CN205499346U - Many rotor unmanned aerial vehicle fast folding mechanism - Google Patents
Many rotor unmanned aerial vehicle fast folding mechanism Download PDFInfo
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- CN205499346U CN205499346U CN201520812224.2U CN201520812224U CN205499346U CN 205499346 U CN205499346 U CN 205499346U CN 201520812224 U CN201520812224 U CN 201520812224U CN 205499346 U CN205499346 U CN 205499346U
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- wing
- connecting portion
- folding
- folding part
- rotating shaft
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Abstract
The utility model provides a many rotor unmanned aerial vehicle fast folding mechanism relates to the unmanned air vehicle technique field. Wing and back wing before the many rotor unmanned aerial vehicle fast folding mechanism, preceding wing place plane is a little more than back wing place plane, preceding wing includes first connecting portion, first folding portion and first pivot, back wing includes second connecting portion, the folding portion of second and second pivot, wherein, the first folding portion of preceding wing is close to pivot department and still is equipped with spacing post, spacing post is used for restricting the rotation of first pivot, back wing is still including head and the tail first bracing piece of articulated and second bracing piece, first bracing piece and second bracing piece articulate respectively in second connecting portion and the folding portion of second. The utility model has the advantages of it is folding fast, folding efficient, can effectual solution case, transport or carry inconvenient problem.
Description
Technical field
This utility model design unmanned air vehicle technique field, specifically refers to a kind of Quick folding mechanism on many rotor wing unmanned aerial vehicles.
Background technology
Unmanned plane is to start the most practical a kind of aircraft at present, its have maneuverability, reaction quickly, unmanned flight, operation require the advantages such as low.Unmanned plane loads multiclass sensor, such as photographic head, it is possible to achieve image real-time Transmission, high-risk areas detecting function, be widely used in the fields such as fire-fighting, military affairs, traffic, police service, exploration and meteorology, to realize finger
Determine cruise shooting and the supervision in region.At present, unmanned plane is that flight theory based on helicopter is designed manufacturing mostly, can
Realizing vertical lift and high-altitude hovering, thus meet the requirement taken photo by plane and monitor, most common is fixed-wing formula and many rotary wind types (such as, four rotor).It is relatively big to there is size in many rotor wing unmanned aerial vehicles of prior art, cases, transports or problem inconvenient to carry.Although also there being some foldable structures; but it has a problem in that; when support arm folds, rotor Chang Huiyu fuselage interferes; cannot realize folding completely; that is the unmanned plane overall structure under support arm folded state is the compactest, and the size after folding the most not can solve vanning, transport or problem inconvenient to carry.
The folding mode of the horn of many rotor wing unmanned aerial vehicles in the market is vertically oriented mostly, but, such folding mode has certain restriction to the size of type, thus has limited the power size of overall type.And many rotor wing unmanned aerial vehicles that minority horizontal direction is folded, need folding and retraction one by one when folding horn, the lateral dimension of whole fuselage can be increased, comparatively speaking, folding and unfolding process steps is more, and the mode of folding is relatively complicated, have impact on folding rate and efficiency.
Utility model content
The purpose of this utility model is to solve the problems referred to above and propose a kind of many rotor wing unmanned aerial vehicles Quick folding mechanism, this fold mechanism has the advantage that folding rate is fast, folding efficiency is high, in addition, the overall dimensions of fuselage will not be destroyed when this fold mechanism is in folded state, solve vanning, transport or problem inconvenient to carry.
To achieve these goals, the technical scheme that this practicality is taked is as follows:
The utility model proposes a kind of many rotor wing unmanned aerial vehicles Quick folding mechanism, including wing, described wing includes front wing and rear wing, described front wing place plane is different from rear wing place plane, described front wing includes the first connecting portion, the first folding part and the first rotating shaft, described first connecting portion is fixedly connected on fuselage, and one end of the first connecting portion is located in described first rotating shaft, and described first folding part is rotatablely connected with the first connecting portion by the first rotating shaft；Described rear wing includes that the second connecting portion, the second folding part and the second rotating shaft, described second connecting portion are fixedly connected on fuselage, and one end of the second connecting portion is located in described second rotating shaft, and described second folding part is rotatablely connected with the second connecting portion by the second rotating shaft.
First folding part of described front wing is additionally provided with limited post at the first rotating shaft, and described limited post is for limiting the rotation of the first rotating shaft；Described rear wing also includes the first the most hinged support bar and the second support bar, and described first support bar and the second support bar are hingedly connected to the second connecting portion and the second folding part.
Described first connecting portion and the second connecting portion favour head and the afterbody of fuselage respectively, and when wing is in deployed condition, described first folding part is perpendicular to fuselage, and described second folding part and described second connecting portion are in same straight line.
Ka Hebu, described first support bar or the second support bar cocker is further respectively had and in described card and portion on described second connecting portion and the second folding part.
The end of described first folding part and the second folding part is respectively equipped with motor.
The beneficial effects of the utility model:
The most compared with prior art, front wing of the present utility model and rear wing are on different horizontal planes, and when after wing-folding, front wing and rear wing overlap the overall lateral dimensions without increasing fuselage, advantageously in vanning, transport or carry；
The most front wing and rear wing are respectively equipped with the first rotating shaft and the second rotating shaft so that wing can quickly, carry out smoothly when folding；
Front wing and rear wing are fixed by the limited post on the most front wing and hinged the first support bar of the head and the tail on rear wing and the second support bar respectively, after preventing wing from launching or folding built on the sand, improve the unmanned plane stationarity when flight.
Accompanying drawing explanation
Constituting a part of Figure of description of the present utility model and be further appreciated by of the present utility model in order to providing, schematic description and description of the present utility model is used for explaining this utility model, is not intended that improper restriction of the present utility model.In the accompanying drawings:
Fig. 1 is that this utility model a kind of many rotor wing unmanned aerial vehicles Quick folding mechanism is in the structural representation under deployed condition；
Fig. 2 is that this utility model a kind of many rotor wing unmanned aerial vehicles Quick folding mechanism is in the structural representation under folded state；
Fig. 3 is the structural representation of the front wing of this utility model a kind of many rotor wing unmanned aerial vehicles Quick folding mechanism；
Fig. 4 is the structural representation of the rear wing of this utility model a kind of many rotor wing unmanned aerial vehicles Quick folding mechanism.
Wherein, above-mentioned accompanying drawing includes the following drawings labelling:
Wing before 1-, wing after 2-, 3-motor, 11-the first connecting portion, 12-the second folding part, 13-the first rotating shaft, 14-limited post, 21-the second connecting portion, 22-the second folding part, 23-the 3rd rotating shaft, 24-the first support bar, 25-the second support bar, 26-card and portion.
Detailed description of the invention
For clearer, complete explanation the purpose of this utility model, technical scheme and advantage, below in conjunction with the accompanying drawing in this utility model embodiment, this utility model is further described.
As shown in Figure 1-2, the utility model proposes a kind of many rotor wing unmanned aerial vehicles Quick folding mechanism, including wing, wing includes front wing 1 and rear wing 2.
Wherein, front wing place plane is different from rear wing place plane, in conjunction with Fig. 3, described front wing 1 includes the first connecting portion the 11, first folding part 12 and the first rotating shaft 13, described first connecting portion 11 is fixedly connected on fuselage, one end of the first connecting portion 11 is located in described first rotating shaft 13, and described first folding part 12 is rotatablely connected with the first connecting portion 11 by the first rotating shaft 13；In conjunction with Fig. 4, described rear wing 2 includes the second connecting portion the 21, second folding part 22 and the second rotating shaft 23, described second connecting portion 11 is fixedly connected on fuselage, one end of the second connecting portion 21 is located in described second rotating shaft 23, and described second folding part 22 is rotatablely connected with the second connecting portion 21 by the second rotating shaft 23.Front wing 1 and rear wing 2 are respectively equipped with the first rotating shaft 13 and the second rotating shaft 23 so that wing can quickly, carry out smoothly when folding.First connecting portion 11 of the present utility model and the second connecting portion 21 are respectively arranged on the fore-end of fuselage and the rear end part of fuselage, and first connecting portion 11 and the second connecting portion 21 favour head and the afterbody of fuselage respectively, arrange in " rice " font on the whole, when making wing be in deployed condition, described first folding part 12 is perpendicular to fuselage, and described second folding part 22 is in same straight line with described second connecting portion 21.First connecting portion 11 and the second connecting portion 21 are not at same level, first connecting portion 11 and the second connecting portion 21 all stretch out from the inside of fuselage, i.e. first connecting portion 11 and second connecting portion 21 part are in inside fuselage, another part is in the outside of fuselage, this kind of version, make when, after wing-folding, the vanning of the lateral dimension that fuselage is overall, beneficially unmanned plane being reduced, transport or carry.
First folding part 12 of described front wing 1 is additionally provided with limited post 14 at the first rotating shaft 13, and described limited post 14 is for limiting the rotation of the first rotating shaft 13；Described rear wing 3 also includes the first support bar 24 and the second support bar 25 that head and the tail are hinged, and described first support bar 14 and the second support bar 25 are hingedly connected to the second connecting portion 21 and the second folding part 22.For front wing 1, limited post 14 is connected to the first rotating shaft 13, and limited post 14 can be stirred left and right in the first folding part 12, limits the rotation of the first rotating shaft 13 by stirring limited post 14, thus realizes fixing front wing 1；nullFor rear wing 2，Limit fixation mainly to be completed by the first the most hinged support bar 24 and the second support bar 25，It is specific as follows: when rear wing 2 is in folded state，Now the first support bar 24 and the second support bar 25 are in stacked state，And the stability of wing during in order to improve wing-folding or launch，Card and portion 26 is further respectively had on second connecting portion 21 and the second folding part 22，At this moment，The first support bar 24 and the second support bar 25 that are in stacked state snap in the card and portion 26 being located on the second folding part 22，When wing is launched by needs，Only need to be by the second folding part 22 breaking outward gently，First support bar 24 and the second support bar 25 can be departed from card and portion 26，Continue to break the second folding part 22 outward，First support bar 24 and the second support bar 25 will slowly stretch from stacked state，When the first support bar 24 and the second support bar 25 are in same straight line，Second connecting portion 21 and the second folding part 22 are also at same linear position，Now，First support bar 24 and the second support bar 25 will snap in the card and portion 26 being positioned on the second connecting portion 21，Complete fixing under rear wing 3 deployed condition.This utility model uses the limited post 14 on front wing 1 and hinged the first support bar 24 of the head and the tail on rear wing 3 and the second support bar 25 to be fixed front wing 1 and rear wing 2 respectively, after preventing wing from launching or folding built on the sand, improve the unmanned plane stationarity when flight.
