CN106218855A - Unmanned plane horizontal tail device for quickly disassembling - Google Patents
Unmanned plane horizontal tail device for quickly disassembling Download PDFInfo
- Publication number
- CN106218855A CN106218855A CN201610626991.3A CN201610626991A CN106218855A CN 106218855 A CN106218855 A CN 106218855A CN 201610626991 A CN201610626991 A CN 201610626991A CN 106218855 A CN106218855 A CN 106218855A
- Authority
- CN
- China
- Prior art keywords
- horizontal tail
- collision bead
- fuselage
- face
- intubate
- 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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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
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/068—Fuselage sections
- B64C1/069—Joining arrangements therefor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Processing Of Solid Wastes (AREA)
Abstract
The present invention relates to a kind of device for quickly disassembling, particularly to a kind of unmanned plane horizontal tail device for quickly disassembling.Its structure includes fuselage and horizontal tail, intubate before being provided with horizontal tail on fuselage and intubate after horizontal tail, intubate before described horizontal tail and intubate corresponding inserting respectively and be embedded in the sleeve pipe on described horizontal tail end face after horizontal tail, described horizontal tail end face and fuselage end face are additionally provided with the collision bead push-pull structure of mutual inlay card.A kind of unmanned plane horizontal tail device for quickly disassembling of the present invention, it is on the basis of meeting horizontal tail and fuselage bonding strength, it is achieved the purpose of fast assembling-disassembling horizontal tail.
Description
Technical field
The present invention relates to a kind of device for quickly disassembling, particularly to a kind of unmanned plane horizontal tail device for quickly disassembling.
Background technology
China's unmanned plane field quickly grows in recent years, and the unmanned plane yield of China occupies first place in the world.Existing part is unmanned
The horizontal tail of machine is fixed with fuselage and is used the fixing mode being connected, and takies big quantity space during packing, transporting and collect, and
Being easily damaged, transport is got up very inconvenient.Some unmanned planes use plug-in type horizontal tail, i.e. horizontal tail to be installed to fuselage pluggablely
On, and be screwed, but the location comparison of screw is hidden, is not easy to dismounting.The unmanned plane horizontal tail also having and the company of fuselage
The mode of connecing adopt be screwed, these fixed form reliabilities of mode that rubber band is fixing the best, easy aged deterioration, dismount numerous
Trivial, part is many, thereby results in working performance outside relatively low.
Summary of the invention
In order to solve problem of the prior art, the invention provides a kind of unmanned plane horizontal tail device for quickly disassembling, it is satisfied flat
On the basis of tail and fuselage bonding strength, it is achieved the purpose of fast assembling-disassembling horizontal tail.
The technical solution adopted in the present invention is as follows:
A kind of unmanned plane horizontal tail device for quickly disassembling, including fuselage and horizontal tail, intubate before fuselage is provided with horizontal tail with horizontal tail after
Intubate, intubate before described horizontal tail and intubate corresponding inserting respectively and be embedded in the sleeve pipe on described horizontal tail end face after horizontal tail, described
The collision bead push-pull structure of mutual inlay card it is additionally provided with on horizontal tail end face and fuselage end face.
Collision bead push-pull structure includes the horizontal tail base being fixed on described horizontal tail end face and the machine being fixed on fuselage end face
Body base, described horizontal tail base is provided with and meets and discusses, and described machine body base is provided with collision bead groove, in described collision bead groove
Being provided with collision bead, described collision bead is internally provided with spring, outside spacing by collision bead groove, described collision bead and the side met and discussed
Coordinate the mutual inlay card realizing collision bead push-pull structure.
The sidewall met and discussed is circular arc.
Lift and the moment of torsion of horizontal tail, as the force transmission mechanism of horizontal tail Yu fuselage, are passed to fuselage by the sleeve pipe in horizontal tail.
The effect of collision bead push-pull structure is to prevent horizontal tail transverse movement, is not involved in the transmission of power between horizontal tail and fuselage.
The technical scheme that the present invention provides has the benefit that
The unmanned plane horizontal tail device for quickly disassembling of the present invention is plugged with the sleeve pipe on fuselage and collision bead by intubating in horizontal tail
Mechanism with the use of, screw need not be used, just achieve being reliably connected of horizontal tail and fuselage, and then achieve horizontal tail and fuselage
Fast assembling-disassembling.
Accompanying drawing explanation
For the technical scheme being illustrated more clearly that in the embodiment of the present invention, in embodiment being described below required for make
Accompanying drawing be briefly described, it should be apparent that, below describe in accompanying drawing be only some embodiments of the present invention, for
From the point of view of those of ordinary skill in the art, on the premise of not paying creative work, it is also possible to obtain other according to these accompanying drawings
Accompanying drawing.
Fig. 1 is the overall structure schematic diagram of the unmanned plane horizontal tail device for quickly disassembling of the present invention；
Fig. 2 is the collision bead push-pull structure structural representation of the unmanned plane horizontal tail device for quickly disassembling of the present invention.
