CN208198825U - A kind of aerodone fuselage of low windage - Google Patents
A kind of aerodone fuselage of low windage Download PDFInfo
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- CN208198825U CN208198825U CN201820666951.6U CN201820666951U CN208198825U CN 208198825 U CN208198825 U CN 208198825U CN 201820666951 U CN201820666951 U CN 201820666951U CN 208198825 U CN208198825 U CN 208198825U
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- wing
- fuselage
- auxiliary wing
- buckle
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Abstract
The utility model discloses a kind of aerodone fuselage of low windage, including fuselage main body and the wing being connected in fuselage main body；Fuselage main body includes head, fuselage, afterbody, which includes first level wing, the second horizontal wings, vertical tail；The left and right ends of first level wing are connected separately with left end auxiliary wing, right end auxiliary wing；The left and right ends of first level wing are provided with first connecting portion, and left end auxiliary wing, right end auxiliary wing are equipped with second connecting portion；First connecting portion has the first connecting groove, is recessed with the first card slot on the front and back cell wall of the first connecting groove；Second connecting portion has the first Connection protrusion, and the front and rear sides of the first Connection protrusion are equipped with the first buckle；First buckle adapts in corresponding first card slot；The outer of first connecting groove is equipped with the first flange around the first connecting groove because of on first level wing；Whereby, reduce the windage of aerodone, and be dismounted easily, reduce the occupancy of placement space.
Description
Technical field
The utility model relates to aerodone field technologies, refer in particular to a kind of aerodone fuselage of low windage.
Background technique
With the continuous development of science and technology with innovation, high-tech product also plays more next in people's daily life
More important role.Such as aerial model airplane, it frequently occurs in daily life as drawn banner, taking photo by plane, play games, sending fastly
It passs, embodies the extensive of the powerful and purposes of its function significantly.But the most structure wind of aerial model airplane in the prior art
It hinders larger, causes cruise duration shorter, and can not dismantle mostly between wing and fuselage, biggish placement space can be occupied,
There are also demountable aerial model airplanes, but its disassembly and assembly structure is complex, and between package assembly it is easy to increase its
Windage and influence cruise duration.
Therefore, it is necessary to develop the new technical solution of one kind to solve the above problems.
Utility model content
In view of this, the utility model is in view of the existing deficiencies of the prior art, main purpose is to provide a kind of low windage
Aerodone fuselage, it is larger which solve windage and cause cruise duration is shorter, dismounting is inconvenient to occupy biggish placement space etc.
Problem.
To achieve the above object, the utility model is using following technical solution:
A kind of aerodone fuselage of low windage, including fuselage main body and the wing being connected in fuselage main body；The fuselage
Main body includes head, fuselage, afterbody, which includes first level wing, the second horizontal wings, vertical tail；This
One horizontal wings are fixed on leading portion in fuselage, and second horizontal wings, vertical tail are both secured to afterbody；
The left and right ends of the first level wing are removably connected respectively left end auxiliary wing, right end auxiliary wing；
The first level wing, left end auxiliary wing, right end auxiliary wing are concave-convex aerofoil profile；The left and right ends of the first level wing
It is provided with the first connecting portion for connecting auxiliary wing, correspondingly, is accordingly set on left end auxiliary wing, right end auxiliary wing
It is equipped with second connecting portion；The second connecting portion is packed into corresponding first connecting portion；
The first connecting portion has recessed before the first connecting groove on first level wing, first connecting groove
The first card slot is recessed on cell wall afterwards；The second connecting portion has the first Connection protrusion, the front and back two of first Connection protrusion
Side is equipped with the first buckle；First buckle adapts in corresponding first card slot；
The outer of first connecting groove is equipped with the first flange because of surrounding the first connecting groove on first level wing, this
One flange is the streamlined structure from after going to, which penetrates through to the first flange outer sides；In left end auxiliary wing,
The first recess is correspondingly provided on right end auxiliary wing, the first flange adapts to the outside of corresponding first recess, the first flange
The outer surface of outer end and the outer surface of corresponding left end auxiliary wing or right end auxiliary wing form flush type split；
The left end auxiliary wing, right end auxiliary wing all have the first leading edge, the first rear, the first lateral margin, the first leading edge
Be it is streamlined, the left and right sides end of the first lateral margin is provided with the first upward dihedral of angle；Second horizontal wings tool
Have the second leading edge, the second rear, the second lateral margin, the second leading edge be it is streamlined, the left and right sides end of the second lateral margin all has the
Two dihedrals；The direction of second dihedral and the direction of the first dihedral are consistent.
As a preferred embodiment, one end of second horizontal wings is provided with third interconnecting piece, after the fuselage
The left and right ends in section region are provided with the 4th interconnecting piece, and third interconnecting piece is dismountable to be adapted on the 4th interconnecting piece.
As a preferred embodiment, the third interconnecting piece has the second Connection protrusion, the front and back two of the second Connection protrusion
Side is equipped with the second buckle；4th interconnecting piece all have it is recessed in the second connecting groove on aft body region, second
The second card slot is recessed on the front and back cell wall of connecting groove；Second buckle adapts in the second card slot.
As a preferred embodiment, the outer of second connecting groove is equipped with the because of surrounding the second connecting groove on fuselage
Two flanges, the second flange are the streamlined structure from after going to, which penetrates through to the second flange outer sides.
As a preferred embodiment, the first level wing is shaped on fuselage.
As a preferred embodiment, the first level wing has first level wing EPP main body and the first stiffening plate,
First stiffening plate is laterally extended formula and is located in first level wing EPP main body, and aforementioned first card slot shape is corresponded in the first stiffening plate
At there is resigning mouthful, lateral bayonet is respectively formed in the two sides of resigning mouthful；And left end auxiliary wing, right end auxiliary wing are equal
With auxiliary wing EPP main body and the second stiffening plate, the second stiffening plate is laterally extended formula and is located in auxiliary wing EPP main body, preceding
State the outer end that the first buckle is integrally connected to the second stiffening plate, the first buckle is stretched out from the outer end of auxiliary wing EPP main body, the
The forward and backward side of one buckle is convexly equipped with back-off portion, and back-off portion adapts in corresponding lateral buckle.
As a preferred embodiment, first buckle includes that there are two the buckle arm of the symmetrical spacing arrangement in front and back, front sides
Buckle arm on front side of be convexly equipped with aforementioned back-off portion, be convexly equipped with aforementioned back-off portion on rear side of the buckle arm of rear side.
As a preferred embodiment, the first level wing is connected into fuselage, head, afterbody, vertical tail
There is integral type EPP main body and the inserted intracorporal integral type of integral type EPP master that is located to add for integral structure, the integral structure
Strong plate, integral type stiffening plate are in cross-shaped structure, and aforementioned first stiffening plate is located at the left and right side position of integral type stiffening plate.
The utility model has clear advantage and beneficial effect compared with prior art, specifically, by above-mentioned technology
After scheme is it is found that its first flange for mainly passing through streamlined structure can make the first buckle be caught in the first card slot, avoid
The aerodone windage that first connecting portion, second connecting portion are subject to since connection gap is excessive in flight course is excessive to ask
Topic, to reduce the windage of aerodone；By by the first dihedral, the second dihedral direction be set as the same direction, it can be achieved that
Stable airline operation；First level wing is removably connected left end auxiliary wing, right end auxiliary wing, is also beneficial to normal
Rule wing tip easily occur in the case of losing, wounding, can by the dismounting of left end auxiliary wing, right end auxiliary wing come
Maintenance replacement, saves cost；
And after the second buckle capable of being made to be caught in the second card slot by the second flange of streamlined structure, avoid
The excessive problem of the windage that connection gap between two horizontal wings and fuselage is excessive and is subject to, further reduces aerodone
Windage；And be dismounted easily, reduce the occupancy of placement space；
In addition, the setting of stiffening plate improves the durability of product so that overall structural strength is more preferable.
For structure feature, technological means and its specific purposes achieved and function for more clearly illustrating the utility model
Can, the utility model is described in further detail with specific embodiment with reference to the accompanying drawing.
Detailed description of the invention
Fig. 1 is the general configuration schematic diagram of the embodiment one of the utility model；
Fig. 2 is the substantially decomposition texture schematic diagram of the embodiment one of the utility model；
Fig. 3 is the partial enlargement diagram of Fig. 2；
Fig. 4 is the partial structural diagram of the embodiment two of the utility model；
Fig. 5 is the cross section structure schematic diagram of the embodiment one of the utility model.
Description of drawing identification:
1, head 2, fuselage
201, the second flange 3, afterbody
4, first level wing 5, the second horizontal wings
401, first connecting portion 402, the first connecting groove
403, the first card slot 404, the first flange
501, the second leading edge 502, the second rear
503, the second lateral margin 504, the second dihedral
6, vertical tail 7, left end auxiliary wing
8, right end auxiliary wing 701, second connecting portion
702, the first Connection protrusion 703, first buckles
703 ', first the 704, first leading edge of buckle
705, the first rear 706, the first lateral margin
707, the first dihedral 708, the first recess
9, the first stiffening plate 10, the second stiffening plate.
Specific embodiment
It please refers to shown in Fig. 1 to Fig. 5, that show the specific structures of the embodiment of the utility model.
The aerodone fuselage of the low windage includes fuselage main body and the wing that is connected in fuselage main body；Fuselage master
Body includes head 1, fuselage 2, afterbody 3, which includes first level wing 4, the second horizontal wings 5, vertical tail 6；
The first level wing 4 is fixed on leading portion in fuselage 2, and second horizontal wings 5, vertical tail 6 are both secured to afterbody 3.
The left and right ends of the first level wing 4 are removably connected respectively left end auxiliary wing 7, right end auxiliary wing
8；The first level wing 4, left end auxiliary wing 7, right end auxiliary wing 8 are concave-convex aerofoil profile；A left side for the first level wing 4
Right both ends are provided with the first connecting portion 401 for connecting auxiliary wing, correspondingly, in left end auxiliary wing 7, right end auxiliary machine
Second connecting portion 701 is correspondingly provided on the wing 8；The second connecting portion 701 is packed into corresponding first connecting portion 401；First company
Socket part 401 has recessed in the first connecting groove 402 on first level wing 4, the front and back cell wall of first connecting groove 402
On be recessed with the first card slot 403；The second connecting portion 701 has the first Connection protrusion 702, first Connection protrusion 702
Front and rear sides are equipped with the first buckle 703；First buckle 703 adapts in corresponding first card slot 403；First connecting groove
402 outer is equipped with the first flange 404 because of surrounding the first connecting groove 402 on first level wing 4, which is
Streamlined structure from after going to, first connecting groove 402 perforation to 404 outside of the first flange；In left end auxiliary wing 7,
The first recess 708 is correspondingly provided on right end auxiliary wing 8, the first flange 404 adapts to the outside of corresponding first recess 708,
The outer surface of the outer end of first flange 404 forms with the outer surface of corresponding left end auxiliary wing 7 or right end auxiliary wing 8 and flushes
Formula split.Herein, it after the first flange 404 of the streamlined structure can make the first buckle 703 be caught in the first card slot 403, keeps away
The aerodone windage that first connecting portion 401, second connecting portion 701 are subject to since connection gap is excessive in flight course is exempted from
Excessive problem, to reduce the windage of aerodone.
The left end auxiliary wing 7, right end auxiliary wing 8 all have the first leading edge 704, the first rear 705, the first lateral margin
706, the first leading edge 704 be it is streamlined, the left and right sides end of the first lateral margin 706 is provided with the first upward dihedral of angle
707；Second horizontal wings 5 have the second leading edge 501, the second rear 502, the second lateral margin 503, and the second leading edge 501 is streamline
Type, the left and right sides end of the second lateral margin 503 all have the second dihedral 504；Direction and the first dihedral of second dihedral 504
707 direction is consistent.Herein, by setting the same direction, it can be achieved that flat for the direction of the first dihedral 707, the second dihedral 504
Steady airline operation.
One end of second horizontal wings 5 is provided with third interconnecting piece, the left and right ends in the back segment region of the fuselage 2
It is provided with the 4th interconnecting piece, third interconnecting piece is dismountable to be adapted on the 4th interconnecting piece；The third interconnecting piece has second
Connection protrusion, the front and rear sides of the second Connection protrusion are equipped with the second buckle；4th interconnecting piece all has recessed in fuselage 2
The second connecting groove on back segment region is recessed with the second card slot on the front and back cell wall of the second connecting groove；Second buckle is suitable
Assigned in the second card slot；The outer of second connecting groove is equipped with the second flange around the second connecting groove because of on fuselage 2
201, the second flange 201 is the streamlined structure from after going to, which penetrates through to 201 outside of the second flange.In
In the present embodiment, the third interconnecting piece, the 4th interconnecting piece structure respectively with first connecting portion 401, second connecting portion 701
Structure is identical (as shown in Figure 2 first connecting portion 401,701 structure of second connecting portion), and only size dimension is different.Herein, the stream
After second flange 201 of linear structure can make the second buckle be caught in the second card slot, aerodone is avoided in flight course
The excessive problem of the windage that connection gap between second horizontal wings 5 and fuselage 2 is excessive and is subject to, to further reduce
The windage of aerodone.
The first level wing 4 has first level wing EPP main body and the first stiffening plate 9, and the first stiffening plate 9 is laterally
Extension is located in first level wing EPP main body, and aforementioned first card slot 403 is corresponded in the first stiffening plate 9 and is formed with resigning mouthful,
Lateral bayonet is respectively formed in the two sides of resigning mouthful；And left end auxiliary wing 7, right end auxiliary wing 8 all have auxiliary machine
Wing EPP main body and the second stiffening plate 10, the second stiffening plate 10 are laterally extended formula and are located in auxiliary wing EPP main body, and aforementioned first
Buckle 703 is integrally connected to the outer end of the second stiffening plate 10, and the first buckle 703 is stretched out from the outer end of auxiliary wing EPP main body,
The forward and backward side of first buckle 703 is convexly equipped with back-off portion, and back-off portion adapts in corresponding lateral buckle.
As shown in figure 4, first buckle 703 ' includes that there are two the cards of the symmetrical spacing arrangement in front and back in embodiment two
Buckle arm is convexly equipped with aforementioned back-off portion on front side of the buckle arm of front side, is convexly equipped with aforementioned back-off portion on rear side of the buckle arm of rear side.
In addition, in this present embodiment, the first level wing 4 and fuselage 2, head 1, afterbody 3, vertical tail 6
The formula that links into an integrated entity structure, the integral structure have integral type EPP main body and it is inserted be located at integral type EPP master intracorporal one
Body formula stiffening plate, integral type stiffening plate are in cross-shaped structure, and aforementioned first stiffening plate 9 is located at the left and right side of integral type stiffening plate
Position.
In conclusion the design focal point of the utility model is, mainly pass through the first flange energy of streamlined structure
So that after first is caught in the first card slot, avoid aerodone in flight course first connecting portion, second connecting portion by
In the excessive problem of the windage that connection gap is excessive to be subject to, to reduce the windage of aerodone；By by the first dihedral,
The direction of two dihedrals is set as the same direction, it can be achieved that stable airline operation；First level wing is removably connected left end
Auxiliary wing, right end auxiliary wing are also beneficial in the case of losing, wounding easily occur in the tip of conventional airfoil, Ke Yitong
Cross left end auxiliary wing, the dismounting of right end auxiliary wing is replaced to repair, saving cost；And pass through streamlined structure
After two flanges can make the second buckle be caught in the second card slot, the connection gap mistake between the second horizontal wings and fuselage is avoided
The excessive problem of windage that is big and being subject to, further reduces the windage of aerodone；And be dismounted easily, reduce placement space
It occupies；In addition, the setting of stiffening plate improves the durability of product so that overall structural strength is more preferable.
The above descriptions are merely preferred embodiments of the present invention, not makees to the technical scope of the utility model
Any restrictions, therefore any trickle amendment made by the above technical examples according to the technical essence of the present invention, equivalent change
Change and modify, is still within the scope of the technical solutions of the present invention.
Claims (8)
1. a kind of aerodone fuselage of low windage, it is characterised in that: including fuselage main body and the machine being connected in fuselage main body
The wing；The fuselage main body includes head, fuselage, afterbody, which includes first level wing, the second horizontal wings, vertical
Empennage；The first level wing is fixed on leading portion in fuselage, and second horizontal wings, vertical tail are both secured to afterbody；
The left and right ends of the first level wing are removably connected respectively left end auxiliary wing, right end auxiliary wing；This
One horizontal wings, left end auxiliary wing, right end auxiliary wing are concave-convex aerofoil profile；The left and right ends of the first level wing are arranged
There is the first connecting portion for connecting auxiliary wing, correspondingly, is correspondingly provided on left end auxiliary wing, right end auxiliary wing
Second connecting portion；The second connecting portion is packed into corresponding first connecting portion；
The first connecting portion has recessed in the first connecting groove on first level wing, the front and back slot of first connecting groove
The first card slot is recessed on wall；The second connecting portion has the first Connection protrusion, and the front and rear sides of first Connection protrusion are equal
Equipped with the first buckle；First buckle adapts in corresponding first card slot；
The outer of first connecting groove is equipped with the first flange because of surrounding the first connecting groove on first level wing, this is first convex
Edge is the streamlined structure from after going to, which penetrates through to the first flange outer sides；In left end auxiliary wing, right end
The first recess is correspondingly provided on auxiliary wing, the first flange adapts to the outside of corresponding first recess, the outer end of the first flange
The outer surface in portion and the outer surface of corresponding left end auxiliary wing or right end auxiliary wing form flush type split；
The left end auxiliary wing, right end auxiliary wing all have the first leading edge, the first rear, the first lateral margin, and the first leading edge is
Streamlined, the left and right sides end of the first lateral margin is provided with the first upward dihedral of angle；Second horizontal wings have the
Two leading edges, the second rear, the second lateral margin, the second leading edge be it is streamlined, it is anti-that the left and right sides end of the second lateral margin all has second
Angle；The direction of second dihedral and the direction of the first dihedral are consistent.
2. a kind of aerodone fuselage of low windage according to claim 1, it is characterised in that: second horizontal wings
One end is provided with third interconnecting piece, and the left and right ends in the back segment region of the fuselage are provided with the 4th interconnecting piece, third interconnecting piece
It is dismountable to adapt on the 4th interconnecting piece.
3. a kind of aerodone fuselage of low windage according to claim 2, it is characterised in that: the third interconnecting piece has
Second Connection protrusion, the front and rear sides of the second Connection protrusion are equipped with the second buckle；4th interconnecting piece all have it is recessed in
The second connecting groove on aft body region is recessed with the second card slot on the front and back cell wall of the second connecting groove；Second card
Button adapts in the second card slot.
4. a kind of aerodone fuselage of low windage according to claim 3, it is characterised in that: second connecting groove
The second flange is equipped with because of surrounding the second connecting groove on fuselage outside, and the second flange is the streamlined structure after go to, this
Two connecting grooves are penetrated through to the second flange outer sides.
5. a kind of aerodone fuselage of low windage according to claim 1, it is characterised in that: the first level wing one
It is body formed on fuselage.
6. a kind of aerodone fuselage of low windage according to claim 1, it is characterised in that: the first level wing tool
There are first level wing EPP main body and the first stiffening plate, the first stiffening plate is laterally extended formula and is located at first level wing EPP main body
It is interior, aforementioned first card slot is corresponded in the first stiffening plate and is formed with resigning mouthful, is respectively formed with lateral bayonet in the two sides of resigning mouthful；
And left end auxiliary wing, right end auxiliary wing all have auxiliary wing EPP main body and the second stiffening plate, the second stiffening plate is horizontal
It is located in auxiliary wing EPP main body to extension, aforementioned first buckle is integrally connected to the outer end of the second stiffening plate, the first buckle
It is stretched out from the outer end of auxiliary wing EPP main body, is convexly equipped with back-off portion in the forward and backward side of the first buckle, back-off portion adapts to phase
In the lateral buckle answered.
7. a kind of aerodone fuselage of low windage according to claim 6, it is characterised in that: it is described first buckle include
The buckle arms of the symmetrical spacing arrangement in two front and backs are convexly equipped with aforementioned back-off portion, the buckle arm of rear side on front side of the buckle arm of front side
Rear side be convexly equipped with aforementioned back-off portion.
8. a kind of aerodone fuselage of low windage according to claim 6, it is characterised in that: the first level wing with
Fuselage, head, afterbody, vertical tail link into an integrated entity formula structure, which has integral type EPP main body and edge
Embedded is located at the intracorporal integral type stiffening plate of integral type EPP master, and integral type stiffening plate is in cross-shaped structure, aforementioned first stiffening plate
Positioned at the left and right side position of integral type stiffening plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820666951.6U CN208198825U (en) | 2018-05-07 | 2018-05-07 | A kind of aerodone fuselage of low windage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820666951.6U CN208198825U (en) | 2018-05-07 | 2018-05-07 | A kind of aerodone fuselage of low windage |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208198825U true CN208198825U (en) | 2018-12-07 |
Family
ID=64519013
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820666951.6U Active CN208198825U (en) | 2018-05-07 | 2018-05-07 | A kind of aerodone fuselage of low windage |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN208198825U (en) |
-
2018
- 2018-05-07 CN CN201820666951.6U patent/CN208198825U/en active Active
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