CN115108017A - High-bearing-capacity electric seat adjusting device for airplane - Google Patents
High-bearing-capacity electric seat adjusting device for airplane Download PDFInfo
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- CN115108017A CN115108017A CN202210776218.0A CN202210776218A CN115108017A CN 115108017 A CN115108017 A CN 115108017A CN 202210776218 A CN202210776218 A CN 202210776218A CN 115108017 A CN115108017 A CN 115108017A
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- gear
- planet carrier
- shifting
- sleeve
- shifting sleeve
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- 230000007246 mechanism Effects 0.000 claims abstract description 33
- 230000005540 biological transmission Effects 0.000 claims abstract description 18
- 230000009467 reduction Effects 0.000 claims abstract description 15
- 230000009471 action Effects 0.000 claims abstract description 10
- 230000006835 compression Effects 0.000 abstract description 2
- 238000007906 compression Methods 0.000 abstract description 2
- 238000006243 chemical reaction Methods 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
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Classifications
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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
- B64D11/00—Passenger or crew accommodation; Flight-deck installations not otherwise provided for
- B64D11/06—Arrangements of seats, or adaptations or details specially adapted for aircraft seats
- B64D11/0639—Arrangements of seats, or adaptations or details specially adapted for aircraft seats with features for adjustment or converting of seats
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Retarders (AREA)
Abstract
The invention provides an airplane high-bearing electric seat adjusting device.A driving motor is provided with an internal gear and is connected with an external gear arranged on a planetary reduction mechanism; the planetary reduction mechanism comprises a sun wheel, a plurality of uniformly distributed planet wheels, a planet carrier and an embedding hole, the planet wheels are fixedly connected with the planet carrier, and the sun wheel is matched with the planet carrier (9) through a gear; the shifting sleeve is arranged on the planet carrier, the front end of the shifting sleeve is connected with the planet carrier, and the rear end of the shifting sleeve is meshed with an external spline of the rear-stage gear; cylindrical pins with the number matched with that of the planet gears are arranged on the dial sleeve, one end of the dial sleeve can be meshed with corresponding embedded holes (18) in the end face of the planet carrier through the uniformly distributed cylindrical pins, and the other end of the dial sleeve is sequentially provided with a spring, a rear-stage gear, a transmission gear and an output gear (16), so that the driving motor works to transmit power to the output gear to move axially, and the seat adjustment is realized; the shifting sleeve compression spring is shifted to move axially, and the cylindrical pin is separated from the embedded hole in the end face of the planet carrier, so that the output gear realizes seat adjustment under the action of external force.
Description
Technical Field
The invention relates to an electric seat adjusting device for an airplane, in particular to an adjusting device with high bearing capacity.
Background
The cockpit of a domestic and foreign transport plane can not always supply power to the seats, but the positions of the seats in the cockpit need to be adjusted at any time under special conditions such as ground maintenance before and after flight, so that the electric seats need to be backed up by electric and manual adjusting functions, the seats can be adjusted and locked at any time, the double backup function of all electric seats and airbus series electric seat adjusting mechanisms in China at present is realized by using a friction clutch, and the bearing capacity is limited by friction parts, so that the seats need to be additionally locked by operating a locking device before emergency landing.
Therefore, this technique has problems in that the frictional force provides insufficient locking force, and the additional locking means is complicated to operate and has poor reliability.
Disclosure of Invention
The purpose of the invention is as follows: the invention provides the transporter electric seat adjusting device with reliable structure and simple operation in order to overcome the defects of the prior art, can solve the problem of insufficient bearing capacity of the conventional electric adjusting mechanism, and realizes seat adjustment of an airplane under the conditions of power supply and no power under various working conditions such as flight, ground maintenance, test flight, trial use and the like.
