CN206125405U - Fin reaches fixed wing uavs including it - Google Patents
Fin reaches fixed wing uavs including it Download PDFInfo
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- CN206125405U CN206125405U CN201621175995.6U CN201621175995U CN206125405U CN 206125405 U CN206125405 U CN 206125405U CN 201621175995 U CN201621175995 U CN 201621175995U CN 206125405 U CN206125405 U CN 206125405U
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- horizontal tail
- fixed
- unmanned plane
- wing unmanned
- empennage
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Abstract
The utility model provides the utility model discloses a fixed wing uavs's fin, it includes installs vertical fin and the horizontal tail at the fixed wing uavs afterbody, the vertical fin with no instrument dismouting mode with fixed wing uavs connection of after section. The utility model provides a fixed wing uavs including above -mentioned fin. Compare in current fin, the utility model discloses an easy dismounting is connected with no instrument dismouting mode to vertical fin and fuselage. The horizontal tail is passed through the horizontal tail rocking arm and is connected, and the horizontal tail rocking arm can regard as rotor support shaft, makes tail wing structure simple.
Description
Technical field
The utility model is related to a kind of empennage, more particularly to a kind of empennage for fixed-wing unmanned plane and consolidating including it
Determine wing unmanned plane.
Background technology
Miniaturization, Highgrade integration with electric load, small-sized electric unmanned plane is particularly the electronic nothing that hand throws transmitting
Man-machine quick development, has application at military, civilian aspect.Empennage includes vertical fin and horizontal tail, current vertical fin, horizontal tail group
The mode being mounted on fuselage is complex.
Utility model content
In view of this, embodiment of the present utility model provides a kind of empennage and the fixed-wing including it of simple structure
Unmanned plane.
The utility model provides a kind of empennage for fixed-wing unmanned plane, and it includes being arranged on the unmanned drive end unit of fixed-wing
Vertical fin, horizontal tail and coupling assembly, the horizontal tail includes horizontal tail main body and holding part, in the horizontal tail main body installation offered
Groove, the holding part is installed in the side wall of the mounting groove, and the coupling assembly includes horizontal tail rocking arm and steady pin, the horizontal tail
Rocking arm include the connection end for being connected with the unmanned drive end unit and for insert the mounting groove with the horizontal tail main body
First linking arm of connection, first linking arm extends to be formed from the connection end, and the steady pin passes through the unmanned plane
Afterbody, the connection end, the end of steady pin described in the holding part clamping.
Preferably, connecting hole is offered on the connection end, the steady pin is through the unmanned drive end unit and the company
Hole is connect, and protrudes from the unmanned drive end unit.
Preferably, the mounting groove is surrounded by the end wall of two side walls of two side walls and connection, the end wall
On offer link slot, first linking arm inserts the link slot so as to be connected with the horizontal tail.
Preferably, the holding part insertion offers the through hole of two connections, and its end offers and connects with the through hole
Logical V-shaped groove, the steady pin inserts the through hole via the V-shaped groove, so as to fixed described in holding part elasticity clamping
Pin.
Preferably, the holding part is two, is separately mounted on described two side walls, respectively steady pin described in clamping
Two ends.
Preferably, the horizontal tail rocking arm also includes from the connection end extending the second linking arm to be formed, and described first
Linking arm and second linking arm constitute V-arrangement, and second linking arm is used to be connected with horizontal tail steering wheel connecting rod.
Preferably, the horizontal tail is flying tail.
The utility model also provides a kind of fixed-wing unmanned plane, and the fixed-wing unmanned plane includes above-mentioned empennage.
Preferably, the afterbody of the fixed-wing unmanned plane is formed with rotating shaft fixing end, and the rotating shaft fixing end offers company
Slit is connect, and installing hole is offered through the connection slit, the connection slit, institute are inserted in the connection end of the horizontal tail rocking arm
Steady pin is stated through the installing hole and the connection end.
Preferably, the section semicircular in shape of the rotating shaft fixing end.
Compared to existing empennage, vertical fin of the present utility model is with fuselage with the connection without instrument dismounting mode, easy accessibility.
Horizontal tail is connected by horizontal tail rocking arm, and horizontal tail rocking arm can make tail structure simple as rotating support shaft.
Description of the drawings
Technical scheme in order to be illustrated more clearly that embodiment of the present utility model, below will be to institute in embodiment description
The accompanying drawing that needs are used is briefly described.
Fig. 1 is the unmanned plane stereogram of the utility model embodiment.
Fig. 2 is the vertical fin structural representation of unmanned plane shown in Fig. 1.
Fig. 3 is the horizontal tail part-structure schematic diagram of unmanned plane shown in Fig. 1.
Fig. 4 is the horizontal tail rocker structure schematic diagram of unmanned plane shown in Fig. 1.
Fig. 5 is the horizontal tail rocking arm and fuselage assembling schematic diagram of unmanned plane shown in Fig. 1.
Specific embodiment
It is new to this practicality below in conjunction with accompanying drawing to make the purpose of this utility model, technical scheme and advantage clearer
The unmanned plane of type embodiment is further described.
Fig. 1 to Fig. 5 is referred to, the unmanned plane of the utility model embodiment includes fuselage 10 and empennage（Figure is not marked）, tail
The wing includes vertical fin 40, horizontal tail 50 and coupling assembly, and vertical fin 40 and horizontal tail 50 are arranged at the afterbody of fuselage 10, and coupling assembly includes
Horizontal tail rocking arm 70 and steady pin 80, horizontal tail 50 is connected by horizontal tail rocking arm 70 and steady pin 80 with fuselage 10.It is appreciated that nobody
Machine also includes other functions component, mechanism, wing, rudder, hatchcover is such as electric-only propulsion, to save space, hereafter not to this
A little other functions modules are described in detail.
Fig. 5 is referred to, the afterbody of fuselage 10 is formed with rotating shaft fixing end 11, and the section of rotating shaft fixing end 11 is substantially in semicircle
Shape, its middle part offers connection slit 110, and offers installing hole through connection slit 110.
Fig. 2 is referred to, vertical fin 40 is the afterbody of plug connector 41 and fuselage 10 with without the connection by way of instrument dismounting.Vertical fin
40 are also formed with installing space 401, and horizontal tail manipulates steering wheel（It is not shown）With rudder control steering wheel（It is not shown）It is installed in peace
In dress space 401.
Refer to Fig. 3, horizontal tail 50 is flying tail, its clamping for including horizontal tail main body 51 and being installed in horizontal tail main body 51
Part 53, the medium position of horizontal tail main body 51 offers mounting groove 510, and mounting groove 510 is by two relative side walls 5101 and connection
The end wall 5103 of two side walls 5101 is surrounded, and the middle part of end wall 5103 offers link slot 5105.Holding part 53 is two, its point
It is not installed on 510 two side walls 5101 of mounting groove, the middle part insertion of holding part 53 offers the through hole 530 of two connections, and its
End offers the V-shaped groove 532 connected with through hole 530, so that holding part 53 has elasticity, can be to inserting via V-shaped groove 532
The object of through hole 530 carries out elastic clamping.Any electronic equipment is not contained in horizontal tail 50, to prevent from being damaged when landing is decomposed.
Refer to Fig. 4, horizontal tail rocking arm 70 include connection end 71, for the first linking arm 73 for be connected with horizontal tail 50 and with put down
Tail actuator connecting rod（It is not shown）Second linking arm 75 of connection, the first linking arm 73 and the second linking arm 75 prolong from connection end 71
Stretch to be formed, and the first linking arm 73 and the second linking arm 75 constitute V-arrangement.The middle part of connection end 71 offers connecting hole 710.Second connects
Connect arm 75 and offer connecting hole 750 away from one end of connection end 71, for being connected with horizontal tail steering wheel connecting rod.
