CN112855883B - Continuous rotation-to-reciprocating rotation mechanism for vibrating aircraft - Google Patents
Continuous rotation-to-reciprocating rotation mechanism for vibrating aircraft Download PDFInfo
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- CN112855883B CN112855883B CN202110078827.4A CN202110078827A CN112855883B CN 112855883 B CN112855883 B CN 112855883B CN 202110078827 A CN202110078827 A CN 202110078827A CN 112855883 B CN112855883 B CN 112855883B
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- 230000001360 synchronised effect Effects 0.000 claims description 3
- 238000009434 installation Methods 0.000 claims description 2
- 230000005540 biological transmission Effects 0.000 abstract description 2
- 230000000149 penetrating effect Effects 0.000 description 7
- 238000005096 rolling process Methods 0.000 description 5
- 230000009286 beneficial effect Effects 0.000 description 1
- 125000004122 cyclic group Chemical group 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
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- 230000004048 modification Effects 0.000 description 1
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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
- F16H19/00—Gearings comprising essentially only toothed gears or friction members and not capable of conveying indefinitely-continuing rotary motion
- F16H19/02—Gearings comprising essentially only toothed gears or friction members and not capable of conveying indefinitely-continuing rotary motion for interconverting rotary or oscillating motion and reciprocating motion
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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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- 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
- F16H57/00—General details of gearing
- F16H57/02—Gearboxes; Mounting gearing therein
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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
- F16H57/00—General details of gearing
- F16H57/02—Gearboxes; Mounting gearing therein
- F16H57/021—Shaft support structures, e.g. partition walls, bearing eyes, casing walls or covers with bearings
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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
- F16H57/00—General details of gearing
- F16H57/02—Gearboxes; Mounting gearing therein
- F16H57/023—Mounting or installation of gears or shafts in the gearboxes, e.g. methods or means for assembly
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Retarders (AREA)
- Transmission Devices (AREA)
Abstract
The invention relates to a continuous rotation-rotation reciprocating rotation mechanism for a vibrating aircraft, wherein a clockwise rotation inner gear ring is arranged on the upper end surface of a lower fixed support flange and is provided with a first support bearing between a convex ring on the upper end surface of the lower fixed support flange, the upper end surface of the side wall of the clockwise rotation inner gear ring is detachably connected with the lower end surface of a swing output shell, the upper end surface of the swing output shell is detachably connected with the lower end surface of the side wall of an anticlockwise rotation inner gear ring, and a second support bearing is arranged between the anticlockwise rotation inner gear ring and a convex ring on the lower end surface of an upper fixed support flange. The advantages are that: the continuous high-speed rotation can be converted into 120-degree reciprocating rotation, the rotational inertia is small, the speed fluctuation is small, and the device can be used for vibrating an aircraft or other devices needing the transmission.
Description
Technical Field
The invention relates to a continuous rotation-to-reciprocating rotation mechanism for a vibrating aircraft.
Background
The reciprocating mechanism comprises two gears, a rolling body and a guide device, wherein the tooth profile curve of the two gears is a smooth curve, the rolling body is positioned between the tooth surfaces of the two gears and is in clearance fit or interference fit with the tooth surfaces of the two gears, the center of the rolling body and the centers of the two gears are positioned on the same straight line L, the guide device is connected with the rolling body, and the guide direction of the guide device is consistent with the reciprocating direction of the rolling body. The disadvantages are that: the structure is complex, the inertia is large, and the speed fluctuation is large.
Disclosure of Invention
The invention aims to solve the defects in the prior art and provides a continuous rotation-rotation reciprocating rotation mechanism for a vibrating aircraft.
In order to achieve the purpose, the invention adopts the following technical scheme: a continuous rotation-rotation reciprocating rotation mechanism for a vibrating aircraft comprises an upper fixed support flange, a lower fixed support flange, a fixed flange connecting column, an input shaft, a reversing shaft, a first incomplete gear, a second incomplete gear, a reversing gear, a swinging output shell, a clockwise rotation inner gear ring and an anticlockwise rotation inner gear ring, wherein the clockwise rotation inner gear ring is arranged on the upper end face of the lower fixed support flange and is provided with a first support bearing between a convex ring on the upper end face of the lower fixed support flange, the upper end face of the side wall of the clockwise rotation inner gear ring is detachably connected with the lower end face of the swinging output shell, the upper end face of the swinging output shell is detachably connected with the lower end face of the side wall of the anticlockwise rotation inner gear ring, the anticlockwise rotation inner gear ring is arranged on the lower end face of the upper fixed support flange and is provided with a second support bearing between the convex ring on the lower end face of the upper fixed support flange, a connecting shaft, a shaft, a mounting cavity is formed between the lower fixed supporting flange, the swing output shell, the clockwise rotating inner gear ring and the anticlockwise rotating inner gear ring, the upper fixed supporting flange and the lower fixed supporting flange are fixedly connected at the outer side of the swing output shell through a fixed flange connecting column, one end of an input shaft penetrates through the lower fixed supporting flange, a first incomplete gear is arranged in the cavity corresponding to the clockwise rotating inner gear ring, the first incomplete gear penetrates through the center of a circle from one end of the input shaft and is fixedly connected, and the tooth side of the first incomplete gear is meshed with teeth on the inner side of the corresponding clockwise rotating inner gear ring; two meshed reversing gears are arranged in the cavity corresponding to the position of the swing output shell, the circle center of one reversing gear is fixedly connected with one end of the input shaft, the circle center of the other reversing gear is fixedly connected with one end of the reversing shaft, a second incomplete gear is arranged in the cavity corresponding to the position of the anticlockwise rotating inner gear ring, incomplete teeth of the second step penetrate through one end of the reversing shaft at the circle center and are fixedly connected, the second incomplete gear is provided with teeth, the teeth sides can be meshed with teeth on the inner side of the corresponding anticlockwise rotating inner gear ring, and the teeth sides of the first incomplete gear and the teeth sides of the second incomplete gear are meshed with the corresponding teeth in a staggered mode.
Furthermore, the other end of the reversing shaft is inserted into the upper fixed supporting flange, and a reversing shaft supporting bearing is arranged between the other end of the reversing shaft and the upper fixed supporting flange; an input shaft supporting bearing is arranged between the input shaft and the lower fixed supporting flange.
Furthermore, a first rotating shaft supporting plate is covered at the position, corresponding to the lower end face of the swing output shell, in the cavity, and a supporting plate supporting bearing is arranged between the first rotating shaft supporting plate and the inner wall of the swing output shell; a second rotating shaft supporting plate is covered at the position, corresponding to the upper end face of the swing output shell, in the cavity, a supporting plate supporting bearing is arranged between the second rotating shaft supporting plate and the inner wall of the swing output shell, one end of the input shaft penetrates through the first rotating shaft supporting plate and is inserted into the second rotating shaft supporting plate, a first bearing is arranged between one end of the input shaft and the first rotating shaft supporting plate, and a second bearing is arranged between one end of the input shaft and the second rotating shaft supporting plate; one end of the reversing shaft penetrates through the second rotating shaft supporting plate and is inserted into the first rotating shaft supporting plate, a third bearing is arranged between one end of the reversing shaft and the second rotating shaft supporting plate, and a fourth bearing is arranged between one end of the reversing shaft and the first rotating shaft supporting plate.
Furthermore, the input shaft is arranged between the input shaft support bearing and the first incomplete gear, the positioning shaft sleeve is sleeved on the outer side of the input shaft between the first incomplete gear and the first bearing, the positioning shaft sleeve is sleeved on the outer side of the input shaft between the first bearing and the reversing gear, and the positioning shaft sleeve is sleeved on the outer side of the input shaft between the reversing gear and the second bearing.
Furthermore, a positioning shaft sleeve is sleeved on the outer side of the reversing shaft between the reversing shaft supporting bearing and the second incomplete gear, a positioning shaft sleeve is sleeved on the outer side of the input shaft between the second incomplete gear and the third bearing, a positioning shaft sleeve is sleeved on the outer side of the input shaft between the third bearing and the reversing gear, and a positioning shaft sleeve is sleeved on the outer side of the input shaft between the reversing gear and the fourth bearing.
Further, a gap is formed between the upper fixed supporting flange and the upper end face of the anticlockwise rotating inner gear ring; a gap is arranged between the lower fixed supporting flange and the lower end face of the clockwise rotating inner gear ring.
Furthermore, teeth are arranged on the side wall of the second incomplete gear, and the teeth are 120 degrees; the side wall of the first incomplete gear is provided with teeth, and the teeth are 120 degrees; the tooth positions of the teeth on the side wall of the second incomplete gear and the teeth on the side wall of the first incomplete gear are synchronized.
Furthermore, two bulges arranged on the input shaft are correspondingly matched with the grooves on the central hole of the reversing gear and the first incomplete gear, and two bulges arranged on the reversing shaft are correspondingly matched with the grooves on the central hole of the reversing gear and the second incomplete gear.
The invention has the beneficial effects that: the continuous high-speed rotation can be converted into 120-degree reciprocating rotation, the rotational inertia is small, the speed fluctuation is small, and the device can be used for vibrating an aircraft or other devices needing the transmission.
Drawings
Fig. 1 is a schematic structural view of the present invention.
Fig. 2 is a cross-sectional view of the present invention.
Fig. 3 is a relative position structure diagram of the second incomplete gear and the first incomplete gear.
1 is an upper fixed supporting flange, 2 is a lower fixed supporting flange, 3 is a fixed flange connecting column, 4 is an input shaft, 5 is a reversing shaft, 6 is a first incomplete gear, 7 is a second incomplete gear, 8 is a reversing gear, 9 is a swinging output shell, 10 is a clockwise rotating inner gear ring, 11 is a counterclockwise rotating inner gear ring, 12 is a gap, 13 is a first connecting seat, 14 is a second connecting seat, 15 is teeth, 16 is a first supporting bearing, 17 is a second supporting bearing, 18 is an input shaft supporting bearing, 19 is a reversing shaft supporting bearing, 20 is a first rotating shaft supporting plate, 21 is a second rotating shaft supporting plate, 22 is a supporting plate supporting bearing, 23 is a first bearing, 24 is a second bearing, 25 is a third bearing, 26 is a fourth bearing, and 27 is a positioning shaft sleeve.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to fig. 1 to 3 in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all embodiments.
Embodiment 1 referring to fig. 1-3, a continuous rotation-to-reciprocation rotation mechanism for a vibrating aircraft comprises an upper fixed support flange 1, a lower fixed support flange 2, a fixed flange connection column 3, an input shaft 4, a reversing shaft 5, a first incomplete gear 6, a second incomplete gear 7, a reversing gear 8, a swing output housing 9, a clockwise rotation ring gear 10 and a counterclockwise rotation ring gear 11, wherein the clockwise rotation ring gear 10 is arranged on the upper end surface of the lower fixed support flange and is provided with a first support bearing 16 between a convex ring on the upper end surface of the lower fixed support flange, the upper end surface of the side wall of the clockwise rotation ring gear 10 is detachably connected with the lower end surface of the swing output housing 9, the upper end surface of the swing output housing 9 is detachably connected with the lower end surface of the side wall of the counterclockwise rotation ring gear 11, the counterclockwise rotation ring gear is arranged on the lower end surface of the upper fixed support flange and is provided with a second support bearing 17 between the convex ring on the lower end surface of the upper fixed support flange, an installation cavity is formed among the upper fixed supporting flange 1, the lower fixed supporting flange 2, the swing output shell 9, the clockwise rotating inner gear ring 10 and the anticlockwise rotating inner gear ring 11, the upper fixed supporting flange and the lower fixed supporting flange are fixedly connected on the outer side of the swing output shell through a fixed flange connecting column 3, one end of the input shaft 4 penetrates through the lower fixed supporting flange 2, a first incomplete gear 6 is arranged in the cavity corresponding to the clockwise rotating inner gear ring 10, the first incomplete gear 6 penetrates through the fixed connection from one end of the input shaft at the circle center, and the tooth side of the first incomplete gear can be meshed with teeth 15 on the inner side of the corresponding clockwise rotating inner gear ring; two meshed reversing gears 8 are arranged in the cavity corresponding to the position of the swing output shell, the circle center of one reversing gear is fixedly connected with one end of the input shaft 4, the circle center of the other reversing gear is fixedly connected with one end of the reversing shaft 5, a second incomplete gear 7 is arranged in the cavity corresponding to the position of the anticlockwise rotating inner gear ring, incomplete teeth 7 of the second step penetrate through one end of the reversing shaft 5 in the circle center and are fixedly connected, the tooth side of the second incomplete gear can be meshed with teeth on the inner side of the corresponding anticlockwise rotating inner gear ring, and the tooth side of the first incomplete gear and the tooth side of the second incomplete gear are meshed with corresponding teeth in a staggered mode.
A continuous rotation-to-reciprocating rotation mechanism for a vibrating aircraft is characterized in that the other end of a reversing shaft is inserted into an upper fixed supporting flange, and a reversing shaft supporting bearing 19 is arranged between the other end of the reversing shaft and the upper fixed supporting flange; an input shaft support bearing 18 is provided between the input shaft and the lower fixed support flange.
A continuous rotation and rotation reciprocating rotation mechanism for a vibrating aircraft is characterized in that a first rotating shaft support plate 20 is covered on the lower end face, corresponding to a swing output shell, in a cavity, and a support plate support bearing 22 is arranged between the first rotating shaft support plate and the inner wall of the swing output shell; a second rotating shaft supporting plate 21 is covered at the position, corresponding to the upper end face of the swing output shell, in the cavity, a supporting plate supporting bearing 22 is arranged between the second rotating shaft supporting plate and the inner wall of the swing output shell, one end of an input shaft penetrates through the first rotating shaft supporting plate and is inserted into the second rotating shaft supporting plate, a first bearing 23 is arranged between one end of the input shaft and the first rotating shaft supporting plate, and a second bearing 24 is arranged between one end of the input shaft and the second rotating shaft supporting plate; one end of the reversing shaft penetrates through the second rotating shaft supporting plate and is inserted into the first rotating shaft supporting plate, a third bearing 25 is arranged between one end of the reversing shaft and the second rotating shaft supporting plate, and a fourth bearing 26 is arranged between one end of the reversing shaft and the first rotating shaft supporting plate.
A continuous rotation-to-reciprocating rotation mechanism for a vibrating aircraft is characterized in that a convex ring is arranged on the inner side of a swing output shell, 2 first step surfaces are formed on the convex ring in the swing output shell and the upper end surface and the lower end surface of the swing output shell, a convex ring is arranged on an input shaft, and 2 second step surfaces are formed on the convex ring on the input shaft and the two ends of the input shaft; a convex ring is arranged on the reversing shaft, 2 third step surfaces are formed at the convex ring on the reversing shaft and two ends of the reversing shaft, an upward fourth step surface is arranged on the inner wall of the input shaft penetrating hole of the first rotating shaft supporting plate and the inner wall of the reversing shaft penetrating hole, a downward fifth step surface is arranged on the inner wall of the input shaft penetrating hole of the second rotating shaft supporting plate and the inner wall of the reversing shaft penetrating hole,
the upper edge of the first rotating shaft supporting plate 20 is abutted against one first step surface, and the lower edge of the second rotating shaft supporting plate 21 is covered on the other first step surface;
a first bearing 23 is arranged between a fourth step surface and a second step surface in the input shaft penetrating hole of the first rotating shaft supporting plate 20, and a fourth bearing 26 is arranged between the fourth step surface and a third step surface in the reversing shaft penetrating hole of the first rotating shaft supporting plate 20; a second bearing 24 is arranged between the fifth step surface and the other second step surface in the hole for the input shaft of the second rotating shaft supporting plate 21 to pass through; a third bearing 25 is arranged between the fifth step surface and the other third step surface in the reversing shaft penetrating hole of the second rotating shaft supporting plate 21.
A continuous rotation and rotation reciprocating rotation mechanism for a vibrating aircraft is characterized in that a positioning shaft sleeve 27 is sleeved on the outer side of an input shaft between an input shaft supporting bearing and a first incomplete gear, the positioning shaft sleeve is sleeved on the outer side of the input shaft between the first incomplete gear and the first bearing, the positioning shaft sleeve is sleeved on the outer side of the input shaft between the first bearing and a reversing gear, and the positioning shaft sleeve is sleeved on the outer side of the input shaft between the reversing gear and a second bearing.
A continuous rotation and rotation reciprocating rotation mechanism for a vibrating aircraft is characterized in that a positioning shaft sleeve 27 is sleeved on the outer side, located between a reversing shaft supporting bearing and a second incomplete gear, of a reversing shaft 5, the positioning shaft sleeve 27 is sleeved on the outer side, located between the second incomplete gear and a third bearing, of an input shaft, the positioning shaft sleeve 27 is sleeved on the outer side, located between the third bearing and the reversing gear, of the input shaft, and the positioning shaft sleeve 27 is sleeved on the outer side, located between the reversing gear and a fourth bearing, of the input shaft.
A continuous rotation-to-reciprocating rotation mechanism for a vibrating aircraft is characterized in that a gap 12 is arranged between an upper fixed supporting flange and the upper end face of an anticlockwise rotation inner gear ring; a gap 12 is arranged between the lower fixed supporting flange and the lower end surface of the clockwise rotation inner gear ring.
A continuous rotation-to-reciprocating rotation mechanism for a vibrating aircraft is characterized in that a second connecting seat 14 is arranged between an upper fixed supporting flange 1 and the upper end face of an anticlockwise rotation inner gear ring 11; a first connecting seat 13 is arranged between the lower fixed supporting flange and the lower end surface of the clockwise rotating inner gear ring 10; a gap is formed between the upper fixed supporting flange 1 and the upper end face of the second connecting seat; a gap is formed between the lower fixed supporting flange and the lower end face of the first connecting seat; the bolt passes through the second connecting seat and the anticlockwise rotating inner gear ring to be connected to the swing output shell, and the bolt passes through the first connecting seat and the anticlockwise rotating inner gear ring to be connected to the swing output shell.
Sixth step surfaces for limiting 16 are arranged on the first connecting seat 13 and the second connecting seat 14 and are used as first supporting bearings, and 17 are used as second supporting bearings.
A continuous rotation and rotation reciprocating rotation mechanism for a vibrating aircraft is characterized in that a second connecting seat is arranged on the lower end face of an upper fixed supporting flange, and a second supporting bearing is arranged between the second connecting seat and a convex ring on the lower end face of the upper fixed supporting flange.
A continuous rotation-to-reciprocating rotation mechanism for a vibrating aircraft is characterized in that a first connecting seat is arranged on the upper end face of a lower fixed support flange, and a first support bearing is arranged between the first connecting seat and a convex ring on the upper end face of the lower fixed support flange.
A continuous rotation and reciprocating rotation mechanism for a vibrating aircraft is characterized in that teeth are arranged on the side wall of a second incomplete gear, and the teeth are 120 degrees; the side wall of the first incomplete gear is provided with teeth, and the teeth are 120 degrees; the tooth positions of the teeth on the side wall of the second incomplete gear and the teeth on the side wall of the first incomplete gear are synchronized.
A continuous rotation and rotation reciprocating rotation mechanism for a vibrating aircraft is characterized in that an input shaft is provided with two protrusions which are correspondingly matched with a groove in a central hole of a reversing gear and a groove in a central hole of a first incomplete gear, and the reversing shaft is provided with two protrusions which are correspondingly matched with a groove in the central hole of the reversing gear and a groove in the central hole of a second incomplete gear.
The utility model provides a continuous rotation changes reciprocal slewing mechanism for vibration aircraft, goes up fixed stay flange and plays the fixed action with lower fixed stay flange, conveniently is connected with motor casing, and the fixed flange spliced pole will go up fixed stay flange and fixed stay flange links together down. The input shaft continuously rotates to drive the first incomplete gear, the first incomplete gear is meshed with the clockwise rotating inner gear ring, the output of the swing output shell rotates clockwise, and when the first incomplete gear and the clockwise rotating inner gear ring are disengaged, the swing output shell rotates 120 degrees clockwise. The rotation of the input shaft enables the reversing shaft to always keep anticlockwise rotation through the reversing gear. When the first incomplete gear is disengaged from the clockwise rotating inner gear ring, the second incomplete gear is engaged with the anticlockwise rotating inner gear ring, so that the swinging output shell rotates anticlockwise and rotates 120 degrees to be disengaged. By the cyclic reciprocating, the continuous rotation of the input shaft can be converted into the reciprocating 120-degree rotation of the swinging output shell.
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art should be able to cover the technical scope of the present invention and the equivalent alternatives or modifications according to the technical solution and the inventive concept of the present invention within the technical scope of the present invention.
Claims (8)
1. The utility model provides a vibrating aircraft changes reciprocating rotation mechanism with continuous rotation, includes fixed stay flange, lower fixed stay flange, fixed flange spliced pole, input shaft, reversing shaft, first incomplete gear, the incomplete gear of second, reversing gear, swing output casing, clockwise rotation ring gear and anticlockwise rotation ring gear, its characterized in that: a first supporting bearing is arranged between the upper end face of the clockwise rotating inner gear ring arranged on the upper end face of the lower fixed supporting flange and the convex ring on the upper end face of the lower fixed supporting flange, the upper end face of the side wall of the clockwise rotating inner gear ring is detachably connected with the lower end face of the swinging output shell, the upper end face of the swinging output shell is detachably connected with the lower end face of the side wall of the anticlockwise rotating inner gear ring, a second supporting bearing is arranged between the anticlockwise rotating inner gear ring arranged on the lower end face of the upper fixed supporting flange and the convex ring on the lower end face of the upper fixed supporting flange, an installation cavity is formed between the upper fixed supporting flange, the lower fixed supporting flange, the swinging output shell, the clockwise rotating inner gear ring and the anticlockwise rotating inner gear ring, the upper fixed supporting flange and the lower fixed supporting flange are fixedly connected through a fixed flange connecting column outside the swinging output shell, one end of an input shaft penetrates through the lower fixed supporting flange, and a first incomplete gear is arranged in the cavity corresponding to the position of the clockwise rotating inner gear ring, the first incomplete gear penetrates through and is fixedly connected with one end of the input shaft at the circle center, and the tooth side of the first incomplete gear is provided with teeth which can be meshed with teeth on the inner side of the corresponding clockwise rotating inner gear ring; two meshed reversing gears are arranged in the cavity corresponding to the position of the swing output shell, the circle center of one reversing gear is fixedly connected with one end of the input shaft, the circle center of the other reversing gear is fixedly connected with one end of the reversing shaft, a second incomplete gear is arranged in the cavity corresponding to the position of the anticlockwise rotating inner gear ring, incomplete teeth of the second step penetrate through one end of the reversing shaft at the circle center and are fixedly connected, the second incomplete gear is provided with teeth, the teeth sides can be meshed with teeth on the inner side of the corresponding anticlockwise rotating inner gear ring, and the teeth sides of the first incomplete gear and the teeth sides of the second incomplete gear are meshed with the corresponding teeth in a staggered mode.
2. The continuous rotary reciprocating rotary mechanism for the vibrating aircraft according to claim 1, wherein: the other end of the reversing shaft is inserted into the upper fixed supporting flange, and a reversing shaft supporting bearing is arranged between the other end of the reversing shaft and the upper fixed supporting flange; an input shaft supporting bearing is arranged between the input shaft and the lower fixed supporting flange.
3. The continuous rotary reciprocating rotary mechanism for the vibrating aircraft according to claim 2, wherein: a first rotating shaft supporting plate is arranged in the cavity and corresponds to the lower end face of the swing output shell, and a supporting plate supporting bearing is arranged between the first rotating shaft supporting plate and the inner wall of the swing output shell; a second rotating shaft supporting plate is covered at the position, corresponding to the upper end face of the swing output shell, in the cavity, a supporting plate supporting bearing is arranged between the second rotating shaft supporting plate and the inner wall of the swing output shell, one end of the input shaft penetrates through the first rotating shaft supporting plate and is inserted into the second rotating shaft supporting plate, a first bearing is arranged between one end of the input shaft and the first rotating shaft supporting plate, and a second bearing is arranged between one end of the input shaft and the second rotating shaft supporting plate; one end of the reversing shaft penetrates through the second rotating shaft supporting plate and is inserted into the first rotating shaft supporting plate, a third bearing is arranged between one end of the reversing shaft and the second rotating shaft supporting plate, and a fourth bearing is arranged between one end of the reversing shaft and the first rotating shaft supporting plate.
4. A continuous rotary-reciprocating rotary mechanism for a vibrating aircraft according to claim 3, wherein: the input shaft is located the outside cover between input shaft support bearing and the first incomplete gear and establishes the location axle sleeve, and the input shaft is located the outside cover between first incomplete gear and the first bearing and establishes the location axle sleeve, and the input shaft is located the outside cover between first bearing and reversing gear and establishes the location axle sleeve, and the input shaft is located the outside cover between reversing gear and the second bearing and establishes the location axle sleeve.
5. The continuous rotary reciprocating rotary mechanism for the vibrating aircraft according to claim 4, wherein: the reversing shaft is arranged on the outer side between the reversing shaft supporting bearing and the second incomplete gear in a sleeved mode, the input shaft is arranged on the outer side between the second incomplete gear and the third bearing in a sleeved mode, the input shaft is arranged on the outer side between the third bearing and the reversing gear in a sleeved mode, and the input shaft is arranged on the outer side between the reversing gear and the fourth bearing in a sleeved mode.
6. The continuous rotary reciprocating rotary mechanism for the vibrating aircraft according to claim 1, wherein: a gap is arranged between the upper fixed supporting flange and the upper end surface of the anticlockwise rotating inner gear ring; a gap is arranged between the lower fixed supporting flange and the lower end face of the clockwise rotating inner gear ring.
7. The continuous rotary reciprocating rotary mechanism for the vibrating aircraft according to claim 1, wherein: the side wall of the second incomplete gear is provided with teeth, and the teeth are 120 degrees; the side wall of the first incomplete gear is provided with teeth, and the teeth are 120 degrees; the tooth positions of the teeth on the side wall of the second incomplete gear and the teeth on the side wall of the first incomplete gear are synchronized.
8. The continuous rotary reciprocating rotary mechanism for the vibrating aircraft according to claim 1, wherein: the input shaft is provided with two bulges which are correspondingly matched with the grooves on the central hole of the reversing gear and the first incomplete gear, and the reversing shaft is provided with two bulges which are correspondingly matched with the grooves on the central hole of the reversing gear and the grooves on the central hole of the second incomplete gear.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110078827.4A CN112855883B (en) | 2021-01-21 | 2021-01-21 | Continuous rotation-to-reciprocating rotation mechanism for vibrating aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110078827.4A CN112855883B (en) | 2021-01-21 | 2021-01-21 | Continuous rotation-to-reciprocating rotation mechanism for vibrating aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112855883A CN112855883A (en) | 2021-05-28 |
| CN112855883B true CN112855883B (en) | 2022-02-15 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202110078827.4A Active CN112855883B (en) | 2021-01-21 | 2021-01-21 | Continuous rotation-to-reciprocating rotation mechanism for vibrating aircraft |
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Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN118182801A (en) * | 2024-05-20 | 2024-06-14 | 西北工业大学宁波研究院 | Driving reversing device of simulated ray aircraft |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103573949B (en) * | 2013-11-04 | 2015-11-18 | 重庆大学 | A kind of reciprocating type gear box with intermittent gearing mechanism |
| DE102016216879A1 (en) * | 2016-09-06 | 2018-03-08 | Brose Fahrzeugteile Gmbh & Co. Kommanditgesellschaft, Bamberg | Drive device for a window regulator, with a contact structure on a carrier element |
| CN207278789U (en) * | 2017-10-16 | 2018-04-27 | 深圳卓创传动科技有限公司 | Helical gear planetary reducer |
| CN211737954U (en) * | 2020-04-03 | 2020-10-23 | 武义县东达电器有限公司 | Reciprocating gear box |
| CN212318671U (en) * | 2020-05-20 | 2021-01-08 | 广东万盛兴智能技术研究院有限公司 | Forward and reverse rotation output device |
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| CN112855883A (en) | 2021-05-28 |
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