CN204587295U - Inserting module multi-rotor aerocraft frame - Google Patents
Inserting module multi-rotor aerocraft frame Download PDFInfo
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- CN204587295U CN204587295U CN201520109484.3U CN201520109484U CN204587295U CN 204587295 U CN204587295 U CN 204587295U CN 201520109484 U CN201520109484 U CN 201520109484U CN 204587295 U CN204587295 U CN 204587295U
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- middle heart
- reinforcing member
- hollow tubular
- heart
- motor component
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Abstract
The utility model discloses a kind of inserting module multi-rotor aerocraft frame, relate to vehicle technology field, comprise middle heart, master control cover plate, mechanical motor component and wing; It is characterized in that: described middle heart comprises middle heart upper plate and middle heart lower plate; Heart reinforcing member in being provided with between described middle heart upper plate and middle heart lower plate; Described master control cover plate is installed on middle heart upper plate; Be fixedly connected with between described middle heart upper plate, middle heart reinforcing member, middle heart lower plate; Described wing comprises hollow tubular and mechanical motor component; The sidewall of middle heart reinforcing member is provided with multiple connecting bore; Described wing comprises hollow tubular, mechanical motor component and Connector Clip; One end of described hollow tubular is connected with middle heart reinforcing member by Connector Clip; The other end and the mechanical motor component of described hollow tubular plug.The utility model has feature easy to assembly, that quality is little, firm in structure.
Description
Technical field
The utility model relates to vehicle technology field, particularly relates to a kind of inserting module multi-rotor aerocraft frame.
Background technology
Multi-axis aircraft have cost low, easy to operate, there is high degree of flexibility and can the feature such as hedgehopping, its photographic equipment carried can be utilized to carry out picture photographing, obtain image data, and obtained image data is sent back ground.Multi-axis aircraft be widely used at present take photo by plane, power-line patrolling, aerial reconnaissance, simulated flight, the field such as subsidy unmanned plane, in order to monitor the observation etc. of evidence obtaining and specific position, the transmission implementing live video picture can be realized, carrying out decision-making and judgement for director, is a kind of important tool of obtaining information.In addition, the Multi-axis aircraft of easy structure also receives at toy art and likes widely.
Frame is the main body of aircraft, and at present, the aircraft frame on market mainly contains two kinds of structures: one, global formation; Two, with bolts between each parts, found by practice, there is following defect respectively in above-mentioned two kinds of structures: for the aircraft frame of global formation, and owing to being subject to the restriction of volume and shape and structure, first it is course of processing more complicated; Simultaneously when local sends damage (such as fall, touch), then need entirety to change, therefore waste material resources, too increase cost simultaneously; For aircraft frame with bolts between each parts, it is loaded down with trivial details to there is assembling process in it, and installation effectiveness is low; Meanwhile, the use of a large amount of bolt, too increases the weight of aircraft.Therefore, design and develop the aircraft frame that unanimously can overcome above-mentioned defect and seem it is particularly important.
Utility model content
The technical problems to be solved in the utility model is: provide a kind of easy to assembly, inserting module multi-rotor aerocraft frame that quality is little.
The technical scheme that the utility model is taked for the technical matters existed in solution known technology is:
A kind of inserting module multi-rotor aerocraft frame, comprises middle heart, master control cover plate, mechanical motor component and wing; It is characterized in that: described middle heart comprises middle heart upper plate and middle heart lower plate; Heart reinforcing member in being provided with between described middle heart upper plate and middle heart lower plate; Described master control cover plate is installed on middle heart upper plate; Be fixedly connected with between described middle heart upper plate, middle heart reinforcing member, middle heart lower plate; Described wing comprises hollow tubular and mechanical motor component; The sidewall of middle heart reinforcing member is provided with multiple connecting bore; Described wing comprises hollow tubular, mechanical motor component and Connector Clip; One end of described hollow tubular is connected with middle heart reinforcing member by Connector Clip; The other end and the mechanical motor component of described hollow tubular plug.
As preferably, the utility model additionally uses following technical scheme:
Further: described middle heart reinforcing member is equilateral polygon cyclic structure.
The sidewall of described middle heart reinforcing member is net structure; Described connecting bore is positioned at the drift angle place of equilateral polygon.
The cross section of described connecting bore is " D " font.
The advantage that the utility model has and good effect are: in the utility model, the wing of aircraft frame adopts plug-in to be connected with between middle heart reinforcing member, also adopt plug-in to connect between all parts of wing, therefore connection procedure is fairly simple, convenient, simultaneously, when the local et out of order of aircraft, then can change these damage parts in time, economize on resources, reduce costs; Transport also facilitates; Owing to adding middle heart reinforcing member, therefore, it is possible to strengthen the structural strength of aircraft frame well; The impact resistance of aircraft is greatly improved.
Accompanying drawing explanation
Fig. 1 is exploded view of the present utility model;
Fig. 2 is local structure schematic diagram of the present utility model, is mainly used in the structure of display centre version reinforcing member;
Fig. 3 is part sectional view of the present utility model, is mainly used in showing the annexation between each parts of wing.
Wherein: 1, master control cover plate; 2, middle heart upper plate; 3, Connector Clip; 4, hollow tubular; 5, mechanical motor component; 6, middle heart lower plate; 7, middle heart reinforcing member; 71, connecting bore.
Detailed description of the invention
For utility model content of the present utility model, Characteristic can be understood further, hereby exemplify following examples, and coordinate accompanying drawing to be described in detail as follows:
Refer to Fig. 1, Fig. 2 and Fig. 3: a kind of inserting module multi-rotor aerocraft frame, comprises middle heart, master control cover plate 1, mechanical motor component 5 and wing; Wherein: described middle heart comprises middle heart upper plate 2 and middle heart lower plate 6; Heart reinforcing member 7 in being provided with between described middle heart upper plate 2 and middle heart lower plate 6; Described master control cover plate 1 is installed on middle heart upper plate; Be fixedly connected with between described middle heart upper plate 2, middle heart reinforcing member 7, middle heart lower plate 6; Described wing comprises hollow tubular 4 and mechanical motor component 5; The sidewall of middle heart reinforcing member 7 is provided with multiple connecting bore 71; Described wing comprises hollow tubular 4, mechanical motor component 5 and Connector Clip 3; One end of described hollow tubular 4 is connected with middle heart reinforcing member 7 by Connector Clip 3; The other end and the mechanical motor component 5 of described hollow tubular 4 plug.Hollow tubular 4 and Connector Clip 3 are hollow structure, can reduce the volume of aircraft so on the one hand; Meanwhile, hollow structure is also convenient to the connection of data line, wire; One end of data line, wire is connected with motor, and one end is connected with the electronic devices and components on master control cover plate 1 in addition;
As preferably, described middle heart reinforcing member 7 is equilateral polygon cyclic structure.Be convenient to processing like this, also can ensure the positional precision of each connecting bore simultaneously.
The sidewall of described middle heart reinforcing member is net structure; Described connecting bore is positioned at the drift angle place of equilateral polygon.The structural strength of aircraft can be improved like this, the quality of aircraft can be reduced simultaneously largely.
The cross section of described connecting bore is " D " font.The fastness of grafting can be ensured like this.
Above embodiment of the present utility model has been described in detail, but described content being only preferred embodiment of the present utility model, can not being considered to for limiting practical range of the present utility model.All equalizations done according to the utility model application range change and improve, and all should still belong within patent covering scope of the present utility model.
