CN204548501U - Symmetrical oar and the aircraft comprising it - Google Patents
Symmetrical oar and the aircraft comprising it Download PDFInfo
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- CN204548501U CN204548501U CN201520016168.1U CN201520016168U CN204548501U CN 204548501 U CN204548501 U CN 204548501U CN 201520016168 U CN201520016168 U CN 201520016168U CN 204548501 U CN204548501 U CN 204548501U
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- blade
- oar
- symmetrical
- aircraft
- axle portion
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Abstract
The utility model provides a kind of symmetrical oar and comprises its aircraft, the at least two panels blade that this symmetrical oar comprises a central axle portion and is connected with this central axle portion, this blade comprises a leading edge and a trailing edge, this symmetrical oar from forward position overturn 180 ° be in reverse position time, when this forward position, the leading edge of this blade becomes the trailing edge of this blade when this reverse position, when this forward position, the trailing edge of this blade becomes the leading edge of this blade when this reverse position, at least can provide in the service area of lift at this blade, the upper half blade that this blade is intercepted by a curved surface and lower half blade can overlap with another sheet after a slice overturns 180 ° wherein.Symmetrical oar of the present utility model makes aircraft anti-to fly to become possibility.Aircraft achieve can just fly and can be anti-fly, also can negative side take off.
Description
Technical field
The utility model relates to a kind of oar for aircraft, particularly a kind of symmetrical oar and comprise its aircraft.
Background technology
At present, along with the development in model plane market, the user playing model plane gets more and more, simultaneously also more and more higher to the performance requriements of model plane.To new hand, require lower to enter gate threshold, comprise the complexity etc. of model plane price, model plane flight introduction; For professional player, namely require that model plane have higher playability, than if complete more more complicated more cruel stunts, the function etc. of more practicalities can be increased.
Mostly be six axle pattern introductions in the market and add three axle patterns to increase playability, wherein, six axle patterns refer in conjunction with six axle gyroscopes (speed sensor and acceleration pick-up), make aircraft realize from steady; Three axle patterns refer to by using three-axis gyroscope speed sensor, make aircraft keep the current rotary regimes of own motor, thus keep aircraft flight attitude.But six axle patterns of this introduction substantially can not tilt to take off or counter putting is taken off, what harsh takeoff condition can increase player greatly picks up aircraft cost.Such as, inclination or inverted state is just in time in when aircraft lands, at this moment be often difficult to manipulation take off, player has to go to after aircraft is picked up or placed by its forward by position that aircraft lands allows it take off again, bring a lot of burden to player, for new hand, greatly can reduce the recreational of object for appreciation model plane especially.And sometimes, when playing model plane especially out of doors, may due to the place causing aircraft to drop on being difficult to pick up easily or even cannot pick up with a varied topography at all, at this moment may a large amount of manpower and materials will be spent to pick up aircraft, even thoroughly lost aircraft because of picking up less than, bringing massive losses to player.And for three axle patterns, aircraft conversely after just can only fall down, so aircraft cannot realize anti-flying, this defect can limit the space that player develop stunt greatly.
As can be seen here, at least there are two defects in the model of an airplane of the prior art, and the first cannot tilt to take off or counter putting is taken off, and increases player and pick up the cost of aircraft, and it two is to realize anti-flying, and restriction player develops the space of stunt.
Utility model content
The technical problems to be solved in the utility model is to overcome above-mentioned defect of the prior art, provides a kind of symmetrical oar and comprises its aircraft.
The utility model solves above-mentioned technical matters by following technical proposals:
A kind of symmetrical oar, the at least two panels blade comprising a central axle portion and be connected with this central axle portion, this blade comprises a leading edge and a trailing edge, this symmetrical oar from forward position overturn 180 ° be in reverse position time, when this forward position, the leading edge of this blade becomes the trailing edge of this blade when this reverse position, when this forward position, the trailing edge of this blade becomes the leading edge of this blade when this reverse position, its feature is, at least can provide in the service area of lift at this blade, the upper half blade that this blade is intercepted by a curved surface and lower half blade can overlap with another sheet after a slice overturns 180 ° wherein.Wherein, the upper and lower surface of this blade is respectively blade back and blade face, and this curved surface is the virtual curved surface of between this blade back and this blade face.
Preferably, the shape of this blade when this forward position is identical with the shape when this reverse position.Same lift can be produced when no matter blade is in forward position and reverse position so in theory.
Preferably, this blade is two panels, and this two panels blade is relative to this central axle portion Central Symmetry.
Preferably, this central axle portion and those blades one-body molded.The bulk strength of symmetrical oar can be improved like this.
Preferably, this central axle portion is provided with a fixed orifice vertically.For being connected with the rotating shaft of motor.
The utility model also provides a kind of aircraft, and it comprises above-mentioned symmetrical oar.
The utility model also provides a kind of aircraft, and it comprises a fuselage, and its feature is, this aircraft comprises four above-mentioned symmetrical oars, these four symmetrical oars are positioned at the surrounding of fuselage, and wherein the symmetrical oar of two diagonal angle layouts is for rotating forward oar, and the symmetrical oar that another two diagonal angles are arranged is counter-rotating rotors.This is on general quadrotor, be equipped with above-mentioned symmetrical oar, because symmetrical oar can produce roughly the same lift when forward position and reverse position, aircraft just can be flown, can instead fly again.
In the utility model, above-mentioned optimum condition can combination in any on the basis meeting this area general knowledge, obtains each preferred embodiment of the utility model.
Positive progressive effect of the present utility model is: symmetrical oar of the present utility model is due to the profile design of its uniqueness, similar with the shape of reverse position in forward position, thus roughly the same lift can be produced at forward, reverse position, make aircraft anti-and fly to become possibility.Adopt the aircraft of this symmetrical oar to achieve the function that just can fly and can instead fly, expanded the space that player develops stunt, considerably increased the playability of aircraft.Meanwhile, aircraft also possesses the ability of taking off under severe conditions, and especially when aircraft is positioned at inclination or upside down position, aircraft of the present utility model also can take off, and reduces the cost that player picks up aircraft, improves recreational.
Accompanying drawing explanation
Fig. 1 is the structural representation of symmetrical oar (counter-rotating rotors) in forward position of the utility model embodiment 1.
Fig. 2 is the structural representation of symmetrical oar (counter-rotating rotors) at reverse position of the utility model embodiment 1.
Fig. 3 is the plan sketch of symmetrical oar (counter-rotating rotors) in forward position of the utility model embodiment 1.
Fig. 4 is the cutaway view along A-A line in Fig. 3.
Fig. 5 is the plan sketch of symmetrical oar (counter-rotating rotors) at reverse position of the utility model embodiment 1.
Fig. 6 is the cutaway view of the symmetrical oar (counter-rotating rotors) along B-B line in Fig. 4.
Fig. 7 is the cutaway view of the symmetrical oar (counter-rotating rotors) along C-C line in Fig. 4.
Fig. 8 is the cutaway view of the symmetrical oar (counter-rotating rotors) along D-D line in Fig. 4.
Fig. 9 is the structural representation of the aircraft of the utility model embodiment 2.
Figure 10 is the plan sketch of rotating forward oar in forward position of the utility model embodiment 2.
Figure 11 is the cutaway view along A-A line in Figure 10.
Figure 12 is the plan sketch of rotating forward oar at reverse position of the utility model embodiment 2.
Figure 13 is the cutaway view of the rotating forward oar along B-B line in Figure 11.
Figure 14 is the cutaway view of the rotating forward oar along C-C line in Figure 11.
Figure 15 is the cutaway view of the rotating forward oar along D-D line in Figure 11.
Figure 16 is the structural representation showing the symmetrical oar (counter-rotating rotors) of a curved surface in the utility model embodiment 1.
Description of reference numerals
Central axle portion 1
Fixed orifice 11
Blade 2
Leading edge 21
Trailing edge 22
Leading edge 23
Trailing edge 24
Blade back 25
Blade face 26
Aircraft 3
Fuselage 31
Rotate forward oar 4
Counter-rotating rotors 5
Curved surface 6
Upper half blade 7
Lower half blade 8
Detailed description of the invention
Lift two preferred embodiments below, and come by reference to the accompanying drawings clearlyer intactly the utility model to be described.
Embodiment 1
As shown in Figure 1, 2, the two panels blade 2 that the symmetrical oar of the present embodiment comprises a central axle portion 1 and is connected with this central axle portion, this two panels blade is relative to this central axle portion Central Symmetry.Certainly, central axle portion also can connect more than two panels blade, to meet different needs.The surrounding that multi-disc blade can be centered around central axle portion is uniformly distributed.For the symmetrical oar with two panels blade in the present embodiment.This two panels blade includes leading edge 21 and a trailing edge 22, this symmetrical oar from forward position overturn 180 ° be in reverse position time, when this forward position, the leading edge of this blade becomes the trailing edge of this blade when this reverse position, and when this forward position, the trailing edge of this blade becomes the leading edge of this blade when this reverse position.Be positioned at that edge first windward, front when the leading edge of blade refers to that blade rotates windward, trailing edge is then that edge relative with leading edge on blade.Lift is produced when blade rotates windward.Overturn 180 ° to refer to and spun upside down by symmetrical oar, so symmetrical oar will be turned to reverse position from forward position.Before and after upset, the change of frontier and rear, can be understood by composition graphs 1,2.Fig. 1 is the structural representation of the symmetrical oar in forward position, and Fig. 2 is the structural representation of the symmetrical oar at reverse position.In FIG, the leading edge of symmetrical oar is leading edge 21, and the trailing edge of symmetrical oar is trailing edge 22, when symmetrical oar is in the reverse position shown in Fig. 2, the leading edge of symmetrical oar is 23, and the trailing edge of symmetrical oar is 24, in fact, leading edge 21 and trailing edge 24 are same places, and trailing edge 22 and leading edge 23 are same places.In other words, see from top to bottom in FIG, the symmetrical oar of left-hand revolution can produce lift windward, sees from top to bottom in fig. 2, and the symmetrical oar of left-hand revolution can produce lift equally.The upper and lower surface of this blade is respectively blade back 25 and blade face 26.As shown in figure 16, at least can provide in the service area of lift at this blade, the upper half blade 7 that this blade is intercepted by a curved surface 6 and lower half blade 8 can overlap with another sheet after a slice overturns 180 ° wherein.This curved surface is the virtual curved surface of between this blade back and this blade face.One skilled in the art will appreciate that blade can provide the service area of lift mainly to refer to the stage casing of blade, blade root part and the blade tip parts at blade two ends do not belong to the service area that can provide lift.Certainly, in theory, the whole region of blade can be designed to the structure meeting foregoing description, and does not need the service area that is confined to provide lift.
The full symmetric that symmetrical oar can be done in theory, namely the shape of this blade when this forward position is identical with the shape when this reverse position.At this moment, under same rotating speed, the forward lift that symmetrical oar provides and reverse lift are 1:1.
In practical application, under same rotating speed, might not require the forward lift that provides and reverse lift just the same, certain difference can be there is in both, this difference can be made up by adjustment motor power and rotating speed, ensure that blade still provides roughly the same lift at forward and reverse position, so the shape of blade adopts analog structure just passable under two states, namely under forward and reverse position, the invariant position of leading edge and trailing edge, so just can ensure under forward, reverse position, symmetrical oar can provide enough lift for aircraft.
This central axle portion and those blades one-body molded.Certainly, central axle portion and blade also can be fixedly connected with.This central axle portion is provided with vertically a fixed orifice 11, for being connected with the rotating shaft of motor.
Fig. 3 shows the plan sketch of symmetrical oar when forward position.Fig. 4 shows the cutaway view along A-A line in Fig. 3.Fig. 5 then shows the plan sketch of symmetrical oar when reverse position.In order to show the shape and structure of symmetrical oar further, Fig. 6-8 also respectively illustrates the cutaway view along the symmetrical oar of B-B line, C-C line, D-D line in Fig. 4.Wherein, B-B line, C-C line, D-D line position all can provide in the service area of lift at blade.
Symmetrical oar of the present utility model is due to the profile design of its uniqueness, similar with the shape of reverse position in forward position, thus can produce roughly the same lift at forward, reverse position, makes counter the flying of aircraft become possibility.
Embodiment 2
As shown in Figure 9, the aircraft 3 of the present embodiment comprises a fuselage 31, and also comprise four symmetrical oars described as embodiment 1, these four symmetrical oars are positioned at the surrounding of fuselage, wherein the symmetrical oar of two diagonal angle layouts is for rotating forward oar 4, and the symmetrical oar that another two diagonal angles are arranged is counter-rotating rotors 5.
Certainly, it will be understood by those skilled in the art that this aircraft using four rotors as the direct driving force source of flight is exactly quadrotor.Quadrotor generally all can adopt the arrangement of this rotating forward oar and counter-rotating rotors.Certainly, aircraft of the present utility model is without the need to being confined to quadrotor, and namely aircraft comprises four symmetrical oars without the need to being confined to, and also can comprise the symmetrical oar of other quantity.
For rotating forward oar and counter-rotating rotors.See from top to bottom in FIG, what clickwise produced lift is rotate forward oar, and what left-hand revolution produced lift is counter-rotating rotors.Rotating forward oar and counter-rotating rotors are specular.Embodiment 1 specifically describes for the structure of counter-rotating rotors to symmetrical oar.
The structure rotating forward oar can with reference to shown in figure 10-15.Wherein, Figure 10 shows and rotates forward the plan sketch of oar when forward position.Figure 11 shows the cutaway view along A-A line in Figure 10.Figure 12 then shows and rotates forward the plan sketch of oar when reverse position.In order to show the shape and structure rotating forward oar further, Figure 13-15 also respectively illustrates the cutaway view along the symmetrical oar of B-B line, C-C line, D-D line in Figure 11.
It is owing to adopting symmetrical oar that aircraft of the present utility model can play the positive and negative effect flown.No matter this symmetrical oar is rotate forward oar, or counter-rotating rotors, and under its blade is in forward position, and by under the reverse position of inverted for blade (and rotating 180 °), the shape under two kinds of positions is similar; Thus no matter symmetrical oar is just being flown or instead to fly (i.e. aircraft anti-fly), the effect of generation is identical, thus aircraft just can be flown or instead to fly.Meanwhile, aircraft also possesses the ability of taking off under severe conditions, and especially when aircraft is positioned at inclination or upside down position, aircraft of the present utility model also can take off, and reduces the cost that player picks up aircraft, improves recreational.
Although the foregoing describe detailed description of the invention of the present utility model, it will be understood by those of skill in the art that these are only casehistorys, protection domain of the present utility model is defined by the appended claims.Those skilled in the art, under the prerequisite not deviating from principle of the present utility model and essence, can make various changes or modifications to these embodiments, but these change and amendment all falls into protection domain of the present utility model.
Claims (7)
1. a symmetrical oar, the at least two panels blade comprising a central axle portion and be connected with this central axle portion, this blade comprises a leading edge and a trailing edge, this symmetrical oar from forward position overturn 180 ° be in reverse position time, when this forward position, the leading edge of this blade becomes the trailing edge of this blade when this reverse position, when this forward position, the trailing edge of this blade becomes the leading edge of this blade when this reverse position, it is characterized in that, at least can provide in the service area of lift at this blade, the upper half blade that this blade is intercepted by a curved surface and lower half blade can overlap with another sheet after a slice overturns 180 ° wherein.
2. symmetrical oar as claimed in claim 1, is characterized in that, the shape of this blade when this forward position is identical with the shape when this reverse position.
3. symmetrical oar as claimed in claim 1, is characterized in that, this blade is two panels, and this two panels blade is relative to this central axle portion Central Symmetry.
4. symmetrical oar as claimed in claim 1, is characterized in that, this central axle portion and those blades one-body molded.
5. symmetrical oar as claimed in claim 1, is characterized in that, this central axle portion is provided with a fixed orifice vertically.
6. an aircraft, is characterized in that, it comprises as the symmetrical oar in claim 1-5 as described in any one.
7. an aircraft, it comprises a fuselage, it is characterized in that, this aircraft comprises four as the symmetrical oar in claim 1-5 as described in any one, these four symmetrical oars are positioned at the surrounding of fuselage, wherein the symmetrical oar of two diagonal angle layouts is for rotating forward oar, and the symmetrical oar that another two diagonal angles are arranged is counter-rotating rotors.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520016168.1U CN204548501U (en) | 2015-01-09 | 2015-01-09 | Symmetrical oar and the aircraft comprising it |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520016168.1U CN204548501U (en) | 2015-01-09 | 2015-01-09 | Symmetrical oar and the aircraft comprising it |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204548501U true CN204548501U (en) | 2015-08-12 |
Family
ID=53823645
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520016168.1U Active CN204548501U (en) | 2015-01-09 | 2015-01-09 | Symmetrical oar and the aircraft comprising it |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204548501U (en) |
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2015
- 2015-01-09 CN CN201520016168.1U patent/CN204548501U/en active Active
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| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |