CN108261785A - Unpowered flight mechanism - Google Patents
Unpowered flight mechanism Download PDFInfo
- Publication number
- CN108261785A CN108261785A CN201611257391.0A CN201611257391A CN108261785A CN 108261785 A CN108261785 A CN 108261785A CN 201611257391 A CN201611257391 A CN 201611257391A CN 108261785 A CN108261785 A CN 108261785A
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- CN
- China
- Prior art keywords
- fuselage
- wing
- flight mechanism
- mechanism according
- empennage
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- 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.)
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Classifications
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- A—HUMAN NECESSITIES
- A63—SPORTS; GAMES; AMUSEMENTS
- A63H—TOYS, e.g. TOPS, DOLLS, HOOPS OR BUILDING BLOCKS
- A63H27/00—Toy aircraft; Other flying toys
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- Toys (AREA)
Abstract
The present invention relates to a kind of unpowered flight mechanism, comprising：One fuselage,The front side of fuselage is equipped with a head,Rear side is equipped with an empennage,And it is respectively arranged on the left side and the right side a wing in fuselage,Head is equipped with an introducing port for entering fuselage for air,Fuselage is equipped with a conducting orifice connected with outside,And the rear side of fuselage is equipped with an export mouth,And fuselage is internally provided with one by introducing port,The flow-guiding channel that conducting orifice and export mouth are interconnected each other,Pass through the design of flow-guiding channel of the present invention,So that unpowered flight mechanism of the present invention is launched to during airflight,Air can enter fuselage via introducing port,And the design of conducting orifice and export mouth is communicated in using flow-guiding channel,Air just can be shunted and be left simultaneously by body upper and fuselage tail end,Form the air-flow in two kinds of different paths,Thereby stablize the flight stability of unpowered flight mechanism of the present invention,And the probability that fuselage rocks is greatly reduced.
Description
Technical field
The present invention relates to a kind of aviation mechanism, espespecially a kind of thrown away aviation mechanism in itself by performing projectile motion is thrown out
It goes, and aviation mechanism is caused to empty the skyborne amusement and recreation equipment of flight.
Background technology
The mankind in the air with air force is theoretical and buoyancy, it is designed go out aviation mechanism have origin history, very
Before 2000 can be traced back to, aviation mechanism kite, bamboo dragonfly, paper helicopter, aircraft, hang gliding, Aircraft etc. such as, wherein again
Engine can be sub-divided into and without two kinds of different dynamic sources of engine.
And as in the aviation mechanism of recreational use, if referring to prevalence in fashion and making ease, answer
Based on toy airplane, and toy airplane can be divided into electronic operated toy airplane with engine or without engine
Fan-fold paper (making materials such as paper, cardboard, wood chip, sheet) unpowered type toy airplane.
Wherein, unpowered type toy airplane has that (consumer's purchase intention is higher) at low cost, everyone all takes conveniently
Making material and make at any time, using it is simple the advantages that, but also have be easily damaged simultaneously, single flight time and flying distance
It is short, fuselage is thin, flight rocks that unstable, flare maneuver is dull, easily fall suddenly, flight shape is greatly made soon
User is thrown away angle of departure degree/or thrown away with difference throws the missings such as skill influence.
Invention content
It is a primary object of the present invention to provide it is a kind of have rock more by a small margin and be capable of stabilized flight it is unpowered fly
Row mechanism by designing a diversion space connected with outside, directs the air into and exports, actually reach stable machine respectively
The effect of body.
To reach the purpose, the present invention provides a kind of unpowered flight mechanism, comprising：One fuselage, the front side of the fuselage
Equipped with a head, rear side is equipped with an empennage, and in the wing that is respectively arranged on the left side and the right side of the fuselage, it is characterised in that：Institute
State the introducing port that head enters the fuselage equipped with one for air, the fuselage is equipped with one and the external conducting orifice connected, and institute
The rear side for stating fuselage is equipped with an export mouth, and the fuselage is internally provided with one by the introducing port, conducting orifice and export mouth
Interconnected flow-guiding channel each other.
In a preferable possible embodiments, the flow-guiding channel towards the upside of the fuselage width, less than the machine
The width of the downside of body so that the side wall of the flow-guiding channel is rendered as an inclined pattern.
Moreover, the wing is collectively formed by a first part and a second part, the first part is by the head
Portion is extended to form towards fuselage, and the second part is extended to form by the fuselage towards empennage, and the first part
Thickness is more than the thickness of the second part so that and the wing is rendered as one by the head towards the thinning pattern of empennage,
Also, the wing width of the first part is incrementally increased from front to back, the wing width of the second part from front to back by
Gradually reduce, the width of the wing, which is rendered as one, first increases the pattern reduced afterwards.
Wherein, the area of the introducing port is less than the area of the export mouth.
In a preferable possible embodiments, the wing is connected to the fuselage in a manner that oblique angle intersects.
Wherein, the rear of the export mouth of the fuselage is connected to the empennage activity, the width of the empennage is by institute
The rear for stating export mouth forms a tapered pattern outwardly, can carry out the swing of upper and lower directions, and it is opposite to change the empennage
In the relative angle of the fuselage.
In a preferable possible embodiments, the bottom of the fuselage is further provided with a bottom wing.
Separately in a preferable possible embodiments, the bottom of the fuselage is further provided with a clump weight, the clump weight point
It is distributed between the butting section and the bottom wing.
By preceding description it is found that the advantage of the invention is that：When unpowered flight mechanism of the present invention is delivered to external force, and then
Empty flight when aerial, just can by flow-guiding channel respectively with the introducing port on head, the conducting orifice of fuselage surface and position
The design of export mouth on rear side of fuselage forms one for flowing into fuselage and the rear water conservancy diversion road for disperseing outflow fuselage in air elder generation
Diameter is designed by such guide flow path for air flowing disengaging, fuselage is stablized and can be reached fuselage is greatly reduced shakes
The degree of rolling manipulates the more a variety of flare maneuver of aircraft progress so as to be conducive to operator, such as：Floating, flat flies etc. at convolution.
In addition, the area design of invention introducing port so just can into the area for being respectively smaller than conducting orifice and export mouth
Air is enough allowed by the introducing port entrance compared with small area, and is guided respectively by the conducting orifice and export mouth of larger area and leaves fuselage,
An air pressure difference is formed, while allows fuselage that there is a flight speed faster.
And the shape of flow-guiding channel of the present invention is also a feature, flow-guiding channel is towards the width on the upside of fuselage, less than direction
Width on the downside of fuselage so that the shape of flow-guiding channel forms a trapezoidal pattern, and the side wall of flow-guiding channel is rendered as an inclination
Pattern, such design is so that by the more part being distributed in towards on the downside of fuselage of air of fuselage interior, in addition to can will
Air is smoothly except guiding to the export mouth being located on rear side of fuselage, additionally it is possible to achieve the effect that stable fuselage.
Description of the drawings
Fig. 1 is the stereogram of unpowered flight mechanism of the present invention；
Fig. 2 is the vertical view of Fig. 1；
Fig. 3 is the sectional view of Fig. 1；
Fig. 4 is the rearview of Fig. 1；
Fig. 5 is air-flow flow path schematic diagram of the air-flow by unpowered flight mechanism.
Reference sign：1- unpowered flights mechanism；2- heads；20- introducing ports；21- butting sections；3-- fuselages；30-
Conducting orifice；31- export mouths；32- flow-guiding channels；33- clump weights；34- side walls；4- wings；40- first parts；41- second
Point；5- empennages；The 6- bottoms wing.
Specific embodiment
Hereby for ease of further to the present invention construction, use and its feature have deeper one layer of clear and definite, full and accurate understanding
With understanding, preferred embodiment is hence enumerated, detailed description are as follows for cooperation diagram：
Such as in this specification occur " on ", " upside ", " under ", " downside ", "left", "right", "front", "rear", " front side ",
" rear side " etc. has the vocabulary of direction row, is all on the basis of the axial direction of fuselage of the present invention, the direction of fuselage towards head is
" preceding ", " front side ", fuselage towards the direction of empennage be " rear ", " rear side ", the left and right two opposite sides meaning of fuselage respectively " left side ",
" right side ", and the top of fuselage and bottom subitem be respectively " on ", " upside ", " under ", " downside ".
It please refers to shown in Fig. 1, unpowered flight mechanism 1 of the present invention mainly includes a head 2, a fuselage 3, a wing 4
And 5 grade of empennage five is most of.