Claims (4)
1. an inserting module multi-rotor aerocraft frame, comprises middle heart, master control cover plate, mechanical motor component and wing; It is characterized in that: described middle heart comprises middle heart upper plate and middle heart lower plate; Heart reinforcing member in being provided with between described middle heart upper plate and middle heart lower plate; Described master control cover plate is installed on middle heart upper plate; Be fixedly connected with between described middle heart upper plate, middle heart reinforcing member, middle heart lower plate; Described wing comprises hollow tubular and mechanical motor component; The sidewall of middle heart reinforcing member is provided with multiple connecting bore; Described wing comprises hollow tubular, mechanical motor component and Connector Clip; One end of described hollow tubular is connected with middle heart reinforcing member by Connector Clip; The other end and the mechanical motor component of described hollow tubular plug.
2. inserting module multi-rotor aerocraft frame according to claim 1, is characterized in that: described middle heart reinforcing member is equilateral polygon cyclic structure.
3. inserting module multi-rotor aerocraft frame according to claim 1 and 2, is characterized in that: the sidewall of described middle heart reinforcing member is net structure; Described connecting bore is positioned at the drift angle place of equilateral polygon.
4. inserting module multi-rotor aerocraft frame according to claim 3, is characterized in that: the cross section of described connecting bore is " D " font.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520109484.3U CN204587295U (en) | 2015-02-15 | 2015-02-15 | Inserting module multi-rotor aerocraft frame |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520109484.3U CN204587295U (en) | 2015-02-15 | 2015-02-15 | Inserting module multi-rotor aerocraft frame |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204587295U true CN204587295U (en) | 2015-08-26 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520109484.3U Expired - Fee Related CN204587295U (en) | 2015-02-15 | 2015-02-15 | Inserting module multi-rotor aerocraft frame |
Country Status (1)
| Country | Link |
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| CN (1) | CN204587295U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104590541A (en) * | 2015-02-15 | 2015-05-06 | 天津晓奇科技发展有限公司 | Plug type modularized multi-rotor aircraft frame |
| CN106005361A (en) * | 2016-04-07 | 2016-10-12 | 珠海市磐石电子科技有限公司 | Aviation power unit and flight frame and modularization aircraft thereof |
| CN107074340A (en) * | 2016-04-01 | 2017-08-18 | 深圳市大疆创新科技有限公司 | Frame connection component and unmanned vehicle for unmanned vehicle |
| CN107628224A (en) * | 2017-09-25 | 2018-01-26 | 安徽瓦尔特机械贸易有限公司 | A kind of unmanned plane |
-
2015
- 2015-02-15 CN CN201520109484.3U patent/CN204587295U/en not_active Expired - Fee Related
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104590541A (en) * | 2015-02-15 | 2015-05-06 | 天津晓奇科技发展有限公司 | Plug type modularized multi-rotor aircraft frame |
| CN107074340A (en) * | 2016-04-01 | 2017-08-18 | 深圳市大疆创新科技有限公司 | Frame connection component and unmanned vehicle for unmanned vehicle |
| WO2017166275A1 (en) * | 2016-04-01 | 2017-10-05 | 深圳市大疆创新科技有限公司 | Airframe connection components for unmanned aerial vehicle, and unmanned aerial vehicle |
| CN107074340B (en) * | 2016-04-01 | 2019-07-30 | 深圳市大疆创新科技有限公司 | Rack connection component and unmanned vehicle for unmanned vehicle |
| CN106005361A (en) * | 2016-04-07 | 2016-10-12 | 珠海市磐石电子科技有限公司 | Aviation power unit and flight frame and modularization aircraft thereof |
| CN106005361B (en) * | 2016-04-07 | 2019-06-28 | 珠海市磐石电子科技有限公司 | Aviation power unit and flight frame and modularization aircraft thereof |
| CN107628224A (en) * | 2017-09-25 | 2018-01-26 | 安徽瓦尔特机械贸易有限公司 | A kind of unmanned plane |
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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: 20150826 Termination date: 20190215 |
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| CF01 | Termination of patent right due to non-payment of annual fee |