CN205469799U - Six collapsible rotor crafts - Google Patents
Six collapsible rotor crafts Download PDFInfo
- Publication number
- CN205469799U CN205469799U CN201620030215.2U CN201620030215U CN205469799U CN 205469799 U CN205469799 U CN 205469799U CN 201620030215 U CN201620030215 U CN 201620030215U CN 205469799 U CN205469799 U CN 205469799U
- Authority
- CN
- China
- Prior art keywords
- type
- hinge
- seat
- support arm
- fixing seat
- 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.)
- Expired - Fee Related
Links
Landscapes
- Seats For Vehicles (AREA)
Abstract
The utility model belongs to an unmanned vehicles, in particular to microminiature rotor craft. Its technical scheme is: a six collapsible rotor crafts, includes: two Y type power module (1), two I type list support arms (3) and aircraft fuselage (5), Y type power module (1) through Y type folding assembly (2) I type list support arm (3) is connected to through single support arm folding assembly (4) aircraft fuselage (5), the utility model discloses folding back volume reduces 54% when launching, has solved the not problem of portable transportation of the many rotor crafts of multiaxis effectively to simple structure chooses moulding material for use, can effectively reduce aircraft self cost.
Description
Technical field
This utility model belongs to a kind of unmanned vehicle, particularly to a kind of Microminiature rotorcraft.
Background technology
The course of new aircraft that six rotorcraft is a kind of novel structure, manipulation is simple, stability is high, it have VTOL,
Unique flight function such as hovering and motor-driven avoidance, it is possible to more preferably complete aerial mission in less space.At present, six rotation
Rotor aircraft is all widely used army and police and civil area, plays significant role in the development of the national economy, existing in disaster
The fields such as field relief, traffic monitoring, unmanned plant protection also possess huge application potential.
Tradition six rotorcraft owing to support arm is connected with main body, the compactest, cause its transport and
Use when assembling extremely inconvenient.In order to solve this problem, occur in that folding six rotor wing unmanned aerial vehicles of support arm.But, mesh
Support arm folding structure on front market, all uses both sides rotor doubling, forms the folding effect of " one " font；This kind of folding
Folded mode can only reduce the space of fuselage both sides, and the space of fuselage rear and front end does not the most change.
Summary of the invention
The purpose of this utility model is: provides that a kind of foldability is strong, be easy to carry, six rotorcraft simple to operate.
The technical solution of the utility model is: a kind of collapsible six rotorcraft, including: two Y type power plant modules, two
I type list support arm and aircraft fuselage；Y type power plant module passes through single support arm foldable assembly by Y type foldable assembly, I type list support arm
It is connected to aircraft fuselage；
Y type foldable assembly includes: connect the first fixing seat of hinge of aircraft fuselage, connects the Y type seat of Y type power plant module,
Hinged first fixing seat of hinge and the first hinge pin of Y type seat, lock the first fixing seat of hinge and Y type seat first fixes spiral shell
Bolt；Y type seat is turned over around the first hinge pin and turn 90 degrees, fix bolt by first and be installed into the first bolt hole, then make Y type power
Module expands into state of flight；Fix bolt to take out first, by Y type seat around the first hinge pin reverse flip 90 degree, then make
Y type power plant module is in folded state；
Single support arm foldable assembly includes: connect the second fixing seat of hinge of aircraft fuselage, connects the single tube seat of I type list support arm,
Hinged second fixing seat of hinge and connect the second hinge pin of I type list support arm, locks the of the second fixing seat of hinge and single tube seat
Two fix bolt；Single tube seat is turned over around the second fixing seat of hinge and turn 90 degrees, fix bolt by second and be installed into the second bolt hole, then
I type list support arm is made to expand into state of flight；Fix bolt to take out second, by single tube seat around the second hinge pin reverse flip 90
Degree, then make I type list support arm be in folded state.
Beneficial effect: reduce 54% when this utility model volume after folding is relatively launched, efficiently solve multiaxis multi-rotor aerocraft
The problem of not readily portable transport, and simple in construction, select moulding material, can effectively reduce aircraft cost taken by themselves.
Accompanying drawing explanation
Fig. 1 is that this utility model launches state of flight axis side view；
Fig. 2 is that this utility model launches state of flight front view；
Fig. 3 is this utility model folded state front view；
Fig. 4 is the upward view of Fig. 3；
Fig. 5 is this utility model attachment structure schematic diagram；
Fig. 6 is Y type folding component element structure schematic diagram in this utility model；
Fig. 7 is single support arm folding component element structure schematic diagram in this utility model.
Detailed description of the invention
Develop simultaneously embodiment below in conjunction with the accompanying drawings, is described in detail this utility model.
See each accompanying drawing, a kind of collapsible six rotorcraft, including: two Y type power plant modules 1, two I type list support arms 3
With aircraft fuselage 5；Y type power plant module 1 passes through single support arm foldable assembly 4 by Y type foldable assembly 2, I type list support arm 3
It is connected to aircraft fuselage 5；
Y type foldable assembly 2 includes: connect the first fixing seat of hinge 21 of aircraft fuselage 5, connects Y type power plant module 1
Y type seat 22, the first hinge pin 23 of hinged first fixing seat of hinge 21 and Y type seat 22, lock the first fixing seat of hinge 21
Bolt is fixed with the first of Y type seat 22；Y type seat 22 is turned over around the first hinge pin 23 and turn 90 degrees, fix bolt by first
It is installed into the first bolt hole 24, then makes Y type power plant module 1 expand into state of flight；Fix bolt to take out first, by Y type
Seat 22 around the first hinge pin 23 reverse flip 90 degree, then makes Y type power plant module 1 be in folded state；
Single support arm foldable assembly 4 includes: connect the second fixing seat of hinge 41 of aircraft fuselage 5, connects I type list support arm 3
Single tube seat 43, hinged second fixing seat of hinge 41 and the second hinge pin 42 of connection I type list support arm 3, lock the second hinge
The second of fixing seat 41 and single tube seat 43 fixes bolt；Single tube seat 43 is turned over around the second fixing seat of hinge 41 and turn 90 degrees, by
Two fix bolt is installed into the second bolt hole 44, then make I type list support arm 3 expand into state of flight；Fix bolt to take out second,
By single tube seat 43 around the second hinge pin 42 reverse flip 90 degree, then I type list support arm 3 is made to be in folded state.
For ease of producing and using, the first fixing seat of hinge 21 is identical with the second fixing seat of hinge 41, the first hinge pin 23 and
Second fixing seat of hinge 41 is identical.
In sum, these are only preferred embodiment of the present utility model, be not intended to limit protection model of the present utility model
Enclose.All within spirit of the present utility model and principle, any modification, equivalent substitution and improvement etc. made, should be included in
Within protection domain of the present utility model.
Claims (2)
1. a collapsible six rotorcraft, including two Y type power plant module (1), two I type list support arm (3) and
Aircraft fuselage (5)；It is characterized in that: described Y type power plant module (1) is propped up by Y type foldable assembly (2), described I type list
Arm (3) is connected to described aircraft fuselage (5) by single support arm foldable assembly (4)；
Described Y type foldable assembly (2) including: connects first fixing seat of hinge (21) of described aircraft fuselage (5), connects
Y type seat (22) of described Y type power plant module (1), hinged described first fixing seat of hinge (21) and described Y type seat (22)
The first hinge pin (23), lock described first fixing seat of hinge (21) and described Y type seat (22) first fixes bolt；
Described Y type seat (22) is turned over around described first hinge pin (23) and turn 90 degrees, fix bolt by described first and be installed into first
Bolt hole (24), then make described Y type power plant module (1) expand into state of flight；Fix bolt to take out described first, will
Described Y type seat (22) around described first hinge pin (23) reverse flip 90 degree, then makes described Y type power plant module (1)
It is in folded state；
Described single support arm foldable assembly (4) including: connects second fixing seat of hinge (41) of described aircraft fuselage (5), even
Connect the single tube seat (43) of described I type list support arm (3), hinged described second fixing seat of hinge (41) and the described I type list of connection
Second hinge pin (42) of support arm (3), locks the of described second fixing seat of hinge (41) and described single tube seat (43)
Two fix bolt；Described single tube seat (43) is turned over around described second fixing seat of hinge (41) and turn 90 degrees, fix described second
Bolt is installed into the second bolt hole (44), then make described I type list support arm (3) expand into state of flight；Fix described second
Bolt takes out, and by described single tube seat (43) around described second hinge pin (42) reverse flip 90 degree, then makes described I type list
Support arm (3) is in folded state.
The collapsible six rotorcraft of one the most according to claim 1, is characterized in that: described first fixing seat of hinge
(21) identical with described second fixing seat of hinge (41), described first hinge pin (23) and described second fixing seat of hinge
(41) identical.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620030215.2U CN205469799U (en) | 2016-01-13 | 2016-01-13 | Six collapsible rotor crafts |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620030215.2U CN205469799U (en) | 2016-01-13 | 2016-01-13 | Six collapsible rotor crafts |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205469799U true CN205469799U (en) | 2016-08-17 |
Family
ID=56667757
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620030215.2U Expired - Fee Related CN205469799U (en) | 2016-01-13 | 2016-01-13 | Six collapsible rotor crafts |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205469799U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107416176A (en) * | 2017-04-18 | 2017-12-01 | 深圳市易飞行科技有限公司 | Support arm turns down folding and unfolding unmanned plane |
| CN110816836A (en) * | 2019-12-06 | 2020-02-21 | 沈阳旋飞航空技术有限公司 | Support arm folding mechanism for unmanned aerial vehicle |
-
2016
- 2016-01-13 CN CN201620030215.2U patent/CN205469799U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107416176A (en) * | 2017-04-18 | 2017-12-01 | 深圳市易飞行科技有限公司 | Support arm turns down folding and unfolding unmanned plane |
| CN110816836A (en) * | 2019-12-06 | 2020-02-21 | 沈阳旋飞航空技术有限公司 | Support arm folding mechanism for unmanned aerial vehicle |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US10414483B2 (en) | Tiltrotor articulated wing extension | |
| Min et al. | Aircraft morphing wing concepts with radical geometry change | |
| CN107000834B (en) | More rotor unmanned aircrafts | |
| CN204895844U (en) | Many rotor unmanned aerial vehicle | |
| CN102556336A (en) | Wing fast unfolding device for folding-wing unmanned plane | |
| CN205891225U (en) | Spherical unmanned aerial vehicle of portable and foldable | |
| CN205469799U (en) | Six collapsible rotor crafts | |
| CN109050898A (en) | Non-homogeneous ten rotor wing unmanned aerial vehicle of power arrangement formula | |
| CN107031828A (en) | A kind of unmanned plane | |
| CN205239891U (en) | Multiaxis aircraft fuselage structure | |
| CN207580155U (en) | A kind of unmanned plane undercarriage folded piece | |
| CN205707294U (en) | Folding piece in a kind of horn on Multi-axis aircraft | |
| CN208360493U (en) | A kind of portable aerial survey quadrotor drone | |
| CN204197271U (en) | A kind of collapsible dynamic-delta-wing wing | |
| CN205469801U (en) | Horn folding device of multiaxis aircraft | |
| CN205010465U (en) | Unmanned aerial vehicle | |
| CN209506060U (en) | A kind of small type tail synchronous folding mechanism, folding wings unmanned plane and emission system | |
| CN204937498U (en) | The foldable mechanism of rotor arm on a kind of novel oil electricity mixing plant protection unmanned plane | |
| CN109515732B (en) | Combined aircraft based on barrel type launching | |
| CN206841703U (en) | Support arm turns down folding and unfolding unmanned plane | |
| CN208715473U (en) | Non-homogeneous ten rotor wing unmanned aerial vehicle of power arrangement formula | |
| CN105314088A (en) | Four-rotor craft | |
| CN207311833U (en) | A kind of unmanned plane horn and unmanned plane | |
| CN205499346U (en) | Many rotor unmanned aerial vehicle fast folding mechanism | |
| CN204846358U (en) | Foldable unmanned aerial vehicle horn locking device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160817 Termination date: 20180113 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |