CN204737032U - From many rotor crafts of dismissal formula - Google Patents
From many rotor crafts of dismissal formula Download PDFInfo
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- CN204737032U CN204737032U CN201520377111.4U CN201520377111U CN204737032U CN 204737032 U CN204737032 U CN 204737032U CN 201520377111 U CN201520377111 U CN 201520377111U CN 204737032 U CN204737032 U CN 204737032U
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- fuselage
- cantilever
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- shaped frame
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Abstract
The utility model discloses a from many rotor crafts of dismissal formula, including the fuselage, the fuselage upper cover closes the cover, and cantilever installation rotor is passed through in inclining in week of fuselage, the installation cavity that has a plurality of intercommunications in the fuselage, install the multiple modules subassembly in the installation cavity respectively, equal mountable has the parachute on module for light, cover and the cantilever, cover and cantilever are connected with the organism through the mechanism of dismissing certainly. The utility model discloses in, constitute a plurality of independent module for light with the part in the fuselage to descend through the parachute respectively, resolve into multiple modules with the aircraft, to the damage on ground, protect the core component in the aircraft, reduce loss when reducing whole falling. (Pbpnum='1' /)
Description
Technical field
The utility model relates to multi-rotor aerocraft technical field, is specifically related to a kind of multi-rotor aerocraft that can certainly dismiss.
Background technology
At present, multi-rotor aerocraft application is more and more extensive, and its micro-camera of can arranging in pairs or groups records airborne video, also can be used for carrying various measuring instrument, carry out aerological ascent or the throwing of high-altitude object, the various fields such as agricultural, detection, meteorology, hazard forecasting and rescue can be applied in.
Existing multi-rotor aerocraft does not have from dismissing function, and when a failure occurs, aircraft entirety is fallen, and causes serious damage on the one hand to ground, and another aspect internal structure of aircraft particularly core component is easily damaged, and causes larger loss.
Utility model content
In order to solve the problem; the utility model discloses a kind of from the formula of dismission multi-rotor aerocraft; intraware is carried out modularization by it, to each module particularly nucleus module protect, to the extent of injury on ground and the loss of self-destruction when significantly reducing aircraft fault.
The technical solution of the utility model is as follows:
A kind of from the formula of dismission multi-rotor aerocraft, comprise fuselage, fuselage covers cover, rotor is installed by cantilever in all sides of fuselage, with the installation cavity of multiple connection in described fuselage, be separately installed with multiple modular assembly in described installation cavity, described modular assembly, cover and cantilever all can be provided with parachute; Described cover and cantilever are by being connected with body from dismissing mechanism.
Further improvement as technique scheme:
Described mechanism of certainly dismissing comprises the public plug and female that cooperatively interact, and public plug is connected with cover and cantilever, and female is fixedly installed in fuselage.
Described female comprises spaced two U-shaped framves, and install by the first spring and with the first patch jack being positioned at the first spring side at the bottom of the U-type groove of U-shaped frame, the outside of U-shaped frame is with the second patch jack; Symmetrical hinged swing locking bar in clearance space between two U-shaped framves, the tapered end that the oriented UXing Jia center of upper end band swinging locking bar is protruded, two lower ends swinging locking bar are connected with connecting rod, and the lower end of connecting rod connects drive spindle jointly, and described drive spindle is connected with the steering wheel in fuselage; The lower end of described public plug is inserted in described U-type groove, and the end face of its lower end is with the connection plug coordinated with the first patch jack, and the both sides of public plug are with the lockhole coordinated with tapered end.
With boss protruding upward in the middle part of the bottom land of the U-type groove of described U-shaped frame, with the groove matched with described boss in the middle part of the lower end of public plug.
Described U-shaped frame is provided with the second spring with the hinged place swinging locking bar.
Advantageous Effects of the present utility model is:
In the utility model; parts in fuselage are grouped into multiple independently modular assembly; modular assembly is configured with corresponding parachute according to own wt; aircraft realizes modularization landing when breaking down or fly into forbidden zone; thus the damage reduced ground; core component in protection aircraft, reduces the loss.
Accompanying drawing explanation
Fig. 1 is three-dimensional structure diagram of the present utility model.
Fig. 2 is decomposition chart of the present utility model.
