CN201849660U - Supporting arm structure of multi-rotary aerofoil - Google Patents
Supporting arm structure of multi-rotary aerofoil Download PDFInfo
- Publication number
- CN201849660U CN201849660U CN2010206095731U CN201020609573U CN201849660U CN 201849660 U CN201849660 U CN 201849660U CN 2010206095731 U CN2010206095731 U CN 2010206095731U CN 201020609573 U CN201020609573 U CN 201020609573U CN 201849660 U CN201849660 U CN 201849660U
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- pin
- arm portions
- hole
- otic placode
- bearing pin
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Abstract
The utility model discloses a supporting arm structure of a multi-rotary aerofoil, which is characterized in that a supporting arm is divided into at least two supporting arm sections capable of being bent; a connection component (2) is arranged between the two adjacent supporting arm sections (1a and 1b) and comprises a hinged piece (2a) and a locking piece (2b); one supporting arm section (1a) in the two adjacent supporting arm sections is fixedly connected with the connection component (2), and the other supporting arm section (1b) is hinged with the hinged piece (2a) through a hinged part on the other supporting arm section (1b), and a locking part used for being combined with the locking piece (2b) to be convenient for locking the two adjacent supporting arm sections (1a and 1b) form a whole body incapable of bent is also arranged on the other supporting arm section (1b). The supporting arm structure of the aerofoil can be bent to ensure that the aerofoil is reduced in volume, is convenient to carry and transport and can be quickly and conveniently installed when in use; and the connection structure between the supporting arms is simple.
Description
Technical field
The utility model relates to a kind of support arm structure of aircraft, relates in particular to a kind of support arm structure that is used for the large volume multi-rotor aerocraft.
Background technology
At present, UAV (Unmanned Aerial Vehicles, be called for short unmanned plane) is widely used in a plurality of fields such as air remote sensing, territory supervision, city planning, water conservancy construction, forestry management, monitoring in real time, aerial reconnaissance, video display are taken photo by plane, advertisement photography, military affairs.Because unmanned plane has advantages such as volume is little, in light weight, obtained applying widely, people have higher requirement to the ability of its safety, stability, cost performance and the various environments for use of adaptation is strong etc.Small aircraft is simple in structure, and alerting ability is strong, but its load-carrying capacity is very limited, and its load-carrying capacity of large volume unmanned plane is strong, but the large volume unmanned plane is because volume is bigger, carries, transports very inconvenient.
Summary of the invention
The purpose of this utility model is exactly in order to overcome the problem that above-mentioned prior art exists, a kind of support arm structure of multi-rotor aerocraft is provided, the support arm structure of this aircraft can bend, to reduce the volume of aircraft, be convenient for carrying, transport, and can install quickly and easily again when using, support arm structure is simple.
For realizing the purpose of this utility model, provide following technical scheme:
A kind of support arm structure of multi-rotor aerocraft, described support arm are divided at least two bent joint arm portions, are provided with coupling assembling between the two adjacent arm portions, comprise articulated section and locking member; Wherein, an arm portions in the two adjacent arm portions is captiveed joint with coupling assembling, another arm portions is hinged by articulated section and articulated section on it, and also is provided with on another arm portions and is used for combining so that with the not bent single-piece tight lock part of the locked formation of two adjacent arm portions with locking member.
Wherein, the articulated section comprises the first pin-and-hole seat that is fixed on described another arm portions adjacency termination of a described arm portions, has pin-and-hole on it; Described articulated section comprises: first pair of otic placode, be fixed on a described arm portions on the termination of another arm portions, and have pin-and-hole on it; First bearing pin is fixedly mounted in the pin-and-hole on the first pin-and-hole seat and the first pair of otic placode.
Wherein, tight lock part comprises the second pin-and-hole seat that is fixed on described another arm portions adjacency termination of a described arm portions, with the described first pin-and-hole seat positioned opposite, has pin-and-hole on it; Described locking member comprises: second pair of otic placode, be fixed on a described arm portions on the termination of another arm portions, and with described first pair of otic placode positioned opposite, have pin-and-hole on it; Second bearing pin is removably mounted in the pin-and-hole on the second pin-and-hole seat and the second pair of otic placode.
Particularly, locking member comprises also and being used for the locked snap close of described second bearing pin that the one end is provided with the hook part that is used to catch on the described second bearing pin tail end, and the other end is hinged on described first bearing pin.
The inboard level of hook part, the inboard of described hook part has the groove that is used to hold described second bearing pin.
Particularly, first pair of otic placode is connected as a single entity with second pair of otic placode respectively.
Particularly, multi-rotor aerocraft is four rotor crafts.
The beneficial effects of the utility model embody in the following areas:
1, articulated section and locking member are set between adjacent arm portions, when realizing being articulated and connected between the adjacent arm portions, make and to realize that with the combination of tight lock part fixing and locking is connected by locking member between the adjacent support arm, thereby adjacent arm portions is connected into not bent support arm integral body, made things convenient for the flight of large volume aircraft; Perhaps by with locking member and lock portion from, thereby support arm is bent, make things convenient for carrying and transporting of large volume aircraft;
2, the structure design of articulated section and locking member is simple, and is easy to operate, dependable performance.
Description of drawings
Fig. 1 is that the master of the support arm structure of multi-rotor aerocraft of the present utility model looks scheme drawing;
Fig. 2 is the structural representation in support arm structure when bending of multi-rotor aerocraft among Fig. 1;
Fig. 3 is the right side view of the support arm structure of multi-rotor aerocraft among Fig. 2.
Description of reference numerals: 1a, 1b-support arm; The 2-coupling assembling; The 2a-articulated section; The 2b-locking member; The 3-snap close; The 3b-hook part; The 3c-groove;
The 20a-first pin-and-hole seat; The 20b-second pin-and-hole seat; First pair of otic placode of 21a, 22a-; Second pair of otic placode of 21b, 22b-; 23a-first bearing pin; 23b-second bearing pin.
The specific embodiment
Master as the support arm structure of Fig. 1 multi-rotor aerocraft of the present utility model looks shown in the scheme drawing, support arm structure of the present utility model is divided at least two bent joint arm portions, be provided with coupling assembling 2 between two adjacent arm portions 1a, the 1b, comprise articulated section 2a and locking member 2b; Wherein, an arm portions 1a in the two adjacent arm portions is captiveed joint with coupling assembling 2, another arm portions 1b is hinged by articulated section and articulated section 2a on it, and also is provided with on another arm portions 1b and is used for combining so that with two adjacent arm portions 1a, the not bent single-piece tight lock part of the locked formation of 1b with locking member 2b.
When between the two adjacent arm portions when locked, as shown in Figure 1, can't relatively rotate between the two adjacent arm portions, thereby make two adjacent arm portions be fixed into an integral body; When releasing between the two adjacent arm portions is locked, as shown in Figure 2, just only there is the annexation that is hinged between the adjacent arm portions, therefore two adjacent arm portions can relatively rotate.When multi-rotor aerocraft need be opened support arm and carries out work, locking member 2b is combined with tight lock part, with locked between the two adjacent arm portions, make the more piece arm portions be fixedly connected into a support arm integral body, multi-rotor aerocraft just can be worked; When carrying for convenience, transporting, in the time of need reducing the volume of multi-rotor aerocraft,, just can relatively rotate between the two adjacent arm portions, the volume of support arm bending just can reducing multi-rotor aerocraft with the locked releasing between the two adjacent arm portions.
Wherein, multi-rotor aerocraft of the present utility model is four rotor crafts.
As shown in Figure 1, 2, coupling assembling 2 is fixed on the termination of arm portions 1a, comprises up and down the articulated section 2a and the locking member 2b that distribute, and during locked the opening of two adjacent arm portions 1a, 1b upper end, two arm portions 1a, 1b just can relatively rotate, as shown in Figure 2.
Shown in Fig. 2,3, the articulated section comprises and is fixed on the first pin-and-hole seat 20a of arm portions 1b on the end of arm portions 1a, has pin-and-hole on the first pin-and-hole seat 20a.
Articulated section 2a comprises: be fixed on first pair otic placode 21a, the 22a of arm portions 1a on the end of arm portions 1b, two otic placode 21a, 22a lay respectively at the left and right sides (as shown in Figure 3) of arm portions 1a, have pin-and-hole on two otic placode 21a, the 22a; The first pin-and-hole seat 20a is positioned over two otic placode 21a, between the 22a, and make pin-and-hole and two otic placode 21a on the pin-and-hole seat 20a that wins, pin-and-hole alignment on the 22a, the first bearing pin 23a is passed pin-and-hole on the otic placode 22a successively, pin-and-hole on the first pin-and-hole seat 20a, pin-and-hole on the otic placode 21a, and the nut of screwing at the two ends of the first bearing pin 23a, thereby the first bearing pin 23a is fixedly mounted on the first pin-and-hole seat 20a and first couple of otic placode 21a, in the pin-and-hole on the 22a, and can in pin-and-hole, not deviate from, as shown in Figure 3, so just, realized being hinged of arm portions 1b and articulated section 2a, arm portions 1b can freely rotate around the first bearing pin 23a.
