CN206437197U - A kind of dismountable unmanned plane - Google Patents
A kind of dismountable unmanned plane Download PDFInfo
- Publication number
- CN206437197U CN206437197U CN201621329559.XU CN201621329559U CN206437197U CN 206437197 U CN206437197 U CN 206437197U CN 201621329559 U CN201621329559 U CN 201621329559U CN 206437197 U CN206437197 U CN 206437197U
- Authority
- CN
- China
- Prior art keywords
- unmanned plane
- connection framework
- fuselage
- side section
- dismountable
- 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.)
- Active
Links
Landscapes
- Toys (AREA)
Abstract
A kind of dismountable unmanned plane that the utility model is provided, a kind of dismountable unmanned plane that the utility model is provided, by the way that the fuselage of unmanned plane is divided into the first side section and tow side section, it is attached with reference to the connected mode of the first connection framework and the second connection framework detachable connection, one dismountable fuselage of structure is constituted with this, so cause when local damage occurs in the fuselage of unmanned plane, corresponding can remove the position for occurring damaging and be repaired, it is simple, convenient.And when fuselage it is local because appearance is damaged can not repair when, can also the position that can not repair of corresponding dismounting, the position that can not be repaired is substituted, overcome in the prior art because fuselage is using integrated global design, and when make it that fuselage local damage occur can not repair, the technological deficiency that hand throws the whole fuselage of unmanned plane must not be changed without, maintenance cost is significantly reduced；The wing of unmanned plane is also detachable simultaneously, is convenient for carrying.
Description
Technical field
The utility model belongs to unmanned air vehicle technique field, more particularly to a kind of dismountable unmanned plane.
Background technology
UAV referred to as " unmanned plane ", is manipulated using radio robot and the presetting apparatus provided for oneself
Not manned aircraft.Without driving cabin on machine, but the equipment such as automatic pilot, presetting apparatus, information collecting device are installed.
On ground, naval vessels or machine tool remote control station personnel are by equipment such as radars, it is tracked, positioned, remote control, remote measurement and numeral are passed
It is defeated.It can take off or be launched with booster rocket as conventional airplane under wireless remotecontrol, can also be taken in the air by machine tool
Deliver flight.
For unmanned plane, unmanned aerial vehicle body of the prior art is formed using integrally formed structure fabrication.However,
Making is designed using fuselage as an entirety, causes and repairs extremely inconvenient, and when damage nothing occurs in a certain position of fuselage
When method is repaired, have to change the whole fuselage of unmanned plane, significantly increase maintenance cost.
Utility model content
The utility model provides a kind of dismountable unmanned plane, solves or part solves unmanned plane in the prior art of knowing clearly
The high technological deficiency of fuselage maintenance cost, while wing is also detachable, be convenient for carrying.
The utility model provides a kind of dismountable unmanned plane, including fuselage and wing, and the fuselage includes the first side
Section, tow side section, the first connection framework, the second connection framework, supporting part, it is characterised in that first connection framework and the
One end connection of side section, second connection framework is connected with one end of tow side section, first connection framework and second
Connection framework is connected, and the supporting part includes four support bars for being symmetrically distributed in fuselage interior, and the support bar runs through
The first side section, tow side section, the first connection framework and the second connection framework；The wing is in hollow-core construction, wing
Portion is disposed with main connecting tube and secondary connecting tube before and after being provided with the styling components for maintaining wing shapes, the fuselage, described
Main connecting tube and secondary connecting tube extend transversely through fuselage, and the styling components are provided with corresponding with main connecting tube and secondary connecting tube position
And the main fixing pipe of internal diameter identical and secondary fixing pipe, the fuselage side is provided with permanent magnetism suction disc, the styling components setting
There is magnetizing a property suction disc matched with permanent magnetism suction disc, the permanent magnetism suction disc and magnetizing property the suction disc surface that fits are set respectively
There are the anticreep groove matched and anticreep raised.
Wing structure of the present utility model, during installation only need to from any prior art shaft stretch into main connecting tube and
Both are connected inside main fixing pipe, then the shaft from another prior art is stretched into inside secondary connecting tube and secondary fixing pipe
Connect both, you can to realize positioning, acted on by the magnetic absorption of permanent magnetism suction disc and magnetizing property suction disc by fuselage and wing
Be fixedly connected, be it is further strengthen fixed effect, be respectively provided with phase on permanent magnetism suction disc and magnetizing property the suction disc surface that fits
The anticreep groove and anticreep of matching are raised, easy to assembly, accurate positioning, efficiency high.
The anticreep convex cross section is stretched to above wing and rear respectively in 270 ° of arc-shapeds, the raised cut surface of anticreep；
Limiting plate is provided with the outside of the styling components.
The off-loadable one end for being connected to the first side section of first connection framework；Second connection framework is detachable
The one end for being connected to the tow side section carried.
First connection framework is to include between the double-deck tetragonal structure of bottom and surface layer, two layers by positioned at corner
The cotter slot of hollow cylindrical be fixedly connected, fabric, which is located inside the symmetrically arranged positioning hole in bottom two ends, bottom, to be set
It is equipped with cross framework, positioned at the cross junction provided with circular connecting portion, the connecting portion
Center is provided with screw.
The bottom two ends of first connection framework are provided with the first stopper slot and the second stopper slot, first stopper slot
The spacing hole that cross section is rectangle respectively symmetrically is provided with inside portion and the second stopper slot.
Second connection framework is consistent with the structure of first connection framework.
A kind of described dismountable unmanned plane, in addition to the first position limiting structure and the second position limiting structure, first limit
Bit architecture includes base, and the symmetrically arranged clamping piece extended from base, and the clamping piece is internally provided with two limits
Position groove, the base is symmetrically arranged with two spacing slotted eyes, and the stopper slot is connected with spacing slotted eye；Second position limiting structure
Including base, and the clamping piece extended from base, the clamping piece is internally provided with stopper slot, and the base sets limited
Position slotted eye, the stopper slot is connected with spacing slotted eye.By the way that banking stop is inserted into the first limit respectively by the spacing slotted eye of base
In the stopper slot of bit architecture and the second position limiting structure, it is ensured that the stabilization of fuselage in the process of running.
Positional symmetry of the two ends of first side intersegmental part in four corners is provided with 4 locating rings.
Positional symmetry of the two ends of second side intersegmental part in four corners is provided with 4 locating rings.
In the utility model, by the effect of support bar, the first side section, the locating ring of tow side section and the are each passed through
One connection framework, the whole fuselage that act as of the connection member of the second connection framework are provided a supporting role；The support bar can be from
Fuselage is unloaded；By by the engagement corresponding with the bottom of the second connection framework of the first connection framework, passing through the first position limiting structure, second
Position limiting structure, and fixation is connected by screw into the screw of connecting portion, pin is inserted into cotter slot, you can real
Show being fixedly connected for unmanned aerial vehicle body.Further spacing by the way that banking stop is inserted into first respectively by the spacing slotted eye of base
In the stopper slot of structure and the second position limiting structure, it is ensured that the stabilization of fuselage in the process of running.
The beneficial effects of the utility model：
A kind of dismountable unmanned plane that the utility model is provided, by the way that the fuselage of unmanned plane is divided into the first side section and the
Tow side section, is attached with reference to the connected mode of the first connection framework and the second connection framework detachable connection, is constituted with this
One dismountable fuselage of structure, so that when local damage occurs in the fuselage of unmanned plane, corresponding can remove and occur
The position of damage is repaired, simple, convenient.And when fuselage it is local because appearance is damaged can not repair when, can also
The position that corresponding dismounting can not be repaired, i.e., substitute the position that can not be repaired, and overcomes in the prior art because of machine
Body uses integrated global design, and when make it that fuselage local damage occur can not repair, it has to more hand-off throwing unmanned plane
The technological deficiency of whole fuselage, significantly reduces maintenance cost；The wing of unmanned plane is also detachable simultaneously, is convenient for carrying.
Brief description of the drawings
Fig. 1 is structural representation of the present utility model；
Fig. 2 is structural representation of the present utility model；
Fig. 3 is structural representation of the present utility model；
Fig. 4 is structural representation of the present utility model；
Fig. 5 is structural representation of the present utility model；
Fig. 6 is structural representation of the present utility model；
Fig. 7 is structural representation of the present utility model；
Fig. 8 is structural representation of the present utility model.
Embodiment
Below in conjunction with the accompanying drawing in the utility model embodiment, the technical scheme in the utility model embodiment is carried out
Clearly and completely describe, it is clear that described embodiment is only a part of embodiment of the utility model, rather than whole
Embodiment.Based on the embodiment in the utility model, those of ordinary skill in the art are not under the premise of creative work is made
The every other embodiment obtained, belongs to the scope of the utility model protection.
