preceding connecting piece 2, and the other end of preceding tailshaft 3 passes through the vice one end of being connected with back tailshaft 8 of spline, and the other end of back tailshaft 8 passes through back connecting piece 9 and is connected with the one end of back diaphragm coupling 10, and spline flange 11 is connected to the other end of back diaphragm coupling 10, and preceding bearing frame subassembly 4 dress is on preceding tailshaft 3, and back bearing frame subassembly 7 dress is on back tailshaft 8.
The utility model has the advantages that:
1) the front and rear tail transmission shafts are connected with the torque transmission shaft through the spline pair in the middle, and the structure can realize the separation and assembly of the front and rear shafting without any tool, thereby solving the problems of difficult disassembly, assembly and maintenance and inconvenient transportation;
2) meanwhile, the problems of small angular displacement compensation amount and axial displacement compensation amount and high vibration level of the tail transmission shaft system for the helicopter can be solved; the angular displacement compensation quantity and the axial displacement compensation quantity of the tail transmission shaft can be greatly improved, and the vibration level of the tail transmission shaft and the whole machine is reduced.
Drawings
Fig. 1 is a schematic structural diagram of the present invention.
Fig. 2 is a cross-sectional structural schematic view of the front bearing block assembly 4.
Fig. 3 is a schematic sectional view of the rear bearing block assembly 7.
In the attached drawing 1, 1 is a front diaphragm coupling, 2 is a front connecting piece, 3 is a front tail shaft, 4 is a front bearing seat assembly, 5 is an external spline, 6 is an internal spline, 7 is a rear bearing seat assembly, 8 is a rear tail shaft, 9 is a rear connecting piece, 10 is a rear diaphragm coupling, 11 is a spline flange, 12 is an A bolt, 13 is a B bolt, 14 is a C bolt, 15 is an A bolt nut, 16 is a B bolt nut, 17 is a bolt nut assembly, 4-1 is a front bearing seat metal framework, 4-2 is a front bearing seat vibration reduction body, 4-3 is an A bearing, 4-4 is an A bearing positioning sleeve, 4-5 is an A mounting screw, 4-6 is an A lining sleeve, 4-7 is an A shaft elastic retainer ring, 7-1 is a rear bearing seat metal framework, 7-2 is a rear bearing seat vibration reduction body, 7-3 is a B bearing, 7-4 is a B bearing positioning sleeve, 7-5 is a B inner bushing, 7-6 is a B mounting screw, 7-7 is a B shaft elastic retainer ring, 7-8 is an end cover metal framework, and 7-9 is an end cover vibration damper.
Detailed Description
A helicopter tail transmission shaft device structurally comprises a front diaphragm coupling 1, a front connecting piece 2, a front tail shaft 3, a front bearing seat assembly 4, a spline pair, a rear bearing seat assembly 7, a rear tail shaft 8, a rear connecting piece 9, a rear diaphragm coupling 10 and a spline flange 11; wherein, preceding diaphragm coupling 1 is connected with the one end of preceding tailshaft 3 through preceding connecting piece 2, and the other end of preceding tailshaft 3 passes through the vice one end of being connected with back tailshaft 8 of spline, and the other end of back tailshaft 8 passes through back connecting piece 9 and is connected with the one end of back diaphragm coupling 10, and spline flange 11 is connected to the other end of back diaphragm coupling 10, and preceding bearing frame subassembly 4 dress is on preceding tailshaft 3, and back bearing frame subassembly 7 dress is on back tailshaft 8.
The spline pair comprises an external spline 5 and an internal spline 6; one end of the external spline 5 is connected with the other end of the front tail shaft 3, the other end of the external spline 5 is connected with one end of the internal spline 6 through a spline, and the other end of the internal spline 6 is connected with one end of the rear tail shaft 8; preferably, one end of the external spline 5 is inserted into the front tail shaft 3, and one end of the external spline 5 is connected to the front tail shaft 3 preferably by an a bolt 12, and preferably, the other end of the internal spline 6 is inserted into the rear tail shaft 8, and the other end of the internal spline 6 is connected to the rear tail shaft 8 preferably by a B bolt 13.
The front tail shaft 3 and the rear tail shaft 8 are both hollow tubular.
The front bearing seat assembly 4 comprises a front bearing seat metal framework 4-1, a front bearing seat vibration damping body 4-2, an A bearing 4-3, an A bearing positioning sleeve 4-4, an A mounting screw 4-5, an A inner bushing 4-6 and an A shaft elastic retainer ring 4-7; the A inner bushing 4-6 is positioned in the tubular interior of the front tail shaft 3, the whole A inner bushing 4-6 is vertical to the length direction of the front tail shaft 3, the end surface of the A inner bushing 4-6 is tightly attached to the hollow tubular inner wall of the front tail shaft 3, the A bearing positioning sleeve 4-4 is sleeved on the periphery of the front tail shaft 3, four A screw holes which are uniformly distributed along the circumference of the pipe wall are arranged on the pipe wall of the front tail shaft 3, an A mounting screw 4-5 is arranged in each A screw hole, each A mounting screw 4-5 penetrates through the corresponding A screw hole and then is inserted into the end surface of the A inner bushing 4-6, and the A bearing positioning sleeve 4-4 is fixed on the front tail shaft 3 through the four A mounting screws 4-5; the bearing locating sleeve 4-4, the front tail shaft 3 and the inner bushing 4-6 of the bearing A are sequentially connected and fixed together through four mounting screws 4-5 of the bearing A.
The bearing A4-3 is sleeved on the periphery of the bearing positioning sleeve A4-4, the inner ring of the bearing A4-3 is fixedly connected with the bearing positioning sleeve A4-4, one end of the bearing positioning sleeve A4-4 is provided with a bulge, the outer surface of the bearing positioning sleeve A4-4 is provided with a groove, an elastic check ring for the shaft A4-7 is fixed in the groove, and the inner ring of the bearing A4-3 is fixed between the elastic check ring for the shaft A4-7 and the bulge at one end of the bearing positioning sleeve A4-4; the inner ring of the bearing A4-3 is fixedly connected with the bearing positioning sleeve A4-4, so that the bearing A4-3, the bearing positioning sleeve A4-4, the front tail shaft 3 and the inner bushing A4-6 are also connected into a whole.
The front bearing seat metal framework 4-1 is sleeved on the periphery of the outer ring of the bearing A4-3, a front bearing seat vibration damping body 4-2 is arranged between the front bearing seat metal framework 4-1 and the outer ring of the bearing A4-3, and the front bearing seat vibration damping body 4-2 is utilized to play a role in vibration damping; the outer ring of the bearing A4-3 is closely contacted with the front bearing seat damping body 4-2 but is not fixedly connected with the front bearing seat damping body; therefore, the bearing A4-3 can move left and right along the length direction of the front and tail shaft 3 together with the bearing positioning sleeve A4-4, the front and tail shaft 3 and the inner bushing A4-6 relative to the front bearing seat metal framework 4-1 and the front bearing seat vibration damper 4-2, and the effect that the bearing A4-3 has no axial limit and can move axially in the length direction of the front and tail shaft 3 in the front bearing seat assembly 4 is realized.
The front bearing seat vibration reduction body 4-2 is preferably fixedly connected with the front bearing seat metal framework 4-1; preferably, the outer surface of the front bearing seat vibration damping body 4-2 is convexly embedded on the inner surface of the bearing seat metal framework 4-1.
The front bearing block damping body 4-2 is preferably made of damping materials, and is further preferably made of polyurethane materials.
The rear bearing seat assembly 7 comprises a rear bearing seat metal framework 7-1, a rear bearing seat vibration damping body 7-2, a B bearing 7-3, a B bearing positioning sleeve 7-4, a B inner bushing 7-5, a B mounting screw 7-6, an elastic retainer ring 7-7 for a B shaft, an end cover metal framework 7-8 and an end cover vibration damping body 7-9; the B inner bushing 7-5 is positioned in the tubular interior of the rear tail shaft 8, the whole B inner bushing 7-5 is vertical to the length direction of the rear tail shaft 8, the end face of the B inner bushing 7-5 is tightly attached to the hollow tubular inner wall of the rear tail shaft 8, the B bearing positioning bushing 7-4 is sleeved on the periphery of the rear tail shaft 8, four B screw holes which are uniformly distributed along the circumference of the pipe wall are formed in the pipe wall of the rear tail shaft 8, a B mounting screw 7-6 is arranged in each B screw hole, each B mounting screw 7-6 penetrates through the corresponding B screw hole and then is inserted into the end face of the B inner bushing 7-5, and the B bearing positioning bushing 7-4 is fixed on the rear tail shaft 8 through the four B mounting screws 7-6; the bearing locating sleeve 7-4, the rear tail shaft 8 and the inner bushing 7-5 of the B are sequentially connected and fixed together through four mounting screws 7-6 of the B.
The B bearing 7-3 is sleeved on the periphery of the B bearing positioning sleeve 7-4, the inner ring of the B bearing 7-3 is fixedly connected with the B bearing positioning sleeve 7-4, one end of the B bearing positioning sleeve 7-4 is provided with a bulge, the outer surface of the B bearing positioning sleeve 7-4 is also provided with a groove, an elastic check ring 7-7 for the B shaft is fixed in the groove, and the inner ring of the B bearing 7-3 is fixed between the elastic check ring 7-7 for the B shaft and the bulge at one end of the B bearing positioning sleeve 7-4; the inner ring of the bearing B7-3 is fixedly connected with the bearing B locating sleeve 7-4, so that the bearing B7-3, the bearing B locating sleeve 7-4, the rear tail shaft 8 and the inner bushing B7-5 are also connected into a whole.
The rear bearing seat metal framework 7-1 is sleeved on the periphery of an outer ring of the B bearing 7-3, a rear bearing seat vibration damping body 7-2 is arranged between the rear bearing seat metal framework 7-1 and the outer ring of the B bearing 7-3, one side of the bearing seat metal framework 7-1 and one side of the rear bearing seat vibration damping body 7-2 extend to one side of the outer ring of the B bearing 7-3 towards the direction of a rear tail shaft 8, the outer ring of the B bearing 7-3 is tightly contacted with the rear bearing seat vibration damping body 7-2, the other side of the bearing seat metal framework 7-1 and the rear bearing seat vibration damping body 7-2 is fixedly connected with an end cover metal framework 7-8, an end cover vibration damping body 7-9 is arranged between the end cover metal framework 7-8 and the other side of the outer ring of the B bearing 7-3, and the rear bearing seat vibration damping body 7; the two sides of the outer ring of the B bearing 7-3 are limited and fixed by the rear bearing seat vibration damping body 7-2 and the end cover vibration damping body 7-9, so that the B bearing 7-3 cannot move left and right relative to the rear bearing seat metal framework 7-1 and the rear bearing seat vibration damping body 7-2 along the length direction of the rear tail shaft 8, and the effects that the bearing 7-3 is axially limited and cannot move axially in the length direction of the rear tail shaft 8 in the rear bearing seat assembly are achieved.
The rear bearing seat vibration reduction body 7-2 and the rear bearing seat metal framework 7-1 are preferably fixedly connected.
The rear bearing seat damping body 7-2 and the end cover damping body 7-9 are preferably made of damping materials, and further preferably made of polyurethane materials.
The front diaphragm coupling 1, the front connecting piece 2, the front tail shaft 3 and the front bearing seat component 4 of the utility model form the front section of the tail transmission shaft, and the rear bearing seat component 7, the rear tail shaft 8, the rear connecting piece 9, the rear diaphragm coupling 10 and the spline flange 11 form the rear section of the tail transmission shaft; the front section of the tail transmission shaft is supported by a front diaphragm coupling 1 and a front bearing seat assembly 4 (without axial restraint) with a vibration reduction function, and the rear section of the tail transmission shaft is supported by a rear bearing seat assembly 7 (with axial restraint) with a vibration reduction function and a spline flange 11 connected with a rear diaphragm coupling 10; the front and rear tail transmission shafts are connected and torque-transmitted through a spline pair formed by the external spline 5 and the internal spline 6, and are connected through the spline between the external spline 5 and the internal spline 6, so that the utility model can realize the separation and assembly of the front section of the tail transmission shaft and the rear section of the tail transmission shaft without any tool, is convenient to maintain, and facilitates the product transportation after the disassembly; the problem of current helicopter tail transmission shaft system adopt integral type structure, dismouting maintenance difficulty is solved.
The front diaphragm coupling 1 is preferably connected to the front connecting piece 2 by means of C-bolts 14.
One end of the front connecting piece 2 is preferably inserted into the front tail shaft 3 and is in opposite penetrating connection with the front tail shaft 3 through an A bolt and a nut 15.
The rear connecting piece 9 and the rear tail shaft 8 are connected in a penetrating mode through a B bolt and nut 16, and the rear diaphragm coupling 10 is connected with the rear connecting piece 9 and the spline flange 11 through a bolt and nut assembly 17.
The utility model discloses a preceding diaphragm coupling 1 and the flexible support of preceding tail-shaft 3 is realized to preceding chock subassembly 4 of no axial restraint, adopts the flexible support of the back chock subassembly 7 that has the axial restraint and the realization of back diaphragm coupling 10 to back tail-shaft 8, and the vibration level of greatly reduced tail transmission shaft improves tail transmission shaft life.
The whole tail transmission shaft of the utility model adopts a split type flexible supporting structure, and when in use, the spline flange 11 is butted with a driven piece to form another spline pair; the front diaphragm coupler 1 and the rear diaphragm coupler 10 can compensate angular displacement deviation caused by processing and installation and axial displacement deviation in a small range (0.5 mm-1.0 mm), the spline pair formed by the external spline 5 and the internal spline 6 and the spline pair formed by the spline flange 11 and a driven part can compensate axial displacement deviation in a large range (5 mm-10 mm) caused by butt joint of a machine body, and meanwhile, the front flexible bearing seat and the rear flexible bearing seat can reduce the vibration level of a tail transmission shaft; the utility model discloses tail transmission shaft device has that the offset is big, the vibration level is low, characteristics such as installation maintenance convenience.
The utility model greatly improves the tail transmission shaft angular displacement compensation amount and the axial displacement compensation amount through a front diaphragm coupling and a rear diaphragm coupling and two spline pairs, and simultaneously, a front tail shaft 3 and a rear tail shaft 8 are respectively supported by a front diaphragm coupling 1, a front bearing seat assembly 4, a rear diaphragm coupling 10 and a rear bearing seat assembly 7; the structural form reduces the assembly precision requirement on the whole machine, and further reduces the vibration level of the tail transmission shaft and the whole machine; in addition, this helicopter tail transmission shaft device adopts split type design, and the dismouting is maintained conveniently, and the transportation is convenient.
The present invention will be described in further detail with reference to the following examples:
example 1
The tail transmission shaft device of the unmanned helicopter comprises a front diaphragm coupling 1, a front connecting piece 2, a front tail shaft 3, a front bearing seat assembly 4, an external spline 5, an internal spline 6, a rear bearing seat assembly 7, a rear tail shaft 8, a rear connecting piece 9, a rear diaphragm coupling 10 and a spline flange 11; wherein, preceding diaphragm coupling 1 is connected with the one end of preceding tailshaft 3 through preceding connecting piece 2, the other end of preceding tailshaft 3 is connected with the one end of external splines 5, the other end of external splines 5 is connected with the one end of internal splines 6, the other end of internal splines 6 is connected with the one end of back tailshaft 8, the other end of back tailshaft 8 passes through back connecting piece 9 and is connected with the one end of back diaphragm coupling 10, spline flange 11 is connected to the one end of back diaphragm coupling 10, the cover of front bearing seat subassembly 4 is on preceding tailshaft 3, the cover of back bearing seat subassembly 7 is on back tailshaft 8.
This unmanned helicopter tail transmission shaft device has entered the trial-manufacturing stage of small batch, and this tail transmission shaft device satisfies the index requirement that angular displacement compensation amount is no less than 1.5, axial displacement compensation amount is no less than 10mm in debugging flight examination along with the complete machine, the tail transmission shaft vibration level is no more than 0.1g, and the dismouting is maintained conveniently, transports conveniently.
Claims (10)
1. A helicopter tail transmission shaft device is characterized by comprising a front diaphragm coupling (1), a front connecting piece (2), a front tail shaft (3), a front bearing seat assembly (4), a spline pair, a rear bearing seat assembly (7), a rear tail shaft (8), a rear connecting piece (9), a rear diaphragm coupling (10) and a spline flange (11); the front diaphragm coupling (1) is connected with one end of a front tail shaft (3) through a front connecting piece (2), the other end of the front tail shaft (3) is connected with one end of a rear tail shaft (8) through a spline pair, the other end of the rear tail shaft (8) is connected with one end of a rear diaphragm coupling (10) through a rear connecting piece (9), the other end of the rear diaphragm coupling (10) is connected with a spline flange (11), a front bearing seat assembly (4) is installed on the front tail shaft (3), and a rear bearing seat assembly (7) is installed on the rear tail shaft (8).
2. A helicopter tail shaft assembly according to claim 1 wherein said spline pair comprises an external spline (5), an internal spline (6); one end of the external spline (5) is connected with the other end of the front tail shaft (3), the other end of the external spline (5) is connected with one end of the internal spline (6) through a spline, and the other end of the internal spline (6) is connected with one end of the rear tail shaft (8).
3. A helicopter tail shaft assembly according to claim 2 wherein one end of said external spline (5) is inserted into the front tail shaft (3) and one end of the external spline (5) is connected to the front tail shaft (3) by a bolt a (12), the other end of the internal spline (6) is inserted into the rear tail shaft (8) and the other end of the internal spline (6) is connected to the rear tail shaft (8) by a bolt B (13).
4. A helicopter tail shaft assembly according to claim 1, characterised in that the front tail shaft (3) and the rear tail shaft (8) are both hollow and tubular.
5. The helicopter tail transmission shaft device according to claim 4, characterized in that the front bearing block assembly (4) comprises a front bearing block metal framework (4-1), a front bearing block vibration damping body (4-2), an A bearing (4-3), an A bearing positioning sleeve (4-4), an A mounting screw (4-5), an A inner bushing (4-6) and an A shaft elastic retainer ring (4-7); the A inner bushing (4-6) is located in the tubular interior of the front tail shaft (3), the whole A inner bushing (4-6) is perpendicular to the length direction of the front tail shaft (3), the end face of the A inner bushing (4-6) is tightly attached to the hollow tubular inner wall of the front tail shaft (3), the A bearing positioning sleeve (4-4) is sleeved on the periphery of the front tail shaft (3), four A screw holes are uniformly distributed along the circumference of the pipe wall on the pipe wall of the front tail shaft (3), an A mounting screw (4-5) is arranged in each A screw hole, each A mounting screw (4-5) penetrates through the corresponding A screw hole and then is inserted into the end face of the A inner bushing (4-6), and the A bearing positioning sleeve (4-4) is fixed on the front tail shaft (3) through the four A mounting screws (4-5).
6. The helicopter tail transmission shaft device according to claim 5, characterized in that the A bearing (4-3) is sleeved on the periphery of the A bearing positioning sleeve (4-4), the inner ring of the A bearing (4-3) is fixedly connected with the A bearing positioning sleeve (4-4), one end of the A bearing positioning sleeve (4-4) is provided with a bulge, the outer surface of the A bearing positioning sleeve (4-4) is provided with a groove, an elastic check ring (4-7) for the A shaft is fixed in the groove, and the inner ring of the A bearing (4-3) is fixed between the elastic check ring (4-7) for the A shaft and the bulge at one end of the A bearing positioning sleeve (4-4).
7. The helicopter tail transmission shaft device according to claim 5, characterized in that the front bearing seat metal framework (4-1) is sleeved on the periphery of the outer ring of the bearing A (4-3), a front bearing seat damping body (4-2) is arranged between the front bearing seat metal framework (4-1) and the outer ring of the bearing A (4-3), and the outer ring of the bearing A (4-3) is tightly contacted with but not fixedly connected with the front bearing seat damping body (4-2).
8. The helicopter tail transmission shaft device according to claim 4, characterized in that the rear bearing block assembly (7) comprises a rear bearing block metal framework (7-1), a rear bearing block vibration damping body (7-2), a B bearing (7-3), a B bearing positioning sleeve (7-4), a B inner bushing (7-5), a B mounting screw (7-6), a B shaft elastic retainer ring (7-7), an end cover metal framework (7-8) and an end cover vibration damping body (7-9); the B inner bushing (7-5) is positioned in the tubular interior of the rear tail shaft (8), the whole B inner bushing (7-5) is perpendicular to the length direction of the rear tail shaft (8), the end face of the B inner bushing (7-5) is tightly attached to the hollow tubular inner wall of the rear tail shaft (8), the B bearing positioning sleeve (7-4) is sleeved on the periphery of the rear tail shaft (8), four B screw holes are uniformly distributed along the circumference of the pipe wall on the pipe wall of the rear tail shaft (8), a B mounting screw (7-6) is arranged in each B screw hole, each B mounting screw (7-6) penetrates through the corresponding B screw hole and then is inserted into the end face of the B inner bushing (7-5), and the B bearing positioning sleeve (7-4) is fixed on the rear tail shaft (8) through the four B mounting screws (7-6).
9. The helicopter tail transmission shaft device as claimed in claim 8, characterized in that the B bearing (7-3) is sleeved on the periphery of the B bearing positioning sleeve (7-4), the inner ring of the B bearing (7-3) is fixedly connected with the B bearing positioning sleeve (7-4), one end of the B bearing positioning sleeve (7-4) is provided with a protrusion, the outer surface of the B bearing positioning sleeve (7-4) is provided with a groove, a B shaft circlip (7-7) is fixed in the groove, and the inner ring of the B bearing (7-3) is fixed between the B shaft circlip (7-7) and the protrusion at one end of the B bearing positioning sleeve (7-4).
10. The helicopter tail transmission shaft device according to claim 8, characterized in that the rear bearing seat metal framework (7-1) is sleeved on the periphery of the outer ring of the B bearing (7-3), a rear bearing seat vibration damping body (7-2) is arranged between the rear bearing seat metal framework (7-1) and the outer ring of the B bearing (7-3), one side of the bearing seat metal framework (7-1) and the rear bearing seat vibration damping body (7-2) extends to one side of the outer ring of the B bearing (7-3) towards the direction of the rear tail shaft (8), the outer ring of the B bearing (7-3) is tightly contacted with the rear bearing seat vibration damping body (7-2), the other side of the bearing seat metal framework (7-1) and the rear bearing seat vibration damping body (7-2) is fixedly connected with the end cover metal framework (7-8), and the other side of the end cover metal framework (7-8) and the outer ring of the B bearing (7-3) is tightly The two sides of the outer ring of the bearing B (7-3) are limited and fixed by the rear bearing seat vibration damping body (7-2) and the end cover vibration damping body (7-9).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922136816.8U CN211711095U (en) | 2019-12-03 | 2019-12-03 | Helicopter tail transmission shaft device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922136816.8U CN211711095U (en) | 2019-12-03 | 2019-12-03 | Helicopter tail transmission shaft device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN211711095U true CN211711095U (en) | 2020-10-20 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201922136816.8U Expired - Fee Related CN211711095U (en) | 2019-12-03 | 2019-12-03 | Helicopter tail transmission shaft device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN211711095U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112249343A (en) * | 2020-10-29 | 2021-01-22 | 中国航发湖南动力机械研究所 | Tail transmission shaft and helicopter |
| CN112591114A (en) * | 2021-03-03 | 2021-04-02 | 北京清航紫荆装备科技有限公司 | Cross double-rotor unmanned helicopter and power system thereof |
| CN114735207A (en) * | 2022-06-13 | 2022-07-12 | 北京航景创新科技有限公司 | Tail transmission structure of unmanned helicopter |
-
2019
- 2019-12-03 CN CN201922136816.8U patent/CN211711095U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112249343A (en) * | 2020-10-29 | 2021-01-22 | 中国航发湖南动力机械研究所 | Tail transmission shaft and helicopter |
| CN112591114A (en) * | 2021-03-03 | 2021-04-02 | 北京清航紫荆装备科技有限公司 | Cross double-rotor unmanned helicopter and power system thereof |
| CN112591114B (en) * | 2021-03-03 | 2021-07-16 | 北京清航紫荆装备科技有限公司 | Cross double-rotor unmanned helicopter and power system thereof |
| CN114735207A (en) * | 2022-06-13 | 2022-07-12 | 北京航景创新科技有限公司 | Tail transmission structure of unmanned helicopter |
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| GR01 | Patent grant | ||
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| CF01 | Termination of patent right due to non-payment of annual fee | ||
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Granted publication date: 20201020 |