Detailed description of the invention
For making the object, technical solutions and advantages of the present invention clearer, below in conjunction with accompanying drawing to embodiment party of the present invention
Formula is described in further detail.
Embodiment one
As shown in Figure 1, a kind of unmanned plane horizontal tail device for quickly disassembling, including fuselage 1 and horizontal tail 2, fuselage 1 is provided with horizontal tail
Before intubate 3 and horizontal tail after intubate 4, intubate before described horizontal tail 3 and horizontal tail after intubate 4 respectively corresponding inserting be embedded in described horizontal tail 2 end
In sleeve pipe 5 on face, described horizontal tail end face and fuselage end face are additionally provided with the collision bead push-pull structure 6 of mutual inlay card.
As shown in Figure 2, collision bead push-pull structure 6 includes the horizontal tail base 61 being fixed on described horizontal tail 2 end face and fixes
Machine body base 62 on fuselage 1 end face, described horizontal tail base 61 is provided with and meets and discusses 63, described machine body base 62 sets
Being equipped with collision bead groove 64, be provided with collision bead 65 in described collision bead groove 64, described collision bead 65 is internally provided with spring, and outside is passed through
Collision bead groove 64 is spacing, described collision bead 65 with meet and discuss 63 side-fit realize the mutual inlay card of collision bead push-pull structure 6.
Meet and discuss 63 sidewall be circular arc.
Intubate before horizontal tail 3 and horizontal tail after intubate in the sleeve pipe 5 of 4 insertion fuselage 1 correspondences, then will meet and discuss and 63 snap in machine body base
In the collision bead groove 64 of 62 correspondences, just complete the fixing of horizontal tail 2 and fuselage 1.During dismounting horizontal tail 2, by plug auxiliary block firmly
Just horizontal tail 2 can be extracted.Horizontal tail anterior cannula 3 and horizontal tail rear sleeve 4 are as horizontal tail 2 and the force transmission mechanism of fuselage 1, by horizontal tail 2
Lift and moment of torsion pass to fuselage 1.The effect of collision bead push-pull structure 6 is to prevent horizontal tail 2 transverse movement, is not involved in horizontal tail 2 and machine
1 power of body and the transmission of moment of torsion.
The foregoing is only presently preferred embodiments of the present invention, not in order to limit the present invention, all spirit in the present invention and
Within principle, any modification, equivalent substitution and improvement etc. made, should be included within the scope of the present invention.
Claims (3)
1. a unmanned plane horizontal tail device for quickly disassembling, including fuselage and horizontal tail, it is characterised in that be provided with horizontal tail on described fuselage
Before intubate and intubate after horizontal tail, intubate before described horizontal tail and intubate corresponding inserting respectively and be embedded on described horizontal tail end face after horizontal tail
In sleeve pipe, described horizontal tail end face and fuselage end face are additionally provided with the collision bead push-pull structure of mutual inlay card.
Unmanned plane horizontal tail device for quickly disassembling the most according to claim 1, it is characterised in that described collision bead push-pull structure includes
The horizontal tail base being fixed on described horizontal tail end face and the machine body base being fixed on fuselage end face, described horizontal tail base sets
It is equipped with and meets and discusses, described machine body base is provided with collision bead groove, is provided with collision bead in described collision bead groove, inside described collision bead
Being provided with spring, outside spacing by collision bead groove, described collision bead realizes the phase of collision bead push-pull structure with the side-fit met and discussed
Inlay card mutually.
Unmanned plane horizontal tail device for quickly disassembling the most according to claim 2, it is characterised in that the described sidewall met and discussed is circular arc
Shape.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610626991.3A CN106218855A (en) | 2016-08-03 | 2016-08-03 | Unmanned plane horizontal tail device for quickly disassembling |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610626991.3A CN106218855A (en) | 2016-08-03 | 2016-08-03 | Unmanned plane horizontal tail device for quickly disassembling |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106218855A true CN106218855A (en) | 2016-12-14 |
Family
ID=57535125
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610626991.3A Pending CN106218855A (en) | 2016-08-03 | 2016-08-03 | Unmanned plane horizontal tail device for quickly disassembling |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106218855A (en) |
Cited By (2)
| 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 |
| CN109808870A (en) * | 2019-04-01 | 2019-05-28 | 西北工业大学 | A kind of fast assembling disassembling structure of the vertical horizontal tail connection of unmanned plane |
-
2016
- 2016-08-03 CN CN201610626991.3A patent/CN106218855A/en active Pending
Cited By (2)
| 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 |
| CN109808870A (en) * | 2019-04-01 | 2019-05-28 | 西北工业大学 | A kind of fast assembling disassembling structure of the vertical horizontal tail connection of unmanned plane |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20161214 |
|
| WD01 | Invention patent application deemed withdrawn after publication |