It please refers to shown in Fig. 1 to Fig. 3, head 2 of the present invention is rendered as the pattern that tip extension is widened to fuselage 3, described
Head 2 is equipped with an introducing port 20, and in a preferable possible embodiments, the quantity of the introducing port 20 is set as two, and Divisional
In the left and right sides position on the head 2.
The upside of the fuselage 3 is equipped with a conducting orifice 30, and the rear side of the fuselage 3 is equipped with an export mouth 31, and described
Fuselage 3 is internally provided with a flow-guiding channel 32, and the front side of the flow-guiding channel 32 connect conducting, and thereafter with the introducing port 20
Side connect conducting with the export mouth 31, and center of the flow-guiding channel 32 between the introducing port 20 and export mouth 31
Range connect conducting with the conducting orifice 30, forms one using the flow-guiding channel 32 respectively by the introducing port 20, conducting orifice
30 and 31 three of export mouth are connected with each other the pattern of conducting each other.
Referring again to shown in Fig. 1 to Fig. 4, in a preferred embodiment, the downside of the fuselage 3 is adjacent to described equipped with one
The butting section 21 on head 2, a clump weight 33 and a bottom wing 6, the butting section 21 can supply a springy elastic component temporary
Ground abutting contact, in a preferable possible embodiments, the elastic component can be set as a rubber band or have that bullet can be restored
Property or provide and assist the object that leaves of the fuselage 3 ejection, 33 branch of clump weight is located at the butting section 21 and the bottom wing 6
Between the two.
In addition, in a preferable possible embodiments, wing 4 of the present invention be design be connected in a manner that oblique angle intersects it is described
Fuselage 3 (non-parallel or vertical direction), moreover, the wing 4 have a first part 40 and a second part 41, described first
Part 40 is extended to form by the head 2 towards 3 direction of fuselage, and the second part 41 by the fuselage 3 towards 5 side of empennage
To extending to form, and the thickness of the first part 40 is more than the thickness of the second part 41 so that the wing 4 forms one
By the head 2 towards the thinning pattern in 5 direction of empennage, direction is gradual from front to back for 4 width of wing of the first part 40
Ground increases, and 4 width of wing of the second part 41 gradually reduces in direction from front to back.
It please continue with reference to shown in Fig. 4, the width of the flow-guiding channel 32 towards the upside of the fuselage 3 is less than the fuselage
The width of 3 downside so that the sidewall 34 of the flow-guiding channel 32 is rendered as an inclined pattern, and such design can allow entrance
The air overwhelming majority inside the flow-guiding channel 32 rests on the downside of the fuselage 3, just will can successfully be located at described
Air inside flow-guiding channel 32 is guided to the export mouth 31, can also achieve the effect that assist to stablize the fuselage 3 simultaneously.
In a preferable possible embodiments, empennage 5 of the present invention is connected to leading for the fuselage 3 with being designed to activity
The rear of outlet 31, the width of the empennage 5 form a tapered pattern outwardly by the rear of the export mouth 31, and can be into
The swing in the upper and lower two kinds of directions of row, and change relative angle of the empennage 5 relative to the fuselage 3.
Please refer to shown in Fig. 5, when unpowered flight mechanism 1 of the present invention driven by external force and fly stay in aerial when,
The guide flow path for following the introducing port 20, flow-guiding channel 32, conducting orifice 30 and export mouth 31 is entered and guided by air
It leaves to the outside of the fuselage 3, due to two kinds of conducting orifices 30 and export mouth for being located at 3 different location of fuselage of present invention design
31 can leave the fuselage 3 for air simultaneously, stablize the fuselage 3 therefore, it is possible to reach and are greatly reduced the machine
The chance that body 3 rocks.
Described above to be merely exemplary for the purpose of the present invention, and not restrictive, those of ordinary skill in the art understand,
In the case where not departing from the spirit and scope that claim is limited, can many modifications may be made, variation or equivalent, but will all fall
Enter within protection scope of the present invention.
Claims (10)
1. a kind of unpowered flight mechanism, comprising：One fuselage, the front side of the fuselage are equipped with a head, and rear side is equipped with an empennage,
And in the wing that is respectively arranged on the left side and the right side of the fuselage, it is characterised in that：The head is equipped with one for described in air entrance
The introducing port of fuselage, the fuselage is equipped with a conducting orifice connected with outside, and the rear side of the fuselage is equipped with an export mouth, and
The fuselage is internally provided with a flow-guiding channel that the introducing port, conducting orifice and export mouth are interconnected each other.
2. unpowered flight mechanism according to claim 1, it is characterised in that：The flow-guiding channel is towards the fuselage
The width of upside is less than the width of the downside of the fuselage so that the side wall of the flow-guiding channel is rendered as an inclined pattern.
3. unpowered flight mechanism according to claim 1, it is characterised in that：The wing has a first part and one
Second part, the first part is extended to form by the head towards fuselage, and the second part is by the fuselage direction
Empennage extends to form, and the thickness of the first part is more than the thickness of the second part so that the wing formed one by
The head is towards the thinning pattern of empennage.
4. unpowered flight mechanism according to claim 3, it is characterised in that：The wing width of the first part is by preceding
It is incrementally increased after, the wing width of the second part gradually reduces from front to back.
5. unpowered flight mechanism according to claim 1, it is characterised in that：The area of the introducing port is less than described lead
Outlet and the area of conducting orifice.
6. unpowered flight mechanism according to claim 1, it is characterised in that：The wing connects in a manner that oblique angle intersects
It is connected to the fuselage.
7. unpowered flight mechanism according to claim 1, it is characterised in that：It is temporary for elastic component that the head is equipped with one
The butting section contacted against to property.
8. unpowered flight mechanism according to claim 1, it is characterised in that：The bottom of the fuselage is additionally provided with a bottom
The wing.
9. unpowered flight mechanism according to claim 8, it is characterised in that：The bottom of the fuselage is additionally provided with a counterweight
Block, the clump weight is between the butting section and the bottom wing.
10. unpowered flight mechanism according to claim 1, it is characterised in that：It is connected to institute to the empennage activity
The rear of the export mouth of fuselage is stated, the width of the empennage forms a tapered pattern, Neng Goujin outwardly by the rear of export mouth
The swing of row upper and lower directions, and change relative angle of the empennage relative to the fuselage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611257391.0A CN108261785A (en) | 2016-12-30 | 2016-12-30 | Unpowered flight mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611257391.0A CN108261785A (en) | 2016-12-30 | 2016-12-30 | Unpowered flight mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108261785A true CN108261785A (en) | 2018-07-10 |
Family
ID=62754587
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611257391.0A Pending CN108261785A (en) | 2016-12-30 | 2016-12-30 | Unpowered flight mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108261785A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2405630Y (en) * | 1999-11-24 | 2000-11-15 | 杨明堂 | Ejection-type toy plane |
| CN2510136Y (en) * | 2001-11-02 | 2002-09-11 | 张天龙 | Improved flight apparatus |
| CN203634824U (en) * | 2013-12-27 | 2014-06-11 | 蔡瑞标 | Aircraft having kite function and being capable of being thrown or launching |
| CN204563605U (en) * | 2015-02-27 | 2015-08-19 | 成都学尚科技有限公司 | A kind of unpowered aircraft |
| CN206473811U (en) * | 2016-12-30 | 2017-09-08 | 周文峯 | Unpowered flight mechanism |
-
2016
- 2016-12-30 CN CN201611257391.0A patent/CN108261785A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2405630Y (en) * | 1999-11-24 | 2000-11-15 | 杨明堂 | Ejection-type toy plane |
| CN2510136Y (en) * | 2001-11-02 | 2002-09-11 | 张天龙 | Improved flight apparatus |
| CN203634824U (en) * | 2013-12-27 | 2014-06-11 | 蔡瑞标 | Aircraft having kite function and being capable of being thrown or launching |
| CN204563605U (en) * | 2015-02-27 | 2015-08-19 | 成都学尚科技有限公司 | A kind of unpowered aircraft |
| CN206473811U (en) * | 2016-12-30 | 2017-09-08 | 周文峯 | Unpowered flight mechanism |
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|---|---|---|---|
| PB01 | Publication | ||
| 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 |
Application publication date: 20180710 |
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| WD01 | Invention patent application deemed withdrawn after publication |