The utility model provides a kind of dismountable unmanned plane, including fuselage 10 and wing 20, and the fuselage includes the
Side section 1, tow side section 2, the first connection framework 3, the second connection framework 4, supporting part 5, it is characterised in that first connection
Framework 3 is connected with one end of the first side section 1, and second connection framework 4 is connected with one end of tow side section 2, and described first connects
Connect framework 3 to be connected with the second connection framework 4, the supporting part includes four support bars for being symmetrically distributed in fuselage interior,
The support bar is through first side section 1, tow side section 2, the first connection framework 3 and the second connection framework 4；The wing
For hollow-core construction, wing is disposed with main company before and after being internally provided with the styling components 21 for maintaining wing shapes, the fuselage
Adapter 22 and secondary connecting tube 23, the main connecting tube and secondary connecting tube extend transversely through fuselage, and the styling components are provided with and master
Connecting tube and secondary connecting tube position correspondence and the main fixing pipe 24 of internal diameter identical and secondary fixing pipe 25, the fuselage side is provided with
Permanent magnetism suction disc 26, the styling components are provided with the magnetizing property suction disc 27 matched with permanent magnetism suction disc, and the permanent magnetism is inhaled
Plate and magnetizing property the suction disc surface that fits are respectively arranged with the anticreep groove 28 matched and anticreep projection 29.
Raised 29 sections of the anticreep in 270 ° of arc-shapeds, the raised cut surface of anticreep stretch to respectively above wing and after
Side；Limiting plate 211 is provided with the outside of the styling components.
The off-loadable one end for being connected to the first side section 1 of first connection framework 3；Second connection framework 4
Off-loadable one end for being connected to the tow side section 2.
First connection framework 3 is to include between the double-deck tetragonal structure of bottom and surface layer, two layers by positioned at four
The cotter slot 31 of the hollow cylindrical at angle is fixedly connected, and fabric is located at the symmetrically arranged positioning hole 32 in bottom two ends, bottom
It is internally provided with cross framework 33, it is described positioned at the cross junction provided with circular connecting portion 34
Connecting portion center is provided with screw 35.
The bottom two ends of first connection framework 3 are provided with the first stopper slot 36 and the second stopper slot 37, first limit
The spacing hole that cross section is rectangle respectively symmetrically is provided with inside the groove of position and inside the second stopper slot.
Access Division 8 is symmetrically arranged with below first connection framework, the support bar fixes clamping with the Access Division.
Second connection framework 4 is consistent with the structure of first connection framework 3.
A kind of described dismountable unmanned plane, in addition to the first position limiting structure 6 and the second position limiting structure 7, described first
Position limiting structure includes base 61, and the symmetrically arranged clamping piece 62 extended from base, and the clamping piece is internally provided with
Two stopper slots, the base is symmetrically arranged with two spacing slotted eyes, and the stopper slot is connected with spacing slotted eye；Second limit
Bit architecture includes base 71, and the clamping piece 72 extended from base, and the clamping piece is internally provided with stopper slot, the bottom
Seat is provided with spacing slotted eye, and the stopper slot is connected with spacing slotted eye.
Positional symmetry of the two ends in four corners inside the first side section 1 is provided with 4 locating rings（Do not mark）.
Positional symmetry of the two ends in four corners inside the tow side section 2 is provided with 4 locating rings（Do not mark）.
Finally it should be noted that：Preferred embodiment of the present utility model is the foregoing is only, this is not limited to
Utility model, although the utility model is described in detail with reference to the foregoing embodiments, for those skilled in the art
For, it can still modify to the technical scheme described in foregoing embodiments, or to which part technical characteristic
Equivalent substitution is carried out, all within spirit of the present utility model and principle, any modification, equivalent substitution and improvements made etc.,
It should be included within protection domain of the present utility model.Originally it is all technical characteristics not being described in detail in utility model,
Realized by any prior art.
Claims (9)
1. a kind of dismountable unmanned plane, including fuselage and wing, it is characterised in that the fuselage includes the first side section, second
Side section, the first connection framework, the second connection framework, supporting part, it is characterised in that first connection framework and the first side section
One end is connected, and second connection framework is connected with one end of tow side section, first connection framework and the second connection framework
It is connected, the supporting part includes four support bars for being symmetrically distributed in fuselage interior, the support bar runs through described first
Side section, tow side section, the first connection framework and the second connection framework；The wing is hollow-core construction, and wing is internally provided with
Maintain to be disposed with main connecting tube and secondary connecting tube, the main connecting tube before and after the styling components of wing shapes, the fuselage
And secondary connecting tube extends transversely through fuselage, the styling components are provided with and internal diameter phase corresponding with main connecting tube and secondary connecting tube position
Same main fixing pipe and secondary fixing pipe, the fuselage side is provided with permanent magnetism suction disc, and the styling components are provided with and permanent magnetism
The magnetizing property suction disc that property suction disc matches, the permanent magnetism suction disc and magnetizing property the suction disc surface that fits is respectively arranged with and matched
Anticreep groove and anticreep it is raised.
2. a kind of dismountable unmanned plane according to claim 1, it is characterised in that the anticreep convex cross section is in 270 °
Arc-shaped, the raised cut surface of anticreep stretches to above wing and rear respectively；Limiting plate is provided with the outside of the styling components.
3. a kind of dismountable unmanned plane according to claim 1, it is characterised in that first connection framework is off-loadable
The one end for being connected to first side section；The off-loadable one end for being connected to the tow side section of second connection framework.
4. a kind of dismountable unmanned plane according to claim 1, it is characterised in that first connection framework is to include
The double-deck tetragonal structure of bottom and surface layer, is fixedly connected by the cotter slot of the hollow cylindrical positioned at corner between two layers,
Fabric is located at the symmetrically arranged positioning hole in bottom two ends, and bottom is internally provided with cross framework, positioned at described ten
The junction of font is provided with screw provided with circular connecting portion, the connecting portion center.
5. a kind of dismountable unmanned plane according to claim 3, it is characterised in that the bottom of first connection framework
Two ends are provided with inside the first stopper slot and the second stopper slot, first stopper slot and respectively symmetrically set inside the second stopper slot
There is the spacing hole that cross section is rectangle.
6. a kind of dismountable unmanned plane according to claim 1, it is characterised in that second connection framework with it is described
The structure of first connection framework is consistent.
7. a kind of dismountable unmanned plane according to claim 1, it is characterised in that also including the first position limiting structure and
Two position limiting structures, first position limiting structure includes base, and the symmetrically arranged clamping piece extended from base, the card
Contact pin is internally provided with two stopper slots, and the base is symmetrically arranged with two spacing slotted eyes, the stopper slot and spacing slotted eye
Connection；Second position limiting structure includes base, and the clamping piece extended from base, and the clamping piece is internally provided with limit
Position groove, the base is provided with spacing slotted eye, and the stopper slot is connected with spacing slotted eye.
8. a kind of dismountable unmanned plane according to claim 1, it is characterised in that the two ends of first side intersegmental part
Positional symmetry in four corners is provided with 4 locating rings.
9. a kind of dismountable unmanned plane according to claim 1, it is characterised in that the two ends of second side intersegmental part
Positional symmetry in four corners is provided with 4 locating rings.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621329559.XU CN206437197U (en) | 2016-12-06 | 2016-12-06 | A kind of dismountable unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621329559.XU CN206437197U (en) | 2016-12-06 | 2016-12-06 | A kind of dismountable unmanned plane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206437197U true CN206437197U (en) | 2017-08-25 |
Family
ID=59648308
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621329559.XU Active CN206437197U (en) | 2016-12-06 | 2016-12-06 | A kind of dismountable unmanned plane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206437197U (en) |
-
2016
- 2016-12-06 CN CN201621329559.XU patent/CN206437197U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN206939031U (en) | A kind of electronic unmanned plane of fixed-wing | |
| US10046850B2 (en) | Aircraft wing shift device | |
| CN107600414B (en) | Unmanned aerial vehicle capable of taking off in box and rapidly assembling without tools | |
| CN106125766A (en) | A kind of railway line based on unmanned plane patrols and examines monitoring system and method for inspecting | |
| US20160069299A1 (en) | Orientable rocket-motor system | |
| CN102351045A (en) | Wing folding mechanism suitable for folding wing at any angle | |
| CN205221105U (en) | Solar energy VTOL fixed wing uavs | |
| CN107010205A (en) | A kind of aircraft and its control method with the empennage that can vert | |
| CN206437197U (en) | A kind of dismountable unmanned plane | |
| US20160144950A1 (en) | Wing aerial refueling system | |
| CN204223179U (en) | A kind of three rotor wing unmanned aerial vehicles high with flexible hook accurate positioning intensity | |
| CN202429344U (en) | Unmanned aerial vehicle | |
| CN206231611U (en) | Off-loadable unmanned aerial vehicle body structure | |
| CN205819543U (en) | A kind of composite wing unmanned plane wing of fast demountable | |
| TWM524313U (en) | Unmanned aerial vehicle | |
| RU2007108411A (en) | LOW-MIXED UNMANNED AIRCRAFT | |
| CN107161316A (en) | A kind of replaceable horn connect-disconnect structure of unmanned plane | |
| CN102009743B (en) | Blowing based fuselage high incidence pitching moment control method | |
| CN205010465U (en) | Unmanned aerial vehicle | |
| CN106275391A (en) | Aircraft disengaged land undercarriage | |
| CN204197267U (en) | A kind of fixed-wing unmanned plane body two sectional type rapid dismounting apparatus | |
| CN205440851U (en) | A device for wing is connected | |
| CN203497173U (en) | Single-interceptor tail wing of unmanned plane | |
| CN105383683A (en) | Three-section and impact resisting type UAV (Unmanned Aerial Vehicle) wing | |
| CN110861764A (en) | A folding mechanism for unmanned aerial vehicle horn |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |