CN207697982U - A kind of aircraft is from steady structure - Google Patents
A kind of aircraft is from steady structure Download PDFInfo
- Publication number
- CN207697982U CN207697982U CN201721798744.8U CN201721798744U CN207697982U CN 207697982 U CN207697982 U CN 207697982U CN 201721798744 U CN201721798744 U CN 201721798744U CN 207697982 U CN207697982 U CN 207697982U
- Authority
- CN
- China
- Prior art keywords
- flank
- fuselage
- top surface
- aircraft
- fixed frame
- 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.)
- Active
Links
Landscapes
- Toys (AREA)
Abstract
The utility model is related to vehicle technology fields, a kind of aircraft is referred in particular to from steady structure, it includes casing and rotating driving device, the casing includes fuselage, the both sides of the fuselage are respectively connected with flank, the flank of fuselage both sides is both provided with airflow hole, the flank is provided with fixed frame, the fixed frame is located in airflow hole, the rotating driving device includes the propeller for being installed in the motor of fixed frame and being installed in the output shaft of motor, the top surface of the fuselage is higher than the top surface of flank, and the top surface of the flank is higher than the peak of propeller.The utility model has the advantages of simple structure, ingenious in design, and stable structure, service life is long, and the aircraft convenient for putting upside down restores normal state of flight, is suitble to open air flight.
Description
Technical field
The utility model is related to vehicle technology field, a kind of aircraft is referred in particular to from steady structure.
Background technology
With the development of science and technology, due to flying instrument have maneuverability, reaction speed it is fast, it is unmanned, accurately control
The advantages that, thus aircraft applied in industry-by-industry field it is more and more extensive, therefore by consumers in general and enterprise
Favor.Traditional aircraft, which awing falls on the ground, to be caused to put upside down, and aircraft is just had no way normal flight, and people can only be depended on
Work restore manually aircraft regular flight condition could normal flight again, and traditional aircraft is easily damaged, the service life compared with
It is short.
Invention content
The technical problem to be solved by the present invention is to provide a kind of aircraft from steady structure, and simple in structure, design is skilful
Wonderful, stable structure, service life is long, and the aircraft convenient for putting upside down restores normal state of flight, is suitble to open air flight.
In order to solve the above-mentioned technical problem, the utility model adopts the following technical solution：
A kind of aircraft is from steady structure comprising casing and rotating driving device, the casing include fuselage, the fuselage
Both sides be respectively connected with flank, the flank of fuselage both sides is both provided with airflow hole, and the flank is provided with fixed frame, the fixation
Frame is located in airflow hole, and the rotating driving device includes the spiral shell for being installed in the motor of fixed frame and being installed in the output shaft of motor
Paddle is revolved, the top surface of the fuselage is higher than the top surface of flank, and the top surface of the flank is higher than the peak of propeller.
Further, the rotating driving device further includes the rotation lid for being rotatably dispose in propeller, the rotation lid
Top surface is higher than the top surface of flank.
Further, the fixed frame includes the fixed part for being connected to flank and the mounting portion for being connected to fixed part, described
Fixed part is placed in airflow hole, and the mounting portion stretches out airflow hole, and the mounting portion is provided with the peace for housing motor
Tankage.
Further, the fixed frame further includes the buffer part for being connected to mounting portion, between the buffer part and mounting portion
It is provided with dashpot.
Further, the buffer part is provided with supporting block.
Further, the top surface of the fuselage is in convex structure.
Further, the both sides of the fuselage are all connected with there are two flank.
Further, the casing constructs for integral type.
Further, the cylindrical structure of the flank.
The beneficial effects of the utility model：A kind of aircraft is from steady structure comprising casing and rotating driving device, it is described
Casing includes fuselage, and the both sides of the fuselage are respectively connected with flank, and the flank of fuselage both sides is both provided with airflow hole, the flank
Be provided with fixed frame, the fixed frame is located in airflow hole, the rotating driving device include be installed in fixed frame motor and
It is installed in the propeller of the output shaft of motor, the top surface of the fuselage is higher than the top surface of flank, and the top surface of the flank is higher than spiral shell
Revolve the peak of paddle.When aircraft falls ground and causes to put upside down, since the top surface of fuselage is higher than the top surface of flank, flank
Top surface is higher than the peak of propeller, so propeller will not be attached on the ground, operator passes through remote control control fuselage side
Motor rotates forward, and the motor of rotating forward drives propeller to rotate forward, the motor reversal of the fuselage other side, and the motor of reversion drives propeller anti-
Turn so that the flank of fuselage side generates upward air-flow, i.e., the flank of upward lift, the fuselage other side generates downward gas
Stream, i.e., downward lift, since the top surface of fuselage is higher than the top surface of flank, the fulcrum of fuselage just such as lever so that aircraft
It turns over, restores normal state of flight；This aircraft simple in sturcture, ingenious in design, stable structure, service life from steady structure
Long, the aircraft convenient for putting upside down restores normal state of flight, is suitble to open air flight.
