CN204548489U - Multi-axis aircraft - Google Patents
Multi-axis aircraft Download PDFInfo
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- CN204548489U CN204548489U CN201520124518.6U CN201520124518U CN204548489U CN 204548489 U CN204548489 U CN 204548489U CN 201520124518 U CN201520124518 U CN 201520124518U CN 204548489 U CN204548489 U CN 204548489U
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- lift arm
- fuselage
- arm component
- axis aircraft
- snap close
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Abstract
The utility model provides a kind of Multi-axis aircraft, comprises fuselage and lift arm component, and fuselage and lift arm component are removably locked by lockout mechanism or unlock, and wherein, in the position that fuselage and lift arm component lock, fuselage is electrically connected with lift arm component.The purpose of this utility model is to provide Multi-axis aircraft that can be portable, to facilitate the installation and removal of fuselage and lift arm, thus the transport that is easy to carry.
Description
Technical field
The utility model relates to a kind of Multi-axis aircraft.
Background technology
Existing Multi-axis aircraft great majority are all all-in-one-piece, and several lift arm is fixed on fuselage, and the area taken is very large, and volume is also very large, is not easy to carry very much.So just limit the propagation and employment of Multi-axis aircraft.
The space that some large-scale Multi-axis aircraft takies when carrying to reduce, is modified into lift arm fabricated.Be that plug-in lift arm or bendable lift arm all can add some mechanisms, these additional mechanism providing additional operations not only complex structure but also add many flying weights, affects airworthiness.These schemes just seem impracticable for small-sized multi-axis aircraft, microminiature Multi-axis aircraft are difficult to adopt plug-in or collapsible lift arm.So, be not easy to carry the distinct disadvantage being difficult to popularization into these microminiature Multi-axis aircrafts.
Utility model content
For Problems existing in correlation technique, the purpose of this utility model is to provide a kind of Multi-axis aircraft, realizes in portable mode the installation and removal facilitating fuselage and lift arm, thus the transport that is easy to carry.
For achieving the above object, the utility model provides a kind of Multi-axis aircraft, comprises fuselage and lift arm component, fuselage and lift arm component are removably locked by lockout mechanism or unlock, wherein, in the position that fuselage and lift arm component lock, fuselage is electrically connected with lift arm component.
According to the utility model, lockout mechanism comprise be arranged on fuselage and lift arm component one of any on dead bolt and be arranged on fuselage and the lift arm component snap close on another, it is non-circular lockhole that snap close is configured to shape, dead bolt is configured to rotatable cage knob through snap close also rotatably, by fuselage and the locking of lift arm component.
Preferably, lockout mechanism comprise be arranged on fuselage and lift arm component one of any on engaging member and be arranged on fuselage and the lift arm component snap close on another, engaging member is configured to the mode utilizing elasticity to be clamped by described snap close, by fuselage and the locking of lift arm component.
According to the utility model, fuselage and lift arm component one of any on be provided with plug, fuselage and lift arm component are provided with electric jack on another, and the electrical connection between fuselage with lift arm component is embodied as: plug coordinates with electric jack grafting.
According to the utility model, lift arm component is provided with engine installation, and fuselage interior is provided with electric supply installation; Coordinated with the grafting of electric jack by plug, electric supply installation is electrically connected with engine installation.
Preferably, fuselage and lift arm component one of any on be provided with spacing preiection, fuselage and lift arm component are provided with position-limited trough on another, and spacing preiection can be connected with position-limited trough relative sliding.
Preferably, fuselage is provided with holding tank, and lift arm component is removably locked in holding tank by lockout mechanism.
Advantageous Effects of the present utility model is:
1. the fuselage of Multi-axis aircraft of the present utility model and lift arm component are by lockout mechanism detachable locking or unblock, achieve the quickly and easily assembling between fuselage and lift arm component and disassemble, and can be placed in very little container after the fuselage of Multi-axis aircraft and lift arm decompose, therefore be not only convenient to user carry but also crush injury can not occur, assembling Sum decomposition is all very convenient.
2. lockout mechanism is optionally embodied as the structure that dead bolt utilizes elasticity to be clamped by snap close through snap close the structure of spin locking or engaging member, thus the assembled relation that can simplify between fuselage and lift arm component, and the weight of such structure to Multi-axis aircraft does not have considerable influence, thus harmful effect can not be produced to the airworthiness of Multi-axis aircraft, be convenient to the carrying of Multi-axis aircraft, promotion and application.
3. achieve fuselage be connected with the fast electric of lift arm component by being separately positioned on Multi-axis aircraft fuselage and the plug on lift arm component and electric jack, and then also achieve and be arranged on engine installation on lift arm component and the fast electric of electric supply installation in fuselage is set is connected, make Multi-axis aircraft can normal operation flight.
4. by arrange the sliding block joint of spacing preiection on fuselage and lift arm component and position-limited trough respectively and be arranged on fuselage for holding the holding tank of lift arm component, achieve the accurate assembling between lift arm component and fuselage, namely, lift arm component and fuselage mutually mate in shape and size, can realize installing fast and accurately when assembling.
Accompanying drawing explanation
Fig. 1 is the top perspective view of the utility model Multi-axis aircraft;
Fig. 2 is the top perspective view of the released state of an embodiment of the utility model Multi-axis aircraft;
Fig. 3 is the face upwarding stereogram of lock-out state embodiment illustrated in fig. 1;
Fig. 4 is the partial enlargement face upwarding stereogram of released state embodiment illustrated in fig. 3;
Fig. 5 is the partial enlargement face upwarding stereogram of lock-out state embodiment illustrated in fig. 3;
Fig. 6 is the face upwarding stereogram of fuselage embodiment illustrated in fig. 1;
Fig. 7 is the top perspective view of a lift arm in middle lift arm component embodiment illustrated in fig. 1;
Fig. 8 is the face upwarding stereogram of the released state of another embodiment of the utility model Multi-axis aircraft;
Fig. 9 is the face upwarding stereogram of lock-out state embodiment illustrated in fig. 8.
Detailed description of the invention
Referring now to accompanying drawing, the utility model is described.Multi-axis aircraft of the present utility model is divided into the unblock of fuselage and lift arm component in the accompanying drawings and locks two states and illustrates.
Particularly, referring to figs. 1 through the block diagram of the released state shown in Fig. 5 and lock-out state, Multi-axis aircraft 10 of the present utility model, comprises fuselage 20 and lift arm component 30, and fuselage 20 is removably locked with lift arm component 30 by lockout mechanism 40 or unlocked.Wherein, fuselage 20 and lift arm component 30 locks and refer to that fuselage 20 and lift arm component 30 fit together, and can become a complete Multi-axis aircraft to perform aerial mission.In this latched position, fuselage 20 is electrically connected with lift arm component 30.Fuselage 20 and lift arm component 30 unlock and refer to when Multi-axis aircraft does not perform aerial mission, and fuselage 20 and lift arm component 30 are disassembled thus can be placed in very little container, to carry out transporting and carrying.Therefore Multi-axis aircraft of the present utility model had not only been convenient to user and is carried but also crush injury can not occur, and assembling Sum decomposition is all very convenient.So just greatly the promotion and application of Multi-axis aircraft are expanded.
In an alternate embodiment of the invention, lockout mechanism 40 can be illustrated by following specific embodiment, such as, lockout mechanism 40 of the present utility model can be the structure of dead bolt and snap fit, or also can be the structure of engaging member and snap close snap-fit, can also be the structure that other similar such as bolt and nut etc. can realize simple the locking and unlocking.Certainly should be appreciated that the utility model is not limited to said structure, other mode that can realize the locking and unlocking all can be applicable in the utility model, and this can determine according to concrete service condition, and the utility model is not limited to this.
In the first embodiment of the present utility model gone out as shown in Figures 1 to 7, lockout mechanism 40 comprise be arranged on fuselage 20 and lift arm component 30 one of any on dead bolt 41 and be arranged on fuselage 20 and lift arm component 30 snap close 42 on another.In other words, when dead bolt 41 is arranged on fuselage 20, snap close 42 is arranged on lift arm component 30 with regard to correspondence; When dead bolt 41 is arranged on lift arm component 30, snap close 42 is just arranged on fuselage 20.In embodiment as shown in Figures 1 to 7, to be arranged on fuselage 20 for dead bolt 41 and snap close 42 is arranged on accordingly on lift arm component 30 and is described.