This utility model end in the first folding part 12 and the second folding part 22 is respectively equipped with motor 3, for providing power to wing.
Only as described above, it is only the preferred embodiment of this utility model, certainly the scope of this novel enforcement can not be limited with this, the most generally make simple equivalence change according to the content described in this utility model claim and utility model description and modify, within the most still belonging to this utility model claim scope.Additionally, summary part and title are intended merely to assist patent document search to be used, not it is used for limiting the interest field of this utility model.
Claims (4)
1. rotor wing unmanned aerial vehicle Quick folding mechanism more than a kind, including wing, described wing includes front wing (1) and rear wing (2), it is characterized in that: described front wing (1) place plane is different from rear wing (2) place plane, described front wing (1) includes the first connecting portion (11), first folding part (12) and the first rotating shaft (13), described first connecting portion (11) is fixedly connected on fuselage, described first rotating shaft (13) is located at one end of the first connecting portion (11), described first folding part (12) is rotatablely connected with the first connecting portion (11) by the first rotating shaft (13)；Described rear wing (2) includes the second connecting portion (21), the second folding part (22) and the second rotating shaft (23), described second connecting portion (21) is fixedly connected on fuselage, described second rotating shaft (23) is located at one end of the second connecting portion (21), and described second folding part (22) is rotatablely connected with the second connecting portion (21) by the second rotating shaft (23)；
Wherein, first folding part (12) of described front wing (1) is additionally provided with limited post (14) near the first rotating shaft (13) place, and described limited post (14) is for limiting the rotation of the first rotating shaft (13)；Described rear wing (2) also includes the most hinged the first support bar (24) and the second support bar (25), and described first support bar (24) and the second support bar (25) are hingedly connected to the second connecting portion (21) and the second folding part (22).
One many rotor wing unmanned aerial vehicles Quick folding mechanism the most according to claim 1, it is characterized in that: described first connecting portion (11) and the second connecting portion (21) favour head and the afterbody of fuselage respectively, when wing is in deployed condition, described first folding part (12) is perpendicular to fuselage, and described second folding part (22) and described second connecting portion (21) are in same straight line.
One many rotor wing unmanned aerial vehicles Quick folding mechanism the most according to claim 1, it is characterized in that: on described second connecting portion (21) and the second folding part (22), further respectively have Ka Hebu (26), described first support bar (24) or the second support bar (25) cocker and in described card and portion (26).
One many rotor wing unmanned aerial vehicles Quick folding mechanism the most according to claim 1, it is characterised in that: the end of described first folding part (11) and the second folding part (21) is respectively equipped with motor (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520812224.2U CN205499346U (en) | 2015-10-21 | 2015-10-21 | Many rotor unmanned aerial vehicle fast folding mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520812224.2U CN205499346U (en) | 2015-10-21 | 2015-10-21 | Many rotor unmanned aerial vehicle fast folding mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205499346U true CN205499346U (en) | 2016-08-24 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520812224.2U Expired - Fee Related CN205499346U (en) | 2015-10-21 | 2015-10-21 | Many rotor unmanned aerial vehicle fast folding mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205499346U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2017120654A1 (en) * | 2016-01-12 | 2017-07-20 | Dragan, Zenon | Multi-rotor uav with compact folding rotor arms |
| CN109353487A (en) * | 2018-10-17 | 2019-02-19 | 蔡强 | A kind of unmanned plane of wing rotary folding |
-
2015
- 2015-10-21 CN CN201520812224.2U patent/CN205499346U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2017120654A1 (en) * | 2016-01-12 | 2017-07-20 | Dragan, Zenon | Multi-rotor uav with compact folding rotor arms |
| CN109353487A (en) * | 2018-10-17 | 2019-02-19 | 蔡强 | A kind of unmanned plane of wing rotary folding |
| CN109353487B (en) * | 2018-10-17 | 2023-08-29 | 蔡强 | Unmanned aerial vehicle with rotary and folding wings |
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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: 20160824 Termination date: 20171021 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |