CN204322958U - The vehicle seat of electronic land and air double-used aircraft - Google Patents
The vehicle seat of electronic land and air double-used aircraft Download PDFInfo
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- CN204322958U CN204322958U CN201420783857.0U CN201420783857U CN204322958U CN 204322958 U CN204322958 U CN 204322958U CN 201420783857 U CN201420783857 U CN 201420783857U CN 204322958 U CN204322958 U CN 204322958U
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Abstract
The utility model discloses a kind of vehicle seat of electronic land and air double-used aircraft, described vehicle seat comprises the left and right handrail being arranged at both sides, left handrail is provided with flying speed controller, right handrail is provided with heading controller.Vehicle seat of the present utility model is provided with flying speed controller and heading controller on handrail, and user can control the flight of electronic land and air double-used aircraft easily on vehicle seat.
Description
The divisional application that the application is the applying date is on November 29th, 2014, application number is 201420740729.8, name is called the patent application of electronic land and air double-used aircraft.
Technical field
The utility model relates to a kind of vehicle, particularly relates to a kind of vehicle seat of electronic land and air double-used aircraft can travelling on road surface and can depart from ground flying.
Background technology
Along with social economy's development, be no matter the traffic construction of city and country, or mountain area or Plain network of highways are built, great development has been had to improve, but, have more cities and towns and urban residents to purchase automobile, to facilitate the trip of oneself because living standard improves.But the blocking up of current road still becomes the problem that increasing city is difficult to avoid, even if having automobile, trip also may not conceptive such convenience.In addition, along with the increase of automobile quantity, the pollution of air is more and more serious, creates adverse influence to the life of people.
Just as described above, traffic congestion has been some places particularly metropolitan traffic normalities, brings inconvenience to daily life.So alleviating traffic congestion is one of important topic faced at present.
Therefore, be necessary to provide one on the way to run quickly, the vehicle that can aloft fly again.
Utility model content
The technical problems to be solved in the utility model is to provide a kind of land and air double-used electric vehicle.
For solving the problems of the technologies described above, the utility model provides following technical scheme: a kind of vehicle seat of electronic land and air double-used aircraft, described vehicle seat comprises the left and right handrail being arranged at both sides, left handrail is provided with flying speed controller, right handrail is provided with heading controller.
In one embodiment, described flying speed controller is a mobilizable handle.
In one embodiment, described heading controller is a mobilizable handle.
The utility model also provides following technical scheme: a kind of vehicle seat of electronic land and air double-used aircraft, and described vehicle seat comprises the left and right handrail being arranged at both sides, right handrail is provided with flying speed controller, left handrail is provided with heading controller.
In one embodiment, described flying speed controller is a mobilizable handle.
In one embodiment, described heading controller is a mobilizable handle.
Vehicle seat of the present utility model is provided with flying speed controller and heading controller on handrail, and user can control the flight of electronic land and air double-used aircraft easily on vehicle seat.
Accompanying drawing explanation
Accompanying drawing of the present utility model is to further illustrate the utility model, but not the restriction to utility model scope.
Fig. 1 is the schematic perspective view of the electronic land and air double-used aircraft of the utility model, and wherein left and right two support arms are in the state of propping up.
Fig. 2 is the schematic perspective view of the electronic land and air double-used aircraft of the utility model, and wherein left and right two support arms are in collapse state.
Fig. 3 is the cross-sectional schematic that the electronic land and air double-used aircraft of the utility model drives wheel.
Fig. 4 is the schematic diagram of the electronic land and air double-used aircraft flight control system of the utility model.
Fig. 5 is the support installing portion of another embodiment of the electronic land and air double-used aircraft of the utility model and the assembling schematic diagram of support arm.
Fig. 6 is the folded position schematic diagram of a kind of embodiment of stirrup, and wherein stirrup is not amounted to completely.
Fig. 7 is the schematic diagram of the straight configuration of stirrup shown in Fig. 6, and its middle sleeve does not screw in connection first bar portion and the second bar portion completely.
Fig. 8 is the folded position schematic diagram of the another kind of embodiment of stirrup, and wherein stirrup is not amounted to completely.
Fig. 9 is the schematic diagram of the straight configuration of stirrup shown in Fig. 8.
Detailed description of the invention
Embodiment of the present utility model is to explain explanation further to the utility model, but not to utility model scope restriction of the present utility model.
