CN205022843U - Unmanned aerial vehicle organism is automatic to expand and folding mechanism - Google Patents
Unmanned aerial vehicle organism is automatic to expand and folding mechanism Download PDFInfo
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- CN205022843U CN205022843U CN201520580567.0U CN201520580567U CN205022843U CN 205022843 U CN205022843 U CN 205022843U CN 201520580567 U CN201520580567 U CN 201520580567U CN 205022843 U CN205022843 U CN 205022843U
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- rotor
- limiting stopper
- quadrotor
- latch
- steering wheel
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Abstract
The utility model provides an unmanned aerial vehicle organism is automatic to expand and folding mechanism, includes four rotor craft main tributary stay tubes (1), four rotor stay tube (2), steering wheel (4), stopper (5), bolt (6), and when four rotor crafts were folding, steering wheel (4) drove four rotor stay tube (2) and rotate until spacing by stopper (5), and bolt (6) are fixed with four rotor craft main tributary stay tubes (1), four rotor stay tube (2) locking, when four rotor crafts expanded, it is fixed that locking is relieved in bolt (6), and steering wheel (4) drive four rotor stay tube (2) and rotate until spacing by stopper (5), and bolt (6) are fixed four rotor craft main tributary stay tubes (1), four rotor stay tube (2) again. Compared with the prior art, the utility model, fold four rotor crafts, reduced the biggest outline diameter, saved the space of depositing, be convenient for the storage with the transportation.
Description
Technical field
The utility model relates to multi-rotor aerocraft field, particularly a kind of unmanned plane body Automatic-expanding and fold mechanism.
Background technology
With its size, little, lightweight, the easy to operate and advantage such as to fly under severe Airflow Environment receives much attention in many countries traditional multi-rotor aerocraft.Compared with other rotary aircraft, multi-rotor aerocraft can produce larger lift, and have higher propulsion coefficient, structure is compacter, and noise is little, disguised high.Therefore all can be used widely in the field such as civilian, military.
Many rotor wing unmanned aerial vehicles traditional at present mainly comprise the configurations such as four rotors, six rotors and eight rotors, wherein quadrotor is a kind of multi-rotor aerocraft the most common, it installs the fixing rotor in four inclination angles at grade, compared with traditional single-rotor helicopter, quadrotor can adopt less rotor, thus make flight become safer, and the static state that the thrust that the more single rotor of thrust of four rotor generations produces can better realize aircraft is spiraled.
Multi-rotor aerocraft has little, lightweight, the easy to operate and advantage such as to fly under severe meteorological conditions of size, but due to this unmanned plane be made up of 4 to 8 strut bars, to launch volume larger, inconvenience is there is in carrying and storing process, binding bolt is needed to lay down, even needing to remove strut bar, bringing a lot of inconvenience for using.Such as can carry four rotor wing unmanned aerial vehicles of about 5kg load, at least need the aircraft rack of about 1.4 meters diameters, be unfavorable for depositing and transporting of unmanned plane.And adopt the mode of removing binding bolt or complete machine dismounting can save storage space, but add the work capacity of user.
Utility model content
The technical matters that the utility model solves is: overcome the deficiencies in the prior art, provide and a kind ofly by steering wheel, the main support tube of quadrotor, four flight support pipe rotary foldings, limiting stopper to be limited its folding radius, reduce unmanned plane body Automatic-expanding and the fold mechanism of the maximum outline diameter of four rotodynes.
Technical solution of the present utility model is: a kind of unmanned plane body Automatic-expanding and fold mechanism, comprises the main support tube of quadrotor, four flight support pipes, steering wheel, limiting stopper, latch, wherein
Limiting stopper is the hollow cylindrical structure that one end is provided with step-like projection, internal protrusion is circular, outer projection is arc-shaped and diameter is greater than internal protrusion, limiting stopper other end inside is provided with groove, groove is larger away from protruding end opening, less near protruding end opening, latch one end is provided with hold assembly, hold assembly lower end is provided with spring, it is the first circular baffle plate between hold assembly and spring, lower spring end is provided with the second circular baffle plate be fixedly connected with latch, latch bottom is provided with gore, and gore geomery is less than groove away from protruding end opening, be greater than groove near protruding end opening,
The main support tube one end of quadrotor is fixedly connected with steering wheel, limiting stopper, and steering wheel is connected with four flight support pipe one end by gear, and four these ends of flight support pipe are connected by the main support tube of limiting stopper and quadrotor; The main support tube of described quadrotor, four flight support pipes are the criss-cross girder of quadrotor frame, for connecting main rotor, secondary rotor.
The radian of described limiting stopper peripheral projection is 120 degree.
Described limiting stopper and latch all adopt aircraft aluminum material.
The main support tube of described quadrotor, four flight support pipes all adopt carbon fibre material.
The utility model advantage is compared with prior art:
(1) the utility model launches to be limited its folding radius by steering wheel rotary folding, limiting stopper the main support tube of quadrotor, four flight support pipes with fold mechanism, reduces the maximum outline diameter of four rotodynes;
(2) the utility model launch with fold mechanism compared with prior art, to quadrotor carry out folding after, be reduced to 840mm from 1310mm after maximum outline diameter is folding, save deposit space, be convenient to store with transport;
(3) compared with prior art, be easy to carry, reduce traffic cost, be applicable to various complex environment, applicability is wider for the utility model expansion and fold mechanism.
Accompanying drawing explanation
Fig. 1 (a)-(d) is a kind of unmanned plane body Automatic-expanding of the utility model and fold mechanism schematic diagram;
Fig. 2 is limiting stopper schematic diagram in a kind of unmanned plane body Automatic-expanding of the utility model and fold mechanism;
Fig. 3 is latch schematic diagram in a kind of unmanned plane body Automatic-expanding of the utility model and fold mechanism.
Detailed description of the invention
The utility model proposes a kind of unmanned plane body Automatic-expanding and fold mechanism, the main support tube of quadrotor 1, four flight support pipe 2, secondary rotor 3, steering wheel 4, limiting stopper 5, latch 6 is comprised as shown in Fig. 1 (a), (b), (c), (d), wherein, steering wheel 4 is mainly used in Automatic-expanding and the recovery of unmanned owner's support tube 1 and four flight support pipes 2, by controlling the rotation of steering wheel 4, four flight support pipes 2 are driven to move to assigned address; Limiting stopper 5 is for the location, position after completing main support tube 1 and four flight support pipes 2 and opening; Latch 6 is fastening for what complete that main support tube 1 and four flight support pipes 2 are opened to after assigned address, when packing up, extract latch 6, operated by steering wheel 4 and regained, when moving to limited piece of 5 opposite sides and blocking, be stowed position, below in conjunction with accompanying drawing, the utility model expansion and fold mechanism be described in detail.
As shown in Fig. 1 (c), (d), the utility model launches to use steering wheel 4 rotary folding with fold mechanism by main support tube 1 and four flight support pipes 2, and by limiting stopper 5, its folding radius is limited, reduce the maximum outline diameter of aircraft, improve the applicability of unmanned plane.Upon deployment, outside, steering wheel 4 operates latch 6, and rotor system is launched, and in figure, dotted line direction is framework pipe link (four flight support pipes 2) axis direction; Be in control position when rotor plate turns to limited piece 5 and blocks, insert with latch 6 and be located; The triangle fritter of latch 6 lower end turns in limiting stopper, is tightened up by top spring.Rotor system is fixed; The utility model launches can to rotor system effect one power upwards with fold mechanism, balancing gravity is to the moment of flexure of steering wheel 4, reduce the linear deformation of rotor system, wherein, quadrotor main support tube 1, four flight support pipe 2 is the criss-cross girder of quadrotor frame, and for connecting main rotor, duct and secondary rotor, both all adopt carbon fibre material, wherein main support tube length is 80 centimetres, and four flight support length of tube are 30 centimetres.
As shown in Figure 2, the hollow cylindrical structure of limiting stopper 5 step-like projection for one end is provided with, internal protrusion is circular, outer projection is arc-shaped and diameter is greater than internal protrusion, limiting stopper 5 other end inside is provided with groove, and groove is comparatively large away from protruding end opening, less near protruding end opening, the radian of outer projection is 100 degree of-140 degree, is preferably 120 degree.
Latch 6 one end is provided with hold assembly as shown in Figure 3, hold assembly lower end is provided with spring, it is the first circular baffle plate between hold assembly and spring, lower spring end is provided with the second circular baffle plate be fixedly connected with latch, and latch bottom is provided with gore, and gore geomery is less than groove away from protruding end opening, be greater than groove near protruding end opening, wherein, limiting stopper 5 and latch 6 all adopt aircraft aluminum material, lighter weight.
Quadrotor main support tube 1 one end is fixedly connected with steering wheel 4, limiting stopper 5, and steering wheel 4 is connected with four flight support pipe 2 one end by gear, and four these ends of flight support pipe 2 are connected by the main support tube 1 of limiting stopper 5 and quadrotor.When quadrotor folds, steering wheel 4 rotates until four flight support pipes 2 limited piece of 5 one end are spacing by drive four flight support pipe 2, rotate until gore enters the groove of limiting stopper 5 after the mesopore that latch 6 inserts limiting stopper 5 makes spring elongation, spring tightens up and drives gore upward movement in limiting stopper 5 groove, is locked by main for quadrotor support tube 1, four flight support pipe 2, when quadrotor launches, latch 6 rotates after making spring elongation, gore moves downward and produces in groove in limiting stopper groove, remove the main support tube 1 of quadrotor, four flight support pipes 2 are locked, steering wheel 4 rotates until four flight support pipes 1 limited piece of 5 other ends are spacing by drive four flight support pipe 1, rotate until gore enters the groove of limiting stopper 5 after the mesopore that latch 6 inserts limiting stopper 5 makes spring elongation, spring tightens up and drives gore upward movement in limiting stopper 5 groove, by main for quadrotor support tube 1, four flight support pipes 2 are fixed.
A kind of novel many rotor wing unmanned aerial vehicles body Automatic-expanding that the utility model proposes with and folding device, can be used as the folding of the aircrafts such as current four rotors, six rotors and device for opening, have that structure is simple, reliability is high, the feature of automatic operation, and effectively can save the parking space of unmanned plane.
The content be not described in detail in the utility model specification sheets belongs to the known technology of those skilled in the art.
Claims (4)
1. a unmanned plane body Automatic-expanding and fold mechanism, it is characterized in that comprising the main support tube of quadrotor (1), four flight support pipes (2), steering wheel (4), limiting stopper (5), latch (6), wherein
The hollow cylindrical structure of limiting stopper (5) step-like projection for one end is provided with, internal protrusion is circular, outer projection is arc-shaped and diameter is greater than internal protrusion, limiting stopper (5) other end inside is provided with groove, groove is larger away from protruding end opening, less near protruding end opening, latch (6) one end is provided with hold assembly, hold assembly lower end is provided with spring, it is the first circular baffle plate between hold assembly and spring, lower spring end is provided with the second circular baffle plate be fixedly connected with latch, latch bottom is provided with gore, and gore geomery is less than groove away from protruding end opening, be greater than groove near protruding end opening,
The main support tube of quadrotor (1) one end is fixedly connected with steering wheel (4), limiting stopper (5), steering wheel (4) is connected with four flight support pipe (2) one end by gear, and four flight support pipe (2) these ends are connected with the main support tube of quadrotor (1) by limiting stopper (5); The criss-cross girder that the main support tube of described quadrotor (1), four flight support pipes (2) are quadrotor frame, for connecting main rotor, secondary rotor.
2. a kind of unmanned plane body Automatic-expanding according to claim 1 and fold mechanism, is characterized in that: the radian of described limiting stopper (5) peripheral projection is 120 degree.
3. a kind of unmanned plane body Automatic-expanding according to claim 1 and 2 and fold mechanism, is characterized in that: described limiting stopper (5) and latch (6) all adopt aircraft aluminum material.
4. a kind of unmanned plane body Automatic-expanding according to claim 1 and 2 and fold mechanism, is characterized in that: the main support tube of described quadrotor (1), four flight support pipes (2) all adopt carbon fibre material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520580567.0U CN205022843U (en) | 2015-08-04 | 2015-08-04 | Unmanned aerial vehicle organism is automatic to expand and folding mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520580567.0U CN205022843U (en) | 2015-08-04 | 2015-08-04 | Unmanned aerial vehicle organism is automatic to expand and folding mechanism |
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| Publication Number | Publication Date |
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| CN205022843U true CN205022843U (en) | 2016-02-10 |
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| CN201520580567.0U Active CN205022843U (en) | 2015-08-04 | 2015-08-04 | Unmanned aerial vehicle organism is automatic to expand and folding mechanism |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105912023A (en) * | 2016-05-31 | 2016-08-31 | 王翔 | Portable multifunctional unmanned aerial vehicle and control system and control method thereof |
| CN114194371A (en) * | 2020-09-02 | 2022-03-18 | 新疆大学 | Rotor unmanned aerial vehicle modularization changeability frame |
-
2015
- 2015-08-04 CN CN201520580567.0U patent/CN205022843U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105912023A (en) * | 2016-05-31 | 2016-08-31 | 王翔 | Portable multifunctional unmanned aerial vehicle and control system and control method thereof |
| CN105912023B (en) * | 2016-05-31 | 2019-12-13 | 南京禾谱航空科技有限公司 | portable multifunctional unmanned aerial vehicle |
| CN114194371A (en) * | 2020-09-02 | 2022-03-18 | 新疆大学 | Rotor unmanned aerial vehicle modularization changeability frame |
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| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |