CN106965923A - Driven helicopter - Google Patents
Driven helicopter Download PDFInfo
- Publication number
- CN106965923A CN106965923A CN201710214431.1A CN201710214431A CN106965923A CN 106965923 A CN106965923 A CN 106965923A CN 201710214431 A CN201710214431 A CN 201710214431A CN 106965923 A CN106965923 A CN 106965923A
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- China
- Prior art keywords
- fin
- propeller
- driven
- driven helicopter
- helicopter
- 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.)
- Pending
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- 238000010276 construction Methods 0.000 abstract description 5
- 238000004519 manufacturing process Methods 0.000 abstract description 5
- 230000008859 change Effects 0.000 description 3
- 238000005457 optimization Methods 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000008030 elimination Effects 0.000 description 1
- 238000003379 elimination reaction Methods 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/06—Helicopters with single rotor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
The invention discloses a kind of driven helicopter, including body, propeller, drive device and controller, propeller is arranged on body upper；Wherein, in addition to fin, fin is arranged on body, and fin is independently driven by drive device, the quantity at least two of fin, and it is along the circumferential uniform of body.A kind of driven helicopter that the present invention is provided, its is rational in infrastructure, and tab construction can offset the torsion of propeller；The use of pitch has been abandoned, by controlling fin to realize the adjustment of body heading, structure has both been simplified, the manufacturing cost of driven helicopter is saved again.
Description
Technical field
The present invention relates to vehicle technology field, more particularly to a kind of driven helicopter.
Background technology
Aircraft is increasingly favored by people, and its modeling structure also emerges in an endless stream, on the market it is relatively common go straight up to it is winged
Row device, fixed wing aircraft, multi-rotor aerocraft etc., wherein common unmanned driven helicopter includes body and remote control, body
Including propeller unit, fuselage and undercarriage, propeller unit is single-blade formula or double paddle, and propeller is driven by motor, single-blade
Formula is one group of propeller in back, and double paddle are provided in a pair of propellers of back, for realizing flight
The lift-off of device.
Driven helicopter provides lift by propeller rotation, but the rotation of propeller can cause body to have a reverse torsion
Power；To offset this torsion, going straight up to drive end unit needs to set propeller either jet mechanism or to use double-rotor type, rotates
It is in opposite direction to offset torsion.
Driven helicopter is in flight course, and typically by pitch come change of flight direction, but pitch price is high
It is expensive, the cost of driven helicopter is virtually added, its popularization is have impact on to a certain extent.
The content of the invention
The present invention is for above-mentioned technical problem there is provided a kind of driven helicopter, and its is rational in infrastructure, and tab construction can be supported
Disappear the torsion of propeller；The use of pitch has been abandoned, by controlling fin to realize the adjustment of body heading, had both been simplified
Structure, saves the manufacturing cost of driven helicopter again.
Technical scheme
In order to solve the above-mentioned technical problem, the invention provides a kind of driven helicopter, it includes body, propeller and control
Device processed, propeller is arranged on body upper；Also include fin, fin is arranged on body, the quantity at least two of the fin,
It is along the circumferential uniform of body, to ensure that body is had a smooth flight.
Further, the front face area on the outside of the fin is more than the front face area on the inside of fin.In this application, control
Device control drive device action, drive device drives fin rotation, and fin is while counteracting propeller rotates the torsion to be formed
Downward component can be produced, the lift of aircraft is influenceed, because the front face area on the outside of fin is more than the front face area of inner side, the wing
The arm of force on the outside of piece is big, can drop to the influence to aircraft lift most offsetting while propeller rotates the torsion to be formed
It is low.
Further, internal body is provided with drive device, the fin is independently driven by drive device.
Further, the deflection angle of the fin is adjustable, reverse by the rotation for adjusting fin, it is possible to achieve go straight up to winged
The adjustment of row device heading.
Further, the fin on the body sets multiple rows of, and fin can set two rows even more many.
Further, undercarriage is provided with the fin on the downside of the body, undercarriage is set on fin, can be simplified
The structure of driven helicopter, reduces manufacturing cost.
Further, the fin is shaped as L-type or T-shaped, and wherein front face area on the outside of fin is more than meeting for inner side
Wind area.
Beneficial effect of the present invention：
A kind of driven helicopter disclosed by the invention, its is rational in infrastructure, and tab construction can offset aircraft because of propeller
Rotate the torsion produced；The use of pitch has been abandoned, by controlling fin to realize the adjustment of body heading, had both been simplified
Structure, saves the manufacturing cost of driven helicopter again.Specific effect is as follows：
(1) the fin rotation on adjustment body, can offset the torsion of propeller；
(2) anglec of rotation of fin is controlled, the adjustment of body heading can be realized.
Brief description of the drawings
By the detailed description made in conjunction with the following drawings, advantages of the present invention will be apparent and be easier to understand,
These accompanying drawings are schematical, are not intended to limit the present invention, wherein：
Fig. 1 is the structural representation of the present invention；
Fig. 2 is the structural representation in driven helicopter change of flight direction of the present invention.
