CN110886815A - Gear transmission steering device of aircraft landing gear - Google Patents
Gear transmission steering device of aircraft landing gear Download PDFInfo
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- CN110886815A CN110886815A CN201911045947.3A CN201911045947A CN110886815A CN 110886815 A CN110886815 A CN 110886815A CN 201911045947 A CN201911045947 A CN 201911045947A CN 110886815 A CN110886815 A CN 110886815A
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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
- F16H1/00—Toothed gearings for conveying rotary motion
- F16H1/28—Toothed gearings for conveying rotary motion with gears having orbital motion
- F16H1/32—Toothed gearings for conveying rotary motion with gears having orbital motion in which the central axis of the gearing lies inside the periphery of an orbital gear
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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
- F16H1/00—Toothed gearings for conveying rotary motion
- F16H1/28—Toothed gearings for conveying rotary motion with gears having orbital motion
- F16H1/46—Systems consisting of a plurality of gear trains each with orbital gears, i.e. systems having three or more central gears
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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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- General Engineering & Computer Science (AREA)
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Abstract
The invention discloses an aircraft landing gear transmission steering device, and aims to provide an aircraft nose landing gear steering device which is compact in structure, light in weight and capable of converting high-rotating-speed and small-torque power source into low-rotating-speed and large-torque power source. The technical scheme adopted for achieving the purpose of the invention is that the planetary gear set comprises a power source, a shell, a first-stage planetary gear train, a second-stage planetary gear train and an output parallel shaft fixed-axis gear train. The transmission mechanism of the device is driven by an external power source, and the rotating speed is initially reduced through a first-stage planetary gear train; the rotation speed is further reduced through a second-stage planetary gear train; and finally, the output parallel shaft pinion is meshed with a parallel shaft bull gear on an undercarriage support to be converted into rotary motion with low rotating speed and high torque, so that the steering action of the nose undercarriage of the aviation aircraft is realized.
Description
Technical Field
The invention relates to an aircraft accessory device.
Background
At present, when the aerocraft turns on the ground, the aerocraft is turned by the steering structure of the nose landing gear under the guidance action of the nose landing gear.
In the past, the aircraft is steered by changing the thrust difference of an engine, but the control is not easy; the method for steering the aircraft by adopting a braking mode is only suitable for a rear three-point aircraft and a light aircraft; the steering mechanism driven by the actuating cylinder has a relatively complex structure, is troublesome to operate and occupies a large space. The existing steering mechanism of the unmanned aerial vehicle is designed for the unmanned aerial vehicle with relatively light weight, but cannot reduce speed and increase torque.
Therefore, there is a need to develop a new device that is easy to control, simple to operate and capable of steering the nose landing gear leg of a heavy aircraft.
Disclosure of Invention
The invention aims to provide an aircraft nose landing gear steering device which is compact in structure, light in weight and capable of converting high-rotating-speed small torque of a power source into low-rotating-speed large torque.
The technical scheme adopted for achieving the purpose of the invention is that the gear transmission steering device of the aircraft landing gear comprises a power source, a shell, a first-stage planetary gear train, a second-stage planetary gear train and an output parallel shaft fixed axle gear train.
The power source is positioned right above the shell, a first-stage planetary gear train and a second-stage planetary gear train are arranged inside the shell, and the first-stage planetary gear train is positioned above the second-stage planetary gear train.
The first-stage planetary gear train comprises a sun gear shaft I, an inner gear ring I, a planet gear I, a needle bearing I without an inner ring and an outer ring and a planet carrier I.
Be provided with internal spline I on the output shaft of power supply, be provided with on sun gear shaft I with I assorted external spline I of internal spline, the output shaft of power supply stretches into the casing, the output shaft of power supply and sun gear shaft I carry out accordant connection through internal spline I and external spline I.
The sun gear I is assembled on the sun gear shaft I and is respectively meshed with the three planet gears I, the three planet gears I are all meshed with the inner gear ring I, and the inner gear ring I is fixed on the inner wall of the shell.
Each planet wheel I is assembled on a corresponding planet wheel shaft I through a needle bearing I without an inner ring and an outer ring, and each planet wheel shaft I is fixed on the planet carrier I.
The second-stage planetary gear train comprises a sun gear shaft II, a planet carrier II, an inner gear ring II, a planet gear II and a needle bearing II without an inner ring and an outer ring.
The sun gear shaft II is connected to the lower surface of the planet carrier I, and a sun gear II is assembled on the sun gear shaft II. The sun gear II is respectively meshed with the four planet gears II, the four planet gears II are all meshed with the inner gear ring II, and the inner gear ring II is fixed on the inner wall of the shell.
Each planet wheel II is assembled on a corresponding planet wheel shaft II through a needle bearing II without an inner ring and an outer ring, and each planet wheel shaft II is fixed on the planet carrier II.
The lower end of the planet carrier II is used as an output shaft of the second-stage planetary gear train, the lower end of the planet carrier II is provided with a stepped shaft, and the stepped shaft is sequentially provided with a first shaft section, a second shaft section and a third shaft section from top to bottom. The first shaft section is sleeved with an angular contact ball bearing, and the first shaft section is clamped and fixed with the shell through the angular contact ball bearing. The second shaft section is provided with an external spline II, and a needle bearing without an inner ring is arranged between the third shaft section and the shell.
The output parallel shaft fixed-axis wheel system comprises a parallel shaft gear wheel and an output parallel shaft pinion arranged in the shell, an inner spline II matched with the outer spline II is arranged on the output parallel shaft pinion, and the output parallel shaft pinion and the second shaft section are connected in a matched mode through the inner spline II and the outer spline II.
The side wall of the shell at the height of the output parallel shaft pinion is provided with a meshing port, a parallel shaft bull gear positioned outside the shell is meshed with the output parallel shaft pinion at the meshing port, and the parallel shaft bull gear is installed on an aircraft landing gear support.
The outer surface of the shell is fixed in the aircraft landing gear through a connecting earring.
Further, install thrust ball bearing I between the lower terminal surface of sun gear shaft I and planet carrier I, install thrust ball bearing II between the lower terminal surface of sun gear shaft II and the planet carrier II, all only contain the ball in thrust ball bearing I and the thrust ball bearing II.
Furthermore, the upper end and the lower end of the needle bearing I without the inner ring and the outer ring are both sleeved with a planet wheel gasket I, and the upper end and the lower end of the needle bearing II without the inner ring and the outer ring are both sleeved with a planet wheel gasket II.
Further, a gear washer is sleeved on the outer surface of the upper end of the needle roller bearing without the inner ring, the upper plate surface of the gear washer is tightly abutted to the lower plate surface of the output parallel shaft pinion, and the lower plate surface of the gear washer is tightly abutted to the shell.
Furthermore, the inside of the sun gear shaft II is hollow, and the lower end of the planet carrier II is a stepped shaft with the hollow inside.
Furthermore, the upper end and the lower end of the planet wheel shaft I are open and hollow, and the upper end of each planet wheel shaft I is provided with a hole stopper I. The upper end and the lower end of the planetary wheel shaft II are open and hollow, and the upper end of each planetary wheel shaft II is provided with a hole stopper II.
Further, the first shaft section at the lower end of the planet carrier II is sleeved with a lip-shaped oil seal, the upper end of the lip-shaped oil seal is tightly abutted to the angular contact ball bearing, and the lower end and the outer side wall of the lip-shaped oil seal are tightly abutted to the shell.
