CN105889725B - Cradle head structure and its fixed frame, aircraft body and aircraft - Google Patents
Cradle head structure and its fixed frame, aircraft body and aircraft Download PDFInfo
- Publication number
- CN105889725B CN105889725B CN201610355180.4A CN201610355180A CN105889725B CN 105889725 B CN105889725 B CN 105889725B CN 201610355180 A CN201610355180 A CN 201610355180A CN 105889725 B CN105889725 B CN 105889725B
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- Prior art keywords
- fixed frame
- aircraft body
- aircraft
- cradle head
- head structure
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- 230000001360 synchronised effect Effects 0.000 claims description 3
- 230000037431 insertion Effects 0.000 claims 1
- 238000003780 insertion Methods 0.000 claims 1
- 238000010586 diagram Methods 0.000 description 8
- 230000000007 visual effect Effects 0.000 description 4
- 238000000034 method Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000035939 shock Effects 0.000 description 2
- 239000007787 solid Substances 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 230000006978 adaptation Effects 0.000 description 1
- 230000003044 adaptive effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16M—FRAMES, CASINGS OR BEDS OF ENGINES, MACHINES OR APPARATUS, NOT SPECIFIC TO ENGINES, MACHINES OR APPARATUS PROVIDED FOR ELSEWHERE; STANDS; SUPPORTS
- F16M13/00—Other supports for positioning apparatus or articles; Means for steadying hand-held apparatus or articles
- F16M13/02—Other supports for positioning apparatus or articles; Means for steadying hand-held apparatus or articles for supporting on, or attaching to, an object, e.g. tree, gate, window-frame, cycle
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
- B64D47/08—Arrangements of cameras
-
- G—PHYSICS
- G03—PHOTOGRAPHY; CINEMATOGRAPHY; ANALOGOUS TECHNIQUES USING WAVES OTHER THAN OPTICAL WAVES; ELECTROGRAPHY; HOLOGRAPHY
- G03B—APPARATUS OR ARRANGEMENTS FOR TAKING PHOTOGRAPHS OR FOR PROJECTING OR VIEWING THEM; APPARATUS OR ARRANGEMENTS EMPLOYING ANALOGOUS TECHNIQUES USING WAVES OTHER THAN OPTICAL WAVES; ACCESSORIES THEREFOR
- G03B17/00—Details of cameras or camera bodies; Accessories therefor
- G03B17/56—Accessories
- G03B17/561—Support related camera accessories
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Buckles (AREA)
- Toys (AREA)
Abstract
The disclosure is directed to a kind of cradle head structure and its fixed frame, aircraft body and aircraft, the bottom of the fixed frame can be fixedly attached to the holder ontology top of the cradle head structure；Fixed card buckle is equipped at a side at the top of the fixed frame, can be connected with the default card slot of aircraft body bottom；At least one block button hole is equipped with relative to another side edge of described a side on the fixed frame, can be connected with the default lock of the aircraft body bottom.By the technical solution of the disclosure, being bonded between cradle head structure and aircraft body and fast assembling-disassembling can be realized.
Description
Technical field
This disclosure relates to flight control technique field more particularly to a kind of cradle head structure and its fixed frame, aircraft body and fly
Row device.
Background technology
By the cradle head structure assembled on aircraft body, the stability and controlled manner of the process of taking photo by plane can be promoted.
Aircraft body of the prior art is in integrated design with cradle head structure so that and aircraft integrally needs to occupy big quantity space,
Not readily portable and transport.
It proposes in the related art and is separated from each other aircraft body and cradle head structure, i.e., split type aircraft, but need
Aircraft body and cradle head structure are attached by cooperation by screw, there are connection reliability it is poor, not easy to assemble the problems such as.
Invention content
The disclosure provides a kind of cradle head structure and its fixed frame, aircraft body and aircraft, to solve in the relevant technologies
Deficiency.
According to the embodiment of the present disclosure in a first aspect, providing a kind of fixed frame of cradle head structure, the bottom of the fixed frame
The holder ontology top of the cradle head structure can be fixedly attached to；Fixing card is equipped at a side at the top of the fixed frame
Button, can be connected with the default card slot of aircraft body bottom；Relative to the another of described a side on the fixed frame
At least one block button hole is equipped at a side, can be connected with the default lock of the aircraft body bottom.
Optionally, the fixed card buckle by the top of the fixed frame in the outwardly directed convex ribs shape of described a side
Into.
Optionally, another side is slightly tilted to the inside of the fixed frame.
