CN104896049B - 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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- CN104896049B CN104896049B CN201510275379.1A CN201510275379A CN104896049B CN 104896049 B CN104896049 B CN 104896049B CN 201510275379 A CN201510275379 A CN 201510275379A CN 104896049 B CN104896049 B CN 104896049B
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- 230000009467 reduction Effects 0.000 title abstract description 11
- 239000007787 solid Substances 0.000 claims abstract description 35
- 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
- 238000005096 rolling process Methods 0.000 claims description 4
- 239000000203 mixture Substances 0.000 claims description 2
- 230000007246 mechanism Effects 0.000 description 3
- 230000000979 retarding effect Effects 0.000 description 3
- 230000005540 biological transmission Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000008450 motivation Effects 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000000284 extract Substances 0.000 description 1
- 230000000116 mitigating effect Effects 0.000 description 1
- 230000000737 periodic effect 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, and in particular to a kind of deceleration for being applied to lightweight aircraft and power are mixed
Attach together and put.
Background technology
For a long time, the engine device of various aircraft devices, for security reasons, usually periodic replacement is started
Machine.And for security reasons, generally its safety coefficient arranges larger, before its maximum pot life is not up to, just
More reengine, relatively costly, equipment is using insufficient.
Double dynamical output aircraft, the such as application for a patent for invention of Application No. 201420397029.3 is occurred in that afterwards《It is double
Power output aircraft》In disclose a kind of aircraft of relatively advanced twin-engined output power, starting in system
I output shaft Jing spline couplings I of machine are affixed with belt shaft, affixed belt pulley I on belt shaft, I percutaneous of belt pulley band I be fixed in
The belt pulley II of support shaft III is flexibly connected；II output shaft Jing spline couplings II of electromotor are affixed with sun wheel shaft；Planetary gear
The affixed belt pulley III of frame central shaft, III percutaneous of belt pulley band II are flexibly connected with belt pulley IV；Belt pulley IV is fixed in bevel gear
On the outside of axle, the inner affixed bevel gear of bevel gear shaft, bevel gear are engaged with upper bevel gear and lower bevel gear up and down respectively；Interior axle lower end
Affixed lower bevel gear, the affixed upper rotor in interior axle upper end；The affixed lower rotor in drive socket upper end, the affixed epicone tooth in drive socket lower end
Wheel, drive socket are placed in the middle part of interior axle；The aircraft can strengthen the safety of Miniature Vehicle equipment, increase making for engine apparatus
With rate and service life, aircraft operating cost, simple structure is reduced, it is easy to accomplish, while being capable of achieving reduction gear mechanism.
Though but it is found that using double dynamical way of realization, for realizing purpose, using in its embodiment
Planetary gear construction, physical dimension is larger and weight weight, is not suitable for the design of minute vehicle, and is subject to planetary gear size
Impact, speed reducing ratio is little.
The content of the invention
It is an object of the invention to provide a kind of double dynamical outut device for being applied to minute vehicle, realize it is double dynamical
When, equipment quality is as light as possible and little, is capable of achieving big retarding than transmission.Meanwhile, even if not using clutch, a certain motor
Because when failure is stuck, another motor also can normally drive equipment operation.
The present invention is by motor I 1, shaft coupling I 2, input shaft I 3, shell 4, catch I 5, deceleration frame I 6, hollow rollers I
7th, 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
Axle II 15, catch II 16, shaft coupling II 17, motor II 18, friction inner ring I 19, hollow rollers III 20, bearing shell III 21, belt
22nd, belt wheel II 23, axle 24, wing disk 25, bearing shell IV 26, hollow rollers IV 27, friction inner ring II 28, I 29a of solid roller and solid
II 29b of roller is constituted, and wherein the output shaft of motor I 1 is affixed with input shaft I 3 by shaft coupling I 2, and input shaft I 3 is from right-to-left
Be flexibly connected with the hole IV 33 of shell 4 by IV d of bearing, be flexibly connected with the centre bore of catch I 5, by III c of bearing and deceleration
The centre bore of frame I 6 is flexibly connected, and the centre bore of friction inner ring II 28 it is affixed；The size in the circular shaft face I 37 of deceleration frame I 6
Shape is matched with the size shape of the cambered surface II 42 of the cambered surface I 40 and bearing shell IV 26 of bearing shell I 8.
The solid roller of solid I 29a of roller of I 7,4 identicals of hollow rollers, hollow rollers IV 27 and another 4 identicals I
29a order arrange, be placed in friction inner ring II 28 outer ring and the circular shaft face II 38 of deceleration frame I 6 between, and with friction inner ring II
28 outer ring and the circular shaft face II 38 of deceleration frame I 6 roll connection.
The axle III 45 of planet carrier I 9 is affixed with the right side of the central through hole of belt wheel I 10, axle I 43 and the hollow rolling of planet carrier I 9
The centre bore of post IV 27 is flexibly connected, and the axle II 44 of planet carrier I 9 is flexibly connected with the centre bore of hollow rollers I 7.
The output shaft of motor II 18 is affixed with input shaft II 15 by shaft coupling II 17, and input shaft II 15 leads to from left to right
Cross I a of bearing be flexibly connected with the hole VII 36 of shell 4, be flexibly connected with the centre bore of catch II 16, by II b of bearing and deceleration
The centre bore of frame II 13 is flexibly connected, and the centre bore of friction inner ring I 19 it is affixed；The circular shaft face III 46 of deceleration frame II 13
Size shape is matched with the size shape of the cambered surface VI 51 of the cambered surface III 49 and bearing shell III 21 of bearing shell II 14.
Solid II 29b of roller of II 12,4 identicals of hollow rollers, hollow rollers III 20 and the solid roller of another 4 identicals
II 29b orders are arranged, and are placed between the outer ring and the circular shaft face IV 47 of deceleration frame II 13 of friction inner ring I 19, and interior with friction
Enclose I 19 outer ring and the circular shaft face IV 47 of deceleration frame II 13 and roll connection.
The axle VI 54 of planet carrier II 11 is affixed with the left side of the central through hole of belt wheel I 10, the axle of planet carrier II 11 IV 52 with
The centre bore of hollow rollers III 20 is flexibly connected, and the axle V 53 of planet carrier II 11 is with the centre bore activity of hollow rollers II 12 even
Connect.
Belt wheel I 10 is flexibly connected with belt wheel II 23 by belt 22；The centre bore of belt wheel II 23 and 24 inner affixed, axle of axle
24 outer ends are affixed with the centre bore of wing disk 25.
It is affixed with catch I 5 inside IV 33 side of hole of shell 4, it is affixed with catch II 16 inside VII 36 side of hole of shell 4, outward
The hole I 30 of shell 4 is flexibly connected with the protruding end VI 50 of bearing shell III 21, the protruding end II 41 of the hole of shell 4 III 32 and bearing shell IV 26
It is flexibly connected, 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 convex with bearing shell II 14
Origin or beginning III 48 is flexibly connected.
A kind of micro-scale double-power aero-vehicle bearing deceleration device main working process of the present invention is as follows：
By taking right side power as an example, motor I 1 connects input shaft I 3 by shaft coupling I 2, and band dynamic friction inner ring II 28 is rotated,
Friction inner ring II 28, hollow rollers I 7, IV 27,8 I 29a of solid roller of hollow rollers and deceleration frame I 6 constitute a cylinder
Roller bearing structure, when bearing shell I 8 and bearing shell IV 26 are compressed with deceleration frame I 6, secures deceleration frame I 6, and rub inner ring II 28
Hollow rollers I 7, hollow rollers IV 27 and 8 I 29a of solid roller are driven around the rotation of own axes by frictional force, meanwhile,
Itself rotation drives hollow rollers I 7, hollow rollers IV 27 and 8 I 29a of solid roller along the outer circular shaft of friction inner ring II 28
Face carries out the revolution motion around friction II 28 axis of inner ring, and planet carrier I 9 extracts effective revolution motion, realizes the deceleration of mechanism,
Speed reducing ratio R is equal to 1+ (internal diameter of the external diameter of frame I 6/friction inner ring II 28).Meanwhile, if series connection it is multiple by friction inner ring II 28,
Hollow rollers I 7, IV 27,8 I 29a of solid roller of hollow rollers and deceleration frame I 6 constitute a cylinder roller bearing structure,
It is capable of achieving bigger speed reducing ratio, Nth power of the speed reducing ratio for R, N is the number of the cylinder roller bearing structure of series connection, size is less,
Weight increase is not obvious.
I 9 band movable belt pulley I 10 of planet carrier is rotated afterwards, and power is transferred to via belt 22, belt wheel II 23 and axle 24 again successively
Wing disk 25, wing disk 25 are rotated, there is provided the power of aircraft.
With right side power, left side power realizes that process is similar, it is unique unlike motor II 18 rotation direction with it is electronic
Machine I 1 is contrary.
When right side works, compressed with deceleration frame I 6 by external motor band driving box bearing I 8 and bearing shell IV 26, it is fixed to slow down
Frame I 6；Friction inner ring II 28 is rotated, and drives hollow rollers I 7, IV 27,8 I 29a of solid roller of hollow rollers along fixed
The inner side axial plane motion of deceleration frame I 6, realizes slowing down, then drives the motion of planet carrier I 9, I 9 I 10 turns of movable belt pulley of band of planet carrier
It is dynamic.
When left side works, compressed with deceleration frame II 13 by external motor band driving box bearing II 14 and bearing shell III 21, it is fixed
Deceleration frame II 13；Friction inner ring I 19 is rotated, and drives hollow rollers II 12, III 20,8 II 29b edges of solid roller of hollow rollers
The inner side axial plane motion of fixed deceleration frame II 13, is realized slowing down, then is driven the motion of planet carrier II 11, planet carrier II 11
Band movable belt pulley I 10 is rotated.I 29a of solid roller, II 29b of solid roller
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 are compressed with deceleration frame II 13, and the rotation direction of motor I 1 and motor II 18 is conversely, common
Drive the rotation of wing disk 25.
When only left side work, and the motor I 1 on right side is when hindering stuck for some reason, in the case where outside motor belt motor is dynamic, bearing shell II 14
Compress with deceleration frame II 13 with bearing shell III 21, bearing shell I 8 and bearing shell IV 26 are not compressed with deceleration frame I 6, as described above, electronic
The band movable belt pulley I 10 of machine II 18 is rotated, and belt wheel I 10 drives planet carrier I 9 to rotate, bearing shell I 8 and bearing shell IV 26 not with deceleration frame I 6
Compress, deceleration frame I 6 is movable, according to the property of cylinder roller bearing structure, friction inner ring II 28 is because of the stuck electricity of affixed failure
Motivation I 1 and fix, planet carrier I 9 drives hollow rollers I 7, hollow rollers IV 27 and 8 I 29a of solid roller fortune by rubbing
Move, then drive the rotation of deceleration frame I 6, therefore hindering stuck 1 for some reason does not affect the normal operation of equipment.When only right side work,
And the motor II 18 in left side, when hindering stuck for some reason, running is identical.
The present invention has advantages below and beneficial effect compared with prior art：
1. big retarding ratio is capable of achieving.Friction inner ring II 28, hollow rollers I 7, hollow rollers IV 27, I 29a of solid roller and
Deceleration frame I 6 constitute a cylinder roller bearing structure, speed reducing ratio R equal to 1+ (external diameter of frame I 6/friction inner ring II 28
Internal diameter).Meanwhile, can connect it is multiple by friction inner ring II 28, hollow rollers I 7, IV 27,8 I 29a of solid roller of hollow rollers and
Deceleration frame I 6 constitutes a cylinder roller bearing structure, is capable of achieving bigger speed reducing ratio, and Nth power of the speed reducing ratio for R, N are string
The number of the cylinder roller bearing structure of connection.
2. equipment quality is lighter than existing structure, it is adaptable to minute vehicle.It is friction inner ring II 28, hollow rollers I 7, hollow
IV 27,8 I 29a of solid roller of roller and deceleration frame I 6 constitute the reduction gear mechanism of a cylinder roller bearing structure, quality
Gently.While multiple described cylinder roller bearing structures of connecting, are capable of achieving quality increase while more big retarding ratio unobvious.
3. avoid the use of clutch, reduces cost from mitigating equipment proper mass.According to the property of cylinder roller bearing structure
Matter, when the work of only side, and the motor of other side is when hindering stuck for some reason, under external motor drives, the bearing shell of failure side
Do not compress with deceleration frame, according to the property of cylinder roller bearing structure, the inner ring that rubs of failure side is because affixed failure is stuck
Electromotor and fix, the planet carrier of the side drives solid roller hollow rollers motion by rubbing, then drive deceleration frame from
Turn, therefore hindering stuck motor for some reason does not affect the normal operation of equipment.
Description of the drawings
Structural representations of the Fig. 1 for micro-scale double-power aero-vehicle bearing deceleration device
Fig. 2 is Section A-A view in Fig. 1
Fig. 3 is section B-B view in Fig. 1
Structural representations of the Fig. 4 for shell 4
Fig. 5 is the structural representation of deceleration frame I 6
Structural representations of the Fig. 6 for bearing shell I 8
Structural representations of the Fig. 7 for bearing shell IV 26
Structural representations of the Fig. 8 for planet carrier I 9
Fig. 9 is the structural representation of deceleration frame II 13
Structural representations of the Figure 10 for bearing shell II 14
Structural representations of the Figure 11 for planet carrier II 11
Structural representations of the Figure 12 for bearing shell III 21
Wherein：A. I b. bearings of bearing, II c. bearings, III d. bearings, IV 1. motor, I 2. shaft coupling, I 3. input shaft I
4. 5. catch of shell, I 6. deceleration frame, I 7. hollow rollers, I 8. bearing shell, I 9. planet carrier, I 10. belt wheel, I 11. planet carrier II
12. hollow rollers, II 13. deceleration frame, II 14. bearing shell, II 15. input shaft, II 16. catch, II 17. shaft couplings II 18. are electric
II 24. axle of friction inner ring I 20. hollow rollers, III 21. bearing shell, III 22. belt, 23. belt wheel of motivation II 19., 25. wing disk
Solid II 30. holes I 31. of roller of solid I 29b. of roller of friction II 29a. of inner ring of 26. bearing shell, IV 27. hollow rollers IV 28.
II 32. hole of hole, III 33. hole, IV 34. hole, V 35. hole, VI 36. hole, VII 37. circular shaft face, I 38. circular shaft face, II 39. protruding end
I 40. cambered surface, I 41. protruding end, II 42. cambered surface, II 43. axle, I 44. axle, II 45. axle, III 46. circular shaft face, III 47. circular shaft face
IV 48. protruding end, III 49. cambered surface, III 50. protruding end, VI 51. cambered surface, VI 52. axle, IV 53. axle, V 54. axle VI
Specific embodiment
Below in conjunction with the accompanying drawings embodiments of the present invention are described further.
As shown in figure 1, the present invention by motor I 1, shaft 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, shaft 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 disk 25, bearing shell IV 26, hollow rollers IV 27, friction inner ring II 28, solid roller I
29a and II 29b of solid roller compositions, the wherein output shaft of motor I 1 are affixed with input shaft I 3 by shaft coupling I 2, input shaft I
3 be flexibly connected with the hole IV 33 of shell 4, be flexibly connected with the centre bore of catch I 5 by IV d of bearing from right-to-left, by bearing
III c is flexibly connected with the centre bore of deceleration frame I 6, and the centre bore of friction inner ring II 28 it is affixed；The circular shaft face of deceleration frame I 6
I 37 size shape is matched with the size shape of the cambered surface II 42 of the cambered surface I 40 and bearing shell IV 26 of bearing shell I 8.
As shown in Fig. 2 solid I 29a of roller of I 7,4 identicals of hollow rollers, hollow rollers IV 27 and another 4 identicals
I 29a of solid roller orders are arranged, and are placed between the outer ring and the circular shaft face II 38 of deceleration frame I 6 of friction inner ring II 28, and with
The circular shaft face II 38 of the outer ring of friction inner ring II 28 and deceleration frame I 6 rolls connection.
The axle III 45 of planet carrier I 9 is affixed with the right side of the central through hole of belt wheel I 10, axle I 43 and the hollow rolling of planet carrier I 9
The centre bore of post IV 27 is flexibly connected, and the axle II 44 of planet carrier I 9 is flexibly connected with the centre bore of hollow rollers I 7.
The output shaft of motor II 18 is affixed with input shaft II 15 by shaft coupling II 17, and input shaft II 15 leads to from left to right
Cross I a of bearing be flexibly connected with the hole VII 36 of shell 4, be flexibly connected with the centre bore of catch II 16, by II b of bearing and deceleration
The centre bore of frame II 13 is flexibly connected, and the centre bore of friction inner ring I 19 it is affixed；The circular shaft face III 46 of deceleration frame II 13
Size shape is matched with the size shape of the cambered surface VI 51 of the cambered surface III 49 and bearing shell III 21 of bearing shell II 14.
As shown in figure 3, solid II 29b of roller of II 12,4 identicals of hollow rollers, hollow rollers III 20 are identical with another 4
II 29b of solid roller order arrange, be placed in friction inner ring I 19 outer ring and the circular shaft face IV 47 of deceleration frame II 13 between,
And the circular shaft face IV 47 of the outer ring with friction inner ring I 19 and deceleration frame II 13 rolls and is connected.
The axle VI 54 of planet carrier II 11 is affixed with the left side of the central through hole of belt wheel I 10, the axle of planet carrier II 11 IV 52 with
The centre bore of hollow rollers III 20 is flexibly connected, and the axle V 53 of planet carrier II 11 is with the centre bore activity of hollow rollers II 12 even
Connect.
Belt wheel I 10 is flexibly connected with belt wheel II 23 by belt 22；The centre bore of belt wheel II 23 and 24 inner affixed, axle of axle
24 outer ends are affixed with the centre bore of wing disk 25.
It is affixed with catch I 5 inside IV 33 side of hole of shell 4, it is affixed with catch II 16 inside VII 36 side of hole of shell 4, outward
The hole I 30 of shell 4 is flexibly connected with the protruding end VI 50 of bearing shell III 21, the protruding end II 41 of the hole of shell 4 III 32 and bearing shell IV 26
It is flexibly connected, 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 convex with bearing shell II 14
Origin or beginning III 48 is flexibly connected.
The cylindrical axial plane of friction 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
Rubbing surface is carried all in 26 cambered surface II 42, to realize the transmission of mutual speed and power.
Claims (1)
1. a kind of light-duty double dynamical aero-vehicle bearing deceleration device, it is characterised in that by motor I (1), shaft coupling I (2), input
Axle 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), shaft 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 disk (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 by shaft coupling I (2) and input shaft I
(3) affixed, input shaft I (3) is flexibly connected with the hole IV (33) of shell (4) from right-to-left by bearing IV (d), and catch I (5)
Centre bore be flexibly connected, be flexibly connected with the centre bore of deceleration frame I (6) by bearing III (c), and friction inner ring II (28)
Centre bore it is affixed；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) size shape of cambered surface II (42) matches；Hollow rollers I (7), 4 identicals solid roller I (29a), hollow rollings
Post IV (27) and another 4 identicals solid roller I (29a) order are arranged, and are placed in outer ring and the reductor of friction inner ring II (28)
Between the circular shaft face II (38) of frame I (6), and the circular shaft face II (38) of the outer ring with friction inner ring II (28) and deceleration frame I (6)
Roll connection；The axle III (45) of planet carrier I (9) is affixed with the right side of the central through hole of belt wheel I (10), the axle I of planet carrier I (9)
(43) it is flexibly connected with the centre bore of hollow rollers IV (27), the center of the axle of planet carrier I (9) II (44) and hollow rollers I (7)
Hole is flexibly connected；The output shaft of motor II (18) is affixed with input shaft II (15) by shaft coupling II (17), input shaft II
(15) be flexibly connected with the hole VII (36) of shell (4) by bearing I (a) from left to right, and the centre bore of catch II (16) it is movable
Connect, be flexibly connected with the centre bore of deceleration frame II (13) by bearing II (b), and the centre bore of friction inner ring I (19) it is solid
Connect；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)
The size shape of cambered surface VI (51) match；Hollow rollers II (12), 4 identicals solid roller II (29b), hollow rollers
III (20) and another 4 identicals solid roller II (29b) order arrange, be placed in friction inner ring I (19) outer ring and deceleration frame
Between II (13) circular shaft face IV (47), and the circular shaft face IV of the outer ring with friction inner ring I (19) and deceleration frame II (13)
(47) roll connection；The axle VI (54) of planet carrier II (11) is affixed with the left side of the central through hole of belt wheel I (10), planet carrier II
(11) axle IV (52) is flexibly connected with the centre bore of hollow rollers III (20), axle V (53) and the hollow rolling of planet carrier II (11)
The centre bore of post II (12) is flexibly connected；Belt wheel I (10) is flexibly connected with belt wheel II (23) by belt (22)；Belt wheel II (23)
Centre bore and axle (24) it is inner affixed, axle (24) outer end is affixed with the centre bore of wing disk (25)；IV (33) side of hole of shell (4)
It is internal affixed with catch I (5), it is affixed with catch II (16) inside VII (36) side of hole of shell (4), the hole I (30) of shell (4) and
The flexible connection of protruding end VI (50) of bearing shell III (21), the hole III (32) of shell (4) and the protruding end II (41) of bearing shell IV (26)
Be flexibly connected, 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) and
The protruding end III (48) of bearing shell II (14) is flexibly connected.
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 |
|---|---|
| CN104896049A CN104896049A (en) | 2015-09-09 |
| CN104896049B true CN104896049B (en) | 2017-03-22 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510275379.1A Expired - Fee Related CN104896049B (en) | 2015-05-26 | 2015-05-26 | Mini-type dual-power aircraft bearing speed reduction device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104896049B (en) |
Families Citing this family (2)
| 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 |
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| CN103195804A (en) * | 2012-01-09 | 2013-07-10 | 常州东风轴承有限公司 | Planetary rolling bearing |
| CN104085535A (en) * | 2014-07-18 | 2014-10-08 | 吉林大学 | Double-power-output aircraft |
| CN204677718U (en) * | 2015-05-26 | 2015-09-30 | 吉林大学 | Micro-scale double-power aero-vehicle bearing speed reducer |
-
2015
- 2015-05-26 CN CN201510275379.1A patent/CN104896049B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2869018A1 (en) * | 2004-04-16 | 2005-10-21 | Selim Derbent | Motorization system for e.g. ultra light motorized aircraft, has engine mounted on aircraft via vibration damper units, and transmission assembly connected to shaft of engine by flexible coupling |
| CN101520083A (en) * | 2008-02-28 | 2009-09-02 | 尤洛考普特公司 | Power transmission gearbox presenting a modifiable speed of rotation at outlet thereof, and a corresponding method of operation |
| CN103097243A (en) * | 2010-08-16 | 2013-05-08 | 泰克诺卡德项目股份公司 | A propulsion and motion-transmission assembly, in particular for a rotary-wing aircraft |
| CN103195804A (en) * | 2012-01-09 | 2013-07-10 | 常州东风轴承有限公司 | Planetary rolling bearing |
| CN104085535A (en) * | 2014-07-18 | 2014-10-08 | 吉林大学 | Double-power-output aircraft |
| CN204677718U (en) * | 2015-05-26 | 2015-09-30 | 吉林大学 | Micro-scale double-power aero-vehicle bearing speed reducer |
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| Publication number | Publication date |
|---|---|
| CN104896049A (en) | 2015-09-09 |
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