Shown in Fig. 2,3, tight lock part comprises and is fixed on the second pin-and-hole seat 20b of arm portions 1b on the termination of arm portions 1a, has pin-and-hole on the second pin-and-hole seat 20b, and the second pin-and-hole seat 20b and the first pin-and-hole seat 20a are oppositely arranged (as shown in Figure 2).
Shown in Fig. 2,3, one end of snap close 3 is hinged on the first bearing pin 23a, the other end is provided with the hook part 3b (as shown in Figure 2) of the tail end that is used to catch on the second bearing pin 23b, the inboard level of hook part 3b, and the inboard of hook part 3b has the groove 3c that is used to hold the second bearing pin 23b, thereby snap close 3 is fixed between the first bearing pin 23a and the second bearing pin 23b, and snap close 3 can not rotate around the first bearing pin 23a.
In the time folding arm portions need being connected into a support arm integral body, as shown in Figure 2, firmly rotating snap close 3 makes it rotate counterclockwise around the first bearing pin 23a, and make the hook part 3b of snap close 3 break away from and being connected of the second bearing pin 23b, at this moment, the second bearing pin 23b is extracted out in (as Fig. 3) pin-and-hole on second couple of otic placode 21b, the 22b to the right.
Then, rotating support arm section 1b makes it rotate counterclockwise (Fig. 2) around the first bearing pin 23a, when arm portions 1b turns to the second pin-and-hole seat 20b on it between two otic placode 21b, 22b, and the pin-and-hole on the second pin-and-hole seat 20b is when pin-and-hole on two otic placode 21b, the 22b aligns, and arm portions 1b stops operating.The second bearing pin 23b is inserted in the pin-and-hole on two otic placode 21b, 22b and the second pin-and-hole seat 20b between two otic placode 21b, 22b, so just, the second pin-and-hole seat 20b and second couple of otic placode 21b, 22b are coupled together, thereby making to be mutually permanently connected between arm portions 1a and the arm portions 1b forms an integral body.
In order to prevent that the second bearing pin 23b from deviating from pin-and-hole, clockwise rotate snap close 3 again, tail end until the second bearing pin 23b just snaps in the groove 3c of 3b inboard, hook part, like this, snap close 3 is just locked fixing with the second bearing pin 23b, thereby also that arm portions 1a and arm portions 1b is locked fixing, making is mutually permanently connected between arm portions 1a and the arm portions 1b forms an integral body, state as shown in Figure 1.
In the time support arm integral body need being bent so that reduce the volume of unmanned vehicle, as shown in Figure 1, firmly rotating snap close 3 makes it rotate counterclockwise around the first bearing pin 23a, and make the hook part 3a of snap close 3 break away from the connection of the second bearing pin 23b, at this moment, the second bearing pin 23b is extracted out in (as Fig. 3) pin-and-hole on second couple of otic placode 21b, the 22b to the right, make the releasing that is connected between the second axis pin base 20b and second couple of otic placode 21b, the 22b.
At this moment just can freely clockwise rotate arm portions 1b, make arm portions 1b bend downwards, thereby reduce the volume of aircraft, so that carry, transport.
Then, the second bearing pin 23b is inserted in the pin-and-hole on two otic placode 21b, the 22b, clockwise rotate snap close 3, the tail end of the second bearing pin 23b is just snapped in the groove 3c of 3b inboard, hook part, thereby the second bearing pin 23b is locked, state as shown in Figure 2.
Although above the utility model has been done detailed description; but the utility model is not limited thereto; those skilled in the art can make amendment according to principle of the present utility model; therefore, all various modifications of carrying out according to principle of the present utility model all should be understood to fall into protection domain of the present utility model.
Claims (7)
1. the support arm structure of a multi-rotor aerocraft is characterized in that, described support arm is divided at least two bent joint arm portions, is provided with coupling assembling (2) between the two adjacent arm portions (1a, 1b), comprises articulated section (2a) and locking member (2b);
Wherein, arm portions (1a) in the two adjacent arm portions is captiveed joint with coupling assembling (2), another arm portions (1b) is hinged by articulated section and articulated section (2a) on it, and also is provided with on another arm portions (1b) and is used for combining so that with the not bent single-piece tight lock part of the locked formation of two adjacent arm portions (1a, 1b) with locking member (2b).
2. support arm structure as claimed in claim 1 is characterized in that, described articulated section comprises the first pin-and-hole seat (20a) on the termination that is fixed on described another arm portions (1b) described arm portions of adjacency (1a), has pin-and-hole on it; Described articulated section comprises (2a):
First pair of otic placode (21a, 22a) is fixed on a described arm portions (1a) on the termination of another arm portions (1b), has pin-and-hole on it;
First bearing pin (23a) is fixedly mounted in the pin-and-hole on the first pin-and-hole seat and the first pair of otic placode.
3. support arm structure as claimed in claim 2, it is characterized in that, described tight lock part comprises the second pin-and-hole seat (20b) on the termination that is fixed on described another arm portions (1b) described arm portions of adjacency (1a), with described first pin-and-hole seat (20a) positioned opposite, has pin-and-hole on it; Described locking member (2b) comprising:
Second pair of otic placode (21b, 22b) is fixed on a described arm portions (1a) on the termination of another arm portions (1b), with described first pair of otic placode positioned opposite, has pin-and-hole on it;
Second bearing pin (23b) is removably mounted in the pin-and-hole on the second pin-and-hole seat and the second pair of otic placode.
4. support arm structure as claimed in claim 3, it is characterized in that, described locking member (2b) also comprises and is used for the snap close (3) that described second bearing pin is locked, the one end is provided with the hook part (3b) that is used to catch on described second bearing pin (23b) tail end, and the other end is hinged on described first bearing pin (23a).
5. support arm structure as claimed in claim 4 is characterized in that, the inboard level of described hook part (3b), and the inboard of described hook part (3b) has the groove (3c) that is used to hold described second bearing pin (23b).
6. support arm structure as claimed in claim 3 is characterized in that, described first pair of otic placode (21a, 22a) is connected as a single entity with second pair of otic placode (21b, 22b) respectively.
7. support arm structure as claimed in claim 1 is characterized in that, described multi-rotor aerocraft is four rotor crafts.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010206095731U CN201849660U (en) | 2010-11-15 | 2010-11-15 | Supporting arm structure of multi-rotary aerofoil |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010206095731U CN201849660U (en) | 2010-11-15 | 2010-11-15 | Supporting arm structure of multi-rotary aerofoil |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201849660U true CN201849660U (en) | 2011-06-01 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010206095731U Expired - Lifetime CN201849660U (en) | 2010-11-15 | 2010-11-15 | Supporting arm structure of multi-rotary aerofoil |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201849660U (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105151293A (en) * | 2015-09-25 | 2015-12-16 | 湖南云顶智能科技有限公司 | Arm folding device for unmanned aerial vehicle |
| WO2017107752A1 (en) * | 2015-12-25 | 2017-06-29 | 广州亿航智能技术有限公司 | Multirotor manned aerial vehicle having foldable arms |
| WO2017107721A1 (en) * | 2015-12-24 | 2017-06-29 | 亿航智能设备（广州）有限公司 | Unmanned aerial vehicle and arm folding mechanism thereof |
| WO2017133302A1 (en) * | 2016-02-01 | 2017-08-10 | 广州亿航智能技术有限公司 | Manned aerial vehicle |
| CN108910012A (en) * | 2018-07-26 | 2018-11-30 | 瀚伦贝尔通用航空器有限公司 | A kind of big boom device of folding aircraft |
-
2010
- 2010-11-15 CN CN2010206095731U patent/CN201849660U/en not_active Expired - Lifetime
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105151293A (en) * | 2015-09-25 | 2015-12-16 | 湖南云顶智能科技有限公司 | Arm folding device for unmanned aerial vehicle |
| WO2017107721A1 (en) * | 2015-12-24 | 2017-06-29 | 亿航智能设备（广州）有限公司 | Unmanned aerial vehicle and arm folding mechanism thereof |
| WO2017107752A1 (en) * | 2015-12-25 | 2017-06-29 | 广州亿航智能技术有限公司 | Multirotor manned aerial vehicle having foldable arms |
| WO2017133302A1 (en) * | 2016-02-01 | 2017-08-10 | 广州亿航智能技术有限公司 | Manned aerial vehicle |
| CN108910012A (en) * | 2018-07-26 | 2018-11-30 | 瀚伦贝尔通用航空器有限公司 | A kind of big boom device of folding aircraft |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C56 | Change in the name or address of the patentee | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 528305, No. 7, Jianye Middle Road, Shunde hi tech Zone (Ronggui), Guangdong, Foshan Patentee after: FOSHAN AIRCAM UAV TECHNOLOGY CORPORATION Address before: 528305, No. 7, Jianye Middle Road, Shunde hi tech Zone (Ronggui), Guangdong, Foshan Patentee before: Foshan Aircam Uav Technology Co., Ltd. |
|
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20110601 |