CN206856984U - A kind of small-sized manned vehicle - Google Patents
A kind of small-sized manned vehicle Download PDFInfo
- Publication number
- CN206856984U CN206856984U CN201720550038.5U CN201720550038U CN206856984U CN 206856984 U CN206856984 U CN 206856984U CN 201720550038 U CN201720550038 U CN 201720550038U CN 206856984 U CN206856984 U CN 206856984U
- Authority
- CN
- China
- Prior art keywords
- flabellum
- small
- manned vehicle
- installation crossbeam
- girder
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
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Abstract
The utility model discloses a kind of small-sized manned vehicle, including fuselage and the flabellum that is installed on fuselage.The fuselage has a girder, and the both ends of the girder are equiped with installation crossbeam by universal drive shaft respectively, and the flabellum is installed on the installation crossbeam.The middle part of the girder is provided with cabin, and the lower section of cabin is provided with the rotating speed proportional amplifier that engine connects with engine, and the rotating speed proportional amplifier is connected with the flabellum and drives its rotation.Direction adjustment rotating shaft and direction pedal are provided with the cabin, the direction adjustment rotating shaft is connected with front installation crossbeam and controls its rotational angle, and the direction pedal is connected by zip with the flabellum, for adjusting angle of the flabellum relative to installation crossbeam.The utility model uses said structure design, and it has the advantages of simple to operate, easy to use and security performance is high.
Description
Technical field
It the utility model is related to vehicle technology field, and in particular to a kind of small-sized manned vehicle.
Background technology
The mankind have the ideal flown in the air as birds very early.For a long time, the mankind are most for the fantasy that can fly up into the sky
Various methods.With the continuous development of scientific technology, the dream that the mankind fly in the air becomes reality.It is existing most of
Aircraft is mainly used in scientific research, and cost is sufficiently expensive, is not particularly suited for masses, and needs to stop in the large-scale place such as airport
Put, it is suppressed that the consumption of most people, while existing aircraft operation when due to more complicated, it is therefore desirable to Special Training
It could drive, therefore, urgent need offer is a kind of simple to operate, and the aircraft that security performance is high.
Utility model content
For above-mentioned deficiency, the purpose of this utility model is, there is provided a kind of small-sized manned vehicle, it has operation letter
Singly, the advantages of easy to use and security performance is high.
To achieve the above object, technical scheme provided by the utility model is：
A kind of small-sized manned vehicle, including fuselage and the flabellum that is installed on fuselage.The fuselage has a girder, and
The both ends of the girder are equiped with installation crossbeam by universal drive shaft respectively, and the flabellum is installed on the installation crossbeam.Institute
The middle part for stating girder is provided with cabin, and the lower section of cabin is provided with the rotating speed proportional amplifier that engine connects with engine, and should
Rotating speed proportional amplifier is connected with the flabellum and drives its rotation.Direction adjustment rotating shaft is provided with the cabin and direction is stepped on
Plate, direction adjustment rotating shaft are connected with front installation crossbeam and control its rotational angle, the direction pedal by zip and
The flabellum connection, for adjusting angle of the flabellum relative to installation crossbeam.
Preferably, main frame, laser ranging controller, front and rear synchronizing speed are controlled during the small-sized manned vehicle also includes one
Distributor, center dynamic balance system and engine control system, the middle control main frame are electrically connected at the laser ranging control
Instrument, front and rear synchronizing speed distributor, center dynamic balance system and engine control system.
Preferably, the quantity of the flabellum is 4, and 4 flabellums are installed in the installation horizontal stroke of the girder front and back end respectively
The both ends of beam.
Preferably, each part of the small-sized manned vehicle uses carbon fiber and aluminium alloy, can effectively mitigate fuselage
Weight.
Preferably, the rear and front end of the girder is connected by universal drive shaft with installing the middle part of crossbeam respectively.
The beneficial effects of the utility model are：
In summary, a kind of small-sized manned vehicle of the utility model passes through zip and the fan by the direction pedal
Leaf connects, and for adjusting angle of the flabellum relative to installation crossbeam, and then can change thrust direction flight forward, then the side of passing through
Crossbeam is installed to adjustment rotating shaft and front to be connected and control its rotational angle, can change of flight device left and right directions.It is meanwhile described
Laser ranging controller can control aircraft to be awing not above safe altitude, and then improve the safety system of aircraft
Number.The utility model uses said structure design, and it has the advantages of simple to operate, easy to use and security performance is high.
Below in conjunction with the accompanying drawings with embodiment, the utility model is further illustrated.
Brief description of the drawings
Accompanying drawing is to be further understood for providing to of the present utility model, and a part for constitution instruction, and following
Embodiment be used to explain the utility model together, but do not form to limitation of the present utility model.In the accompanying drawings：
Fig. 1 is a kind of structural representation of small-sized manned vehicle of the utility model.
Fig. 2 is the structure chart of the control system of a kind of pedal of small-sized manned vehicle and flabellum shown in Fig. 1.
Each description of reference numerals is as follows in figure.
Fuselage -1, girder -1a, flabellum -2, universal drive shaft -3, installation crossbeam -4, cabin -5, engine -6,
Rotating speed proportional amplifier -7, direction adjustment rotating shaft -8, direction pedal -9, zip -10.
Embodiment
To describe technology contents of the present utility model, construction feature, the objects and the effects in detail, below in conjunction with implementation
Mode simultaneously coordinates accompanying drawing to be explained in detail.
The technical solution of the utility model is clearly and completely described below in conjunction with accompanying drawing, it is clear that described
Embodiment is the utility model part of the embodiment, rather than whole embodiments.Based on the embodiment in the utility model, sheet
The every other embodiment that field those of ordinary skill is obtained under the premise of creative work is not made, belongs to this practicality
Novel protected scope., it is necessary to explanation in description of the present utility model, term " " center ", " on ", " under ", " left side ",
The orientation or position relationship of the instruction such as " right side ", " vertical ", " level ", " interior ", " outer " are based on orientation shown in the drawings or position
Relation, it is for only for ease of description the utility model and simplifies description, rather than indicates or imply that signified device or element must
There must be specific orientation, with specific azimuth configuration and operation, therefore it is not intended that to limitation of the present utility model.
Refer to Fig. 1 and Fig. 2, a kind of small-sized manned vehicle, including fuselage 1 and the flabellum 2 being installed on fuselage 1.Institute
Stating fuselage 1 has a girder 1a, and girder 1a both ends are equiped with installation crossbeam 4, the fan by universal drive shaft 3 respectively
Leaf 2 is installed on the installation crossbeam 4.The middle part of the girder 1a is provided with cabin 5, available for manned operating aircraft, and machine
The lower section in cabin 5 be provided with engine 6 and in engine 6 connect rotating speed proportional amplifier 7, the engine 6 can be used gasoline or
Person's diesel oil is as fuel oil, and the rotating speed proportional amplifier 7 is connected with the flabellum 2 and drives its rotation, is provided to aircraft dynamic
Power.Direction adjustment rotating shaft 8 and direction pedal 9 are provided with the cabin 5, the direction adjustment rotating shaft 8 connects with front installation crossbeam 4
Connect and control its rotational angle, can change of flight device left and right directions, the direction pedal 9 passes through zip 10 and the flabellum 2
Connection, for adjusting angle of the flabellum 2 relative to installation crossbeam 4, and then thrust direction flight forward can be changed.In the present embodiment
In, the upper end in defining 1 in figure is the preceding extreme direction of aircraft.
Further, main frame, laser ranging controller, front and rear synchronous speed are controlled during the small-sized manned vehicle also includes one
Distributor, center dynamic balance system and engine control system are spent, the middle control main frame is electrically connected at the laser ranging control
Instrument, front and rear synchronizing speed distributor, center dynamic balance system and engine control system processed.Wherein, the laser ranging control
Instrument is used to control aircraft to be awing not above safe altitude, and then improves the safety coefficient of aircraft；It is described front and rear
Synchronizing speed distributor ensure that the speed of the flabellum 2 in operating is consistent, improve dynamic balancing ability；The center dynamic balancing system
System adjustable lower load-bearing is always maintained at center, improves dynamic balancing ability of the aircraft in running, further improves safety system
Number；It is big that the engine control system can regulate and control the output of the rotating speed proportional amplifier 7 of the connection of engine 6 according to power demand
It is small.
In the present embodiment, the quantity of the flabellum 2 is 4, and 4 flabellums 2 are installed in before and after the girder 1a respectively
The both ends of the installation crossbeam 4 at end, reasonable distribution is on four direction, plane figure, the dynamic balancing ability in running, further
Improve safety coefficient.
In the present embodiment, each part of the small-sized manned vehicle uses carbon fiber and aluminium alloy, can effectively subtract
Light fuselage weight.
In the present embodiment, the rear and front end of the girder 1a passes through the middle part of universal drive shaft 3 and installation crossbeam 4 respectively
Connection, it can effectively ensure the balance of aircraft.
For the utility model in use, starting engine 6, engine 6 drives flabellum 2 to rotate by rotating speed proportional amplifier 7,
Then center is always maintained at by center dynamic balance system adjustable lower load-bearing, increases fuel oil throttle, improve the rotating speed of flabellum 2,
Reach after demand thrust aircraft can vertical ascent to the arbitrary height in setting height or safe altitude, the side of depressing as needed
To pedal 9, the angle change of flabellum 2 is driven, changes thrust direction flight forward, manual rotation direction adjusts rotating shaft 8, change of flight
The left and right directions of device.It is automatic to reduce fuel oil throttle after laser range finder feed back height exceedes setting safe altitude, return to peace
Full-height.Fly to after place, decontrol direction of advance pedal 9, be changed into vertical direction, then gradually reduce fuel oil throttle, aircraft
Progressively dropped on level land or flooring during less than thrust, turn off throttle after coming to a complete stop, fix aircraft, prevent wind-force from throwing.
In summary, a kind of small-sized manned vehicle of the utility model passes through zip 10 and institute by the direction pedal 9
State flabellum 2 to connect, for adjusting angle of the flabellum 2 relative to installation crossbeam 4, and then thrust direction flight forward can be changed, so
Rotating shaft 8 and front installation crossbeam 4 is adjusted by direction afterwards to be connected and control its rotational angle, can change of flight device right and left
To.Meanwhile the laser ranging controller can control aircraft to be awing not above safe altitude, and then improve flight
The safety coefficient of device.The utility model uses said structure design, and it has simple to operate, and easy to use and security performance is high
Advantage.
The announcement and teaching of book according to the above description, the utility model those skilled in the art can also be to above-mentioned realities
The mode of applying is changed and changed.Therefore, the utility model is not limited to embodiment disclosed and described above, right
Some modifications and changes of the present utility model should also be as falling into scope of the claims of the present utility model.In addition, to the greatest extent
Some specific terms have been used in pipe this specification, but these terms are merely for convenience of description, not to the utility model
Any restrictions are formed, using same or similar other devices, in scope of protection of the utility model.
Claims (5)
- A kind of 1. small-sized manned vehicle, it is characterised in that：Including fuselage (1) and the flabellum (2) being installed on fuselage (1), institute Stating fuselage (1) has a girder (1a), and the both ends of the girder (1a) are equiped with installation crossbeam by universal drive shaft (3) respectively (4), the flabellum (2) is installed on the installation crossbeam (4), and the middle part of the girder (1a) is provided with cabin (5), cabin (5) Lower section be provided with engine (6) and the rotating speed proportional amplifier (7) in engine (6) connection, and the rotating speed proportional amplifier (7) It is connected with the flabellum (2) and drives its rotation, direction adjustment rotating shaft (8) and direction pedal (9) is provided with the cabin (5), The direction adjustment rotating shaft (8) is connected with front installation crossbeam (4) and controls its rotational angle, and the direction pedal (9) passes through Zip (10) is connected with the flabellum (2), for adjusting angle of the flabellum (2) relative to installation crossbeam (4).
- A kind of 2. small-sized manned vehicle as claimed in claim 1, it is characterised in that：The small-sized manned vehicle also includes Main frame, laser ranging controller, front and rear synchronizing speed distributor, center dynamic balance system and engine control system are controlled in one, It is described it is middle control main frame be electrically connected at the laser ranging controller, front and rear synchronizing speed distributor, center dynamic balance system and Engine control system.
- A kind of 3. small-sized manned vehicle as claimed in claim 1, it is characterised in that：The quantity of the flabellum (2) is 4, And 4 flabellums (2) are installed in the both ends of the installation crossbeam (4) of the girder (1a) front and back end respectively.
- A kind of 4. small-sized manned vehicle as claimed in claim 1, it is characterised in that：Each portion of the small-sized manned vehicle Part uses carbon fiber and aluminium alloy, can effectively mitigate fuselage weight.
- A kind of 5. small-sized manned vehicle as claimed in claim 1, it is characterised in that：The rear and front end of the girder (1a) point It is not connected by universal drive shaft (3) with the middle part of installation crossbeam (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720550038.5U CN206856984U (en) | 2017-05-18 | 2017-05-18 | A kind of small-sized manned vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720550038.5U CN206856984U (en) | 2017-05-18 | 2017-05-18 | A kind of small-sized manned vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206856984U true CN206856984U (en) | 2018-01-09 |
Family
ID=60824281
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720550038.5U Expired - Fee Related CN206856984U (en) | 2017-05-18 | 2017-05-18 | A kind of small-sized manned vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206856984U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107010214A (en) * | 2017-05-18 | 2017-08-04 | 阳喜英 | A kind of small-sized manned vehicle |
| CN108622420A (en) * | 2018-07-02 | 2018-10-09 | 广州天翔航空科技有限公司 | Electronic multi-rotor aerocraft and control method |
-
2017
- 2017-05-18 CN CN201720550038.5U patent/CN206856984U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107010214A (en) * | 2017-05-18 | 2017-08-04 | 阳喜英 | A kind of small-sized manned vehicle |
| CN108622420A (en) * | 2018-07-02 | 2018-10-09 | 广州天翔航空科技有限公司 | Electronic multi-rotor aerocraft and control method |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20180109 Termination date: 20200518 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |