CN209617516U - A kind of active pour angle compensation aircraft seat - Google Patents
A kind of active pour angle compensation aircraft seat Download PDFInfo
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- CN209617516U CN209617516U CN201920186567.0U CN201920186567U CN209617516U CN 209617516 U CN209617516 U CN 209617516U CN 201920186567 U CN201920186567 U CN 201920186567U CN 209617516 U CN209617516 U CN 209617516U
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Abstract
The utility model discloses a kind of active pour angle compensation aircraft seat, including backrest, armrest, seat cushions, middle fixed plate, bottom plate, six-degree-of-freedom parallel connection mechanism, gyroscope and 3-axis acceleration sensor, adjust motor, Arduino controller, seat cushions are connected with backrest by shaft, and armrest is mounted on backrest；The aircraft seat bottom is equipped with six-degree-of-freedom parallel connection mechanism, the features such as using the stability of six-degree-of-freedom parallel connection mechanism, flexibility, strong bearing capacity, realizes that seat in the movement of space six-freedom degree, compensates displacement in each direction and inclination angle.Gyroscope and 3-axis acceleration sensor are installed, aircraft seat angle change can be monitored in real time, synchronous generate instructs to control the movement of regulation motor after data pass to Arduino controller, to realize the angle compensation realized within a very short time to seat.
Description
Technical field
The utility model relates to Intelligent seat technical field more particularly to Active Compensation aircrafts taking off, land, turn or
Person meets with the stabilization aircraft seat at the inclination angle generated when air-flow, specifically a kind of active pour angle compensation aircraft seat.
Background technique
Currently, bourgeois emerge upgrades along with a gigantic and vigorous consumption, the comfort level experience of aviation is mentioned
Higher requirement is gone out.Prolonged journey allows passenger especially to pay close attention to the comfort level of seat simultaneously, and seat comfort degree degree becomes
A bit indispensable in high-end aviation competition.Nearest one is inclined in sex investigation about first saloon passenger, 12 heads listed
Seat comfort degree is of greatest concern in equal cabins important indicator.And when taking off, turning, land, force-land or encounter air-flow, meeting
So that the air force or torque disequilibrium of angular deflection or aircraft, flying speed, flying height or flight appearance occur for aircraft
State deflects, and since seat and cargo hold are rigidly connected, this effect can be directly passed to passenger, cause multiplying for passenger
Discomfort is sat, not only largely effects on the ride experience of passenger, or even safety problem can be generated.Another aspect various countries are for improving seat
The research of comfort level also more to be confined to improve seat material-structure, and adjusts seat stability etc. passively by damping spring
Adjust aspect, patent document " a kind of aero seat of adjustable-angle " (CN207759040U) relates to a kind of adjust angle
Aircraft seat, but also only can manually adjust seat back angle, and for the research at Active Compensation aircraft seat inclination angle at
In the state ignored by people.
Utility model content
In order to overcome the deficiencies of the prior art, the utility model provides a kind of active pour angle compensation aircraft seat.The aircraft
Seat stability is good, and high sensitivity, adjustable extent is wide, simple and compact for structure, being capable of six degree of freedom Active Compensation aircraft flight
Inclination angle.
The technical solution that the utility model solves the technical problem is to design a kind of active pour angle compensation aircraft seat
Chair, which is characterized in that including backrest, armrest, seat cushions, middle fixed plate, bottom plate, six-degree-of-freedom parallel
Structure, gyroscope and 3-axis acceleration sensor adjust motor, Arduino controller, and seat cushions pass through shaft phase with backrest
Even, armrest is mounted on backrest；
Six-degree-of-freedom parallel connection mechanism includes upper mounted plate and support rod, and the support rod is the six roots of sensation, and the end at both ends is set
It is equipped with ball socket bearing；Fixed plate is hexagonal plate, and six roots of sensation support rod with two for one group, divide by one end of three groups of support rods
Three non-conterminous sides of hexagonal plate are not connected to by the flexural pivot on hexagonal plate；Upper mounted plate passes through three fastening screws
It is fixed on seat cushions lower surface；
Middle fixed plate, the shape of bottom plate are identical, and gyroscope and 3-axis acceleration sensor are fixedly mounted on middle fixation
On plate, Arduino controller is mounted on bottom plate, and edge interval is equipped with support between middle fixed plate, bottom plate
Plate；Adjust motor be fixed between middle fixed plate and bottom plate, and its output shaft between middle fixed plate, bottom plate not
It installs at support plate；The output shaft for adjusting motor connects output crank, the other end of each output crank by spline
Equipped with flexural pivot, the support rod of six-degree-of-freedom parallel connection mechanism is connected by the flexural pivot on the ball socket bearing and output crank on its other end
It connects；Bottom plate is rigidly connected by foot lock with the cabin floor below aircraft seat；
The movement of the six-degree-of-freedom parallel connection mechanism is driven by adjusting motor；The gyroscope and 3-axis acceleration
Sensor is connect by data line with Arduino controller, and the adjusting motor is connected by electric wire and Arduino controller
It connects, Arduino controller is connected to external power supply.
Compared with prior art, the utility model beneficial effect achieved is: the aircraft seat bottom is equipped with six certainly
By degree parallel institution, the features such as using the stability of six-degree-of-freedom parallel connection mechanism, flexibility, strong bearing capacity, realize that seat exists
The movement of space six-freedom degree compensates displacement in each direction and inclination angle.Gyroscope and 3-axis acceleration sensing are installed
Aircraft seat angle change can be monitored in real time in device, and synchronous generate instructs to control and adjust after data pass to Arduino controller
The movement of motor is controlled, to realize the angle compensation realized within a very short time to seat, reduction passenger is because of aircraft angle as far as possible
Uncomfortable caused by variation, experience is seized the opportunity in raising.
Detailed description of the invention
Fig. 1 is a kind of overall structure diagram of embodiment of the utility model；
Fig. 2 is a kind of six-degree-of-freedom parallel connection mechanism structural schematic diagram of embodiment of the utility model.
Specific embodiment
The following will be combined with the drawings in the embodiments of the present invention, carries out the technical scheme in the embodiment of the utility model
Clearly and completely describe, it is clear that the described embodiments are only a part of the embodiments of the utility model, rather than whole
Embodiment.Based on the embodiments of the present invention, those of ordinary skill in the art are without making creative work
Every other embodiment obtained, will fall within the protection scope of the utility model.
The utility model provides a kind of active pour angle compensation aircraft seat (abbreviation aircraft seat, referring to Fig. 1-2), including
Backrest 1, armrest 2, seat cushions 3, middle fixed plate 5, bottom plate 6, six-degree-of-freedom parallel connection mechanism 8, gyroscope and three
Axle acceleration sensor 9 adjusts motor 10, Arduino controller 12, and seat cushions 3 are connected with backrest 1 by shaft, seat
Armrest of seat 2 is mounted on backrest 1.
Six-degree-of-freedom parallel connection mechanism 8 includes upper mounted plate 4 and support rod 81, and the support rod 81 is the six roots of sensation, both ends
End is provided with ball socket bearing 83；Fixed plate 4 be hexagonal plate, six roots of sensation support rod 81 with two be one group, three groups of branch
One end of strut 81 is connected on three non-conterminous sides of hexagonal plate by the flexural pivot 82 on hexagonal plate respectively.Upper fixation
Plate 4 is fixed on 3 lower surface of seat cushions by three fastening screws 7.
Middle fixed plate 5, the shape of bottom plate 6 are identical, gyroscope and 3-axis acceleration sensor 9 be fixedly mounted in it is solid
On fixed board 5, Arduino controller 12 is mounted on bottom plate 6, and edge interval is pacified between middle fixed plate 5, bottom plate 6
Equipped with support plate；Adjust motor 10 be fixed between middle fixed plate 5 and bottom plate 6, and its output shaft be located at middle fixed plate 5,
It is not installed at support plate between bottom plate 6；The output shaft for adjusting motor 10 connects output crank 11 by spline, each
The other end of output crank 11 is equipped with flexural pivot, and the support rod 81 of six-degree-of-freedom parallel connection mechanism 8 passes through the flexural pivot on its other end
Bearing 83 is connect with the flexural pivot on output crank 11.Bottom plate 6 passes through foot lock and the cabin floor rigidity below aircraft seat
Connection.
The movement of the six-degree-of-freedom parallel connection mechanism 8 is driven by adjusting motor 10.The gyroscope and three axis add
Velocity sensor 9 connect by data line with Arduino controller 12, the adjusting motor 10 pass through electric wire and
Arduino controller 12 connects, and Arduino controller 12 is connected to external power supply.
The model MPU6050 of the gyroscope and 3-axis acceleration sensor 9.
Fixed plate 4 is hexagonal plate, and being often separated by a side tool, there are two flexural pivots 82 to connection support bar 81.
