CN204956918U - Unmanned aerial vehicle bispin wing structure - Google Patents
Unmanned aerial vehicle bispin wing structure Download PDFInfo
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- CN204956918U CN204956918U CN201520767551.0U CN201520767551U CN204956918U CN 204956918 U CN204956918 U CN 204956918U CN 201520767551 U CN201520767551 U CN 201520767551U CN 204956918 U CN204956918 U CN 204956918U
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- wing
- blade
- paddle
- dcb specimen
- rotor shaft
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Abstract
The utility model discloses an unmanned aerial vehicle bispin wing structure, the rotor is epaxial to be provided with blunt oval radome fairing, the wing section radome fairing is provided with on the rotation axis, subassembly airflow separation and pneumatic interference drag can be reduces to operation to the bispin wing reaches the drag reduction effect, rotor axle and axial are provided with flexible roof beam between, can make the bigger angle displacement of acquisition between of rotor axle and axial to satisfy the paddle motion of hunting, the paddle sets up to throwing the thing paddle, windage in the time of can reducing the operation of the bispin wing, throw thing paddle trailing edge and be provided with one -way glass fiber trailing -edge strip, can improve the paddle rigidity of hunting, throwing thing paddle leading edge and being provided with plumbous counter weight strip, can adjust the tangential focus of paddle, this unmanned aerial vehicle bispin wing structure has the advantage that the resistance is little, the performance is good, has wide market prospect.
Description
Technical field
The utility model relates to unmanned plane field, is specifically related to a kind of unmanned plane DCB Specimen structure.
Background technology
Coaxial double-rotor helicopter has the two secondary rotors up and down rotated around same theory axis a positive and a negative, contrary owing to turning to, the moment of torsion that two secondary rotors produce mutually balances under steady state of flight, always directional control can be realized apart from differential generation overbalance moment of torsion by so-called upper and lower rotor, coaxial double-rotary wing at helicopter in-flight, be lifting surface and in length and breadth to the controlsurface with course, co-axial helicopter also exists aerodynamic interference all to some extent under various state of flight, show as rotor to the impact of the purling of lower rotor and lower rotor to the impact of the fluidised form of upper rotor.
Utility model content
Technical problem to be solved in the utility model is to provide a kind of unmanned plane DCB Specimen structure, to solve the above-mentioned multinomial defect caused in prior art.
For achieving the above object, the utility model provides following technical scheme: a kind of unmanned plane DCB Specimen structure, described DCB Specimen structure is symmetrical structure, described DCB Specimen structure comprises S. A., wing, described wing is divided into top wing and lower wing, described top wing and lower wing be upper and lower longitudinal arrangement on the rotary shaft, described wing comprises rotor shaft and blade, described blade and rotor shaft are by being axially comparatively connected, described rotor shaft is provided with connecting bore, and described wing is connected with S. A. by connecting bore.
Preferably, described rotor shaft is provided with fairing, the shape of described fairing is blunt ellipse, described S. A. is provided with aerofoil profile fairing.
Preferably, described rotor shaft and axially comparatively between be provided with flexible beam.
Preferably, described blade is set to parabolic blade, described parabolic blade comprises C shape crossbeam and glass woven fabric covering, described C shape crossbeam is strut member, described glass woven fabric covering is laid along the exhibition of C shape crossbeam to one-tenth 45 degree of angles, is provided with polyvinyl chloride foam in the cavity between described C shape crossbeam and glass woven fabric covering.
Preferably, described parabolic blade trailing edge is provided with one-way glass fiber trailing-edge strip, and described parabolic blade leading edge is provided with plumbous counter weight strip.
The beneficial effect of above technical scheme is adopted to be: a kind of unmanned plane DCB Specimen structure of the utility model structure, described rotor shaft is provided with blunt oval fairing, described S. A. is provided with aerofoil profile fairing, assembly burbling and pneumatic interference drag can be reduced, thus drag-reduction effect is reached to the running of DCB Specimen, described rotor shaft and axially comparatively between be provided with flexible beam, can make rotor shaft and axially compared with between obtain larger angular transposition, thus meet blade lag motion, described blade is set to parabolic blade, windage during DCB Specimen running can be reduced, described parabolic blade trailing edge is provided with one-way glass fiber trailing-edge strip, blade lagging rigidity can be improved, described parabolic blade leading edge is provided with plumbous counter weight strip, the tangential center of gravity of blade can be adjusted, it is little that this unmanned plane DCB Specimen structure has resistance, the advantage that performance is good, there are wide market outlook.
Accompanying drawing explanation
Fig. 1 is the structural representation of a kind of unmanned plane DCB Specimen of the utility model structure.
Fig. 2 is the structural representation of rotor.
Fig. 3 is the structural representation of blade.
Fig. 4 is the structural representation of S. A. and rotor shaft.
In figure: 1-S. A., 2-top wing, 3-lower wing, 4-rotor shaft, 5-parabolic blade, 6-are axial comparatively, the plumbous counter weight strip of the blunt oval fairing of 7-connecting bore, 8-, 9-aerofoil profile fairing, 10-flexible beam, 11-C shape crossbeam, 12-glass woven fabric covering, 13-polyvinyl chloride foam, 14-one-way glass fiber trailing-edge strip, 15-.
Detailed description of the invention
Preferred implementation of the present utility model is described in detail below in conjunction with accompanying drawing.
Fig. 1 shows detailed description of the invention of the present utility model: a kind of unmanned plane DCB Specimen structure, described DCB Specimen structure is symmetrical structure, described DCB Specimen structure comprises S. A. 1, wing, described wing is divided into top wing 2 and lower wing 3, described top wing 2 and lower wing 3 be upper and lower longitudinal arrangement on S. A. 1, described wing comprises rotor shaft 4 and blade, described blade and rotor shaft 4 are by being axially connected compared with 6, described rotor shaft 4 is provided with connecting bore 7, and described wing is connected with S. A. 1 by connecting bore 7.
In addition, as shown in Figure 2, described rotor shaft 4 is provided with blunt oval fairing 8, described S. A. 1 is provided with aerofoil profile fairing 9, described rotor shaft 4 and axis are comparatively provided with flexible beam 10 between 6, described blade is set to parabolic blade 5, described parabolic blade 5 comprises C shape crossbeam 11 and glass woven fabric covering 12, described C shape crossbeam 11 is strut member, described glass woven fabric covering 12 is opened up along C shape crossbeam 11 and is laid to one-tenth 45 degree of angles, polyvinyl chloride foam 13 is provided with in cavity between described C shape crossbeam 11 and glass woven fabric covering 12, described parabolic blade 5 trailing edge is provided with one-way glass fiber trailing-edge strip 14, described parabolic blade 5 leading edge is provided with plumbous counter weight strip 15.
Based on above-mentioned, the utility model provides a kind of unmanned plane DCB Specimen structure, described rotor shaft is provided with blunt oval fairing, described S. A. is provided with aerofoil profile fairing, assembly burbling and pneumatic interference drag can be reduced, thus drag-reduction effect is reached to the running of DCB Specimen, described rotor shaft and axially comparatively between be provided with flexible beam, can make rotor shaft and axially compared with between obtain larger angular transposition, thus meet blade lag motion, described blade is set to parabolic blade, windage during DCB Specimen running can be reduced, described parabolic blade trailing edge is provided with one-way glass fiber trailing-edge strip, blade lagging rigidity can be improved, described parabolic blade leading edge is provided with plumbous counter weight strip, the tangential center of gravity of blade can be adjusted, it is little that this unmanned plane DCB Specimen structure has resistance, the advantage that performance is good, there are wide market outlook.
Above-described is only preferred implementation of the present utility model; it should be pointed out that for the person of ordinary skill of the art, under the prerequisite not departing from the utility model creation design; can also make some distortion and improvement, these all belong to protection domain of the present utility model.
Claims (5)
1. a unmanned plane DCB Specimen structure, it is characterized in that: described DCB Specimen structure is symmetrical structure, described DCB Specimen structure comprises S. A., wing, described wing is divided into top wing and lower wing, described top wing and lower wing be upper and lower longitudinal arrangement on the rotary shaft, and described wing comprises rotor shaft and blade, and described blade and rotor shaft are by being axially comparatively connected, described rotor shaft is provided with connecting bore, and described wing is connected with S. A. by connecting bore.
2. a kind of unmanned plane DCB Specimen structure according to claim 1, is characterized in that: described rotor shaft is provided with fairing, and the shape of described fairing is blunt ellipse, described S. A. is provided with aerofoil profile fairing.
3. a kind of unmanned plane DCB Specimen structure according to claim 1, is characterized in that: described rotor shaft and axially comparatively between be provided with flexible beam.
4. a kind of unmanned plane DCB Specimen structure according to claim 1, it is characterized in that: described blade is set to parabolic blade, described parabolic blade comprises C shape crossbeam and glass woven fabric covering, described C shape crossbeam is strut member, described glass woven fabric covering is laid along the exhibition of C shape crossbeam to one-tenth 45 degree of angles, is provided with polyvinyl chloride foam in the cavity between described C shape crossbeam and glass woven fabric covering.
5. a kind of unmanned plane DCB Specimen structure according to claim 4, it is characterized in that: described parabolic blade trailing edge is provided with one-way glass fiber trailing-edge strip, described parabolic blade leading edge is provided with plumbous counter weight strip.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520767551.0U CN204956918U (en) | 2015-09-29 | 2015-09-29 | Unmanned aerial vehicle bispin wing structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520767551.0U CN204956918U (en) | 2015-09-29 | 2015-09-29 | Unmanned aerial vehicle bispin wing structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204956918U true CN204956918U (en) | 2016-01-13 |
Family
ID=55051999
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520767551.0U Active CN204956918U (en) | 2015-09-29 | 2015-09-29 | Unmanned aerial vehicle bispin wing structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204956918U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112550691A (en) * | 2021-01-06 | 2021-03-26 | 惠阳航空螺旋桨有限责任公司 | Helicopter rotor blade |
-
2015
- 2015-09-29 CN CN201520767551.0U patent/CN204956918U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112550691A (en) * | 2021-01-06 | 2021-03-26 | 惠阳航空螺旋桨有限责任公司 | Helicopter rotor blade |
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| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |