CN204527628U - A kind of folded double-layered strut bar multi-rotor aerocraft - Google Patents
A kind of folded double-layered strut bar multi-rotor aerocraft Download PDFInfo
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- CN204527628U CN204527628U CN201520220960.9U CN201520220960U CN204527628U CN 204527628 U CN204527628 U CN 204527628U CN 201520220960 U CN201520220960 U CN 201520220960U CN 204527628 U CN204527628 U CN 204527628U
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- strut bar
- screw propeller
- rotor aerocraft
- bar
- aircraft
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Abstract
A kind of folded double-layered strut bar multi-rotor aerocraft.Mainly comprise the actuating device of connection structure, screw propeller and the screw propeller between two-layer strut bar, two-layer strut bar, the intermediate structure of aircraft, the hinge between strut bar and intermediate structure.Screw propeller and actuating device thereof are fixed on strut bar.Screw propeller place plane is between two-layer strut bar, and part strut bar is connected by hinge with between intermediate structure.This structure can protect the screw propeller of aircraft effectively, thus improves the safety of aircraft and operating personal, and firmly light, can easily fold up to improve portability.
Description
Technical field
The utility model relates to a kind of body construction of multi-rotor aerocraft.
Background technology
Known multi-rotor aerocraft, screw propeller shortage is simple and light and solid and reliable, can play the fail-safe structure of disposition to the top of screw propeller, bottom and side.
Although for the toy-type multi-rotor aerocraft that some weight is very little; there is a kind of annular shield structure around screw propeller side; but the weight of this fail-safe structure occupies a larger part for aircraft gross weight amount; therefore be not suitable for relatively large multi-rotor aerocraft load carrying ability being had to requirement, and this fail-safe structure can not protect the top of screw propeller.
Therefore with prior art, still do not possess simple and light and solid and reliable, the fail-safe structure of disposition can be carried out screw propeller.Thus when causing multi-rotor aerocraft out of control because of unforeseen circumstances, easily cause engine breakdown or Personal Risk.
In addition, while screw propeller being carried out to effectively protection, how to make aircraft body have folding characteristic, thus be beneficial to and carry, be also one with prior art still open question.
Summary of the invention
In order to solve the screw propeller disposition problem of rotor craft, the utility model provides a kind of new multi-rotor aerocraft body construction.This is simple and light and solid and reliable, can carry out disposition to the top of screw propeller, bottom and side.Meanwhile, the body construction of multi-rotor aerocraft provided by the present invention has folding characteristic, thus improves the portability of aircraft.
Aircraft body construction provided by the utility model, mainly comprises the actuating device of connection structure, screw propeller and the screw propeller between two-layer strut bar, two-layer strut bar, the intermediate structure of aircraft, the hinge between strut bar and intermediate structure.Screw propeller and actuating device thereof are fixed on strut bar.The plane at screw propeller place, between two-layer strut bar, is connected by hinge between part strut bar and the intermediate structure of aircraft.
Strut bar can adopt the carbon fiber pipe with higher strength-weight ratio.Can with the screw hole perpendicular to axis on strut bar, for other structure concrete mutuallies.The intermediate structure of aircraft can be carbon fiber board or glass mat.The close part at aircraft center of wherein one deck strut bar is connected by hinge with the intermediate structure of aircraft, by this layer of strut bar called after free bearing bar; The part at the close aircraft center of another layer of strut bar and the intermediate structure of aircraft by other means (as spiral nail) are connected, and by this layer of affixed strut bar of strut bar called after.Taken apart the junction of affixed strut bar and intermediate structure, strut bar can rotate around the hinge between free bearing bar and intermediate structure, thus the body of aircraft can be folded up, and is beneficial to and carries.
The end away from aircraft center of strut bar is defined as outside end.The outside end of any one strut bar is greater than the half of the length of screw propeller apart from the horizontal throw of the rotating shaft of any one screw propeller.Like this, when aircraft rolls on the ground, due to the supporting role of strut bar, the screw propeller of High Rotation Speed just can not touch ground.
Multiple connection structure (as aluminium matter pillar stiffener) is fixed between two-layer strut bar.Connection structure not only makes the position of upper and lower two-layer strut bar obtain fixing, and makes whole body construction solid and reliable.Method of attachment between connection structure and strut bar comprises: be 1. fixed on horizontal support bar with spiral nail; 2. adopt mould process to make connection structure and strut bar form the unified entirety that can not disassemble when producing.
In order to strengthen bulk strength further, the outside end of two-layer strut bar can be connected by cord or adopt lighter bar to be connected mutually, to strengthen protective capacities and to improve bulk strength.
With the outside end of strut bar (or being fixed on the upper lower end of the connection structure on strut bar) for the strong point, at the top of aircraft and (or) bottom fixing horizontal grille guard, by connecting the cord of the outside end of strut bar through the grid on grille guard edge, for grille guard is strutted.At the side fixed protection screen of aircraft.Wherein protective shield can be grille guard, also can be cloth, or carbon fiber board.Like this, the top of all screw propellers, bottom and side just obtain omnibearing protection.
In the outside end of strut bar, can fixing flexible anticollison block, as sponge anticollison block, foam anticollison block etc., to protect aircraft further.
The beneficial effects of the utility model are, make aircraft propeller obtain actv. disposition, improve the safety of aircraft and operating personal.The body construction provided is firmly light, and can easily fold up to improve portability.
Accompanying drawing explanation
Below in conjunction with drawings and Examples, the utility model is further illustrated.
Fig. 1 is the block diagram of the basic frame structure of body construction provided by the utility model.For the ease of understanding, marked X, Y, Z tri-orthogonal change in coordinate axis direction in figure, wherein Z axis straight up, and X-axis and Y-axis are positioned on horizontal surface.In order to the outstanding framed structure be made up of horizontal support bar, that motor and screw propeller are drawn is less than normal.
Fig. 2 is the lateral plan of structure shown in Fig. 1.
Fig. 3 is another lateral plan of structure shown in Fig. 1, it gives the folding mode of strut bar.
The intermediate structure of 1. aircraft in figure, comprises bottom plate (1.1) and upper mounted plate (1.2), 2. horizontal support bar, 3. connection structure, 4. screw propeller, 5. propeller driving device, 6. hinge, 7. spiral nail.
Detailed description of the invention
In FIG, the intermediate structure (1) of aircraft is carbon fiber board, comprises bottom plate (1.1) and upper mounted plate (1.2).Horizontal support bar (2) is carbon fiber bar.Connection structure (3) is aluminium matter pillar stiffener.Horizontal support bar (2) is divided into two-layer up and down, and every layer has four.Wherein, the horizontal support bar (2) being positioned at lower floor is connected with bottom plate (1.1) by hinge (6).The horizontal support bar (2) being positioned at upper strata is connected with upper mounted plate (1.2) by spiral nail (7).Meanwhile, be connected by connection structure (3) between two horizontal supporting layers bar (2).Controller, battery etc. can be placed between two adapter plates (1.1) and (1.2).The propeller driving device (5) of screw propeller (4) is driven to be fixed on the horizontal support bar (2) of lower floor.Propeller driving device (5) is electrical motor.The plane at screw propeller (4) place is positioned between upper and lower two horizontal supporting layers bar (2).
Fig. 2 gives the lateral plan of structure shown in Fig. 1.In the figure, clear for simplicity, the strut bar paralleled with sight line and appurtenances above thereof are not drawn.
Fig. 3 gives another lateral plan of structure shown in Fig. 1.In the figure, removed upper mounted plate (1.2), in this case, strut bar (2) can rotate relative to bottom plate (1.1) around hinge (6), thus can fold up.
Claims (7)
1. a folded double-layered strut bar multi-rotor aerocraft, comprise the intermediate structure of aircraft, hinge, upper and lower two-layer strut bar, screw propeller, propeller driving device, is characterized in that: the plane at screw propeller place is between two-layer strut bar, and part strut bar is connected by hinge with between intermediate structure.
2. the body construction of multi-rotor aerocraft according to claim 1, is characterized in that: the outside end of adjacent horizontal support bar is connected by cord.
3. the body construction of multi-rotor aerocraft according to claim 1, is characterized in that: the outside end of horizontal support bar is fixed with grille guard.
4. the body construction of multi-rotor aerocraft according to claim 1, is characterized in that: the outside end of horizontal support bar is fixed with flexible protection block.
5. the body construction of multi-rotor aerocraft according to claim 1, is characterized in that: screw propeller and actuating device thereof are fixed on strut bar.
6. the body construction of multi-rotor aerocraft according to claim 1, is characterized in that: the outside end of any one horizontal support bar is greater than the half of screw propeller length apart from the horizontal throw of the rotating shaft of any one screw propeller.
7. the body construction of multi-rotor aerocraft according to claim 1, is characterized in that: be connected by light rigidity bar between the outside end of adjacent horizontal support bar.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520220960.9U CN204527628U (en) | 2015-04-14 | 2015-04-14 | A kind of folded double-layered strut bar multi-rotor aerocraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520220960.9U CN204527628U (en) | 2015-04-14 | 2015-04-14 | A kind of folded double-layered strut bar multi-rotor aerocraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204527628U true CN204527628U (en) | 2015-08-05 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520220960.9U Expired - Fee Related CN204527628U (en) | 2015-04-14 | 2015-04-14 | A kind of folded double-layered strut bar multi-rotor aerocraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204527628U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105383689A (en) * | 2015-12-11 | 2016-03-09 | 北京恒华伟业科技股份有限公司 | Unmanned rotorcraft and protecting device thereof |
| CN106143887A (en) * | 2015-04-14 | 2016-11-23 | 王欢 | A kind of folded double-layered support bar multi-rotor aerocraft |
-
2015
- 2015-04-14 CN CN201520220960.9U patent/CN204527628U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106143887A (en) * | 2015-04-14 | 2016-11-23 | 王欢 | A kind of folded double-layered support bar multi-rotor aerocraft |
| CN105383689A (en) * | 2015-12-11 | 2016-03-09 | 北京恒华伟业科技股份有限公司 | Unmanned rotorcraft and protecting device thereof |
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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 | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20150805 Termination date: 20200414 |