The adjusting motor and output crank mechanism can realize the function with hydraulic drive mechanism respectively.
Utility model works principle: after the utility model aircraft seat is mounted in cabin floor, when aircraft because rising
When winged, landing, turning or experience slight airflow jolt, angle change can be generated, the gyroscope and three in middle fixed plate 5
9 certain time interval of axle acceleration sensor (such as every 10ms) monitor an angle change, i.e., by aircraft bring X, Y, Z axis
Angle variation can real-time delivery give be located at middle fixed plate 5 on gyroscope and 3-axis acceleration sensor 9, gyroscope and three
Axle acceleration sensor 9 handles data and signal is passed to the control of the Arduino on bottom plate 6 by data line
Device 12 processed, Arduino controller 12, which handles signal according to internal processes and generates order-driven, adjusts the movement of motor 10, adjusts electricity
10 output shaft of machine is directly connect with output crank 11, and output crank 11 is connect by flexural pivot with support rod 81, therefore output crank
11 will adjust the translation for being converted to support rod 81 of motor 10, and 81 upper end of support rod is by flexural pivot and is fixed on seat cushions 3
The upper mounted plate 4 of bottom connects, so that upper mounted plate 4 and seat under seat cushions 3 be driven to keep balance.
The utility model does not address place and is suitable for the prior art.
Claims (3)
1. a kind of active pour angle compensation aircraft seat, which is characterized in that including backrest, armrest, seat cushions, in it is solid
Fixed board, bottom plate, six-degree-of-freedom parallel connection mechanism, gyroscope and 3-axis acceleration sensor adjust motor, Arduino control
Device, seat cushions are connected with backrest by shaft, and armrest is mounted on backrest；
Six-degree-of-freedom parallel connection mechanism includes upper mounted plate and support rod, and the support rod is the six roots of sensation, and the end at both ends is provided with
Ball socket bearing；Fixed plate is hexagonal plate, and with two for one group, one end of three groups of support rods leads to six roots of sensation support rod respectively
The flexural pivot crossed on hexagonal plate is connected to three non-conterminous sides of hexagonal plate；Upper mounted plate is fixed by three fastening screws
On seat cushions lower surface；
Middle fixed plate, the shape of bottom plate are identical, and gyroscope and 3-axis acceleration sensor are fixedly mounted in middle fixed plate,
Arduino controller is mounted on bottom plate, and edge interval is equipped with support plate between middle fixed plate, bottom plate；It adjusts
Section motor is fixed between middle fixed plate and bottom plate, and its output shaft is not installed between middle fixed plate, bottom plate
At support plate；The output shaft for adjusting motor connects output crank by spline, and the other end of each output crank is equipped with ball
The support rod of hinge, six-degree-of-freedom parallel connection mechanism passes through the flexural pivot connection on the ball socket bearing and output crank on its other end；Under
Fixed plate is rigidly connected by foot lock with the cabin floor below aircraft seat；
The movement of the six-degree-of-freedom parallel connection mechanism is driven by adjusting motor；The gyroscope and 3-axis acceleration sensing
Device is connect by data line with Arduino controller, and the adjusting motor is connect by electric wire with Arduino controller,
Arduino controller is connected to external power supply.
2. a kind of active pour angle compensation aircraft seat according to claim 1, which is characterized in that the gyroscope and three
The model MPU6050 of axle acceleration sensor.
3. a kind of active pour angle compensation aircraft seat according to claim 1, which is characterized in that fixed plate is
Hexagonal plate, being often separated by a side tool, there are two flexural pivots to connection support bar.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920186567.0U CN209617516U (en) | 2019-02-02 | 2019-02-02 | A kind of active pour angle compensation aircraft seat |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920186567.0U CN209617516U (en) | 2019-02-02 | 2019-02-02 | A kind of active pour angle compensation aircraft seat |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209617516U true CN209617516U (en) | 2019-11-12 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920186567.0U Active CN209617516U (en) | 2019-02-02 | 2019-02-02 | A kind of active pour angle compensation aircraft seat |
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| CN (1) | CN209617516U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109677620A (en) * | 2019-02-02 | 2019-04-26 | 河北工业大学 | A kind of active pour angle compensation aircraft seat |
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2019
- 2019-02-02 CN CN201920186567.0U patent/CN209617516U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109677620A (en) * | 2019-02-02 | 2019-04-26 | 河北工业大学 | A kind of active pour angle compensation aircraft seat |
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