CN206750129U - Aircraft - Google Patents
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- CN206750129U CN206750129U CN201720475528.3U CN201720475528U CN206750129U CN 206750129 U CN206750129 U CN 206750129U CN 201720475528 U CN201720475528 U CN 201720475528U CN 206750129 U CN206750129 U CN 206750129U
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- main part
- aircraft
- framework
- axial
- limiting component
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Abstract
The utility model, which provides a kind of aircraft, to be included：The aircraft body of the first main part with the first weight and the second main part with the second weight, accommodate the spherical protective cover with three axis accelerometer structure of the aircraft body, wherein, first main part is supported in the three axis accelerometer structure in the opening position of the geometric center of the neighbouring spherical protective cover, second main part suspension is arranged on below first main part, and first weight and second weight configuration are located at the underface of the geometric center of the spherical protective cover into causing the center of gravity of the aircraft body.The utility model can enough realize that the even upward wall of climbing of the horizontal rolling all around of aircraft in the horizontal plane moves, and aircraft body can remain basic horizontal state, it is ensured that the stability of aircraft.
Description
Technical field
The utility model embodiment is related to technical field of aerospace, more particularly to a kind of aircraft.
Background technology
With the development of science and technology, unmanned plane it is more and more extensive be applied to life production various aspects for example, with
In city management, agricultural, geological prospecting, meteorology, shop, rescue and relief work, video capture etc..Present unmanned plane often holds
Easily break, and encounter complex environment with regard to helpless, propeller can only be broken by barrier is knocked, can just fall on ground
On, it is therefore desirable to a protective cover is protected to unmanned plane, avoids unmanned plane from being damaged.It is directed to the above situation, prior art
In further there is the unmanned plane with protective cover, but in the existing unmanned plane with protective cover, unmanned plane body
It can not remain horizontal, easily be protected the influence of cover.Once for example, protective cover it is affected by wind shake or with
Outer barrie thing collides, and protective cover will drive the run-off the straight of unmanned plane body or even overturn, so as to cause unmanned plane to fly
Capable unstability, and potential safety hazard.
Utility model content
The utility model embodiment provides a kind of aircraft, and the aircraft at least to solve in above-mentioned technical problem can not
The technical problem of enough safety and steady flight.
In some embodiments of aircraft of the present utility model, it includes：
The aircraft body of second main part of the first main part and the second weight with the first weight, accommodate institute
The spherical protective cover with three axis accelerometer structure of aircraft body is stated,
Wherein, first main part is supported on described in the opening position of the geometric center of the neighbouring spherical protective cover
In three axis accelerometer structure, second main part suspension is arranged on below first main part, first weight and
Second weight configuration into the center of gravity for causing the aircraft body be located at the geometric center of the spherical protective cover just under
Side.
In the present embodiment, as the protective cover of aircraft aircraft can be caused any by using three axis accelerometer structure
Basic horizontal state is all in rugged environment all the time.And the water all around of aircraft in the horizontal plane can be realized
The even upward wall of climbing of flat rolling moves.In addition, in order to ensure the stability of aircraft, also by by the first weight and described
Two weight are designed so that the center of gravity of the aircraft body is located at the underface of the geometric center of the spherical protective cover, so as to
Ensure that aircraft more can sensitively be returned to basic horizontal state rapidly by during external environment influence, it is ensured that aircraft
Stability.
In certain embodiments, first main part is arranged on the three axis accelerometer structure by vertical connecting rod
On, first main part is socketed in the vertical connecting rod, is disposed with the vertical connecting rod described for supporting
The stopping means of first main part；Wherein, when the vertical connecting rod is in force-free state, the stopping means is by institute
State the first main part and be maintained at first position；When external force of the vertical connecting rod by axis direction, the spacing dress
Put first main part being limited between the scope of the second place and moved along the axis direction, the second place scope bag
Include the first position.
In the present embodiment, the support that aircraft body and three axis accelerometer mechanism are not only realized by stopping means is installed,
And can also be by impact of the outside to aircraft vertical direction (for example, being fallen during aircraft failure by the setting of stopping means
Impact caused by falling) as far as possible to buffering fall, be unlikely to stiff and be directly delivered to aircraft body, aircraft body is made
Into unnecessary damage.
In certain embodiments, the stopping means include the first limiting component being socketed in the vertical connecting rod and
Second limiting component；Wherein, first limiting component is located on first main element, the second limiting component position
Under second main part；First limiting component and second limiting component are elastomeric element.
The upper and lower surface of the first main part of aircraft body is entered respectively by two limiting components in the present embodiment
Restriction is gone so that the first main part can be maintained in the first limiting component and the second limiting component limited range
Row motion (vertical connecting rod by vertical direction impulsive force when), and because the first limiting component and the second limiting component are adopted
With elastomeric material, so impact of the vertical direction to aircraft body can be cut down.
In certain embodiments, the stopping means includes the first limiting component, the first spring, the second limiting component, the
Two springs；First limiting component limits first spring to support the upper surface of first main part, and described the
Two limiting components limit the second spring to support the lower surface of first main part.
In certain embodiments, multiple propellers are installed, the multiple propeller turns in first main part
Direction where axle and plane where first main part are at an acute angle.
By by where direction where the rotating shaft of the propeller in aircraft body and the first main part in the present embodiment
Plane mode at an acute angle enables to keep more smooth flight during aircraft flight, before and after being realized beneficial to aircraft
The deflecting campaign in the directions such as left and right, improve the sensitivity of aircraft deflecting campaign.
In certain embodiments, the three axis accelerometer structure includes the first axial framework, outside the described first axial framework
The second axial framework that side and the described first axial framework are pivotally connected and on the outside of the described second axial framework with described second
The 3rd axial framework that axial framework is pivotally connected.The outline of the 3rd axial framework is circular or polyhedron-shaped.
The first axial framework and the second axial framework are annular framework.When the foreign steamer of the 3rd axial framework in the present embodiment
Exterior feature for it is circular when be advantageous to motion of the aircraft on ground or wall, when to be advantageous to aircraft during polyhedral structure more
Steady quickly landing.
In certain embodiments, the described first axial framework and the second axial framework use rigid material；3rd axle
Elastomeric material is used to framework.
In certain embodiments, the distance between the 3rd axial framework and described second axial framework are set greater than
The 3rd axial framework largest deformation distance.
By in the selection of three axis accelerometer structure different levels structure and the setting of mutual distance in the present embodiment
(according to the setting of the maximum flexibility deformation of selected material distance), is adequately achieved to the impact caused by outside adverse circumstances
Buffering, while so as to ensure that the safe flight of aircraft, avoid the damage to aircraft.
Brief description of the drawings
, below will be to embodiment in order to illustrate more clearly of the utility model embodiment or technical scheme of the prior art
Or the required accompanying drawing used is briefly described in description of the prior art, it should be apparent that, drawings in the following description are
Some embodiments of the utility model, for those of ordinary skill in the art, on the premise of not paying creative work,
Other accompanying drawings can also be obtained according to these accompanying drawings.
Fig. 1 is the structural representation of one embodiment of the utility model aircraft；
Fig. 2 is aircraft body and one embodiment of the first axial framework mounting means in the utility model aircraft
Structural representation；
Fig. 3 is aircraft body and the first axial framework and the second axial framework mounting means in the utility model aircraft
One embodiment structural representation.
Embodiment
It is new below in conjunction with this practicality to make the purpose, technical scheme and advantage of the utility model embodiment clearer
Accompanying drawing in type embodiment, the technical scheme in the embodiment of the utility model is clearly and completely described, it is clear that is retouched
The embodiment stated is the utility model part of the embodiment, rather than whole embodiments.Based on the implementation in the utility model
Example, the every other embodiment that those of ordinary skill in the art are obtained under the premise of creative work is not made, is belonged to
The scope of the utility model protection.
It should be noted that in the case where not conflicting, the feature in embodiment and embodiment in the utility model can
To be mutually combined.Describe the utility model in detail below with reference to the accompanying drawings and in conjunction with the embodiments.
As shown in figure 1, in some embodiments of aircraft of the present utility model, it includes：
Flight including the first main part 21 with the first weight and the second main part 22 with the second weight
Device main body, the spherical protective cover 1 with three axis accelerometer structure of the aircraft body is accommodated,
Wherein, first main part 21 is supported in the opening position of the geometric center of the neighbouring spherical protective cover 1
In the three axis accelerometer structure, second main part 22 suspension is arranged on the lower section of the first main part 21, and described the
One weight and second weight configuration are located in the geometry of the spherical protective cover 1 into causing the center of gravity of the aircraft body
The underface of the heart.
In the present embodiment, it can make it that aircraft is in office as the protective cover 1 of aircraft by using three axis accelerometer structure
Basic horizontal state is all in all the time in what rugged environment.And can realize aircraft in the horizontal plane all around
The even upward wall of climbing of horizontal rolling moves.In addition, in order to ensure the stability of aircraft, also by by the first weight and described
Second weight configuration into causing the center of gravity of the aircraft body to be located at the underface of the geometric center of the spherical protective cover, from
And ensure aircraft by more can sensitively returning to basic horizontal state rapidly during external environment influence, it is ensured that flight
The stability of device.In the present embodiment can by the way that the part of heavier-weight in aircraft body is configured into the second main part,
So as to ensure that the center of aircraft body can be located at the underface of the geometric center of spherical protective cover.
In certain embodiments, the second main part 22 passes through multiple hanger attachment portion parts 23 and first main part
21 connections, hanger attachment portion part 23 is rigid connecting components, to ensure the phase of the second main part 22 and the first main part 21
To fixation.
As shown in figure 1, in certain embodiments, multiple propellers 24 are installed in first main part 22, it is the multiple
Direction and the place plane of the first main part 21 are at an acute angle where the rotating shaft of propeller 24.By that will fly in the present embodiment
The mode at an acute angle with the place plane of the first main part 21 of direction where the rotating shaft of propeller 24 in device main body enables to
More smooth flight is kept during aircraft flight, the deflecting campaign in the direction such as all around is realized beneficial to aircraft, is carried
The sensitivity of aircraft deflecting campaign is risen.
In some embodiments of the utility model, aircraft is quadrotor, the first main body of aircraft body
Four propellers 24 are installed, the first main part 21 generally installs the support of propeller 24 on part 21.Second main part
Points 22 are used for the control sections of installing aircraft, for example, power supply, flying vehicles control mainboard, gyroscope, head, shooting are first-class.It is logical
Cross the main centralized configuration of the weight of aircraft body in the mode of the second main part 22, ensure that the center of gravity of aircraft body
The underface of the geometric center of spherical protective cover 1 can be located at.If necessary, individually it can increase to the second main part 22
Add counterweight, to ensure that aircraft body can remain substantially horizontal attitude in three axis accelerometer structure.
In certain embodiments, first main part 21 is arranged on the three axis accelerometer knot by vertical connecting rod 31
On structure, first main part 21 is socketed in the vertical connecting rod 31, is disposed with and is used in the vertical connecting rod 31
Support the stopping means of first main part 21；Wherein, it is described when the vertical connecting rod 31 is in force-free state
First main part 21 is maintained at first position by stopping means；When the vertical connecting rod 31 is by the outer of axis direction
During power, first main part 21 is limited between the scope of the second place and moved along the axis direction by the stopping means,
The second place scope includes the first position.
In the present embodiment, the support that aircraft body and three axis accelerometer mechanism are not only realized by stopping means is installed,
And can also be by impact of the outside to aircraft vertical direction (for example, being fallen during aircraft failure by the setting of stopping means
Impact caused by falling) buffering as much as possible falls, is unlikely to stiff and is directly delivered to aircraft body, aircraft body is made
Into unnecessary damage.
In certain embodiments, the stopping means includes the first limiting component being socketed in the vertical connecting rod 31
With the second limiting component；Wherein, first limiting component is located on first main element 21, second limiting section
Part is located under second main part 21；First limiting component and second limiting component are elastomeric element.
By two limiting components respectively to the upper and lower surface of the first main part 21 of aircraft body in the present embodiment
It is defined so that the first main part 21 can be maintained at the first limiting component and the second limiting component limited range
Inside moved (vertical connecting rod by vertical direction impulsive force when), and due to the first limiting component and the second limiting component
Elastomeric material is used, so impact of the vertical direction to aircraft body can be cut down.
As shown in Fig. 2 the stopping means includes the first limiting component 32, the first spring 33, the in certain embodiments
Two limiting components 32 ', second spring 33 '；First limiting component 32 limits first spring 33 to support described first
The upper surface of main part 21, second limiting component 32 ' limit the second spring 33 ' to support first main part
Divide 21 lower surface.
In the present embodiment, because aircraft body 1 remains basic horizontal state under the cooperation of three axis accelerometer structure
(this holding automatically adjusting independent of flight control, be that pure mechanic structure is realized), even aircraft
During failure, aircraft body also keep basic horizontal state (basic horizontal state herein is not complete horizontality, but
Include aircraft and the small skew state of aircraft body occur when carrying out winged side or steering), so as to work as aircraft
When hindering for some reason and falling, impulsive force vertically will necessarily be caused to aircraft, at this moment by spacing in the present embodiment
Device can just fall this damping of shocks, avoid impact and damage to aircraft body.
Referring to figs. 1 to Fig. 3, in certain embodiments, the three axis accelerometer structure includes the first axial framework 3, and described
The second axial framework 4 that first axial framework 3 is pivotally connected and the 3rd axial frame being pivotally connected with the described second axial framework 4
Frame 5, the outline of the 3rd axial framework 5 is circular or polyhedron-shaped, wherein the first axial framework 3 is in most
Layer, the second axial framework 4 are located at intermediate layer, and the 3rd axial framework 5 is located at outermost layer.When the 3rd axial framework 5 in the present embodiment
Outline for it is circular when be advantageous to motion of the aircraft on ground or wall, when to be advantageous to fly during polyhedral structure
The more steady quickly landing of device.
In certain embodiments, the first axial 3 and second axial framework 4 of framework can be annular either other shapes
Shape, few this of the utility model limit.
In certain embodiments, the described first axial 3 and second axial framework 4 of framework uses rigid material；Described 3rd
Axial framework 5 uses elastomeric material.
The the first axial 3 and second axial framework 4 of framework made in the present embodiment using rigid material positioned at inner side is ensured
Firm supporting role to aircraft, making the 3rd axial framework 5 using elastomeric material can not only be to the flight of inside
Device main body 1 plays a protective role, but also is capable of the impact of absorbing external, so as to indirectly serve protection to aircraft body
Effect.
In certain embodiments, the distance between the described 3rd axial framework 5 and the described second axial framework 4 are set as greatly
In the described 3rd axial largest deformation distance of framework 5.
In the present embodiment, by the largest deformation distance according to the 3rd axial framework 5 come set the 3rd axial framework 5 with
The mode of the distance between second axial framework 4, it can ensure when aircraft is hit by the external world, even if the 3rd axial framework
5 deform upon, and will not also be contacted with the second axial framework 4 in intermediate layer so that external impact directly to be transmitted into, at utmost
On reduce impact of the external impact to internal aircraft body 1.
In addition, in certain embodiments can also be by being set in the junction of the 3rd axial 5 and second axial framework 4 of framework
The mode of buffer unit is put to avoid outside caused by the direct contact between the 3rd axial 5 and second axial framework 4 of framework rush
The direct transmission hit.
Finally it should be noted that：Above example is only to illustrate the technical solution of the utility model, rather than its limitations；
Although the utility model is described in detail with reference to the foregoing embodiments, it will be understood by those within the art that：
It can still modify to the technical scheme described in foregoing embodiments, or which part technical characteristic is carried out etc.
With replacement；And these modifications or replacement, the essence of appropriate technical solution is departed from various embodiments of the utility model technology
The spirit and scope of scheme.
Claims (10)
- A kind of 1. aircraft, it is characterised in that including：The aircraft body of the first main part with the first weight and the second main part with the second weight,The spherical protective cover with three axis accelerometer structure of the aircraft body is accommodated,Wherein, first main part is supported on three axle in the opening position of the geometric center of the neighbouring spherical protective cover On gyroscope structure, second main part suspension is arranged on below first main part, first weight and described Second weight configuration is located at the underface of the geometric center of the spherical protective cover into causing the center of gravity of the aircraft body.
- 2. aircraft according to claim 1, it is characterised in that first main part is installed by vertical connecting rod In the three axis accelerometer structure, first main part is socketed in the vertical connecting rod, in the vertical connecting rod It is disposed with the stopping means for supporting first main part；Wherein, when the vertical connecting rod is in force-free state When, first main part is maintained at first position by the stopping means；When the vertical connecting rod is by axis direction External force when, first main part is limited between the scope of the second place along the axis direction and transported by the stopping means Dynamic, the second place scope includes the first position.
- 3. aircraft according to claim 2, it is characterised in that the stopping means includes being socketed in the vertical connection The first limiting component and the second limiting component on bar；Wherein, first limiting component be located at first main element it On, second limiting component is located under second main part；First limiting component and second limiting section Part is elastomeric element.
- 4. aircraft according to claim 2, it is characterised in that the stopping means includes the first limiting component, first Spring, the second limiting component, second spring；First limiting component limits first spring to support first main body Partial upper surface, second limiting component limit the second spring to support the lower surface of first main part.
- 5. aircraft according to claim 1, it is characterised in that be provided with multiple spirals in first main part Oar, direction where the rotating shaft of the multiple propeller and plane where first main part are at an acute angle.
- 6. aircraft according to claim 1, it is characterised in that the three axis accelerometer structure includes the first axial framework, The second axial framework for being pivotally connected on the outside of the described first axial framework with the described first axial framework and in second axle The 3rd axial framework being pivotally connected on the outside of to framework with the described second axial framework.
- 7. aircraft according to claim 6, it is characterised in that the first axial framework and the second axial framework For annular framework.
- 8. aircraft according to claim 6, it is characterised in that the outline of the 3rd axial framework to be circular or It is polyhedron-shaped.
- 9. according to the aircraft any one of claim 6-8, it is characterised in that the first axial framework and the second axle Rigid material is used to framework；The 3rd axial framework uses elastomeric material.
- 10. according to the aircraft any one of claim 6-8, it is characterised in that the 3rd axial framework with it is described The distance between second axial framework is set greater than the largest deformation distance of the 3rd axial framework.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720475528.3U CN206750129U (en) | 2017-05-02 | 2017-05-02 | Aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720475528.3U CN206750129U (en) | 2017-05-02 | 2017-05-02 | Aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206750129U true CN206750129U (en) | 2017-12-15 |
Family
ID=60616016
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720475528.3U Active CN206750129U (en) | 2017-05-02 | 2017-05-02 | Aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206750129U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106956768A (en) * | 2017-05-02 | 2017-07-18 | 锐合防务技术（北京）有限公司 | Aircraft |
| CN108706095A (en) * | 2018-04-16 | 2018-10-26 | 国网浙江省电力有限公司 | A kind of miniature multi-rotor unmanned aerial vehicle with anticollision device, collision-prevention device of applicable raceway groove inspection |
| CN109533333A (en) * | 2018-09-05 | 2019-03-29 | 徐州万科标识系统工程有限公司 | Primary-secondary type unmanned plane believes lodge and its sends part method |
-
2017
- 2017-05-02 CN CN201720475528.3U patent/CN206750129U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106956768A (en) * | 2017-05-02 | 2017-07-18 | 锐合防务技术（北京）有限公司 | Aircraft |
| CN108706095A (en) * | 2018-04-16 | 2018-10-26 | 国网浙江省电力有限公司 | A kind of miniature multi-rotor unmanned aerial vehicle with anticollision device, collision-prevention device of applicable raceway groove inspection |
| CN109533333A (en) * | 2018-09-05 | 2019-03-29 | 徐州万科标识系统工程有限公司 | Primary-secondary type unmanned plane believes lodge and its sends part method |
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Legal Events
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20190731 Address after: 518054 Virtual University Park C505, No. 2 Sandao, Yuexing Street, Nanshan District, Shenzhen City, Guangdong Province Patentee after: Shenzhen Ruihe Aircraft Intelligent Equipment Co., Ltd. Address before: 100191 Beijing, Zhichun Road, College of International Building, No. 912,, 1 Patentee before: Sharp Defense Technology (Beijing) Co., Ltd. |