During assembling horizontal tail 50, the second linking arm 75 of horizontal tail rocking arm 70 is connected by connecting hole 750 with horizontal tail steering wheel connecting rod；
Then the connection end 71 of horizontal tail rocking arm 70 is inserted in the connection slit 110 of rotating shaft fixing end 11, and makes the connection of connection end 71
Align with the installing hole of rotating shaft fixing end 11 in hole 710；Again by steady pin 80 through installing hole and connecting hole 710, and protrude from peace
Dress hole, so as to horizontal tail rocking arm 70 be connected together with fuselage 10；Finally, the first linking arm 73 is inserted the link slot of horizontal tail 50
5105, and make the two ends of steady pin 80 insert through hole 530 via the V-shaped groove 532 of holding part 53 respectively, so as to the elastic card of holding part 53
Hold the two ends of steady pin 80.Therefore, horizontal tail 50 is connected together with fuselage 10 and horizontal tail steering wheel connecting rod.
When horizontal tail steering wheel is rotated, the second linking arm 75 for driving the horizontal tail rocking arm 70 being attached thereto is rotated, then horizontal tail is shaken
Arm 70 can think that steady pin 80 is rotating shaft concomitant rotation, and the horizontal tail 50 being connected with the first linking arm 73 of horizontal tail rocking arm 70 also can
With the first linking arm 75 to support, got up as axis of rotation with steady pin 80 under the drive of the second linking arm 75, so as to complete
The precise control that horizontal tail steering wheel is rotated to horizontal tail 50.
Compared to existing empennage, vertical fin of the present utility model 40 and horizontal tail 50 and fuselage 10 are with without instrument dismounting mode
Connection, easy accessibility.Horizontal tail 50 is connected by horizontal tail rocking arm 70 with horizontal tail steering wheel and fuselage 10, holding part 53 can make horizontal tail 50 with
Fuselage 10 can be dismounted without instrument, also be can guarantee that and separated with fuselage 10 when stall is decomposed and landed.In addition, vertical fin 40 and horizontal tail 50
Modularized design, using being connected with fuselage 10 without instrument fast assembling-disassembling mode, can realize that transport is carried convenient, assemble fast
Speed, launch preparation time is short, also being capable of quick replacement even if there is damage.
Herein, the involved noun of locality such as forward and backward, upper and lower is to be located in figure with parts in accompanying drawing and zero
Part position each other is intended merely to the clear and convenient of expression technology scheme come what is defined.It should be appreciated that the noun of locality
Use should not limit the scope that the application is claimed.
In the case where not conflicting, the feature in embodiment herein-above set forth and embodiment can be combined with each other.
Preferred embodiment of the present utility model is the foregoing is only, it is all in this practicality not to limit the utility model
Within new spirit and principle, any modification, equivalent substitution and improvements made etc. should be included in guarantor of the present utility model
Within the scope of shield.
Claims (10)
1. a kind of empennage for fixed-wing unmanned plane, it includes being arranged on vertical fin, horizontal tail and the company of the unmanned drive end unit of fixed-wing
Connected components, it is characterised in that：The horizontal tail includes horizontal tail main body and holding part, offers mounting groove in the horizontal tail main body, institute
The side wall that holding part is installed in the mounting groove is stated, the coupling assembly includes horizontal tail rocking arm and steady pin, the horizontal tail rocking arm
Including the connection end for being connected with the unmanned drive end unit and for inserting the mounting groove to be connected with the horizontal tail main body
The first linking arm, first linking arm extends to be formed from the connection end, the steady pin through the unmanned drive end unit,
The connection end, the end of steady pin described in the holding part clamping.
2. the empennage of fixed-wing unmanned plane is used for as claimed in claim 1, it is characterised in that：The company of offering on the connection end
Hole is connect, the steady pin protrudes from the unmanned drive end unit through the unmanned drive end unit and the connecting hole.
3. the empennage of fixed-wing unmanned plane is used for as claimed in claim 1, it is characterised in that：The mounting groove is by described in two
The end wall of two side walls of side wall and connection is surrounded, and link slot is offered on the end wall, and first linking arm inserts institute
Link slot is stated so as to be connected with the horizontal tail.
4. the empennage of fixed-wing unmanned plane is used for as claimed in claim 1, it is characterised in that：The holding part insertion is offered
The through hole of two connections, and its end offers the V-shaped groove connected with the through hole, the steady pin is inserted via the V-shaped groove
Enter the through hole, so as to steady pin described in holding part elasticity clamping.
5. the empennage of fixed-wing unmanned plane is used for as claimed in claim 4, it is characterised in that：The holding part is two, point
An Zhuan not be on described two side walls, two ends of steady pin described in clamping respectively.
6. the empennage of fixed-wing unmanned plane is used for as claimed in claim 1, it is characterised in that：The horizontal tail rocking arm also include from
The connection end extends the second linking arm to be formed, and first linking arm and second linking arm constitute V-arrangement, and described the
Two linking arms are used to be connected with horizontal tail steering wheel connecting rod.
7. the empennage of fixed-wing unmanned plane is used for as claimed in claim 1, it is characterised in that：The horizontal tail is flying tail.
8. a kind of fixed-wing unmanned plane, it is characterised in that：The fixed-wing unmanned plane is included as described in any one of claim 1-7
Empennage.
9. fixed-wing unmanned plane as claimed in claim 8, it is characterised in that：The afterbody of the fixed-wing unmanned plane is formed with and turns
Axle fixing end, the rotating shaft fixing end offers connection slit, and offers installing hole, the horizontal tail through the connection slit
The connection slit is inserted in the connection end of rocking arm, and the steady pin is through the installing hole and the connection end.
10. fixed-wing unmanned plane as claimed in claim 9, it is characterised in that：The section semicircular in shape of the rotating shaft fixing end.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621175995.6U CN206125405U (en) | 2016-10-25 | 2016-10-25 | Fin reaches fixed wing uavs including it |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621175995.6U CN206125405U (en) | 2016-10-25 | 2016-10-25 | Fin reaches fixed wing uavs including it |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206125405U true CN206125405U (en) | 2017-04-26 |
Family
ID=58576812
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621175995.6U Active CN206125405U (en) | 2016-10-25 | 2016-10-25 | Fin reaches fixed wing uavs including it |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206125405U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108058807A (en) * | 2017-12-06 | 2018-05-22 | 湖南鲲鹏智汇无人机技术有限公司 | A kind of unmanned plane Quick Release horizontal tail bindiny mechanism |
| CN112606997A (en) * | 2020-12-29 | 2021-04-06 | 北京北航天宇长鹰无人机科技有限公司 | Unmanned cargo airplane of tailless overall arrangement |
| CN114044151A (en) * | 2021-11-08 | 2022-02-15 | 中山福昆航空科技有限公司 | Unmanned aerial vehicle power module |
-
2016
- 2016-10-25 CN CN201621175995.6U patent/CN206125405U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108058807A (en) * | 2017-12-06 | 2018-05-22 | 湖南鲲鹏智汇无人机技术有限公司 | A kind of unmanned plane Quick Release horizontal tail bindiny mechanism |
| CN112606997A (en) * | 2020-12-29 | 2021-04-06 | 北京北航天宇长鹰无人机科技有限公司 | Unmanned cargo airplane of tailless overall arrangement |
| CN112606997B (en) * | 2020-12-29 | 2021-10-22 | 北京北航天宇长鹰无人机科技有限公司 | Unmanned cargo airplane of tailless overall arrangement |
| CN114044151A (en) * | 2021-11-08 | 2022-02-15 | 中山福昆航空科技有限公司 | Unmanned aerial vehicle power module |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20171115 Address after: 518000 Guangdong Province, Baoan District Xixiang street Shenzhen City, Chen Tian Bao Tian Yi Lu Industrial District thirty-seventh Building 5 floor West Patentee after: Shenzhen Huaxun ark System Technology Co Ltd Address before: 518000 Guangdong Province, Baoan District Xixiang street Shenzhen City Tian Yi Lu Chen Tian Bao Industrial District thirty-seventh Building 5 floor right Patentee before: Shenzhen Yifei Fonda Technology Co. Ltd. |
|
| TR01 | Transfer of patent right |