The technical scheme of the invention is as follows: an airplane high-bearing electric seat adjusting device comprises a driving motor, a planetary speed reducing mechanism, a shifting fork operating rod, a shifting sleeve, a spring, a rear-stage gear, a transmission gear, an output gear, a cylindrical pin and an embedded hole, wherein the driving motor, the planetary speed reducing mechanism, the shifting sleeve, the spring, the rear-stage gear and the transmission gear are coaxial, the transmission gear is meshed with the output gear, and the driving motor is provided with an inner gear and is connected with an outer gear arranged on the planetary speed reducing mechanism; the planetary reduction mechanism comprises a sun wheel, a plurality of uniformly distributed planet wheels, a planet carrier and an embedding hole, the planet wheels are fixedly connected with the planet carrier, and the sun wheel is matched with the planet carrier through a gear; the shifting sleeve is arranged on the planet carrier, the front end of the shifting sleeve is connected with the planet carrier, and the rear end of the shifting sleeve is meshed with an external spline of the rear-stage gear; cylindrical pins with the number matched with that of the planet gears are arranged on the dial sleeve, one end of the dial sleeve can be meshed with corresponding embedded holes in the end face of the planet carrier through the uniformly distributed cylindrical pins, and the other end of the dial sleeve is sequentially provided with a spring, a rear-stage gear, a transmission gear and an output gear, so that the driving motor works to transmit power to the output gear to move axially, and the seat adjustment is realized; the shifting sleeve compression spring is shifted to move axially, the cylindrical pin is separated from the embedded hole in the end face of the planet carrier, so that the output gear works under the action of external force, and the seat is adjusted.
In the scheme, the number of the planetary reduction mechanisms is three, the planetary gear of the first-stage planetary carrier is matched with an internal gear arranged in the driving motor, and the sun gear of the preceding-stage planetary mechanism is matched with three uniformly distributed planetary gears of the rear-stage planetary mechanism; the shifting sleeve is arranged on the last-stage planet carrier of the planetary reduction.
In the above scheme, the number of the cylindrical pins uniformly distributed at one end of the shifting sleeve is three, the number of the embedded holes in the end face of the planet carrier is three, and the cylindrical pins are connected with or separated from the embedded holes under the action of external force.
In the above scheme, the adjusting device further comprises a shifting fork operating rod and a shifting fork, the shifting fork operating rod is fixedly connected with the shifting fork, and the shifting fork is driven by the rotating shifting fork operating rod to shift the shifting sleeve.
In the above scheme, the adjusting device further comprises an end cover, a shell and a cap, wherein the end cover and the shell are matched with each other; the nut cap and the end cover are provided with screw holes and are installed on the end cover through screw connection.
In the above scheme, the shifting fork operating rod is arranged on the shell through a bearing.
In the above scheme, the inner hole of the shifting sleeve is provided with the inner spline, the rear-stage gear is provided with the outer spline, and the inner spline is meshed with the outer spline.
In the scheme, the shifting fork, the spring and the rear-stage gear are respectively connected with the end cover and the cap through the bearing.
In the above scheme, the adjusting device further comprises a half-shaft gear sleeve, and the half-shaft gear sleeve is fixed on the shell through a screw.
The invention has the advantages and beneficial effects that: the clutch mechanism adopts the pin hole matching to realize reliable locking, thereby avoiding the condition that the original locking torque depending on the mechanism can not meet the emergency landing force, and still adjusting the position of the seat under the condition of power failure. The invention has simple and compact structure, no occupation space, convenient operation, strong practicability and easy popularization and application, and can be used for other manual clutch mechanisms.
Drawings
Fig. 1 is a schematic view of the overall structure of the present invention.
Fig. 2 is a schematic view of the overall structure of the present invention.
Fig. 3 is a schematic structural view of the planet carrier of the present invention.
Fig. 4 is a schematic structural view of the power transmission device of the present invention.
Fig. 5 is an expanded view of the components of the present invention.
Fig. 6 is a schematic view of the motor drive of the present invention.
Fig. 7 is a schematic view of the manual transmission of the present invention.
The automatic transmission comprises an end cover 1, a shell 2, a shifting fork operating rod 3, a cover 4, a driving motor 5, a planetary reduction mechanism 6, a sun gear 7, a planetary gear 8, a planetary carrier 9, a shifting sleeve 10, a shifting fork 11, a spring 12, a rear gear 13, a transmission gear 14, a half shaft gear sleeve 15, an output gear 16, a cylindrical pin 17 and a tabling hole 18.
Detailed Description
The present invention will now be described in further detail with reference to the accompanying drawings.
The utility model provides an adjusting device that possesses high bearing capacity, includes end cover 1, casing 2, shift fork action bars 3, block 4, electric drive mechanism, shift fork clutch, power take-off. The end cover 1 is connected with the shell 2; the cap 4 and the end cover 1 are both provided with threaded holes and the cap 4 is arranged on the end cover 1 through screw connection; the shifting fork operating rod 3 is arranged on the shell 2; the electric transmission mechanism comprises a driving motor 5, a shifting sleeve 10 and a planetary reduction mechanism 6, wherein the planetary reduction mechanism 6 consists of three gears and respectively comprises a sun gear 7, three planetary gears 8 and a planet carrier 9 which are uniformly distributed; three planetary wheels 8 which are uniformly distributed are fixed with a planetary carrier 9, and a sun wheel 7 is matched with the planetary carrier 9 through a gear; an internal gear arranged in the driving motor 5 is matched with three planet wheels 8 of the first-stage planetary reduction mechanism 6, and a sun wheel 7 of the first-stage planetary reduction mechanism is matched with three evenly-distributed planet wheels 8 of the planetary reduction mechanism 6 of the adjacent stage; the shifting sleeve 10 is arranged on the last-stage planet carrier 9 of the planetary speed reduction, the shifting sleeve 10 is provided with three cylindrical pins 17, the three cylindrical pins 17 are uniformly distributed at one end of the shifting sleeve 10, three embedded holes 18 are formed in the end face of the planet carrier, and the three cylindrical pins 17 are connected with the three embedded holes 18; the shifting fork clutch device comprises a shifting fork 11, a spring 12 and a rear-stage gear 13; the shifting fork clutch device is connected with the end cover 1 and the cap 4 through a bearing; an inner hole of the shifting sleeve 10 is designed with an internal spline which is meshed with an external spline arranged in the rear-stage gear 13; the power output device comprises a transmission gear 14, a half shaft gear sleeve 15 and an output gear 16; the transmission gear 14 is meshed with the rear-stage gear 13; the half shaft gear sleeve 15 is fixed on the shell 2 through a screw; the power output device is connected with the end cover 1 and the shell 2 through bearings.
Working principle or action process: the device is a double-margin adjusting and locking device, and the electric and manual adjusting functions are backups of each other.
When the electric adjusting function is used for adjusting, the driving motor 5 is powered on, the shifting fork operating rod 3 is shifted, the shifting fork 11 is driven to shift the shifting sleeve 10, the front end of the shifting sleeve 10 is connected with the planet carrier 6, and the rear end of the shifting sleeve 10 is meshed with the external spline of the rear-stage gear 13 to achieve axial movement and simultaneously achieve transmission of torque. Namely, the driving motor 5 outputs power to drive the gear 16 to rotate through the conversion of the clutch mechanism, the adjustment of the height or the front and back position of the seat is realized through the conversion of the mechanical structure, and when the seat is adjusted to a proper position, the output gear 16 is braked by the driving motor 5, so that the locking of the whole device is realized.
When the manual adjusting function is used for adjustment, the driving motor 5 is powered off, the shifting fork operating rod 3 is rotated to drive the shifting fork 11 to shift the shifting sleeve 10 to compress the spring 12 to perform axial movement, the three cylindrical pins 17 are separated from the three embedded holes in the end face of the planet carrier, and in a separated state, the locking torque of the driving motor 5 can only be transmitted to the planet carrier 6 but cannot be transmitted to the rear-stage gear 13. At this time, the gear 16 can be freely rotated by an external force. When the seat is moved to a proper position, the fork operating lever 3 is released, the clutch is closed, and the seat is locked by a locking mechanism in the electric mechanism.
From this, can cut off the transmission of power or locking power through adjustment shift fork action bars 3, stir shift fork action bars 3 convertible to manual regulation function when electric regulation can't use to unclamp shift fork action bars 3 when the position is adjusted, make the clutch close, the seat locking.
When the seat is subjected to emergency landing load, the electric mechanism in the embodiment can transmit locking torque to the seat structure through gear engagement, so that the seat is ensured to be locked reliably, and the airworthiness safety requirement of the seat is met.
Claims (9)
1. The airplane high-bearing electric seat adjusting device comprises a driving motor (5), a planetary speed reducing mechanism (6), a shifting fork operating rod (3), a shifting sleeve (10), a spring (12), a rear-stage gear (13), a transmission gear (14), an output gear (16), a cylindrical pin (17) and a tabling hole (18), wherein the driving motor (5), the planetary speed reducing mechanism (6), the shifting sleeve (10), the spring (12), the rear-stage gear (13) and the transmission gear (14) are coaxial, and the transmission gear (14) is meshed with the output gear (16), and is characterized in that the driving motor (5) is provided with an internal gear which is connected with an external gear arranged on the planetary speed reducing mechanism (6); the planetary reduction mechanism (6) comprises a sun wheel (7), a plurality of uniformly distributed planet wheels (8), a planet carrier (9) and a tabling hole (18), the planet wheels (8) are fixedly connected with the planet carrier (9), and the sun wheel (7) is matched with the planet carrier (9) through a gear; the shifting sleeve (10) is arranged on the planet carrier (9), the front end of the shifting sleeve is connected with the planet carrier (6), and the rear end of the shifting sleeve is meshed with an external spline of the rear-stage gear (13); the number of the cylindrical pins (17) which is matched with the number of the planet gears (8) is arranged on the shifting sleeve (10), one end of the shifting sleeve (10) can be meshed with the corresponding embedded hole (18) on the end surface of the planet carrier (9) through the uniformly distributed cylindrical pins (17), and the other end of the shifting sleeve (10) is sequentially provided with a spring (12), a rear-stage gear (13), a transmission gear (14) and an output gear (16), so that the driving motor (5) works to transmit power to the output gear (16) to move axially, and seat adjustment is realized; the shifting sleeve (10) is shifted to compress the spring (12) to move axially, and the cylindrical pin (17) is separated from the embedded hole (18) on the end face of the planet carrier, so that the output gear (16) works under the action of external force, and the seat adjustment is realized.
2. The aircraft high-load electric seat adjusting device as claimed in claim 1, wherein the number of the planetary reduction mechanisms (6) is three, the planetary gear (8) of the first-stage planetary carrier is matched with an internal gear arranged inside the driving motor (5), and the sun gear (7) of the preceding-stage planetary mechanism is matched with three uniformly distributed planetary gears (8) of the subsequent-stage planetary mechanism; the shifting sleeve (10) is arranged on the last-stage planet carrier of the planetary reduction.
3. The aircraft high-load electric seat adjusting device as claimed in claim 1, characterized in that the number of the cylindrical pins (17) uniformly distributed at one end of the shifting sleeve (10) is three, the number of the embedding holes (18) on the end surface of the planet carrier (9) is three, and the cylindrical pins (17) are connected with or separated from the embedding holes (18) under the action of external force.
4. The aircraft high-load electric seat adjusting device according to claim 3, characterized in that the adjusting device further comprises a shifting fork operating rod (3) and a shifting fork (11), the shifting fork operating rod (3) and the shifting fork (11) are fixedly connected, and the shifting fork operating rod (3) is rotated to drive the shifting fork (11) to shift the shifting sleeve (10).
5. An aircraft high load power seat adjusting device according to claim 1, characterized in that the adjusting device further comprises an end cover (1), a shell (2) and a cap (4), wherein the end cover (1) and the shell (2) are mutually matched; the cover cap (4) and the end cover (1) are both provided with screw holes and are installed on the end cover (1) through screw connection.
6. An aircraft high load power seat adjustment device according to claim 5, characterized in that the fork operating lever (3) is mounted on the housing (2) by means of a bearing.
7. An aircraft high load-bearing power seat adjusting device according to claim 5, characterized in that the inner hole of the shifting sleeve (10) is designed with an internal spline, the rear stage gear (13) is designed with an external spline, and the internal spline is meshed with the external spline.
8. An aircraft high load electric seat adjusting device according to claim 1, characterized in that the shift fork (11), the spring (12) and the rear gear (13) are respectively connected with the end cover (1) and the cap (4) through bearings.
9. An aircraft high load power seat adjustment device according to claim 5, characterized in that the adjustment device further comprises a side gear sleeve (15), the side gear sleeve (15) being fixed to the housing (2) by means of screws.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210776218.0A CN115108017A (en) | 2022-06-29 | 2022-06-29 | High-bearing-capacity electric seat adjusting device for airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210776218.0A CN115108017A (en) | 2022-06-29 | 2022-06-29 | High-bearing-capacity electric seat adjusting device for airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115108017A true CN115108017A (en) | 2022-09-27 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210776218.0A Pending CN115108017A (en) | 2022-06-29 | 2022-06-29 | High-bearing-capacity electric seat adjusting device for airplane |
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| Country | Link |
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| CN (1) | CN115108017A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103359287A (en) * | 2013-07-05 | 2013-10-23 | 哈尔滨东安发动机（集团）有限公司 | Airplane electric seat horizontally adjusting device |
| EP2765079A1 (en) * | 2013-02-07 | 2014-08-13 | Zodiac Actuation Systems | Cabin seat for aircraft |
| US20180194250A1 (en) * | 2017-01-12 | 2018-07-12 | Toyota Boshoku Kabushiki Kaisha | Power transmission device for power seat |
| CN112224421A (en) * | 2020-10-14 | 2021-01-15 | 航宇救生装备有限公司 | Manual clutch device for pilot seat |
| CN215884081U (en) * | 2021-09-16 | 2022-02-22 | 河南华中星科技电子有限公司 | Aviation seat adjusting mechanism with electric and manual adjusting functions |
| CN217864768U (en) * | 2022-06-29 | 2022-11-22 | 航宇救生装备有限公司 | High-bearing-capacity electric seat adjusting device for airplane |
-
2022
- 2022-06-29 CN CN202210776218.0A patent/CN115108017A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2765079A1 (en) * | 2013-02-07 | 2014-08-13 | Zodiac Actuation Systems | Cabin seat for aircraft |
| CN103359287A (en) * | 2013-07-05 | 2013-10-23 | 哈尔滨东安发动机（集团）有限公司 | Airplane electric seat horizontally adjusting device |
| US20180194250A1 (en) * | 2017-01-12 | 2018-07-12 | Toyota Boshoku Kabushiki Kaisha | Power transmission device for power seat |
| CN112224421A (en) * | 2020-10-14 | 2021-01-15 | 航宇救生装备有限公司 | Manual clutch device for pilot seat |
| CN215884081U (en) * | 2021-09-16 | 2022-02-22 | 河南华中星科技电子有限公司 | Aviation seat adjusting mechanism with electric and manual adjusting functions |
| CN217864768U (en) * | 2022-06-29 | 2022-11-22 | 航宇救生装备有限公司 | High-bearing-capacity electric seat adjusting device for airplane |
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