Description of the drawings
Fig. 1 is the dimensional structure diagram of the utility model.
Fig. 2 is the dimensional structure diagram at another visual angle of the utility model.
Reference sign：
1, fuselage；2, flank；3, airflow hole；4, fixed part；5, mounting portion；6, mounting groove；7, buffer part；
8, dashpot；9, supporting block；10, motor；11, propeller；12, rotation lid.
Specific implementation mode
For the ease of the understanding of those skilled in the art, the utility model is made with reference to embodiment and attached drawing further
Explanation, the content that embodiment refers to not is restriction to the utility model.
As shown in Figure 1 to Figure 2, a kind of aircraft provided by the utility model is from steady structure comprising casing and rotation are driven
Dynamic device, the casing includes fuselage 1, and the both sides of the fuselage 1 are respectively connected with flank 2, and the flank 2 of 1 both sides of fuselage is respectively provided with
There are airflow hole 3, the flank 2 to be provided with fixed frame, the fixed frame is located in airflow hole 3, and the rotating driving device includes
It is installed in the motor 10 of fixed frame and is installed in the propeller 11 of the output shaft of motor 10, the top surface of the fuselage 1 is higher than flank 2
Top surface, the top surface of the flank 2 is higher than the peak of propeller 11；Specifically, the flank 2 of 1 both sides of fuselage is about fuselage 1
Setting substantially symmetrical about its central axis.When aircraft falls ground and causes to put upside down, since the top surface of fuselage 1 is higher than the top surface of flank 2, side
The top surface of the wing 2 is higher than the peak of propeller 11, so propeller 11 will not be attached on the ground, operator passes through remote control control machine
The motor 10 of 1 side of body rotates forward, and the motor 10 of rotating forward drives propeller 11 to rotate forward, and the motor 10 of 1 other side of fuselage inverts, reversion
Motor 10 drive propeller 11 invert so that the flank 2 of 1 side of fuselage generates upward air-flow, i.e., upward lift, fuselage
The flank 2 of 1 other side generates downward air-flow, i.e., downward lift, since the top surface of fuselage 1 is higher than the top surface of flank 2, fuselage
The fulcrum of 1 just such as lever so that aircraft turns over, and restores normal state of flight；Structure letter of this aircraft from steady structure
Single, ingenious in design, stable structure, service life is long, and the aircraft convenient for putting upside down restores normal state of flight, is suitble to outdoor fly
Row.
In the present embodiment, the rotating driving device further includes the rotation lid 12 for being rotatably dispose in propeller 11, described turn
The top surface of dynamic lid 12 is higher than the top surface of flank 2；Rotation lid 12 can be freely rotated relative to propeller 11, when aircraft is put upside down in ground
When face, the top surface of rotation lid 12 contradicts ground, and 10 energy normal driving propeller 11 of motor is rotated relative to rotation lid 12, further
It avoids propeller 11 from being attached on the ground, ensures 11 energy normal rotation of propeller, restore regular flight condition convenient for aircraft.
In the present embodiment, the fixed frame includes the fixed part 4 for being connected to flank 2 and the mounting portion for being connected to fixed part 4
5, the fixed part 4 is placed in airflow hole 3, and the mounting portion 5 stretches out airflow hole 3, and the mounting portion 5 is provided with for holding
Set the mounting groove 6 of motor 10；Specifically, the fixed part 4 is in " Y " shape structure.Mounting groove 6 is assembled convenient for motor 10, and
Play the role of positioning to motor 10.
In the present embodiment, the fixed frame further includes the buffer part 7 for being connected to mounting portion 5, the buffer part 7 and mounting portion
Dashpot 8 is provided between 5；When aircraft lands, dashpot 8 plays the role of buffering, reduces aircraft and is generated with ground
Impact, reduce aircraft vibrations, extend the service life of aircraft.
In the present embodiment, the buffer part 7 is provided with supporting block 9, and supporting block 9 is supported aircraft, avoids buffering
Portion 7 is in direct contact with ground；Specifically, the surface of the supporting block 9 is coated with wearing layer so that supporting block 9 has wear-resisting
Performance extends the service life of supporting block 9.
In the present embodiment, the top surface of the fuselage 1 is in convex structure, and the fuselage 1 of arc-shaped reduces resistance when flight
Power so that the flight stability of aircraft.
In the present embodiment, the both sides of the fuselage 1 are all connected with that there are two flanks 2, improve the stability of Flight Vehicle Structure,
Convenient for aircraft flight.
In the present embodiment, the casing constructs for integral type so that the stable structure of casing, and convenient for casing production system
It makes, reduces the cost of casing production.
In the present embodiment, 2 cylindrical structure of the flank is conducive to the air-flow flowing of the generation of propeller 11, convenient for flying
Row device flies.
In the present embodiment, the propeller 11 is provided with multiple blades, multiple blade circular array settings.
All technical characteristics in the present embodiment can be freely combined according to actual needs.
Above-described embodiment is the preferable implementation of the utility model, and in addition to this, the utility model can be with other sides
Formula realizes that any obvious replacement is in the protection model of the utility model under the premise of not departing from the technical program design
Within enclosing.
Claims (9)
1. a kind of aircraft is from steady structure, it is characterised in that：Including casing and rotating driving device, the casing includes fuselage,
The both sides of the fuselage are respectively connected with flank, and the flank of fuselage both sides is both provided with airflow hole, and the flank is provided with fixed frame,
The fixed frame is located in airflow hole, and the rotating driving device includes being installed in the motor of fixed frame and being installed in the defeated of motor
The propeller of shaft, the top surface of the fuselage are higher than the top surface of flank, and the top surface of the flank is higher than the peak of propeller.
2. a kind of aircraft according to claim 1 is from steady structure, it is characterised in that：The rotating driving device further includes
It is rotatably dispose in the rotation lid of propeller, the top surface of the rotation lid is higher than the top surface of flank.
3. a kind of aircraft according to claim 1 is from steady structure, it is characterised in that：The fixed frame includes being connected to side
The fixed part of the wing and the mounting portion for being connected to fixed part, the fixed part are placed in airflow hole, the mounting portion projection outlet
Discharge orifice, the mounting portion are provided with the mounting groove for housing motor.
4. a kind of aircraft according to claim 3 is from steady structure, it is characterised in that：The fixed frame further includes being connected to
The buffer part of mounting portion is provided with dashpot between the buffer part and mounting portion.
5. a kind of aircraft according to claim 4 is from steady structure, it is characterised in that：The buffer part is provided with support
Block.
6. a kind of aircraft according to claim 1 is from steady structure, it is characterised in that：The top surface of the fuselage is in arc-shaped
Structure.
7. a kind of aircraft according to claim 1 is from steady structure, it is characterised in that：The both sides of the fuselage are respectively connected with
Two flanks.
8. a kind of aircraft according to claim 1 is from steady structure, it is characterised in that：The casing constructs for integral type.
9. a kind of aircraft according to claim 1 is from steady structure, it is characterised in that：The cylindrical structure of flank.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721798744.8U CN207697982U (en) | 2017-12-18 | 2017-12-18 | A kind of aircraft is from steady structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721798744.8U CN207697982U (en) | 2017-12-18 | 2017-12-18 | A kind of aircraft is from steady structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207697982U true CN207697982U (en) | 2018-08-07 |
Family
ID=63027696
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721798744.8U Active CN207697982U (en) | 2017-12-18 | 2017-12-18 | A kind of aircraft is from steady structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207697982U (en) |
-
2017
- 2017-12-18 CN CN201721798744.8U patent/CN207697982U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN201800918U (en) | Rotating telescopic flying device with four rotor wings | |
| CN106004287B (en) | Amphibious multifunctional vertical landing aircraft | |
| KR101217803B1 (en) | Bottom three-propeller control type vehicle | |
| CA2431661C (en) | Propellers, propeller stabilizers, and propeller related vehicles | |
| WO2021098452A1 (en) | Folding paddle mechanism and unmanned aerial vehicle | |
| CN207697982U (en) | A kind of aircraft is from steady structure | |
| CN106864742A (en) | A kind of coaxial double-oar power duct | |
| CN206615387U (en) | A kind of coaxial opposed pair of oar power duct | |
| CN218172586U (en) | Flexible propeller and power device | |
| CN106864734A (en) | A kind of coaxial opposed pair of oar power duct | |
| CN205469818U (en) | Make an uproar screw and helicopter fall | |
| CN207550506U (en) | Ducted propeller and small-sized pilotless aircraft | |
| CN109823523A (en) | A kind of coaxial double-oar aircraft | |
| CN207550505U (en) | Small-sized pilotless aircraft | |
| CN208138391U (en) | A kind of aircraft power drive mechanism | |
| CN208559775U (en) | One kind is verted vector type unmanned plane motor fixing seat | |
| CN206654193U (en) | A kind of new unmanned vehicle drive device | |
| CN207565823U (en) | Ultrasonic wave anti-interference structure and small-sized pilotless aircraft | |
| CN207450245U (en) | Fluting culvert type plume rotor craft | |
| CN207565837U (en) | Radiator structure and the small-sized pilotless aircraft with the radiator structure | |
| CN204895837U (en) | Small -size VTOL aircraft aerodynamic layout | |
| CN206615397U (en) | A kind of coaxial double-oar power duct | |
| CN210919341U (en) | Household mini wind power generation device | |
| CN213620246U (en) | Many rotors environmental monitoring unmanned aerial vehicle | |
| CN203463228U (en) | Constant-speed paddle switching device of wind driven generator |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |