CN104896049A - Mini-type dual-power aircraft bearing speed reduction device - Google Patents
Mini-type dual-power aircraft bearing speed reduction device Download PDFInfo
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- CN104896049A CN104896049A CN201510275379.1A CN201510275379A CN104896049A CN 104896049 A CN104896049 A CN 104896049A CN 201510275379 A CN201510275379 A CN 201510275379A CN 104896049 A CN104896049 A CN 104896049A
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- hollow rollers
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- 230000009467 reduction Effects 0.000 title abstract description 18
- 239000007787 solid Substances 0.000 claims abstract description 34
- 230000008878 coupling Effects 0.000 claims description 17
- 238000010168 coupling process Methods 0.000 claims description 17
- 238000005859 coupling reaction Methods 0.000 claims description 17
- 239000003638 chemical reducing agent Substances 0.000 claims description 4
- 239000000203 mixture Substances 0.000 claims description 3
- 230000007246 mechanism Effects 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000000979 retarding effect Effects 0.000 description 3
- 230000005540 biological transmission Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000000969 carrier Substances 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 239000000284 extract Substances 0.000 description 1
- 230000008569 process Effects 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16H—GEARING
- F16H37/00—Combinations of mechanical gearings, not provided for in groups F16H1/00 - F16H35/00
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- 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
- B64D35/00—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions
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- 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
- B64D35/00—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions
- B64D35/08—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions characterised by the transmission being driven by a plurality of power plants
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Friction Gearing (AREA)
Abstract
The invention belongs to the technical field of aircraft design and discloses a mini-type dual-power aircraft bearing speed reduction device. The mini-type dual-power aircraft bearing speed reduction device adopts two structures composed of inner friction rings, hollow pin rollers, solid pin rollers and speed reduction machine frames to form the structures which are similar to cylindrical roller bearings and are symmetrically arranged on the two sides of the center of an outer shell, output shafts of two motors are fixedly connected with input shafts through couplers, the input shafts are movably connected with holes of a shell through bearings, are movably connected with center holes of the speed reduction machine frames through another bearings and are fixedly connected with center holes of the inner friction rings, a belt wheel I is movably connected with a belt wheel II through a belt, a center hole of the belt wheel II is fixedly connected with the inner end of a shaft, and the outer end of the shaft is fixedly connected with a center hole of a wing plate. The mini-type dual-power aircraft bearing speed reduction device can achieve a large reduction ratio; if multiple cylindrical roller bearing structures are connected in series, a larger reduction ratio can be achieved, and the weight is not obviously increased; as usage of a clutch is avoided, the cost and weight are both reduced. The mini-type dual-power aircraft bearing speed reduction device is suitable for mini-type aircrafts.
Description
Technical field
The invention belongs to technical field of aircraft design, be specifically related to a kind of deceleration and the power mixing arrangement that are applied to lightweight aircraft.
Background technique
For a long time, the engine device of multiple aircraft devices, for the consideration of Security, usually regularly replaces motor.And for the consideration of Security, its safety coefficient arranges comparatively large usually, and before not reaching its maximum pot life, just more reengine, cost is higher, and equipment use is insufficient.
There is double dynamical output aircraft afterwards, if application number is the aircraft disclosing a kind of comparatively advanced twin-engined outputting powers in the application for a patent for invention " double dynamical output aircraft " of 201420397029.3, motor I output shaft in system is affixed through spline coupling I and belt shaft, affixed belt pulley I on belt shaft, belt pulley I is flexibly connected with the belt pulley II being fixed in back shaft III through belt I; Motor II output shaft is affixed through spline coupling II and sun wheel shaft; The affixed belt pulley III of planetary wheel carrier central shaft, belt pulley III is flexibly connected with belt pulley IV through belt II; Belt pulley IV is fixed in outside bevel gear shaft, the inner affixed bevel gear of bevel gear shaft, and bevel gear engages with upper bevel gear and lower bevel gear up and down respectively; The affixed lower bevel gear in interior axle lower end, the affixed upper rotor in interior axle upper end; The affixed lower rotor in drive socket upper end, the affixed upper bevel gear in drive socket lower end, drive socket is placed in the middle part of interior axle; This aircraft can strengthen the Security of Miniature Vehicle equipment, the utilization rate increasing engine apparatus and working life, reduces aircraft operating cost, and structure is simple, is easy to realize, can realizes reduction gear mechanism simultaneously.
But can find in its embodiment, though adopt double dynamical way of realization, for realizing object, what adopt is planetary gear construction, and the comparatively large and Heavy Weight of physical dimension, is not suitable for the design of minute vehicle, and being subject to the impact of planetary pinion size, reduction speed ratio is little.
Summary of the invention
The object of the present invention is to provide a kind of double dynamical output unit being applied to minute vehicle, when realizing double dynamical, equipment quality is light as far as possible and little, can realize big retarding and compare transmission.Meanwhile, even if do not use clutch, a certain motor is because when fault is stuck, another motor also normally can drive equipment operation.
The present invention is by motor I 1, coupling I 2, input shaft I 3, shell 4, catch I 5, deceleration frame I 6, hollow rollers I 7, bearing shell I 8, planet carrier I 9, belt wheel I 10, planet carrier II 11, hollow rollers II 12, deceleration frame II 13, bearing shell II 14, input shaft II 15, catch II 16, coupling II 17, motor II 18, friction inner ring I 19, hollow rollers III 20, bearing shell III 21, belt 22, belt wheel II 23, axle 24, wing dish 25, bearing shell IV 26, hollow rollers IV 27, friction inner ring II 28, solid roller I 29a and solid roller II 29b forms, wherein the output shaft of motor I 1 is affixed by coupling I 2 and input shaft I 3, input shaft I 3 is flexibly connected with the hole IV 33 of shell 4 by bearing IV d from right-to-left, be flexibly connected with the center hole of catch I 5, be flexibly connected with the center hole of deceleration frame I 6 by bearing III c, affixed with the center hole of friction inner ring II 28, the size shape of the cambered surface II 42 of the size shape in the circular shaft face I 37 of deceleration frame I 6 and the cambered surface I 40 of bearing shell I 8 and bearing shell IV 26 matches.
Solid roller I 29a that hollow rollers I 7,4 is identical, hollow rollers IV 27 and the arrangement of another 4 identical solid roller I 29a orders, be placed between the friction outer ring of inner ring II 28 and the circular shaft face II 38 of deceleration frame I 6, and roll with the friction outer ring of inner ring II 28 and the circular shaft face II 38 of deceleration frame I 6 and be connected.
The axle III 45 of planet carrier I 9 is affixed with the right side of the central through bore of belt wheel I 10, and the axle I 43 of planet carrier I 9 is flexibly connected with the center hole of hollow rollers IV 27, and the axle II 44 of planet carrier I 9 is flexibly connected with the center hole of hollow rollers I 7.
The output shaft of motor II 18 is affixed by coupling II 17 and input shaft II 15, input shaft II 15 is flexibly connected with the hole VII 36 of shell 4 by bearing I a from left to right, be flexibly connected with the center hole of catch II 16, be flexibly connected with the center hole of deceleration frame II 13 by bearing II b, and the center hole of the inner ring I 19 that rubs affixed; The size shape of the cambered surface VI 51 of the size shape in the circular shaft face III 46 of deceleration frame II 13 and the cambered surface III 49 of bearing shell II 14 and bearing shell III 21 matches.
Solid roller II 29b that hollow rollers II 12,4 is identical, hollow rollers III 20 and the arrangement of another 4 identical solid roller II 29b orders, be placed between the friction outer ring of inner ring I 19 and the circular shaft face IV 47 of deceleration frame II 13, and roll with the friction outer ring of inner ring I 19 and the circular shaft face IV 47 of deceleration frame II 13 and be connected.
The axle VI 54 of planet carrier II 11 is affixed with the left side of the central through bore of belt wheel I 10, and the axle IV 52 of planet carrier II 11 is flexibly connected with the center hole of hollow rollers III 20, and the axle V 53 of planet carrier II 11 is flexibly connected with the center hole of hollow rollers II 12.
Belt wheel I 10 is flexibly connected with belt wheel II 23 by belt 22; The center hole of belt wheel II 23 and axle 24 are inner affixed, and the center hole of axle 24 outer end and wing dish 25 is affixed.
The side, hole IV 33 of shell 4 is inner affixed with catch I 5, the side, hole VII 36 of shell 4 is inner affixed with catch II 16, the hole I 30 of shell 4 is flexibly connected with the protruding end VI 50 of bearing shell III 21, the hole III 32 of shell 4 is flexibly connected with the protruding end II 41 of bearing shell IV 26, the hole V 34 of shell 4 is flexibly connected with the protruding end I 39 of bearing shell I 8, and the hole VI 35 of shell 4 is flexibly connected with the protruding end III 48 of bearing shell II 14.
A kind of micro-scale double-power aero-vehicle bearing speed reducer main working process of the present invention is as follows:
For right side power, motor I 1 connects input shaft I 3 by coupling I 2, band kinetic friction inner ring II 28 rotates, friction inner ring II 28, hollow rollers I 7, hollow rollers IV 27, 8 solid roller I 29a and deceleration frame I 6 form a roller bearing structure, when bearing shell I 8 and bearing shell IV 26 compress with deceleration frame I 6, secure deceleration frame I 6, friction inner ring II 28 drives hollow rollers I 7 by frictional force, hollow rollers IV 27 and 8 solid roller I 29a are around the rotation of own axes, simultaneously, self rotation drives hollow rollers I 7, hollow rollers IV 27 and 8 solid roller I 29a carry out the revolution motion around friction inner ring II 28 axis along the cylindrical axial plane of friction inner ring II 28, planet carrier I 9 extracts effective revolution motion, realize the deceleration of mechanism, reduction speed ratio R equals 1+ (internal diameter of the external diameter/friction inner ring II 28 of frame I 6).Simultaneously, if connect multiple by friction inner ring II 28, hollow rollers I 7, hollow rollers IV 27,8 solid roller I 29a and deceleration frame I 6 form a roller bearing structure, larger reduction speed ratio can be realized, reduction speed ratio is the Nth power of R, N is the number of the roller bearing structure of series connection, size is less, and weight increases not obvious.
Planet carrier I 9 is with movable belt pulley I 10 to rotate afterwards, and power is passed to wing dish 25 via belt 22, belt wheel II 23 and axle 24 more successively, and wing dish 25 rotates, and provides the power of aircraft.
Left side power and right side power implementation procedure similar, the sense of rotation uniquely unlike motor II 18 is contrary with motor I 1.
When right side works, compressed with deceleration frame I 6 by external motor band driving box bearing I 8 and bearing shell IV 26, fixing deceleration frame I 6; Friction inner ring II 28 rotates, and drives hollow rollers I 7, solid roller I 29a of hollow rollers IV 27,8 to move along the inner side axial plane of fixing deceleration frame I 6, realizes slowing down, then drives the motion of planet carrier I 9, and planet carrier I 9 is with movable belt pulley I 10 to rotate.
When left side works, compressed with deceleration frame II 13 by external motor band driving box bearing II 14 and bearing shell III 21, fixing deceleration frame II 13; Friction inner ring I 19 rotates, hollow rollers II 12, solid roller II 29b of hollow rollers III 20,8 is driven to move along the inner side axial plane of fixing deceleration frame II 13, realize slowing down, then drive the motion of planet carrier II 11, planet carrier II 11 is with movable belt pulley I 10 to rotate.Solid roller I 29a, solid roller II 29b
When the left and right sides works simultaneously, compressed with deceleration frame I 6 by external motor band driving box bearing I 8 and bearing shell IV 26, bearing shell II 14 and bearing shell III 21 compress with deceleration frame II 13, the direction of rotation of motor I 1 and motor II 18, the common rotation driving wing dish 25.
When only having left side work, and the motor I 1 on right side because of fault stuck time, under outside driven by motor, bearing shell II 14 and bearing shell III 21 compress with deceleration frame II 13, bearing shell I 8 and bearing shell IV 26 do not compress with deceleration frame I 6, as mentioned above, motor II 18 is with movable belt pulley I 10 to rotate, belt wheel I 10 drives planet carrier I 9 to rotate, bearing shell I 8 and bearing shell IV 26 do not compress with deceleration frame I 6, deceleration frame I 6 is movable, according to the character of roller bearing structure, friction inner ring II 28 is fixed because of the stuck motor I 1 of affixed fault, planet carrier I 9 drives hollow rollers I 7 by friction, hollow rollers IV 27 and 8 solid roller I 29a move, drive the rotation of deceleration frame I 6 again, therefore because of stuck 1 normal operation not affecting equipment of fault.When only have right side work, and the motor II 18 in left side because of fault stuck time, running is identical.
The present invention compared with prior art has the following advantages and beneficial effect:
1. can realize big retarding ratio.Friction inner ring II 28, hollow rollers I 7, hollow rollers IV 27, a solid roller I 29a and deceleration frame I 6 composition roller bearing structure, reduction speed ratio R equals 1+ (internal diameter of the external diameter/friction inner ring II 28 of frame I 6).Simultaneously, can connect multiple by friction inner ring II 28, hollow rollers I 7, hollow rollers IV 27,8 solid roller I 29a and deceleration frame I 6 form a roller bearing structure, larger reduction speed ratio can be realized, reduction speed ratio is the Nth power of R, and N is the number of the roller bearing structure of series connection.
2. equipment quality is lighter than existing structure, is applicable to minute vehicle.The reduction gear mechanism of friction inner ring II 28, hollow rollers I 7, hollow rollers IV 27, a 8 solid roller I 29a and deceleration frame I 6 composition roller bearing structure, quality is light.To connect multiple described roller bearing structure simultaneously, can realize more while big retarding ratio quality increase not obvious.
3. avoid the use of clutch, reduce costs, alleviate equipment proper mass.According to the character of roller bearing structure, work when only having side, and in addition side motor because of fault stuck time, under external motor drives, the bearing shell of fault side does not compress with deceleration frame, according to the character of roller bearing structure, the friction inner ring of fault side is fixed because of the stuck motor of affixed fault, the planet carrier of this side drives the motion of solid roller hollow rollers by friction, then drives the rotation of deceleration frame, therefore does not affect the normal operation of equipment because of motor that fault is stuck.
Accompanying drawing explanation
Fig. 1 is the structural representation of micro-scale double-power aero-vehicle bearing speed reducer
Fig. 2 is A-A cross sectional view in Fig. 1
Fig. 3 is B-B cross sectional view in Fig. 1
Fig. 4 is the structural representation of shell 4
Fig. 5 is the structural representation of deceleration frame I 6
Fig. 6 is the structural representation of bearing shell I 8
Fig. 7 is the structural representation of bearing shell IV 26
Fig. 8 is the structural representation of planet carrier I 9
Fig. 9 is the structural representation of deceleration frame II 13
Figure 10 is the structural representation of bearing shell II 14
Figure 11 is the structural representation of planet carrier II 11
Figure 12 is the structural representation of bearing shell III 21
Wherein: a. bearing I, b. bearing II, c. bearing III, d. bearing IV, 1. motor I, 2. coupling I, 3. input shaft I, 4. shell, 5. catch I, 6. deceleration frame I, 7. hollow rollers I, 8. bearing shell I, 9. planet carrier I, 10. belt wheel I, 11. planet carriers II, 12. hollow rollers II, 13. deceleration frames II, 14. bearing shells II, 15. input shafts II, 16. catch II, 17. coupling II, 18. motor II, 19. friction inner rings I, 20. hollow rollers III, 21. bearing shells III, 22. belts, 23. belt wheels II, 24. axles, 25. wing dishes, 26. bearing shells IV, 27. hollow rollers IV, 28. friction inner rings II, the solid roller I of 29a., the solid roller II of 29b., 30. holes I, 31. holes II, 32. holes III, 33. holes IV, 34. holes V, 35. holes VI, 36. holes VII, 37. circular shaft faces I, 38. circular shaft faces II, 39. protruding ends I, 40. cambered surfaces I, 41. protruding ends II, 42. cambered surfaces II, 43. axles I, 44. axles II, 45. axles III, 46. circular shaft faces III, 47. circular shaft faces IV, 48. protruding ends III, 49. cambered surfaces III, 50. protruding ends VI, 51. cambered surfaces VI, 52. axles IV, 53. axles V, 54. axles VI
Embodiment
Below in conjunction with accompanying drawing, embodiments of the present invention are described further.
As shown in Figure 1, the present invention is by motor I 1, coupling I 2, input shaft I 3, shell 4, catch I 5, deceleration frame I 6, hollow rollers I 7, bearing shell I 8, planet carrier I 9, belt wheel I 10, planet carrier II 11, hollow rollers II 12, deceleration frame II 13, bearing shell II 14, input shaft II 15, catch II 16, coupling II 17, motor II 18, friction inner ring I 19, hollow rollers III 20, bearing shell III 21, belt 22, belt wheel II 23, axle 24, wing dish 25, bearing shell IV 26, hollow rollers IV 27, friction inner ring II 28, solid roller I 29a and solid roller II 29b forms, wherein the output shaft of motor I 1 is affixed by coupling I 2 and input shaft I 3, input shaft I 3 is flexibly connected with the hole IV 33 of shell 4 by bearing IV d from right-to-left, be flexibly connected with the center hole of catch I 5, be flexibly connected with the center hole of deceleration frame I 6 by bearing III c, affixed with the center hole of friction inner ring II 28, the size shape of the cambered surface II 42 of the size shape in the circular shaft face I 37 of deceleration frame I 6 and the cambered surface I 40 of bearing shell I 8 and bearing shell IV 26 matches.
As shown in Figure 2, solid roller I 29a that hollow rollers I 7,4 is identical, hollow rollers IV 27 and the arrangement of another 4 identical solid roller I 29a orders, be placed between the friction outer ring of inner ring II 28 and the circular shaft face II 38 of deceleration frame I 6, and roll with the friction outer ring of inner ring II 28 and the circular shaft face II 38 of deceleration frame I 6 and be connected.
The axle III 45 of planet carrier I 9 is affixed with the right side of the central through bore of belt wheel I 10, and the axle I 43 of planet carrier I 9 is flexibly connected with the center hole of hollow rollers IV 27, and the axle II 44 of planet carrier I 9 is flexibly connected with the center hole of hollow rollers I 7.
The output shaft of motor II 18 is affixed by coupling II 17 and input shaft II 15, input shaft II 15 is flexibly connected with the hole VII 36 of shell 4 by bearing I a from left to right, be flexibly connected with the center hole of catch II 16, be flexibly connected with the center hole of deceleration frame II 13 by bearing II b, and the center hole of the inner ring I 19 that rubs affixed; The size shape of the cambered surface VI 51 of the size shape in the circular shaft face III 46 of deceleration frame II 13 and the cambered surface III 49 of bearing shell II 14 and bearing shell III 21 matches.
As shown in Figure 3, solid roller II 29b that hollow rollers II 12,4 is identical, hollow rollers III 20 and the arrangement of another 4 identical solid roller II 29b orders, be placed between the friction outer ring of inner ring I 19 and the circular shaft face IV 47 of deceleration frame II 13, and roll with the friction outer ring of inner ring I 19 and the circular shaft face IV 47 of deceleration frame II 13 and be connected.
The axle VI 54 of planet carrier II 11 is affixed with the left side of the central through bore of belt wheel I 10, and the axle IV 52 of planet carrier II 11 is flexibly connected with the center hole of hollow rollers III 20, and the axle V 53 of planet carrier II 11 is flexibly connected with the center hole of hollow rollers II 12.
Belt wheel I 10 is flexibly connected with belt wheel II 23 by belt 22; The center hole of belt wheel II 23 and axle 24 are inner affixed, and the center hole of axle 24 outer end and wing dish 25 is affixed.
The side, hole IV 33 of shell 4 is inner affixed with catch I 5, the side, hole VII 36 of shell 4 is inner affixed with catch II 16, the hole I 30 of shell 4 is flexibly connected with the protruding end VI 50 of bearing shell III 21, the hole III 32 of shell 4 is flexibly connected with the protruding end II 41 of bearing shell IV 26, the hole V 34 of shell 4 is flexibly connected with the protruding end I 39 of bearing shell I 8, and the hole VI 35 of shell 4 is flexibly connected with the protruding end III 48 of bearing shell II 14.
All with rubbing surface in the cambered surface II 42 of the friction cylindrical axial plane of inner ring II 28, the circular shaft face I 37 of deceleration frame I 6, the cambered surface I 40 of bearing shell I 8 and bearing shell IV 26, in order to realize the transmission of mutual speed and power.
Claims (1)
1. a light-duty double dynamical aero-vehicle bearing speed reducer, is characterized in that by motor I (1), coupling I (2), input shaft I (3), shell (4), catch I (5), deceleration frame I (6), hollow rollers I (7), bearing shell I (8), planet carrier I (9), belt wheel I (10), planet carrier II (11), hollow rollers II (12), deceleration frame II (13), bearing shell II (14), input shaft II (15), catch II (16), coupling II (17), motor II (18), friction inner ring I (19), hollow rollers III (20), bearing shell III (21), belt (22), belt wheel II (23), axle (24), wing dish (25), bearing shell IV (26), hollow rollers IV (27), friction inner ring II (28), solid roller I (29a) and solid roller II (29b) composition, wherein the output shaft of motor I (1) is affixed by coupling I (2) and input shaft I (3), and input shaft I (3) is flexibly connected with the hole IV (33) of shell (4) by bearing IV (d) from right-to-left, be flexibly connected with the center hole of catch I (5), be flexibly connected by the center hole of bearing III (c) with deceleration frame I (6), affixed with the center hole of friction inner ring II (28), the size shape of the cambered surface II (42) of the size shape in the circular shaft face I (37) of deceleration frame I (6) and the cambered surface I (40) of bearing shell I (8) and bearing shell IV (26) matches, the solid roller I (29a) that hollow rollers I (7), 4 is identical, hollow rollers IV (27) and the arrangement of another 4 identical solid roller I (29a) orders, be placed between the friction outer ring of inner ring II (28) and the circular shaft face II (38) of deceleration frame I (6), and roll with the friction outer ring of inner ring II (28) and the circular shaft face II (38) of deceleration frame I (6) and be connected, the axle III (45) of planet carrier I (9) is affixed with the right side of the central through bore of belt wheel I (10), the axle I (43) of planet carrier I (9) is flexibly connected with the center hole of hollow rollers IV (27), and the axle II (44) of planet carrier I (9) is flexibly connected with the center hole of hollow rollers I (7), the output shaft of motor II (18) is affixed by coupling II (17) and input shaft II (15), input shaft II (15) is flexibly connected with the hole VII (36) of shell (4) by bearing I (a) from left to right, be flexibly connected with the center hole of catch II (16), be flexibly connected with the center hole of deceleration frame II (13) by bearing II (b), and the center hole of the inner ring I (19) that rubs affixed, the size shape of the cambered surface VI (51) of the size shape in the circular shaft face III (46) of deceleration frame II (13) and the cambered surface III (49) of bearing shell II (14) and bearing shell III (21) matches, the solid roller II (29b) that hollow rollers II (12), 4 is identical, hollow rollers III (20) and the arrangement of another 4 identical solid roller II (29b) orders, be placed between the friction outer ring of inner ring I (19) and the circular shaft face IV (47) of deceleration frame II (13), and roll with the friction outer ring of inner ring I (19) and the circular shaft face IV (47) of deceleration frame II (13) and be connected, the axle VI (54) of planet carrier II (11) is affixed with the left side of the central through bore of belt wheel I (10), the axle IV (52) of planet carrier II (11) is flexibly connected with the center hole of hollow rollers III (20), and the axle V (53) of planet carrier II (11) is flexibly connected with the center hole of hollow rollers II (12), belt wheel I (10) is flexibly connected with belt wheel II (23) by belt (22), the center hole of belt wheel II (23) and axle (24) are inner affixed, and the center hole of axle (24) outer end and wing dish (25) is affixed, the side, hole IV (33) of shell (4) is inner affixed with catch I (5), the side, hole VII (36) of shell (4) is inner affixed with catch II (16), the hole I (30) of shell (4) is flexibly connected with the protruding end VI (50) of bearing shell III (21), the hole III (32) of shell (4) is flexibly connected with the protruding end II (41) of bearing shell IV (26), the hole V (34) of shell (4) is flexibly connected with the protruding end I (39) of bearing shell I (8), the hole VI (35) of shell (4) is flexibly connected with the protruding end III (48) of bearing shell II (14).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510275379.1A CN104896049B (en) | 2015-05-26 | 2015-05-26 | Mini-type dual-power aircraft bearing speed reduction device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510275379.1A CN104896049B (en) | 2015-05-26 | 2015-05-26 | Mini-type dual-power aircraft bearing speed reduction device |
Publications (2)
| Publication Number | Publication Date |
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| CN104896049A true CN104896049A (en) | 2015-09-09 |
| CN104896049B CN104896049B (en) | 2017-03-22 |
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| CN201510275379.1A Expired - Fee Related CN104896049B (en) | 2015-05-26 | 2015-05-26 | Mini-type dual-power aircraft bearing speed reduction device |
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| CN106494625A (en) * | 2016-11-02 | 2017-03-15 | 沈阳航空航天大学 | A kind of gas-electricity power combined system of parallel general-purpose aircraft |
| TWI647149B (en) * | 2017-11-10 | 2019-01-11 | 林瑤章 | Power transmission system |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106494625A (en) * | 2016-11-02 | 2017-03-15 | 沈阳航空航天大学 | A kind of gas-electricity power combined system of parallel general-purpose aircraft |
| TWI647149B (en) * | 2017-11-10 | 2019-01-11 | 林瑤章 | Power transmission system |
| US10495201B2 (en) | 2017-11-10 | 2019-12-03 | Yao-Chang Lin | Power transmission system |
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| CN104896049B (en) | 2017-03-22 |
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