CN203075664U - Flying machine - Google Patents
Flying machine Download PDFInfo
- Publication number
- CN203075664U CN203075664U CN 201320016904 CN201320016904U CN203075664U CN 203075664 U CN203075664 U CN 203075664U CN 201320016904 CN201320016904 CN 201320016904 CN 201320016904 U CN201320016904 U CN 201320016904U CN 203075664 U CN203075664 U CN 203075664U
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- CN
- China
- Prior art keywords
- aircraft
- bar frame
- battery
- controlling organization
- screw
- 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 flying machine which comprises an outer strip frame, screw propellers, a driving control mechanism and a battery are arranged inside the outer strip frame, the driving control mechanism is provided with output shafts, the screw propellers are connected on the output shafts, and the driving control mechanism is electrically connected with the battery. In the process of flying, damage to the screw propellers can be reduced, control can be carried out freely, the outer strip frame is spherical and interestingness can be further increased.
Description
Technical field
The utility model relates to a kind of aircraft.
Background technology
Existing aircraft such as children are with toy airplane, other baby plane etc., and its screw all is directly to expose, and screw is very easily injured in flight course, also gets to the people simultaneously easily, so to the control of the aircraft comparison difficulty that seems.
Summary of the invention
Based on this, the utility model is to overcome the defective of prior art, and a kind of aircraft is provided, the utility model can reduce in the flight course damage to screw, because screw is installed in the outer bar frame, also can well guarantee flight safety simultaneously, can arbitraryly control.
Its technical scheme is as follows:
A kind of aircraft comprises outer bar frame, and the inside of bar frame is provided with screw, drives controlling organization, battery outside, drives controlling organization and has output shaft, and screw is connected on the output shaft, drives controlling organization and battery and electrically connects.
Below further technical scheme is described:
Described outer bar frame is spherical in shape.
Bar frame inside is provided with flow deflector outside described.
Described driving controlling organization includes motor, master controller and remote control receiving element, and motor and remote control receiving element all electrically connect with master controller, and described output shaft is located on the motor.
Described driving controlling organization also includes speed regulator, and this speed regulator and described battery, motor, master controller electrically connect.
Be provided with inner support in the bar frame outside described, described driving controlling organization and battery are located on the inner support.
Described inner support comprises at least two ribs, and the inner of each rib links together, and the outer end is connected with described outer bar frame respectively, and described screw is at least two, is located at respectively on each rib.
Advantage or principle to the aforementioned techniques scheme describes below:
1, because this aircraft has outer bar frame; in the flight course of aircraft; can play a protective role to aircraft; avoid aircraft and other object (as high-altitude building, branch etc.) to bump; in the landing process of aircraft, also can avoid aircraft and ground to bump the more convenient operation of aircraft; long service life, the security performance height.
2, described outer bar frame is spherical in shape, makes the flexible motion that this aircraft can multi-angle when landing, and simultaneously screw is protected, and is safe, as toy for children, also increases interesting.
3, bar frame inside is provided with flow deflector outside described, can increase the stability in the aircraft flight process, flow deflector adopt three or more than, its stablizing effect is better; For the aircraft of single motor, single screw, the stabilization of its flow deflector is extremely important.
4, battery is located at the bottom of described inner support, makes the center of gravity of aircraft more steady.
5, described inner support comprises at least two ribs, and described screw is located at respectively on each rib, and in flight course, at least two propeller-driven aircraft rise stably.
6, described outer bar frame is made by elastomeric material, can the efficient buffer aircraft and exterior object between collision.
Description of drawings
Fig. 1 is the structure chart of the described aircraft of the utility model embodiment;
Fig. 2 is the schematic block circuit diagram of the described aircraft of the utility model embodiment;
Description of reference numerals:
10, outer bar frame, 20, screw, 30, battery, 40, motor, 50, master controller, 60, the remote control receiving element, 70, rib, 80, speed regulator.
The specific embodiment
Below embodiment of the present utility model is elaborated:
As shown in Figure 1 and Figure 2, a kind of aircraft, comprise outer bar frame 10, the inside of bar frame 10 is provided with screw 20, drives controlling organization, battery 30 outside, drive controlling organization and have output shaft, screw 20 is connected on the output shaft, can make output shaft change direction by steering wheel, realize the function of rotation and change pulling force, drive controlling organization and battery 30 electric connections.
Wherein, described outer bar frame 10 is spherical in shape, bar frame 10 inside are provided with the flow deflector (not shown) outside described, described driving controlling organization includes motor 40, master controller 50, remote control receiving element 60 and speed regulator 80, motor 40 and remote control receiving element 60 all electrically connect with master controller 50, and speed regulator 80 electrically connects with described battery 30, motor 40, master controller 50.Described output shaft is located on the motor 40.Be provided with inner support in the bar frame 10 outside described, described driving controlling organization and battery 30 are located on the inner support.Described inner support comprises three ribs 70, and the inner of each rib 70 links together, and the outer end is connected with described outer bar frame 10 respectively, and described screw 20 is three, is located at respectively on each rib 70.
Present embodiment has following advantage:
1, because this aircraft has outer bar frame 10; in the flight course of aircraft; can play a protective role to aircraft; avoid aircraft and other object (as high-altitude building, branch etc.) to bump; in the landing process of aircraft, also can avoid aircraft and ground to bump the more convenient operation of aircraft; long service life, the security performance height.
2, described outer bar frame 10 is spherical in shape, makes the flexible motion that this aircraft can multi-angle when landing, and simultaneously screw 20 is protected, and is safe, as toy for children, also increases interesting.
3, bar frame 10 inside are provided with the flow deflector (not shown) outside described, can increase the stability in the aircraft flight process, flow deflector adopt three or more than, its stablizing effect is better.
4, battery 30 is located at the bottom of described inner support, makes the center of gravity of aircraft more steady.
5, described inner support comprises three ribs 70, and described screw 20 is located at respectively on each rib 70, and in flight course, three screws 20 form stable triangle, keep aircraft to rise stably.
6, described outer bar frame 10 is made by elastomeric material, can the efficient buffer aircraft and exterior object between collision.
The above embodiment has only expressed the specific embodiment of the present utility model, and it describes comparatively concrete and detailed, but can not therefore be interpreted as the restriction to the utility model claim.Should be pointed out that for the person of ordinary skill of the art under the prerequisite that does not break away from the utility model design, can also make some distortion and improvement, these all belong to protection domain of the present utility model.
Claims (9)
1. an aircraft is characterized in that, comprises outer bar frame, and the inside of bar frame is provided with screw, drives controlling organization, battery outside, drives controlling organization and has output shaft, and screw is connected on the output shaft, drives controlling organization and battery and electrically connects.
2. according to the described aircraft of claim 1, it is characterized in that described outer bar frame is spherical in shape.
3. according to the described aircraft of claim 1, it is characterized in that bar frame inside is provided with flow deflector outside described.
4. according to each described aircraft in the claim 1 to 3, it is characterized in that, described driving controlling organization includes motor, master controller and remote control receiving element, and motor and remote control receiving element all electrically connect with master controller, and described output shaft is located on the motor.
5. according to each described aircraft in the claim 1 to 3, it is characterized in that described driving controlling organization also includes speed regulator, this speed regulator and described battery, motor, master controller electrically connect.
6. according to each described aircraft in the claim 1 to 3, it is characterized in that be provided with inner support in the bar frame outside described, described driving controlling organization and battery are located on the inner support.
7. according to the described aircraft of claim 6, it is characterized in that described battery is located at the bottom of described inner support.
8. according to the described aircraft of claim 6, it is characterized in that described inner support comprises at least two ribs, the inner of each rib links together, and the outer end is connected with described outer bar frame respectively, and described screw is at least two, is located at respectively on each rib.
9. according to each described aircraft in the claim 1 to 3, it is characterized in that described outer bar frame is made by elastomeric material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320016904 CN203075664U (en) | 2013-01-11 | 2013-01-11 | Flying machine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320016904 CN203075664U (en) | 2013-01-11 | 2013-01-11 | Flying machine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203075664U true CN203075664U (en) | 2013-07-24 |
Family
ID=48821548
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201320016904 Expired - Fee Related CN203075664U (en) | 2013-01-11 | 2013-01-11 | Flying machine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203075664U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105539808A (en) * | 2016-02-11 | 2016-05-04 | 河南广度超硬材料有限公司 | Tumbler type bouncing foam safety air vehicle |
| CN109432724A (en) * | 2018-12-13 | 2019-03-08 | 福州大学 | Novel body building aircraft and its control method |
-
2013
- 2013-01-11 CN CN 201320016904 patent/CN203075664U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105539808A (en) * | 2016-02-11 | 2016-05-04 | 河南广度超硬材料有限公司 | Tumbler type bouncing foam safety air vehicle |
| CN109432724A (en) * | 2018-12-13 | 2019-03-08 | 福州大学 | Novel body building aircraft and its control method |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20130724 Termination date: 20190111 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |