CN109018296A - A kind of movable tail structure - Google Patents
A kind of movable tail structure Download PDFInfo
- Publication number
- CN109018296A CN109018296A CN201810967624.9A CN201810967624A CN109018296A CN 109018296 A CN109018296 A CN 109018296A CN 201810967624 A CN201810967624 A CN 201810967624A CN 109018296 A CN109018296 A CN 109018296A
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- CN
- China
- Prior art keywords
- empennage
- strut
- connecting rod
- interconnecting piece
- intermediate active
- 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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- 238000003780 insertion Methods 0.000 claims description 2
- 230000037431 insertion Effects 0.000 claims description 2
- 238000010586 diagram Methods 0.000 description 9
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/26—Attaching the wing or tail units or stabilising surfaces
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/42—Adjusting about chordwise axes
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Road Signs Or Road Markings (AREA)
Abstract
The present invention relates to a kind of movable tail structures to be flexibly connected between empennage strut and empennage ontology including empennage strut and two empennage ontologies for being symmetrically disposed on empennage strut two sides；An intermediate active bar is provided on empennage strut, intermediate active bar is arranged along the vertical direction and top is through empennage strut top surface, slides up and down on empennage strut to realize；First connecting rod and the second connecting rod have been respectively articulated on two empennage ontology bottom surfaces；The bottom end of first connecting rod and the second connecting rod and intermediate active bar bottom end are flexibly connected between three, when realizing that intermediate active bar slides up and down, two empennage ontologies are driven to swing up and down；Movable tail structure of the invention can level empennage in the unmanned plane VTOL stage, greatly reduce the empennage front face area under crosswind, to reduce empennage to the yawing of unmanned plane, improve its anti-side wind energy power.
Description
Technical field
The invention belongs to unmanned vehicle technical fields, and in particular to a kind of movable tail structure.
Background technique
Unmanned vehicle be using electrical remote control equipment and provide for oneself presetting apparatus manipulation unmanned aerial vehicle, fixed-wing without
People's aircraft may be implemented to influence to implement transmission, high-risk areas detecting function, be widely used by carrying multiple sensors
In every field.
At this stage, VTOL fixed-wing unmanned vehicle belongs to quadrotor mode, wind resistance energy in the VTOL stage
Whether power directly affects unmanned plane can be in operation under windy condition.Since unmanned plane is in the landing stage, wind direction be it is indefinite, therefore
It is difficult to ensure that being all that wind is carried out in front when relative to unmanned plane.
Existing vertical fin, whether conventional vertical fin or V tail or the tail of falling V, since empennage has very greatly in vertical direction
Windward side, and empennage generally apart from drone center of unmanned aerial vehicle farther out, cause that very big yaw can be generated when wind is carried out in side
Torque has seriously affected the anti-side wind energy power of unmanned plane.
Summary of the invention
Big in order to solve unmanned airplane empennage front face area existing in the prior art, causing cannot be normal when wind is carried out in side
The technical issues of landing, the present invention provides following technical schemes:
A kind of movable tail structure, including empennage strut and two empennage sheets for being symmetrically disposed on empennage strut two sides
Body is flexibly connected between the empennage strut and empennage ontology；
An intermediate active bar is provided on the empennage strut, the intermediate active bar is arranged along the vertical direction and top is run through
Empennage strut top surface is slided up and down on empennage strut with realizing；
First connecting rod and the second connecting rod have been respectively articulated on two empennage ontology bottom surfaces；
The bottom end of the first connecting rod and the second connecting rod and the intermediate active bar bottom end are flexibly connected between three, with
When realizing that the intermediate active bar slides up and down, two empennage ontologies is driven to swing up and down.
As a further explanation of the present invention, intermediate active bar bottom end is fixedly installed left interconnecting piece and right connection
Portion, the left interconnecting piece and right interconnecting piece are with the axial line center symmetric setting of intermediate active bar；
The first connecting rod bottom end is fixedly installed a cutting ferrule, and the cutting ferrule is connected in the left interconnecting piece and right interconnecting piece
Two sides；
Second connecting rod bottom end is fixedly installed a connection piece, and the connector is set to the left interconnecting piece and right connection
Between portion；
Connection is sequentially inserted by a removable pin between the cutting ferrule, left interconnecting piece, right interconnecting piece and connector, to realize
State the flexible connection between intermediate active bar, first connecting rod and the second connecting rod three.
As a further explanation of the present invention, multiple first to be parallel to each other are provided on empennage strut two sides
Fixed part offers axial line on first fixed part and is overlapped pin hole；
It is provided with multiple the second fixed parts being parallel to each other on the end face that the empennage ontology is connect with empennage strut, described second
The pin hole of axial line coincidence is offered on fixed part；
It is mutually inserted between first fixed part and the second fixed part, and pin hole is sequentially inserted by a removable pin, to realize
Flexible connection between the empennage ontology and empennage strut.
Compared with prior art, what the present invention obtained has the beneficial effect that
Empennage can be leveled in the unmanned plane VTOL stage, greatly reduce side by movable tail structure of the invention
Empennage front face area under wind improves its anti-side wind energy power to reduce empennage to the yawing of unmanned plane.
The present invention is described in further details below with reference to accompanying drawings and embodiments.
Detailed description of the invention
Fig. 1 is movable tail structure perspective view.
Fig. 2 is movable tail structure top view.
Fig. 3 is empennage pole structure schematic diagram.
Fig. 4 is empennage body construction schematic diagram.
Fig. 5 is intermediate active rod structure schematic diagram.
Fig. 6 is first connecting rod structural schematic diagram.
Fig. 7 is the second connecting rod structural schematic diagram.
Fig. 8 is removable pin structural schematic diagram.
Fig. 9 is movable tail structure state diagram one.
Figure 10 is movable tail structure state diagram two.
Figure 11 is movable tail structure state diagram three.
In figure: 1, empennage strut；2, empennage ontology；3, first connecting rod；4, intermediate active bar；5, the second connecting rod；6,
Left interconnecting piece；7, right interconnecting piece；8, cutting ferrule；9, connector；10, the first fixed part；11, the second fixed part；12, removable pin.
Specific embodiment
Reach the technical means and efficacy that predetermined purpose is taken for the present invention is further explained, below in conjunction with attached drawing and reality
Example is applied to a specific embodiment of the invention, structure feature and its effect, detailed description are as follows.
In the description of the invention, it is to be understood that term " center ", " longitudinal direction ", " transverse direction ", "upper", "lower",
The orientation or positional relationship of the instructions such as "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outside" is
It is based on the orientation or positional relationship shown in the drawings, is merely for convenience of description the invention and simplifies description, rather than indicate
Or imply that signified device or element must have a particular orientation, be constructed and operated in a specific orientation, therefore cannot understand
For the limitation to the invention.
In addition, term " first ", " second ", " third " etc. are used for description purposes only, it is not understood to indicate or imply
Relative importance or the quantity for implicitly indicating indicated technical characteristic.The feature of " first ", " second " etc. is defined as a result,
It can explicitly or implicitly include one or more of the features.In the description of the invention, unless otherwise indicated,
The meaning of " plurality " is two or more.
Term " installation ", " connected ", " connection " shall be understood in a broad sense, for example, it may be being fixedly connected, be also possible to removable
Connection is unloaded, or is integrally connected；It can be mechanical connection, be also possible to be electrically connected；It can be directly connected, it can also be in
Between medium be indirectly connected, can be the connection inside two elements.For the ordinary skill in the art, can pass through
Concrete condition understands concrete meaning of the above-mentioned term in the invention.
To solve unmanned vehicle existing in the prior art in the VTOL stage, due to the front face area of fixed empennage
It is larger, cause to form biggish yawing when wind is carried out in side, influence the Normal Take-Off And Landing of unmanned vehicle, cause its
The technical issues of being unable to normal operation under wind regime, is carried out in side, the present embodiment provides a kind of movable tail structure, as Fig. 1,
Shown in Fig. 2, including empennage strut 1 and two empennage ontologies 2 for being symmetrically disposed on 1 two sides of empennage strut, empennage strut 1 and empennage
It is flexibly connected between ontology 2；Be provided with an intermediate active bar 4 on empennage strut 1, intermediate active bar 4 be arranged along the vertical direction and
1 top surface of empennage strut is run through on top, is slided up and down on empennage strut 1 with realizing；It is respectively articulated on two 2 bottom surfaces of empennage ontology
There are first connecting rod 3 and the second connecting rod 5；The bottom end of first connecting rod 3 and the second connecting rod 5 and 4 bottom end of intermediate active bar,
It is flexibly connected between three, when realizing that intermediate active bar 4 slides up and down, two empennage ontologies 2 is driven to swing up and down.
Above-mentioned empennage strut 1 is preferably hollow tubular structure, as shown in figure 3, its cross section is rectangle structure, two tails
Wing ontology 2 is symmetrically disposed on two opposite sides, and intermediate active bar 4 is inserted by the circular hole on top and bottom.
Above-mentioned intermediate motion bar 4 is as shown in figure 5, bottom end is fixedly installed left interconnecting piece 6 and right interconnecting piece 7, left interconnecting piece 6
With right interconnecting piece 7 with the axial line center symmetric setting of intermediate active bar 4；First connecting rod 3 is as shown in fig. 6, bottom end fixation is set
It is equipped with a cutting ferrule 8, cutting ferrule 8 is connected in 7 two sides of left interconnecting piece 6 and right interconnecting piece；Second connecting rod 5 is as shown in fig. 7, bottom end is fixed
It is provided with a connection piece 9, connector 9 is set between left interconnecting piece 6 and right interconnecting piece 7；Cutting ferrule 8, left interconnecting piece 6, right connection
Connection is sequentially inserted by a removable pin 12 between portion 7 and connector 9, with realize intermediate active bar 4, first connecting rod 3 with
And the flexible connection between 5 three of the second connecting rod.
The removable pin 12 being inserted between above-mentioned cutting ferrule 8, left interconnecting piece 6, right interconnecting piece 7 and connector 9, the removable pin 12
Axial line and empennage strut 1 axial line it is arranged in parallel, thus when realizing that intermediate active bar 4 slides up and down, drive two
A empennage ontology 2 is swung up and down, to adjust the different conditions of empennage ontology 2.
It is to be noted that passing through the prior art between above-mentioned first connecting rod 3 and the second connecting rod 5 and empennage ontology 2
Articulated structure connection, being flexibly connected between first connecting rod 3 and the second connecting rod 5 and empennage ontology 2 can be met, therefore
The structure be not described in detail.
Multiple the first fixed parts 10 being parallel to each other are provided on above-mentioned 1 two sides of empennage strut, as shown in figure 3, the
Axial line is offered on one fixed part 10 is overlapped pin hole；It is provided on the end face that empennage ontology 2 is connect with empennage strut 1 multiple
The second fixed part 11 being parallel to each other, as shown in figure 4, offering the pin hole of axial line coincidence on the second fixed part 11；First
It is mutually inserted between fixed part 10 and the second fixed part 11, and pin hole is sequentially inserted by a removable pin 12, to realize empennage sheet
Flexible connection between body 2 and empennage strut 1.
Axial line phase of the axial line of above-mentioned first fixed part 10 and the pin hole on the second fixed part 11 with empennage strut 1
It is mutually parallel, to guarantee that two empennage ontologies 2 can be rotated around the axial line.
The removable pin 12 provided in the present embodiment is shared and is used at five, and respectively two empennage ontologies 2 and empennage strut 1 connect
Connect place, two empennage ontologies 2 and first connecting rod 3 and 5 junction of the second connecting rod and first connecting rod 3, intermediate active
5 junction of bar 4 and the second connecting rod, for the removable pin 12 as shown in figure 8, after its insertion respective pin hole, terminal position offers one
A aperture being disposed radially, the aperture is interior to be inserted into a pole, and the axial limiting of removable pin 12 can be realized, make overall structure
It is more firm.
This movable tail structure provided in this embodiment, empennage ontology 2 can be movable in a certain range, at nobody
When aircraft vertical landing, according to environmental factor at that time, adjusts intermediate active bar 4 and slide up and down, drive about 2 empennage ontology
It swings, empennage ontology 2 is made to be in different forms, as shown in Figure 9, Figure 10, to adapt to different flight environment of vehicle, especially hanging down
In the straight landing stage, empennage can be leveled, as shown in figure 11, the empennage front face area under crosswind be greatly reduced, to subtract
Small yawing of the empennage to unmanned plane, improve its anti-side wind can, guarantee that unmanned vehicle is normal in the case where there is wind environment
Operation.
The above content is a further detailed description of the present invention in conjunction with specific preferred embodiments, and it cannot be said that
Specific implementation of the invention is only limited to these instructions.For those of ordinary skill in the art to which the present invention belongs, exist
Under the premise of not departing from present inventive concept, a number of simple deductions or replacements can also be made, all shall be regarded as belonging to of the invention
Protection scope.
Claims (3)
1. a kind of movable tail structure, including empennage strut (1) and it is symmetrically disposed on two of empennage strut (1) two sides
Empennage ontology (2), it is characterised in that: be flexibly connected between the empennage strut (1) and empennage ontology (2)；
Be provided with an intermediate active bar (4) on the empennage strut (1), the intermediate active bar (4) be arranged along the vertical direction and
Empennage strut (1) top surface is run through on top, is slided up and down on empennage strut (1) with realizing；
First connecting rod (3) and the second connecting rod (5) have been respectively articulated on two empennage ontology (2) bottom surfaces；
The bottom end of the first connecting rod (3) and the second connecting rod (5) and intermediate active bar (4) bottom end, it is living between three
Dynamic connection, when realizing that the intermediate active bar (4) slides up and down, drives two empennage ontologies (2) to swing up and down.
2. tail structure according to claim 1, it is characterised in that: intermediate active bar (4) bottom end is fixedly installed
Left interconnecting piece (6) and right interconnecting piece (7), the left interconnecting piece (6) and right interconnecting piece (7) are with the axial line of intermediate active bar (4)
Center symmetric setting；
First connecting rod (3) bottom end is fixedly installed a cutting ferrule (8), and the cutting ferrule (8) is connected in the left interconnecting piece
(6) and right interconnecting piece (7) two sides；
Second connecting rod (5) bottom end is fixedly installed a connection piece (9), and the connector (9) is set to the left connection
Between portion (6) and right interconnecting piece (7)；
Between the cutting ferrule (8), left interconnecting piece (6), right interconnecting piece (7) and connector (9) successively by a removable pin (12)
Insertion connection, to realize the work between the intermediate active bar (4), first connecting rod (3) and the second connecting rod (5) three
Dynamic connection.
3. tail structure according to claim 1 or 2, it is characterised in that: be respectively provided on empennage strut (1) two sides
There are multiple the first fixed parts (10) being parallel to each other, axial line is offered on first fixed part (10) and is overlapped pin hole；
Multiple the second fixed parts being parallel to each other are provided on the end face that the empennage ontology (2) connect with empennage strut (1)
(11), the pin hole of axial line coincidence is offered on second fixed part (11)；
It is mutually inserted between first fixed part (10) and the second fixed part (11), and is sequentially inserted by a removable pin (12)
Pin hole, to realize the flexible connection between the empennage ontology (2) and empennage strut (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810967624.9A CN109018296A (en) | 2018-08-23 | 2018-08-23 | A kind of movable tail structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810967624.9A CN109018296A (en) | 2018-08-23 | 2018-08-23 | A kind of movable tail structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109018296A true CN109018296A (en) | 2018-12-18 |
Family
ID=64628158
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810967624.9A Pending CN109018296A (en) | 2018-08-23 | 2018-08-23 | A kind of movable tail structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109018296A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2582340A (en) * | 2019-03-20 | 2020-09-23 | The Royal Veterinary College | Winged aircraft |
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|---|---|---|---|---|
| US20080128548A1 (en) * | 2004-12-02 | 2008-06-05 | Hawker Beechcraft Corporation | Control linkage |
| CN102874409A (en) * | 2012-10-30 | 2013-01-16 | 东南大学 | Flapping wing and turning device of micro aerial vehicle |
| CN205345313U (en) * | 2015-12-30 | 2016-06-29 | 南昌理工学院 | Unmanned aerial vehicle |
| CN105818962A (en) * | 2016-06-01 | 2016-08-03 | 中电科（德阳广汉）特种飞机系统工程有限公司 | Foldable wing extensible in wingspan |
| CN107380402A (en) * | 2017-02-24 | 2017-11-24 | 南京柯尔航空科技有限公司 | A kind of folding wings unmanned plane |
| CN208915415U (en) * | 2018-08-23 | 2019-05-31 | 西安三翼航空科技有限公司 | A kind of tail structure |
-
2018
- 2018-08-23 CN CN201810967624.9A patent/CN109018296A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20080128548A1 (en) * | 2004-12-02 | 2008-06-05 | Hawker Beechcraft Corporation | Control linkage |
| CN102874409A (en) * | 2012-10-30 | 2013-01-16 | 东南大学 | Flapping wing and turning device of micro aerial vehicle |
| CN205345313U (en) * | 2015-12-30 | 2016-06-29 | 南昌理工学院 | Unmanned aerial vehicle |
| CN105818962A (en) * | 2016-06-01 | 2016-08-03 | 中电科（德阳广汉）特种飞机系统工程有限公司 | Foldable wing extensible in wingspan |
| CN107380402A (en) * | 2017-02-24 | 2017-11-24 | 南京柯尔航空科技有限公司 | A kind of folding wings unmanned plane |
| CN208915415U (en) * | 2018-08-23 | 2019-05-31 | 西安三翼航空科技有限公司 | A kind of tail structure |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2582340A (en) * | 2019-03-20 | 2020-09-23 | The Royal Veterinary College | Winged aircraft |
| CN113784889A (en) * | 2019-03-20 | 2021-12-10 | 皇家兽医学院 | Aircraft with wings |
| GB2582340B (en) * | 2019-03-20 | 2022-12-14 | The Royal Veterinary College | Winged aircraft |
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| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20181218 |
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