Further, as shown in Figure 4 and Figure 5, it is non-circular lockhole that snap close 42 is configured to shape, and namely so long as not circle, lockhole can both pin dead bolt 41 as snap close 42.In the present embodiment, the shape of snap close 42 is Long Circles, and namely snap close 42 has the first radial width and is greater than the second radial width of the first radial width.In embodiment as shown in Figure 4 and Figure 5, the second radial width is the width extended along the longitudinal axes L direction of Multi-axis aircraft.Certainly should be appreciated that in other embodiments, also can be the first radial width extends along the longitudinal axes L direction of Multi-axis aircraft.In other embodiment, the shape of snap close 42 can be the shapes such as ellipse, triangle, square.
Further, dead bolt 41 is configured to rotatable cage knob to pass snap close 42 and rotatable mode, fuselage 20 and lift arm component 30 is locked.As shown in Figure 4 and Figure 5, dead bolt 41 has the non-circular shape similar to snap close 42.By the configuration of such shape, after dead bolt 41 is through snap close 42 also rotation, namely can realize the locking dead bolt 41 and snap close 42.
In the second embodiment of the present utility model such as shown in Fig. 8 and Fig. 9, lockout mechanism 40 comprise be arranged on fuselage 20 and lift arm component 30 one of any on engaging member 43 and be arranged on fuselage 20 and lift arm component 30 snap close 42 on another.In other words, when engaging member 43 is arranged on fuselage 20, snap close 42 is arranged on lift arm component 30 with regard to correspondence; When engaging member 43 is arranged on lift arm component 30, snap close 42 is arranged on fuselage 20 with regard to correspondence.In embodiment as shown in Figure 8 and Figure 9, to be arranged on fuselage 20 for engaging member 43 and snap close 42 is arranged on accordingly on lift arm component 30 and is described.
Further, with reference to Fig. 8, engaging member 43 constructs the mode utilizing elasticity to be clamped by snap close 42, fuselage 20 and lift arm component 30 is locked.Specifically, engaging member 43 is configured to two elastics, and the free end of these two elastics is barb-like.Correspondingly, snap close 42 is the edge of quantity and the position hole corresponding with engaging member 43 or framing member.When these two elastics pass this two apertures accordingly or when arriving rigging position along framing member edge, engaging member 43 utilizes its elasticity that two barbs are fastened on the edge of two apertures or the edge of framing member respectively, to realize the object locked.Such engaging member buckle structure simplifies the assembled relation between fuselage 20 and lift arm component 30, and considerable influence is not had to the weight of Multi-axis aircraft, thus harmful effect can not be produced to the airworthiness of Multi-axis aircraft, be convenient to the carrying of Multi-axis aircraft, promotion and application.
Refer again to Fig. 1 and Fig. 4, in an embodiment of the present utility model, lift arm component 30 comprises the first lift arm and the second lift arm of head and the afterbody that can be locked in fuselage 20 respectively, this the first lift arm and the second lift arm comprise again two sub-lift arms respectively, and this sub-lift arm can become a lift arm then to be locked by a lockout mechanism 40 and fuselage 20 or unlocked as combination of two in above-described embodiment.Certainly, in other embodiment, every sub-lift arm can lock with fuselage 20 or unlock respectively separately through lockout mechanism 40.
Further, in embodiment as shown in Figure 1 and Figure 4, the first lift arm and the second lift arm are all arranged relative to longitudinal axis direction (as shown in arrow L in Fig. 1) the specular ground of fuselage 20.That is, in the present embodiment, the lift arm component 30 of Multi-axis aircraft has four sub-lift arms altogether, and these four sub-lift arms are between two respectively at the head of fuselage 20 and the afterbody longitudinal axis direction specular relative to fuselage 20.In other alternative-embodiments, the first lift arm and the second lift arm can all be arranged relative to the axis of pitch direction (with the direction that the direction in Fig. 1 shown in arrow L is perpendicular) of fuselage 20 specular.Thus Multi-axis aircraft of the present utility model can not be partial to and can stably be flown.
Refer again to Fig. 6 to Fig. 8, in the above-described embodiments, fuselage 20 and lift arm component 30 one of any on be provided with plug 51, fuselage 20 and lift arm component 30 are provided with electric jack 52 on another.In other words, when plug 51 is arranged on fuselage 20, electric jack 52 is arranged on lift arm component 30 with regard to correspondence; When plug 51 is arranged on lift arm component 30, electric jack 52 is arranged on fuselage 20 with regard to correspondence.In embodiment as shown in Figure 6 to 8, to be arranged on lift arm component 30 for plug 51 and electric jack 52 is arranged on accordingly on fuselage 20 and is described.Electrical connection between fuselage 20 with lift arm component 30 is embodied as: plug 51 coordinates with electric jack 52 grafting.In other alternative-embodiments, the electrical connection between fuselage 20 and lift arm component 30 for fuselage 20 and lift arm component 30 arrange conducting strip respectively, can be conducted electricity by conducting strip contact; Or can be other similar structures that conveniently can realize current switching in prior art.Certainly should be appreciated that the utility model is not limited to said structure, other mode that can realize current switching all can be applicable in the utility model, and this can determine according to concrete service condition, and the utility model is not limited to this.
Continue with reference to Fig. 1-Fig. 3, lift arm component 30 is provided with engine installation 60, engine installation 60 comprises screw propeller, electrical motor, gear cluster etc.; Fuselage 20 inside is provided with electric supply installation (not shown), and this electric supply installation is used for the in check drive current providing power supply to export through electronic machine to engine installation 60; Coordinated by the grafting of plug 51 with electric jack 52, electric supply installation is electrically connected with engine installation 60.In other embodiment, coordinate by the contact of conducting strip the electrical connection realizing electric supply installation and engine installation 60.
Continue with reference to Fig. 6 to Fig. 9, in the above-described embodiments, fuselage 20 is provided with holding tank 21, and lift arm component 30 is removably locked in holding tank 21 by lockout mechanism 40.This holding tank 21 can be the formation groove that caves inward on the surface of fuselage 20 shown in accompanying drawing.This groove and lift arm component 30 match in profile and size for the position locked, so lift arm component 30 very snugly can be contained in holding tank 21 and to be locked by lockout mechanism 40.
Further, fuselage 20 and lift arm component 30 one of any on be provided with spacing preiection 33, fuselage 20 and lift arm component 30 are provided with position-limited trough 34 on another, and spacing preiection 33 can be connected with position-limited trough 34 relative sliding.Specifically, on the sidewall of groove forming holding tank 21, outwards be recessed to form position-limited trough 34 or inwardly outstandingly form spacing preiection 33, outwardly forming spacing preiection 33 or cave inward on a sidewall at the position locked and form position-limited trough 34 correspondingly at lift arm component 30.By on a sidewall, form so only spacing preiection 33 or position-limited trough 34 and spacing preiection 33 and position-limited trough 34 relative sliding be connected, achieve the accurate assembling between lift arm component 30 and fuselage 20, namely lift arm component 30 and fuselage 20 mutually mate in shape and size, not needing to rake about assembly relation when assembling, relying on lockout mechanism that lift arm component 30 just can be allowed to be assemblied in correctly, securely on fuselage 20 as long as lift arm is put into relevant position.
The foregoing is only preferred embodiment of the present utility model, be not limited to the utility model, for a person skilled in the art, the utility model can have various modifications and variations.All within spirit of the present utility model and principle, any amendment done, equivalent replacement, improvement etc., all should be included within protection domain of the present utility model.
Claims (7)
1. a Multi-axis aircraft, comprises fuselage (20) and lift arm component (30), it is characterized in that,
Described fuselage (20) and described lift arm component (30) are removably locked by lockout mechanism (40) or unlock,
Wherein, in the position that described fuselage (20) and described lift arm component (30) lock, described fuselage (20) is electrically connected with described lift arm component (30).
2. Multi-axis aircraft according to claim 1, is characterized in that,
Described lockout mechanism (40) comprise be arranged on described fuselage (20) and described lift arm component (30) one of any on dead bolt (41) and be arranged on described fuselage (20) and described lift arm component (30) snap close (42) on another
It is non-circular lockhole that described snap close (42) is configured to shape,
Described dead bolt (41) is configured to rotatable cage knob and passes described snap close (42) and rotatably, described fuselage (20) and described lift arm component (30) locked.
3. Multi-axis aircraft according to claim 1, is characterized in that,
Described lockout mechanism (40) comprise be arranged on described fuselage (20) and described lift arm component (30) one of any on engaging member (43) and be arranged on described fuselage (20) and described lift arm component (30) snap close (42) on another
Described engaging member (43) is configured to the mode utilizing elasticity to be clamped by described snap close (42), by described fuselage (20) and described lift arm component (30) locking.
4. the Multi-axis aircraft according to any one of claim 1-3, is characterized in that,
Described fuselage (20) and described lift arm component (30) one of any on be provided with plug (51), described fuselage (20) and described lift arm component (30) are provided with electric jack (52) on another
Described electrical connection between described fuselage (20) with described lift arm component (30) is embodied as: described plug (51) coordinates with described electric jack (52) grafting.
5. Multi-axis aircraft according to claim 4, is characterized in that,
Described lift arm component (30) is provided with engine installation (60), and described fuselage (20) inside is provided with electric supply installation;
Coordinated by the described grafting of described plug (51) with described electric jack (52), described electric supply installation is electrically connected with described engine installation (60).
6. the Multi-axis aircraft according to Claims 2 or 3, is characterized in that,
Described fuselage (20) and described lift arm component (30) one of any on be provided with spacing preiection (33), described fuselage (20) and described lift arm component (30) are provided with position-limited trough (34) on another
Described spacing preiection (33) can be connected with described position-limited trough (34) relative sliding.
7. Multi-axis aircraft according to claim 1, is characterized in that,
Described fuselage (20) is provided with holding tank (21), and described lift arm component (30) is removably locked in described holding tank (21) by described lockout mechanism (40).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520124518.6U CN204548489U (en) | 2015-03-04 | 2015-03-04 | Multi-axis aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520124518.6U CN204548489U (en) | 2015-03-04 | 2015-03-04 | Multi-axis aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204548489U true CN204548489U (en) | 2015-08-12 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520124518.6U Expired - Fee Related CN204548489U (en) | 2015-03-04 | 2015-03-04 | Multi-axis aircraft |
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| Country | Link |
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| CN (1) | CN204548489U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105939927A (en) * | 2015-12-24 | 2016-09-14 | 深圳市大疆创新科技有限公司 | Quick-detachable structure, multi-rotor unmanned aerial vehicle, assembly, and rotor assembly |
| CN106218881A (en) * | 2016-08-30 | 2016-12-14 | 辽宁壮龙无人机科技有限公司 | Vertical layout fuel power four rotor flying platform |
-
2015
- 2015-03-04 CN CN201520124518.6U patent/CN204548489U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105939927A (en) * | 2015-12-24 | 2016-09-14 | 深圳市大疆创新科技有限公司 | Quick-detachable structure, multi-rotor unmanned aerial vehicle, assembly, and rotor assembly |
| CN106218881A (en) * | 2016-08-30 | 2016-12-14 | 辽宁壮龙无人机科技有限公司 | Vertical layout fuel power four rotor flying platform |
| CN106218881B (en) * | 2016-08-30 | 2019-03-22 | 辽宁壮龙无人机科技有限公司 | Vertical layout fuel power quadrotor flying platform |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20170802 Address after: 518000 Guangdong city of Shenzhen province Nanshan District Guangdong streets Yi of financial science and Technology Software Park building 12 floor Patentee after: Staring (Shenzhen) technology Limited by Share Ltd Address before: 201801 Shanghai city Jiading District abundance Road No. 818 Patentee before: Shanghai Nine Eagles Electronic Technology Co., Ltd. |
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| TR01 | Transfer of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20150812 Termination date: 20180304 |
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| CF01 | Termination of patent right due to non-payment of annual fee |