Embodiment one
Refer to shown in Fig. 1 and Fig. 2, electronic land and air double-used aircraft of the present utility model comprises car body 100, the support 200 be arranged on car body 100, be arranged at four screws 300 on support 200 and provide power supply 400 and the control system of electric power for car body 100 and screw 300.In the present embodiment, the quantity of described screw 300 is four, but screw of the present utility model 300 is not restricted to four, and also can be the quantity such as six, eight, ten, 12, concrete quantity can set as required.
Described car body 100 comprises vehicle frame 101, be installed on three wheels below vehicle frame 101 and be positioned at the handle portion 102 of vehicle frame 101 front portion.In the present embodiment, the quantity of described wheel is three, namely car body is three-wheel vehicle, but the quantity of wheel of the present utility model is not restricted to three, in other embodiments, the quantity of wheel also can be the quantity such as two, four, five, six, and concrete quantity can set as required.Can be all the driving wheel that drive motor is set in described wheel, also can partly for being provided with the driving wheel of drive motor.In the present embodiment, two in described three wheels for being provided with the driving wheel 103 of drive motor, another is non-driven wheel and driven wheel 104.This two drivings wheel 103 is installed on the rear portion of car body 100, and another driven wheel 104 is installed on the front portion of car body, and three wheels are that triangle is installed on car body.Car body 100 is provided with pedal 1001 in the top of driven wheel 104, puts pin for user.
In addition, described three wheels also can be arranged like this, and the driving wheel count being provided with drive motor in three wheels is one, and this driving wheel is installed on the front portion of car body, another two non-driven wheels are installed on the rear portion of car body, and three wheels are that triangle is installed on car body.Described three wheels can also be arranged like this, one of them in three wheels is installed on Vehicular body front, another two are installed on rear vehicle, three wheels are that triangle is installed on car body, two wheels being installed on rear portion are driven as drive motor by same reducing motor, thus as described driving wheel, installing fore wheel is driven wheel.
In the present embodiment, described drive motor is wheel hub motor, refers to shown in Fig. 3, and each drives wheel 103 all can rotate around the wheel shaft 105 of wheel with the wheel hub motor 700 on this wheel.Described wheel hub motor 700 comprises the electric machine support 701 that can be fixedly connected on wheel shaft 105 and the motor steel ring 702 that can rotate relative to electric machine support 701.Described electric machine support 701 is provided with silicon steel circle 703, and this silicon steel circle 703 circumferentially offers some evenly distributed winding bore, and these winding bore are used for copper cash around the home, and silicon steel circle 703 forms the stator of wheel hub motor 700 around the home after copper cash.Described silicon steel circle 703 is set in the periphery of electric machine support 701 and is fixedly connected with electric machine support 701.Motor steel ring 702 inner ring arranges the rotor that some magnet forms wheel hub motor 700.Drive wheel 103 to comprise a wheel hub 1031, the material of this wheel hub 1031 is aluminum alloys that density is lighter.This wheel hub 1031 is that integrally to water finishing work with motor steel ring 702 shaping, namely the motor steel ring 702 of blank is placed in mould, then the aluminum alloy of liquid of casting forms wheel hub and the motor steel ring of integrated blank, forms the integrated wheel hub 1031 and the motor steel ring 702 that meet mounting condition after machine up.So motor steel ring 702 can drive wheel hub 1031 to rotate.Drive wheel 103 also to comprise the hub cap 1032 being installed on both sides, this hub cap 1032 is fixedly connected on motor steel ring 702 by the fastener such as screw or stud, and hub cap 1032 is rotatably mounted on wheel shaft 105 by bearing.Motor steel ring 702 and wheel hub 1031 realize rotating around wheel shaft 105 by hub cap 1032.Described wheel hub motor 700, electric machine support 701, wheel hub 1031, hub cap 1032 and the tire be installed on outside wheel hub 1031 form described driving wheel 103.In the present embodiment, wheel hub 1031 adopts aluminum alloy material can alleviate the weight of wheel.Motor steel ring 702 is one-body molded with wheel hub 1031, does not need other parts both to be fixed together, can save cost.
Described driven wheel 104 does not need motor to drive, and is therefore common wheel.Driven wheel, owing to not arranging drive motor, is conducive to reducing costs.
In other embodiments, described drive motor also can be reducing motor.
The handle portion 102 of described car body 100 front portion connects with the same driven wheel 104 being positioned at car body 100 front portion, makes handle portion 102 can drive driven wheel 104 left and right turn.Described handle portion 102 is mounted with read out instrument 800, this read out instrument 800 for showing the running state of land and air double-used aircraft, such as running velocity, battery electric quantity, flying height etc.In other embodiments, read out instrument 800 also can be installed on other convenient positions observed of car body.
Car body 100 also comprises vehicle seat 106, and these vehicle seat 106 both sides are respectively arranged with left and right handrail 1061,1062, left and right handrail are separately installed with flying speed controller 1063, heading controller 1064.Flying speed controller 1063, heading controller 1064 can intermodulation in the position of left and right handrail, to meet the use habit of user.
In the present embodiment, described power supply 400 is lithium cell, and is installed on the below of vehicle seat 106, because battery weight is comparatively large, is arranged on the center of gravity being conducive to adjusting whole land and air double-used aircraft below vehicle seat 106.
Described support 200 comprises and the support portion 201 that car body 100 is fixedly connected with and the installation portion 202 vertical with support portion 201.Installation portion 202 is provided with the support arm 203 equal with screw 300 quantity, and described support arm 203 is uniformly distributed along installation portion 202 surrounding.In the present embodiment, described installation portion 202 is the framework that a cylinder surrounds, and installation portion 202 is in quadrangle.Described support arm 203 is four, and each support arm 203 is connected on four limits of quadrangle, and the angle often between adjacent two support arms 203 is 90 degree, and four support arms 203 extend towards the four direction all around of car body 100 respectively.Wherein, two support arms 203 extended in left-right direction are rotatably mounted in respectively on installation portion 202, to make about this two support arms 203 can rotate propping up between state and collapse state.Particularly, left and right two support arm 203 is connected on installation portion 202 respectively by a folding, i.e. one page of folding is fixedly connected with support arm 203, and another page is fixedly connected with installation portion 202.When collapse state, left and right two support arm 203 is in vertical state substantially, decreases the space that left and right directions takies, and facilitates land and air double-used aircraft to enter the less space of volume, such as private garage; When propping up state, left and right two support arm 203 and front and rear support arm 203 are in same plane, ensure the normal flight of land and air double-used aircraft.
Support 200 comprises two stirrups 204 that can amount to further, and this two stirrup 204 is installed between left and right support arm 203 and support portion 201 respectively, and the two ends of each stirrup 204 are connected rotationally with support portion 201 and support arm respectively.When left and right two support arm 203 be in prop up state time, two stirrups 204 stretch respectively support left and right two support arm 203, two stirrups forms triangle polyester fibre state with left and right two support arm and support portion respectively, make about two support arm stable position.When left and right two support arm 203 is in collapse state, two stirrups are amounted to.
Described screw 300 is installed on the end of each support arm 203 respectively.Wherein each screw 203 comprises screw propeller motor 301 and is installed on the screw propeller 302 on screw propeller motor 301.Described screw propeller 302 is spatially upper and lower orientation with screw propeller motor 301, and namely screw propeller 302 is arranged on the top of screw propeller motor 301.The beneficial effect of setting like this produces heat when being screw propeller motor 301 energising rotation, and promote air flows down when screw propeller 302 rotates, the air constantly flowed is conducive to the heat radiation of screw propeller motor 301.Described screw 300 is installed on support arm 203 by an aluminum alloy frame, because aluminum alloy has good heat conductivility, so aluminum alloy frame further enhancing the permeability of heat of screw.
Described control system comprises ground control system and flight control system, and the drive motor of wheel is controlled by ground control system, and screw propeller motor is controlled by flight control system.
Described ground control system comprises terrestrial information receiver module, terrestrial information processing module and terrestrial information sending module, terrestrial information receiver module comprises wheel velocity modulator 1021, wheel velocity modulator 1021 receives speed-regulating signal and is sent to terrestrial information processing module, be sent to drive motor through terrestrial information sending module after terrestrial information processing module calculation process, control wheel velocity.Described wheel velocity modulator 1021 is installed on the end of handle portion 102, and this wheel velocity modulator 1021 is rotated by opposite handle portion 102 thus control signal is sent to terrestrial information processing module.Such as, rotation amplitude is larger, and the speed controlling wheel is larger.Electronic land and air double-used aircraft direction on the ground controls front vehicle wheel by handle portion 102 and driven wheel 104 controls, and handle portion 102 is left-handed, and land and air double-used aircraft turns left, handle portion 102 dextrorotation, and land and air double-used aircraft is turned right.
Described terrestrial information receiver module comprises wheel attitude receptor, and wheel attitude receptor receives wheel attitude signal and is sent to terrestrial information processing module, is sent to read out instrument 800 after the computing of terrestrial information processing module through terrestrial information sending module.
Described flight control system comprises flight information receiver module, flight information processing module and flight information sending module, flight information receiver module comprises flying speed controller 1063 and heading controller 1064, flying speed controller 1063, heading controller 1064 receive flying speed respectively and heading control signal is sent to flight information processing module, be sent to screw propeller motor through flight information sending module after the computing of flight information processing module, control flying speed and heading.In the present embodiment, described flying speed controller 1063 rotates to car body front, and flying speed is accelerated, and rotate to car body rear, flying speed slows down; Heading controller 1064 turns left, and land and air double-used aircraft flies left, turning clockwise, and land and air double-used aircraft flies to the right.
More specifically, control system controls the state of flights such as the acceleration of electronic land and air double-used aircraft when state of flight, deceleration, left-hand rotation, right-hand rotation in the following manner and controls self-equalizing by self-balancing system.But be casehistory with under type, be not limited to this kind of mode.
Refer to shown in Fig. 4, when receiving flight Acceleration Signal, flight control system accelerates the signal rotated to the screw propeller motor being positioned at land and air double-used aircraft rear portion, the screw propeller motor at rear portion accelerates with the lift promoting electronic land and air double-used aircraft rear portion, electronic land and air double-used aircraft turns forward and realizes accelerating, now the center of gravity of land and air double-used aircraft turns forward, gyro sensor in flight information receiver module is experienced signal that this center of gravity turns forward and the signal that this center of gravity turns forward is sent to flight information processing module, control signal is produced after flight information processing module calculation process, this control signal sends to the screw propeller motor being positioned at Vehicular body front through flight information sending module, increase the rotating speed of this screw propeller motor, promote the lift of electronic land and air double-used aircraft front portion, reduce the inclination forward of electronic land and air double-used aircraft, thus make land and air double-used aircraft automatically keep balance.
When receiving flight restriction signal, flight control system accelerates the signal rotated to the screw propeller motor being positioned at electronic land and air double-used aircraft front portion, anterior screw propeller motor accelerates the lift promoting electronic land and air double-used aircraft front portion, electronic land and air double-used aircraft tilts backwards and realizes slowing down, now the center of gravity of electronic land and air double-used aircraft tilts backwards, gyro sensor in flight information receiver module is experienced the sweptback signal of this center of gravity and sweptback for this center of gravity signal is sent to flight information processing module, control signal is produced after flight information processing module calculation process, this control signal sends through the screw propeller motor of flight information sending module to electronic land and air double-used aircraft rear portion, increase the rotating speed of the screw propeller motor at this rear portion, promote the lift at electronic land and air double-used aircraft rear portion, reduce the inclination backward of electronic land and air double-used aircraft, thus make land and air double-used aircraft automatically keep balance.When needs are a significant slowdown flight, flight control system accelerates the signal rotated to the screw propeller motor being positioned at electronic land and air double-used aircraft front portion, and simultaneously to the signal of screw propeller decelerating through motor being positioned at rear portion, so can make the inclination that electronic land and air double-used aircraft is relatively large backward, thus the flying speed that realization reduces forward quickly, this deceleration time is sharply very short, so the time that electronic land and air double-used aircraft tilts is also very short, restore balance under the effect of gyro sensor signal subsequently.
When receiving left rotaring signal, flight control system is to being positioned at a land and air double-used aircraft left side, the screw propeller decelerating through motor in front, electronic land and air double-used aircraft is tilted to left front, realize electronic land and air double-used aircraft, now the center of gravity of electronic land and air double-used aircraft tilts to left front, gyro sensor in flight information receiver module experience this center of gravity left top rake signal and the signal of this center of gravity top rake is left sent to flight information processing module, control signal is produced after flight information processing module calculation process, this control signal is through the right side of flight information sending module to electronic land and air double-used aircraft, the screw propeller motor at rear portion sends, reduce this right side, the rotating speed of aft propeller motor, reduce the lift in the right back portion of electronic land and air double-used aircraft thus reduce to the inclination of left front, land and air double-used aircraft is finally made automatically to keep balance.In addition, turn left and can also realize like this, when receiving left rotaring signal, flight control system is to being positioned at the land and air double-used aircraft right side, the screw propeller motor at rear accelerates, electronic land and air double-used aircraft is tilted to left front, realize electronic land and air double-used aircraft, now the center of gravity of electronic land and air double-used aircraft tilts to left front, gyro sensor in flight information receiver module experience this center of gravity left top rake signal and the signal of this center of gravity top rake is left sent to flight information processing module, control signal is produced after flight information processing module calculation process, this control signal is through the left side of flight information sending module to electronic land and air double-used aircraft, anterior screw propeller motor sends, increase this left side, the rotating speed of front propeller motor, promote the lift in the left front portion of electronic land and air double-used aircraft thus reduce to the inclination of left front, land and air double-used aircraft is finally made automatically to keep balance.
When receiving right turn signal, flight control system is right to being positioned at electronic land and air double-used aircraft, the screw propeller decelerating through motor in front, electronic land and air double-used aircraft is tilted to right front, realize land and air double-used aircraft to turn right, now the center of gravity of land and air double-used aircraft tilts to right front, gyro sensor in flight information receiver module is experienced this center of gravity to the signal of right anterior oblique and this center of gravity is sent to flight information processing module to the signal of right anterior oblique, control signal is produced after flight information processing module calculation process, this control signal is through the left side of flight information sending module to electronic land and air double-used aircraft, the screw propeller motor at rear sends, reduce left, the rotating speed of rear screw propeller motor, thus reduce the inclination of electronic land and air double-used aircraft to right front, land and air double-used aircraft is finally made automatically to keep balance.In addition, turn right and can also realize like this, when receiving right turn signal, flight control system is left to being positioned at electronic land and air double-used aircraft, the screw propeller motor at rear accelerates, electronic land and air double-used aircraft is tilted to right front, realize land and air double-used aircraft to turn right, now the center of gravity of electronic land and air double-used aircraft tilts to right front, gyro sensor in flight information receiver module is experienced this center of gravity to the signal of right anterior oblique and this center of gravity is sent to flight information processing module to the signal of right anterior oblique, control signal is produced after flight information processing module calculation process, this control signal is through the right side of flight information sending module to electronic land and air double-used aircraft, the screw propeller motor in front sends, increase right, the rotating speed of front screw propeller motor, thus reduce the inclination of electronic land and air double-used aircraft to right front, land and air double-used aircraft is finally made automatically to keep balance.
Described flight information receiver module comprises flight attitude receptor, and flight attitude receptor receives flight attitude signal and is sent to flight information processing module, is sent to read out instrument 800 after the computing of flight information processing module through flight information sending module.
Described terrestrial information processing module and flight information processing module can be arranged on same circuit card, also can be arranged on different circuit cards respectively.Further, described terrestrial information processing module and flight information processing module can be same message processing module modules, when land and air double-used aircraft travels on the ground, this message processing module resume module terrestrial information, when land and air double-used aircraft switches to state of flight, this this message processing module resume module flight information.
Electronic land and air double-used aircraft of the present utility model, on road that is smooth or that do not block up, can use as land vehicle, and controls its operation by ground control system.When the muddy frustration in road surface or when blocking up, as flight tool, can be controlled by flight control system, screw is rotated, electronic land and air double-used aircraft takes off, and flight under flight control system controls.When needs land, reduce screw rotating speed gradually, electronic land and air double-used aircraft can realize grease it in.Electronic land and air double-used aircraft of the present utility model is simple to operate, emission-free discharge, is the green energy resource vehicle, both can alleviates traffic congestion, also can meet the needs of Consumer's Experience flight.
The control system of electronic land and air double-used aircraft of the present utility model can also arrange GPS navigation locating module, in order to monitor flight path and the real time position of land and air double-used aircraft, user can make land and air double-used aircraft automatically to fly back original place with by the setting of this GPS navigation locating module.
Embodiment two
Below in an example, the part that the structure of electronic land and air double-used aircraft is identical with embodiment one repeats no more.
Refer to shown in Fig. 5, installation portion 202 is the framework that a cylinder surrounds, and installation portion 202 is roughly in quadrangle.Support arm 203 quantity is four, each support arm 203 is connected to four point of intersection of quadrangle, namely the installation portion 202 of described frame-type has four edge 2021,2022,2023,2024, these four edge intersect between two, every two adjacent edge have a point of intersection, so installation portion 202 has four point of intersection, four support arms 203 are assembled in four point of intersection respectively.Installation portion 202 is set to framework, is conducive to expendable weight.
Embodiment three
Refer to shown in Fig. 6 and Fig. 7, stirrup 204 can be arranged as follows, and stirrup 204 comprises the first bar portion 2041 be rotationally connected with support arm 203, the second bar portion 2042 be rotationally connected with support portion 201, attaching parts 2043, sleeve 2044 of rotarying connection respectively with the first bar portion 2041 and the second bar portion 2042.One end that first bar portion 2041 and the second bar portion 2042 are connected with attaching parts 2043 is respectively equipped with outside thread, sleeve 2044 is provided with negative thread, when stirrup 204 needs to strut, first bar portion 2041 and the second bar portion 2042 can manually lift by user, make the first bar portion 2041 and the second bar portion 2042 in a straight line, then turn sleeve 2044, sleeve 2044 is made to connect the first bar portion 2041 and the second bar portion 2042, now the first bar portion 2041 and the second bar portion 2042 relatively fixing, thus stable support plays support arm 203.When stirrup 204 needs to amount to, sleeve 2044 turn is left the junction in the first bar portion 2041 and the second bar portion 2042, two bar portions relatively can rotate and amount to, and support arm 203 rotates to collapse state from propping up state simultaneously.
Embodiment four
Refer to shown in Fig. 8 and Fig. 9, stirrup 204 can be arranged as follows, stirrup 204 comprises the first bar portion 2041 be rotationally connected with support arm 203, the second bar portion 2042 and the buckling piece 2045 be rotationally connected with support portion 201, first bar portion 2041 and the second bar portion 2042 are by a rotating shaft at side rotary connection, and buckling piece 2045 is rotaryed connection with the first bar portion 2041 and the second bar portion 2042 respectively at opposite side.When stirrup 204 stretches, first bar portion 2041 and the second bar portion 2042 rotary motion are in a straight line, move buckling piece 2045 and lock the first bar portion 2041 and the second bar portion 2042, make the first bar portion 2041 and the second bar portion 2042 relatively fixing, thus make stirrup 204 support arm 203.When stirrup 204 needs to amount to, move buckling piece 2045 and lock-out state is removed, thus the first bar portion 2041 and the second bar portion 2042 can relatively rotate and amount to.
Certainly; the above is preferred implementation of the present utility model; certainly also can otherwise realize; should be understood that; for those skilled in the art; without departing from the concept of the premise utility, any apparent replacement is all within protection domain of the present utility model.
Claims (6)
1. a vehicle seat for electronic land and air double-used aircraft, is characterized in that, described vehicle seat comprises the left and right handrail being arranged at both sides, left handrail is provided with flying speed controller, right handrail is provided with heading controller.
2. the vehicle seat of electronic land and air double-used aircraft as claimed in claim 1, is characterized in that, described flying speed controller is a mobilizable handle.
3. the vehicle seat of electronic land and air double-used aircraft as claimed in claim 1 or 2, is characterized in that, described heading controller is a mobilizable handle.
4. a vehicle seat for electronic land and air double-used aircraft, is characterized in that, described vehicle seat comprises the left and right handrail being arranged at both sides, right handrail is provided with flying speed controller, left handrail is provided with heading controller.
5. the vehicle seat of electronic land and air double-used aircraft as claimed in claim 4, is characterized in that, described flying speed controller is a mobilizable handle.
6. the vehicle seat of the electronic land and air double-used aircraft as described in claim 4 or 5, is characterized in that, described heading controller is a mobilizable handle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420783857.0U CN204322958U (en) | 2014-11-29 | 2014-11-29 | The vehicle seat of electronic land and air double-used aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420783857.0U CN204322958U (en) | 2014-11-29 | 2014-11-29 | The vehicle seat of electronic land and air double-used aircraft |
Related Parent Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420740729.8U Division CN204203773U (en) | 2014-11-29 | 2014-11-29 | Electronic land and air double-used aircraft |
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| Publication Number | Publication Date |
|---|---|
| CN204322958U true CN204322958U (en) | 2015-05-13 |
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| CN201420783857.0U Active CN204322958U (en) | 2014-11-29 | 2014-11-29 | The vehicle seat of electronic land and air double-used aircraft |
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| Country | Link |
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