Embodiment
A kind of driven helicopter of the present invention is described in detail with reference to specific embodiment and accompanying drawing.
The embodiment recorded herein is the specific embodiment of the present invention, the design for illustrating the present invention,
It is explanatory and exemplary, should not be construed as the limitation to embodiment of the present invention and the scope of the invention.Except what is recorded herein
Implement exception, those skilled in the art can also be based on the application claims and specification disclosure of that using aobvious
The other technical schemes being clear to, these technical schemes include any obvious using making for the embodiment to recording herein
The technical scheme of substitutions and modifications.
The accompanying drawing of this specification is schematic diagram, aids in illustrating the design of the present invention, it is schematically indicated the shape of each several part
And its correlation.It note that the structure of each part for the ease of clearly showing the embodiment of the present invention, identical reference
Mark for representing identical part.
A kind of structural representation of driven helicopter, as shown in figure 1, it includes body 2, propeller 1, drive device and control
Device processed, propeller 1 is arranged on the top of body 2.
Driven helicopter also includes fin 3, and fin 3 is arranged on body 2, the quantity at least two of fin 3, and it is along body
2 circumference is uniform, to ensure that driven helicopter is had a smooth flight.
The present invention principle be：When propeller 1 is rotated, down draft is formed, drives aircraft to rise；Meanwhile, by
In the presence of fin 3, the airflow function that propeller 1 is produced produces the power opposite with body spin direction, prevents machine in fin 3
Body is rotated.
Internal body is provided with drive device, fin is independently driven by drive device, the direction of rotation or angle of fin
Degree can be consistent, can also be inconsistent.Outside the present embodiment, the quantity of fin 3 can be 2,3,4,5,6 etc., number
Amount is unrestricted, is uniformly arranged in arrangement, such as using 3 fins, then fin is separately arranged on fuselage according to 120 degree of angles
Cloth, by that analogy.Actual quantity demand, is the demand setting according to different driven helicopters, the area size of such as fin, fin
Distance, the torsion of needs resistance of outboard end with body in itself etc..
Two or more fin yawing moment is consistent with angle, it is possible to achieve decline, hovering, the rising of driven helicopter, when
When two or more fin yawing moment or inconsistent angle, it is possible to achieve driven helicopter is all around moved.Pass through fin
Deflection angle control, it is possible to achieve the different actions of driven helicopter.
When the quantity of fin 3 is more than 3, different fins can be used to realize difference in functionality, such as Partial wings are used
In eliminating driven helicopter Rotation, Partial wings are used to manipulate heading and posture.
It is preferred that, the front face area in the outside of fin 3 is more than the front face area of the inner side of fin 3.Herein, it is fixed on the basis of body
Adopted outside and inner side, away from matrix for outside, what it is close to body is inner side.
Because the wind-force on the outside of propeller can be bigger than inner side, while the arm of force is longer on the outside of fin, therefore, airfoil is entered
After row optimization, mitigate fin dead weight simultaneously, more effectively offset the moment of torsion that the rotation of propeller 1 is formed.
It is the arm of force of the horizontal direction using fin, therefore, fin 3 when using fin offset torque in the present invention
Setting height(from bottom) is not required, can be selectively mounted near propeller, can also be selectively mounted to the machine away from propeller
Body position.
Certainly, two groups of fins can be set in driven helicopter of the invention, including for offsetting the torsion that the rotation of propeller 1 is formed
The antitorque fin of power and the direction fin for adjusting aircraft direction, are optimization design, make full use of outside the arm of force, antitorque fin
The front face area of side is more than the front face area on the inside of antitorque fin, and the setting height(from bottom) of antitorque fin therefore is not required, Ke Yixuan
Select and be arranged close near propeller, the body position away from propeller can also be selectively mounted to；And direction fin is then profit
With the arm of force of vertical direction, therefore to reach more preferable effect, the setting height(from bottom) of direction fin should be in the body away from propeller
Position.The flight theory of aircraft is：When propeller 1 is rotated, down draft is formed, drives aircraft to rise；Meanwhile, by
In the presence of antitorque fin, the airflow function that propeller 1 is produced produces the power opposite with body spin direction in antitorque fin,
Prevent body from rotating, certainly, can be by adjusting the windward side of antitorque fin come the size of adjusting force, so as to realize control body
Rotation；The heading of aircraft is can control by adjusting the windward side of direction fin, propeller 1 rotates the airflow function formed
In direction fin so that body run-off the straight, the inclination of fuselage will certainly cause propeller 1 to produce angle with horizontal plane, so that
The control to aircraft flight direction is realized, compared with the pitch of existing helicopter, direction tab construction is simpler, cost
Substantially reduce, can flexibly and easily control aircraft flight direction.
In the present embodiment, the quantity of antitorque fin and direction fin can be 2,3,4,5,6 etc., and quantity is not
It is restricted, is uniformly arranged in arrangement, such as using 3 fins, then fin is separately arranged on fuselage according to 120 degree of angles,
By that analogy.Actual quantity demand, is outside the demand setting according to different driven helicopters, the area size of such as fin, fin
Distance, the torsion of needs elimination of side end with body in itself etc..
Certainly, driven helicopter of the invention is additionally provided with undercarriage, and undercarriage can be arranged on organism bottom, can also set
Put on the fin of direction, the structure of direction fin can also be optimized, directly the lower end of direction fin is regard as undercarriage.
Because direction fin mainly utilizes the arm of force of vertical direction, therefore, direction fin is typically mounted under body 2
Portion, it is not necessary to which the windward side in outside in fin is designed to difference.But in order to standardize making, general direction fin with it is antitorque
The shape of fin is the same, and airfoil can be T-shaped, and the front face area on the outside of fin is more than the front face area on the inside of fin.
For optimization design, the direction fin and antitorque fin of fuselage the same side can be with Integral designs, and now airfoil is L
Type, " one " of L-type fin, partly equivalent to antitorque fin, " Shu " of L-type fin is partly equivalent to direction fin, and L-type fin
" one " part outside (side away from fuselage) windward side it is big, the one end of " Shu " of L-type fin partially away from propeller 1
Front face area it is big." Shu " of L-type fin can be used as undercarriage partially away from one end of propeller 1.
A kind of driven helicopter disclosed by the invention, its is rational in infrastructure, and tab construction can offset the torsion of propeller；Get rid of
The use of pitch has been abandoned, by controlling fin to realize the adjustment of body heading, structure has both been simplified, saves and go straight up to again
The manufacturing cost of aircraft.
The present invention can be widely applied to each field such as depopulated helicopter, manned helicopter, toy helicopter.
The present invention is not limited to the above-described embodiments, and anyone can draw other various forms under the enlightenment of the present invention
Product, it is every that there is technical side identical or similar to the present application however, make any change in its shape or structure
Case, is within the scope of the present invention.
Claims (7)
1. driven helicopter, including body, propeller and controller, propeller are arranged on body upper；Characterized in that, also wrapping
Fin is included, fin is arranged on body, the quantity at least two of the fin, it is uniform along the circumference of body.
2. driven helicopter according to claim 1, it is characterised in that the front face area on the outside of the fin is more than in fin
The front face area of side.
3. driven helicopter according to claim 1, it is characterised in that internal body is provided with drive device, the wing
Piece is independently driven by drive device.
4. driven helicopter according to claim 1, it is characterised in that the deflection angle of the fin is adjustable.
5. driven helicopter according to claim 1, it is characterised in that the fin on the body sets multiple rows of.
6. driven helicopter according to claim 5, it is characterised in that be provided with and rise and fall on the fin on the downside of the body
Frame.
7. driven helicopter according to claim 1, it is characterised in that the fin is shaped as L-type or T-shaped.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710214431.1A CN106965923A (en) | 2017-04-01 | 2017-04-01 | Driven helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710214431.1A CN106965923A (en) | 2017-04-01 | 2017-04-01 | Driven helicopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106965923A true CN106965923A (en) | 2017-07-21 |
Family
ID=59336197
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710214431.1A Pending CN106965923A (en) | 2017-04-01 | 2017-04-01 | Driven helicopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106965923A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108045565A (en) * | 2018-01-15 | 2018-05-18 | 天津大学 | A kind of single shaft aircraft |
| CN109729800A (en) * | 2018-11-21 | 2019-05-10 | 华南农业大学 | A kind of particle scattering mechanism based on unmanned plane |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101990452A (en) * | 2008-04-07 | 2011-03-23 | 史蒂文·戴维斯 | Directionally controllable flying vehicle and a propeller mechanism for accomplishing the same |
| CN205916329U (en) * | 2016-05-25 | 2017-02-01 | 王硕堃 | Coaxial double -oar unmanned vehicles |
| CN207374641U (en) * | 2017-04-01 | 2018-05-18 | 苏州科伊嘉航空科技有限公司 | Driven helicopter |
-
2017
- 2017-04-01 CN CN201710214431.1A patent/CN106965923A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101990452A (en) * | 2008-04-07 | 2011-03-23 | 史蒂文·戴维斯 | Directionally controllable flying vehicle and a propeller mechanism for accomplishing the same |
| CN205916329U (en) * | 2016-05-25 | 2017-02-01 | 王硕堃 | Coaxial double -oar unmanned vehicles |
| CN207374641U (en) * | 2017-04-01 | 2018-05-18 | 苏州科伊嘉航空科技有限公司 | Driven helicopter |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108045565A (en) * | 2018-01-15 | 2018-05-18 | 天津大学 | A kind of single shaft aircraft |
| CN109729800A (en) * | 2018-11-21 | 2019-05-10 | 华南农业大学 | A kind of particle scattering mechanism based on unmanned plane |
| CN109729800B (en) * | 2018-11-21 | 2020-09-22 | 华南农业大学 | Particle scattering device based on unmanned aerial vehicle |
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| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20170721 |