Fig. 3 is partial enlarged drawing of the present utility model.
Fig. 4 is from the three-dimensional structure diagram of dismissing mechanism in the utility model.
Fig. 5 is from another three-dimensional structure diagram of dismissing mechanism in the utility model.
Fig. 6 is from the front view of dismissing mechanism in the utility model.
In figure: 1, fuselage; 2, cover; 3, cantilever; 4, rotor; 5, public plug; 51, connection plug; 52, lockhole; 53, groove; 6, female; 61, U-shaped frame; 610, U-type groove; 611, the first patch jack; 612, the second patch jack; 613, boss; 62, locking bar is swung; 621, tapered end; 63, connecting rod; 64, drive spindle; 65, the first spring; 66, the second spring; 7, steering wheel; 8, modular assembly; 9, certainly mechanism is dismissed; 10, parachute.
Detailed description of the invention
As shown in Figure 1 and Figure 2, certainly the dismission formula multi-rotor aerocraft of the present embodiment, comprise fuselage 1, fuselage 1 covers cover 2, rotor 4 is installed by cantilever 3 in all sides of fuselage 1, with the installation cavity of multiple connection in fuselage 1, installation module assembly 8 in installation cavity, modular assembly 8 all can be provided with parachute 10; Cover 2 and cantilever 3 are by being connected with body 1 from dismissing mechanism 9.Wherein, modular assembly 8 is formed by the multiple component combinations in aircraft, and configures corresponding parachute 10 according to its weight.
As shown in Figures 4 to 6, comprise from dismissing mechanism 9 public plug 5 and female 6 that cooperatively interact, public plug 5 is connected with cover 2 and cantilever 3, and female 6 is fixedly installed in fuselage 1.
As shown in Figures 4 to 6, female 6 comprises spaced two U-shaped framves 61, and U-type groove 610 end of U-shaped frame 61 installs by the first spring 65 and with the first patch jack 611 being positioned at the first spring 65 side, and the outside of U-shaped frame 61 is with the second patch jack 612; Symmetrical hinged swing locking bar 62 in clearance space between two U-shaped framves 61, the tapered end 621 that upper end band oriented UXing Jia 61 center swinging locking bar 62 is protruded, two lower ends swinging locking bar 62 are connected with connecting rod 63, the lower end of connecting rod 63 connects drive spindle 64 jointly, and drive spindle 64 is connected with the steering wheel 7 in fuselage 1; The lower end of public plug 5 is inserted in U-type groove 610, and the end face of its lower end is with the connection plug 51 coordinated with the first patch jack 611, and the both sides of public plug 5 are with the lockhole 52 coordinated with tapered end 621.
As shown in Figure 4, Figure 5, with boss 613 protruding upward in the middle part of the bottom land of the U-type groove 610 of U-shaped frame 61, with the groove 53 matched with boss 613 in the middle part of the lower end of public plug 5, boss 613 and groove 53 coordinate and realize public plug 5 and be connected with the buckle of female 6.
As shown in Figure 6, U-shaped frame 61 is provided with the second spring 66 with the hinged place swinging locking bar 62.
During utility model works, when aircraft flies into forbidden zone or falls due to other faults, the mechanism 9 of dismission certainly action in aircraft, wherein steering wheel 7 drives swing locking bar 62 to swing, tapered end 621 and public plug 5 depart from, under the effect of the first spring 65, public plug 5 ejects from female 6, thus cover 2 and cantilever 3 depart from fuselage 1; Modules assembly 8 in fuselage 1 is by the independent landing of parachute 10.
In the utility model; parts in fuselage are grouped into multiple independently modular assembly; modular assembly is configured with corresponding parachute according to own wt; aircraft realizes modularization landing when breaking down or fly into forbidden zone; thus the damage reduced ground; core component in protection aircraft, reduces the loss.
Above-described is only preferred implementation of the present utility model, and the utility model is not limited to above embodiment.Be appreciated that the oher improvements and changes that those skilled in the art directly derive or associate under the prerequisite not departing from spirit of the present utility model and design, all should think and be included within protection domain of the present utility model.
Claims (5)
1. certainly dismiss formula multi-rotor aerocraft for one kind, comprise fuselage (1), fuselage (1) covers cover (2), rotor (4) is installed by cantilever (3) in all sides of fuselage (1), it is characterized in that: with the installation cavity of multiple connection in described fuselage (1), be separately installed with multiple modular assembly (8) in described installation cavity, described modular assembly (8), cover (2) and cantilever (3) all can be provided with parachute (7); Described cover (2) and cantilever (3) are by being connected with body (1) from dismissing mechanism (9).
2. as claimed in claim 1 from the formula of dismission multi-rotor aerocraft, it is characterized in that: described dismissing mechanism (9) comprises the public plug (5) and female (6) that cooperatively interact certainly, public plug (5) is connected with cover (2) and cantilever (3), and female (6) is fixedly installed in fuselage (1).
3. as claimed in claim 2 from the formula of dismission multi-rotor aerocraft, it is characterized in that: described female (6) comprises spaced two U-shaped framves (61), U-type groove (610) bottom land of U-shaped frame (61) is installed by the first spring (65) and with the first patch jack (611) being positioned at the first spring (65) side, and the outside of U-shaped frame (61) is with the second patch jack (612); Symmetrical hinged swing locking bar (62) in clearance space between two U-shaped framves (61), the tapered end (621) that upper end band oriented U-shaped frame (61) center swinging locking bar (62) is protruded, two lower ends swinging locking bar (62) are connected with connecting rod (63), the lower end of connecting rod (63) connects drive spindle (64) jointly, and described drive spindle (64) is connected with the steering wheel (7) in fuselage (1); The lower end of described public plug (5) is inserted in described U-type groove (610), the end face of its lower end is with the connection plug (51) coordinated with the first patch jack (611), and the both sides of public plug (5) are with the lockhole (52) coordinated with tapered end (621).
4. as claimed in claim 3 from the formula of dismission multi-rotor aerocraft, it is characterized in that: with boss (613) protruding upward in the middle part of the bottom land of the U-type groove (610) of described U-shaped frame (61), with the groove (53) matched with described boss (613) in the middle part of the lower end of public plug (5).
5. as claimed in claim 3 from the formula of dismission multi-rotor aerocraft, it is characterized in that: described U-shaped frame (61) is provided with the second spring (66) with the hinged place swinging locking bar (62).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520377111.4U CN204737032U (en) | 2015-06-03 | 2015-06-03 | From many rotor crafts of dismissal formula |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520377111.4U CN204737032U (en) | 2015-06-03 | 2015-06-03 | From many rotor crafts of dismissal formula |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204737032U true CN204737032U (en) | 2015-11-04 |
Family
ID=54418780
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520377111.4U Active CN204737032U (en) | 2015-06-03 | 2015-06-03 | From many rotor crafts of dismissal formula |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204737032U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106564582A (en) * | 2016-04-27 | 2017-04-19 | 重庆零度智控智能科技有限公司 | Unmanned aerial vehicle |
| CN107380435A (en) * | 2017-08-10 | 2017-11-24 | 河南谷翼自动化科技有限公司 | A kind of four axle plant protection unmanned planes for being easy to handling |
| CN113031637A (en) * | 2021-03-05 | 2021-06-25 | 北京理工大学 | Multi-flying-robot integrated operation platform |
-
2015
- 2015-06-03 CN CN201520377111.4U patent/CN204737032U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106564582A (en) * | 2016-04-27 | 2017-04-19 | 重庆零度智控智能科技有限公司 | Unmanned aerial vehicle |
| CN107380435A (en) * | 2017-08-10 | 2017-11-24 | 河南谷翼自动化科技有限公司 | A kind of four axle plant protection unmanned planes for being easy to handling |
| CN113031637A (en) * | 2021-03-05 | 2021-06-25 | 北京理工大学 | Multi-flying-robot integrated operation platform |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 214000 room 411-414, A1 tower 999, Gao Lang Dong Road, Binhu District, Wuxi, Jiangsu. Patentee after: Jiangsu digital Eagle Polytron Technologies Inc Address before: 214000 room 411-414, A1 tower 999, Gao Lang Dong Road, Binhu District, Wuxi, Jiangsu. Patentee before: Jiangsu numeral Accipitridae skill Development Co., Ltd |
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| CP01 | Change in the name or title of a patent holder |