The invention has the beneficial effects that:
1. the device adopts an integrated structure at multiple positions, the whole shell is a component, the planet carrier of the first-stage planetary gear train and the sun gear of the second-stage planetary gear train are made into an integrated structure, and the output end part of the planet carrier of the second-stage planetary gear train is made into a hollow stepped shaft, so that the complexity of the structure is greatly simplified;
2. the device has compact structure, small volume and light weight; the whole transmission device does not contain connecting pieces such as bolts and the like, and simultaneously removes the inner ring and the outer ring of a needle bearing at the position of a planet wheel shaft of the two-stage planetary gear train and the inner ring of the needle bearing at the position of a pinion of the parallel shaft ordinary gear train, so that the quality of the whole transmission device is reduced;
3. the manufacturing cost is low, standardization can be realized, and the transmission efficiency is high; the gears of the two-stage planetary gear train and the parallel shaft gear train of the transmission device are involute cylindrical gears, so that the transmission device is easy to manufacture and can be standardized, and the whole transmission efficiency is high.
Drawings
FIG. 1 is a partial cross-sectional view of the device of the present invention;
FIG. 2 is a general cross-sectional view of the apparatus of the present invention;
FIG. 3 is a sectional view taken along line A-A;
FIG. 4 is a sectional view taken along line B-B;
figure 5 is a diagram of the position of the inventive device in relation to the nose landing gear of an aircraft.
In the figure: the device comprises a power source 1, a sun gear shaft I2, a planet carrier I3, a thrust ball bearing I4, an inner gear ring I5, a shell 6, a connecting lug ring 601, an inner gear ring II 7, a thrust ball bearing II 8, a planet carrier II 9, an angular contact ball bearing 10, a lip oil seal 11, an output parallel shaft pinion 12, a gear washer 13, an inner ring-free needle bearing 14, a hole baffle I15, a planet gear shaft I16, a planet gear washer I17, an inner ring-free needle bearing I18, a planet gear I19, a hole baffle II 20, a planet gear washer II 21, a planet gear shaft II 22, an inner ring-free needle bearing II 23, a planet gear II 24, a parallel shaft big gear 25, a sun gear I26, a sun gear shaft II 27 and a sun.
Detailed Description
The present invention is further illustrated by the following examples, but it should not be construed that the scope of the above-described subject matter is limited to the following examples. Various substitutions and alterations can be made without departing from the technical idea of the invention and the scope of the invention is covered by the present invention according to the common technical knowledge and the conventional means in the field.
Example 1:
the embodiment discloses an aircraft landing gear transmission steering device which comprises a power source 1, a shell 6, a first-stage planetary gear train, a second-stage planetary gear train and an output parallel shaft fixed-axis gear train. Referring to fig. 5, a diagram of the position of the device of the present invention in relation to the nose landing gear of an aircraft is shown, with a dotted box, illustrating a geared steering arrangement for the landing gear of an aircraft.
Referring to fig. 1, the power source 1 is located right above the casing 6, a first-stage planetary gear train and a second-stage planetary gear train are arranged inside the casing 6, and the first-stage planetary gear train is located above the second-stage planetary gear train.
The first-stage planetary gear train comprises a sun gear shaft I2, an inner gear ring I5, a planet gear I19, a needle bearing I18 without an inner ring and an outer ring and a planet carrier I3.
Be provided with internal spline I on the output shaft of power supply 1, be provided with on sun gear shaft I2 with I assorted external spline I of internal spline, the output shaft of power supply 1 stretches into casing 6, and power supply 1's output shaft and sun gear shaft I2 carry out accordant connection through internal spline I and external spline I. The rigidity and the strength of the internal spline I and the external spline I can bear the movement load force generated by acceleration, vibration and impact.
Referring to fig. 1 or 3, a sun gear I26 is assembled on the sun gear shaft I2, the sun gear I26 is respectively meshed with three planet gears I19, the three planet gears I19 are all meshed with an inner gear ring I5, and the inner gear ring I5 is fixed on the inner wall of the shell 6.
Each planet wheel I19 is assembled on the corresponding planet wheel shaft I16 through a needle bearing I18 without an inner ring and an outer ring, and a planet wheel gasket I17 is sleeved at the upper end and the lower end of the needle bearing I18 without the inner ring and the outer ring.
The upper end and the lower end of the planetary wheel shaft I16 are open and hollow, the upper end of each planetary wheel shaft I16 is provided with a hole stopper I15, and each planetary wheel shaft I16 is fixed on the planet carrier I3.
Install thrust ball bearing I4 between the lower terminal surface of sun gear shaft I2 and planet carrier I3, only contain the ball in the thrust ball bearing I4.
Referring to fig. 1, the second-stage planetary gear train comprises a sun gear shaft II 27, a planet carrier II 9, an inner gear ring II 7, a planet gear II 24 and a needle bearing II 23 without an inner ring and an outer ring.
The inner part of the sun gear shaft II 27 is hollow, the sun gear shaft II 27 is connected to the lower surface of the planet carrier I3, and a sun gear II 28 is assembled on the sun gear shaft II 27. The sun gear II 28 is respectively meshed with the four planet gears II 24, the four planet gears II 24 are respectively meshed with the inner gear ring II 7, and the inner gear ring II 7 is fixed on the inner wall of the shell 6.
Each planet gear II 24 is assembled on the corresponding planet gear shaft II 22 through a needle bearing II 23 without an inner ring and an outer ring, and a planet gear gasket II 21 is sleeved at the upper end and the lower end of each needle bearing II 23 without the inner ring and the outer ring.
The upper end and the lower end of the second planetary gear shaft 22 are open and hollow, the upper end of each second planetary gear shaft 22 is provided with a hole stopper II 20, and each second planetary gear shaft 22 is fixed on the second planetary gear carrier 9.
And a thrust ball bearing II 8 is arranged between the lower end face of the sun gear shaft II 27 and the planet carrier II 9, and the thrust ball bearing II 8 only contains balls.
The lower end of the planet carrier II 9 is used as an output shaft of the second-stage planetary gear train, the lower end of the planet carrier II 9 is a stepped shaft with a hollow interior, and the stepped shaft is sequentially provided with a first shaft section, a second shaft section and a third shaft section from top to bottom.
The first shaft section is sleeved with an angular contact ball bearing 10, and the first shaft section is clamped and fixed with the shell 6 through the angular contact ball bearing 10. The first shaft section is sleeved with a lip-shaped oil seal 11, the upper end of the lip-shaped oil seal 11 is tightly abutted to the angular contact ball bearing 10, and the lower end and the outer side wall of the first shaft section are tightly abutted to the shell 6.
The second shaft section is provided with an external spline II, and a needle bearing 14 without an inner ring is arranged between the third shaft section and the shell 6.
The outer surface of the upper end of the needle bearing 14 without the inner ring is sleeved with a gear washer 13, the upper plate surface of the gear washer 13 is tightly abutted with the lower plate surface of the output parallel shaft pinion 12, and the lower plate surface of the gear washer 13 is tightly abutted with the shell 6. The gear washer 13 prevents friction between the end face of the output parallel shaft pinion 12 and the housing 6.
The output parallel shaft ordinary gear train comprises a parallel shaft big gear 25 and an output parallel shaft small gear 12 arranged in the shell 6, an internal spline II matched with the external spline II is arranged on the output parallel shaft small gear 12, and the output parallel shaft small gear 12 and the second shaft section are connected in a matched mode through the internal spline II and the external spline II. And the rigidity and the strength of the inner spline II and the outer spline II can bear the motion load force generated by acceleration, vibration and impact.
Referring to fig. 2 or 4, the side wall of the housing 6 at the height of the output parallel axis pinion 12 is provided with an engaging opening, a parallel axis gearwheel 25 positioned outside the housing 6 is engaged with the output parallel axis pinion 12 at the engaging opening, and the parallel axis gearwheel 25 is mounted on a landing gear support of an aircraft.
When the planetary gear set works, the output shaft of the power source 1 drives the sun gear shaft I2 to rotate at a high rotating speed and a low torque, the sun gear I26 on the sun gear shaft I2 drives the three planet gears I19 to rotate around the planet gear shaft I16, and the three planet gears I19 revolve in the internal gear ring I5, so that the planet carrier I3 is driven to rotate; the sun gear shaft II 27 rotates automatically as the sun gear shaft II 27 is connected with the planet carrier I3; the sun gear shaft II 27 drives the sun gear II 28 to rotate, the sun gear II 28 drives the four planet gears II 24 to rotate around the planet gear shaft II 22, and the four planet gears II 24 revolve around the internal gear ring II 7, so that the planet carrier II 9 is driven to rotate; the second shaft section at the lower end of the planet carrier II 9 drives the output parallel shaft pinion 12 to rotate, the output parallel shaft pinion 12 drives the parallel shaft gearwheel 25, the parallel shaft gearwheel 25 performs low-rotation-speed high-torque rotary motion, and the parallel shaft gearwheel 25 drives the nose landing gear strut to steer so as to guide an aviation aircraft on the ground.
Example 2:
the embodiment discloses an aircraft landing gear transmission steering device which comprises a power source 1, a shell 6, a first-stage planetary gear train, a second-stage planetary gear train and an output parallel shaft fixed-axis gear train.
Referring to fig. 1, the power source 1 is located right above the casing 6, a first-stage planetary gear train and a second-stage planetary gear train are arranged inside the casing 6, and the first-stage planetary gear train is located above the second-stage planetary gear train.
The first-stage planetary gear train comprises a sun gear shaft I2, an inner gear ring I5, a planet gear I19, a needle bearing I18 without an inner ring and an outer ring and a planet carrier I3.
Be provided with internal spline I on the output shaft of power supply 1, be provided with on sun gear shaft I2 with I assorted external spline I of internal spline, the output shaft of power supply 1 stretches into casing 6, and power supply 1's output shaft and sun gear shaft I2 carry out accordant connection through internal spline I and external spline I.
Referring to fig. 3, a sun gear i 26 is assembled on the sun gear shaft i 2, the sun gear i 26 is respectively engaged with three planet gears i 19, the three planet gears i 19 are all engaged with an inner gear ring i 5, and the inner gear ring i 5 is fixed on the inner wall of the shell 6.
Each planet wheel I19 is assembled on the corresponding planet wheel shaft I16 through a needle bearing I18 without an inner ring and an outer ring, and each planet wheel shaft I16 is fixed on the planet carrier I3.
The second-stage planetary gear train comprises a sun gear shaft II 27, a planet carrier II 9, an inner gear ring II 7, a planet gear II 24 and a needle bearing II 23 without an inner ring and an outer ring.
The sun gear shaft II 27 is connected to the lower surface of the planet carrier I3, and a sun gear II 28 is assembled on the sun gear shaft II 27. The sun gear II 28 is respectively meshed with the four planet gears II 24, the four planet gears II 24 are respectively meshed with the inner gear ring II 7, and the inner gear ring II 7 is fixed on the inner wall of the shell 6.
Each planetary gear II 24 is assembled on the corresponding planetary gear shaft II 22 through a needle bearing II 23 without an inner ring and an outer ring, and each planetary gear shaft II 22 is fixed on the planetary carrier II 9.
The lower end of the planet carrier II 9 is used as an output shaft of the second-stage planetary gear train, the lower end of the planet carrier II 9 is provided with a stepped shaft, and the stepped shaft is sequentially provided with a first shaft section, a second shaft section and a third shaft section from top to bottom. The first shaft section is sleeved with an angular contact ball bearing 10, and the first shaft section is clamped and fixed with the shell 6 through the angular contact ball bearing 10. The second shaft section is provided with an external spline II, and a needle bearing 14 without an inner ring is arranged between the third shaft section and the shell 6.
The output parallel shaft ordinary gear train comprises a parallel shaft big gear 25 and an output parallel shaft small gear 12 arranged in the shell 6, an internal spline II matched with the external spline II is arranged on the output parallel shaft small gear 12, and the output parallel shaft small gear 12 and the second shaft section are connected in a matched mode through the internal spline II and the external spline II.
Referring to fig. 2 or 4, the side wall of the housing 6 at the height of the output parallel axis pinion 12 is provided with an engaging opening, a parallel axis gearwheel 25 positioned outside the housing 6 is engaged with the output parallel axis pinion 12 at the engaging opening, and the parallel axis gearwheel 25 is mounted on a landing gear support of an aircraft.
The outer surface of the housing 6 is fixed in the aircraft landing gear by means of a connecting ear 601.
Example 3:
the main structure of this embodiment is the same as that of embodiment 2, and further, referring to fig. 1, a thrust ball bearing i 4 is installed between the lower end surface of the sun gear shaft i 2 and the planet carrier i 3, a thrust ball bearing ii 8 is installed between the lower end surface of the sun gear shaft ii 27 and the planet carrier ii 9, and both the thrust ball bearing i 4 and the thrust ball bearing ii 8 only contain balls.
Example 4:
the main structure of this embodiment is the same as that of embodiment 3, and further, referring to fig. 1, the upper and lower ends of the needle bearing i 18 without the inner and outer rings are all sleeved with a planet wheel gasket i 17, and the upper and lower ends of the needle bearing ii 23 without the inner and outer rings are all sleeved with a planet wheel gasket ii 21.
Example 5:
the main structure of this embodiment is the same as that of embodiment 4, and further, referring to fig. 1, a gear washer 13 is sleeved on the outer surface of the upper end of the needle roller bearing 14 without the inner ring, an upper plate surface of the gear washer 13 abuts against a lower plate surface of the output parallel shaft pinion 12, and a lower plate surface of the gear washer 13 abuts against the housing 6.
Example 6:
the main structure of this embodiment is the same as that of embodiment 5, and further, referring to fig. 1, the sun gear shaft ii 27 is hollow inside, and the lower end of the planet carrier ii 9 is a stepped shaft hollow inside.
Example 7:
the main structure of this embodiment is the same as that of embodiment 6, and further, referring to fig. 1, the upper end and the lower end of the planetary shaft i 16 are open and hollow, and the upper end of each planetary shaft i 16 is provided with a hole stopper i 15. The upper end and the lower end of the planetary gear shaft II 22 are open and hollow, and the upper end of each planetary gear shaft II 22 is provided with a hole stopper II 20.
Example 8:
in this embodiment, the main structure is the same as that of embodiment 7, further, referring to fig. 1, a lip-shaped oil seal 11 is sleeved on the first shaft section at the lower end of the planet carrier ii 9, the upper end of the lip-shaped oil seal 11 abuts against the angular contact ball bearing 10, and the lower end and the outer side wall both abut against the housing 6.
Claims (7)
1. An aircraft landing gear geared steering arrangement, characterized by: the device comprises a power source (1), a shell (6), a first-stage planetary gear train, a second-stage planetary gear train and an output parallel shaft fixed-axis gear train;
the power source (1) is positioned right above the shell (6), a first-stage planetary gear train and a second-stage planetary gear train are arranged inside the shell (6), and the first-stage planetary gear train is positioned above the second-stage planetary gear train;
the first-stage planetary gear train comprises a sun gear shaft I (2), an inner gear ring I (5), a planet gear I (19), a needle roller bearing I (18) without an inner ring and an outer ring and a planet carrier I (3);
an inner spline I is arranged on an output shaft of the power source (1), an outer spline I matched with the inner spline I is arranged on the sun gear shaft I (2), the output shaft of the power source (1) extends into the shell (6), and the output shaft of the power source (1) and the sun gear shaft I (2) are connected in a matched mode through the inner spline I and the outer spline I;
the sun gear shaft I (2) is provided with a sun gear I (26), the sun gear I (26) is respectively meshed with three planet gears I (19), the three planet gears I (19) are all meshed with an inner gear ring I (5), and the inner gear ring I (5) is fixed on the inner wall of the shell (6);
each planet wheel I (19) is assembled on a corresponding planet wheel shaft I (16) through a needle bearing I (18) without an inner ring and an outer ring, and each planet wheel shaft I (16) is fixed on the planet carrier I (3);
the second-stage planetary gear train comprises a sun gear shaft II (27), a planet carrier II (9), an inner gear ring II (7), a planet gear II (24) and a needle bearing II (23) without an inner ring and an outer ring;
the sun gear shaft II (27) is connected to the lower surface of the planet carrier I (3), and a sun gear II (28) is assembled on the sun gear shaft II (27); the sun gear II (28) is respectively meshed with the four planet gears II (24), the four planet gears II (24) are respectively meshed with the inner gear ring II (7), and the inner gear ring II (7) is fixed on the inner wall of the shell (6);
each planet wheel II (24) is assembled on the corresponding planet wheel shaft II (22) through a needle bearing II (23) without an inner ring and an outer ring, and each planet wheel shaft II (22) is fixed on the planet carrier II (9);
the lower end of the planet carrier II (9) is used as an output shaft of the second-stage planetary gear train, the lower end of the planet carrier II (9) is provided with a stepped shaft, and the stepped shaft is sequentially provided with a first shaft section, a second shaft section and a third shaft section from top to bottom; the first shaft section is sleeved with an angular contact ball bearing (10), and the first shaft section is clamped and fixed with the shell (6) through the angular contact ball bearing (10); the second shaft section is provided with an external spline II, and a needle bearing (14) without an inner ring is arranged between the third shaft section and the shell (6);
the output parallel shaft fixed-axis gear train comprises a parallel shaft big gear (25) and an output parallel shaft small gear (12) arranged in the shell (6), an internal spline II matched with the external spline II is arranged on the output parallel shaft small gear (12), and the output parallel shaft small gear (12) and the second shaft section are in matched connection through the internal spline II and the external spline II;
a meshing opening is formed in the side wall of the shell (6) at the height of the output parallel shaft pinion (12), a parallel shaft gearwheel (25) positioned outside the shell (6) is meshed with the output parallel shaft pinion (12) at the meshing opening, and the parallel shaft gearwheel (25) is installed on an aircraft landing gear support;
the outer surface of the shell (6) is fixed in the landing gear of the aviation aircraft through a connecting earring (601).
2. An aircraft landing gear geared steering arrangement according to claim 1, wherein: install thrust ball bearing I (4) between the lower terminal surface of sun gear shaft I (2) and planet carrier I (3), install thrust ball bearing II (8) between the lower terminal surface of sun gear shaft II (27) and planet carrier II (9), all only contain the ball in thrust ball bearing I (4) and thrust ball bearing II (8).
3. An aircraft landing gear geared steering arrangement according to claim 1, wherein: the upper end and the lower end of the needle bearing I (18) without the inner ring and the outer ring are both sleeved with a planet wheel gasket I (17), and the upper end and the lower end of the needle bearing II (23) without the inner ring and the outer ring are both sleeved with a planet wheel gasket II (21).
4. An aircraft landing gear geared steering arrangement according to claim 1, wherein: the outer surface of the upper end of the needle bearing (14) without the inner ring is sleeved with a gear washer (13), the upper plate surface of the gear washer (13) is tightly abutted with the lower plate surface of the output parallel shaft pinion (12), and the lower plate surface of the gear washer (13) is tightly abutted with the shell (6).
5. An aircraft landing gear geared steering arrangement according to claim 1, wherein: the inner part of the sun gear shaft II (27) is hollow, and the lower end of the planet carrier II (9) is a stepped shaft with the hollow inner part.
6. An aircraft landing gear geared steering arrangement according to claim 1, wherein: the upper end and the lower end of the planet wheel shaft I (16) are open and hollow, and the upper end of each planet wheel shaft I (16) is provided with a hole stopper I (15); the upper end and the lower end of the planetary gear shaft II (22) are open and hollow, and the upper end of each planetary gear shaft II (22) is provided with a hole stopper II (20).
7. An aircraft landing gear geared steering arrangement according to claim 1, wherein: the first shaft section of planet carrier II (9) lower extreme goes up the cover and is equipped with lip oil blanket (11), and the upper end and the angular contact ball bearing (10) of lip oil blanket (11) support tightly, and lower extreme and lateral wall all support tightly with casing (6).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911045947.3A CN110886815B (en) | 2019-10-30 | 2019-10-30 | Gear transmission steering device of aircraft landing gear |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911045947.3A CN110886815B (en) | 2019-10-30 | 2019-10-30 | Gear transmission steering device of aircraft landing gear |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110886815A true CN110886815A (en) | 2020-03-17 |
| CN110886815B CN110886815B (en) | 2021-12-28 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911045947.3A Active CN110886815B (en) | 2019-10-30 | 2019-10-30 | Gear transmission steering device of aircraft landing gear |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116384014A (en) * | 2023-06-05 | 2023-07-04 | 中国空气动力研究与发展中心空天技术研究所 | Design method and mechanism of single-rotor adjacent blade reverse constant-speed rotation transmission mechanism |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101665154A (en) * | 2008-05-02 | 2010-03-10 | 通用电气英国航空公司 | Aircraft landing gear steering system |
| FR2951697B1 (en) * | 2009-10-23 | 2012-04-20 | Messier Dowty Sa | DEVICE FOR MANEUVERING AN AIRCRAFT INTERFERENCE |
| CN102791575A (en) * | 2009-12-17 | 2012-11-21 | 米其林集团总公司 | System for electric motorisation of a wheel |
| CN106458319A (en) * | 2014-06-30 | 2017-02-22 | 米其林集团总公司 | Wheel drive system, in particular for an aircraft |
| CN106660631A (en) * | 2014-06-30 | 2017-05-10 | 米其林集团总公司 | Wheel drive system, in particular for aircraft |
| CN110386247A (en) * | 2018-04-18 | 2019-10-29 | 赛峰起落架系统公司 | With the aircraft landing gear that can turn to bottom and the turning facilities simplified |
-
2019
- 2019-10-30 CN CN201911045947.3A patent/CN110886815B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101665154A (en) * | 2008-05-02 | 2010-03-10 | 通用电气英国航空公司 | Aircraft landing gear steering system |
| FR2951697B1 (en) * | 2009-10-23 | 2012-04-20 | Messier Dowty Sa | DEVICE FOR MANEUVERING AN AIRCRAFT INTERFERENCE |
| CN102791575A (en) * | 2009-12-17 | 2012-11-21 | 米其林集团总公司 | System for electric motorisation of a wheel |
| CN106458319A (en) * | 2014-06-30 | 2017-02-22 | 米其林集团总公司 | Wheel drive system, in particular for an aircraft |
| CN106660631A (en) * | 2014-06-30 | 2017-05-10 | 米其林集团总公司 | Wheel drive system, in particular for aircraft |
| CN110386247A (en) * | 2018-04-18 | 2019-10-29 | 赛峰起落架系统公司 | With the aircraft landing gear that can turn to bottom and the turning facilities simplified |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116384014A (en) * | 2023-06-05 | 2023-07-04 | 中国空气动力研究与发展中心空天技术研究所 | Design method and mechanism of single-rotor adjacent blade reverse constant-speed rotation transmission mechanism |
| CN116384014B (en) * | 2023-06-05 | 2023-08-18 | 中国空气动力研究与发展中心空天技术研究所 | Design method and mechanism of single-rotor adjacent blade reverse constant-speed rotation transmission mechanism |
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|---|---|
| CN110886815B (en) | 2021-12-28 |
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