Optionally, connector base is additionally provided at the top of the fixed frame, passes through the fixed frame in the cradle head structure
When being assembled to the aircraft body bottom, the connector base can match with the connector female seat of the aircraft body bottom
Connection is closed, so that the holder ontology of the cradle head structure is electrically connected to the aircraft body.
According to the second aspect of the embodiment of the present disclosure, a kind of cradle head structure is provided, including：
Holder ontology；
The fixed frame of cradle head structure as described in any in above-described embodiment.
According to the third aspect of the embodiment of the present disclosure, a kind of aircraft body is provided, the bottom of the aircraft body is set
There is the groove for the fixed frame that can accommodate cradle head structure；Default card slot is equipped at the side inner wall of the groove, it can be with the fixation
Fixed card buckle at a side of top of the trellis is connected；In opposite side on the groove relative to the side inner wall
At wall be equipped at least one lock, can on the fixed frame relative to the default block button hole of another side edge of described a side
It is connected.
Optionally, the lock is sliding shackle, can be flown when the fixed frame is assembled to the groove to described
The internal slide of row device ontology；The spring for being matched with the sliding shackle is additionally provided in the aircraft body, the spring can
After the fixed frame is assembled to the groove, the sliding shackle is popped up, to stretch into and be matched with phase on the fixed frame
The block button hole answered.
Optionally, it further includes：
The lock push button that can be synchronized with the movement with the sliding shackle；When the lock push button is located at default solution lock-bit, institute
Sliding shackle block button hole corresponding on the fixed frame is stated to be detached from, it is described when the lock push button is located at default locking bit
Sliding shackle can stretch into and be matched with corresponding block button hole on the fixed frame.
Optionally, it further includes：
Connector female seat in the groove is assembled to the flight in the cradle head structure by the fixed frame
During the bottom of device ontology, the connector female seat can be connected with the connector base at the top of the fixed frame, so that described
The holder ontology of cradle head structure is electrically connected to the aircraft body；
Wherein, when the connector base is blade type terminal structure, the connector female seat is equipped with and is respectively used to insert
Enter one group of shrapnel of each blade type terminal, and the shrapnel is equipped with salient point.
Optionally, it further includes：
At least one piece of elastomeric pad is set to the bottom surface of the groove.
According to the fourth aspect of the embodiment of the present disclosure, a kind of aircraft is provided, including：
Cradle head structure as described in above-described embodiment；
Aircraft body as described in any in above-described embodiment.
The technical scheme provided by this disclosed embodiment can include the following benefits：
By above-described embodiment it is found that the disclosure for cradle head structure by providing dedicated fixed frame, and by being fixed at this
The opposite both sides setting fixed card buckle and block button hole of frame upper edge, can be latched with the default card slot on aircraft body and presetting into
Row is quickly connected and dismounting, and can obtain stable connection effect.
It should be understood that above general description and following detailed description are only exemplary and explanatory, not
The disclosure can be limited.
Description of the drawings
Attached drawing herein is incorporated into specification and forms the part of this specification, shows the implementation for meeting the disclosure
Example, and for explaining the principle of the disclosure together with specification.
Fig. 1 is the schematic diagram according to a kind of cradle head structure shown in an exemplary embodiment.
Fig. 2 is according to a kind of aircraft body shown in an exemplary embodiment and the stereochemical structure after cradle head structure assembling
Schematic diagram.
Fig. 3 is the schematic diagram according to a kind of fixed frame shown in an exemplary embodiment.
Fig. 4 is the schematic diagram according to the aircraft body under a kind of first visual angle shown in an exemplary embodiment.
Fig. 5 is the schematic diagram according to the aircraft body under a kind of second visual angle shown in an exemplary embodiment.
Specific embodiment
Here exemplary embodiment will be illustrated in detail, example is illustrated in the accompanying drawings.Following description is related to
During attached drawing, unless otherwise indicated, the same numbers in different attached drawings represent the same or similar element.Following exemplary embodiment
Described in embodiment do not represent all embodiments consistent with the disclosure.On the contrary, they be only with it is such as appended
The example of the consistent device and method of some aspects be described in detail in claims, the disclosure.
Fig. 1 is according to a kind of schematic diagram of cradle head structure shown in an exemplary embodiment, as shown in Figure 1, the holder knot
Structure 1 can include：Holder ontology 11 and fixed frame 12；The bottom of the fixed frame 12 can be fixedly attached to the top of the holder ontology 11
End, for example be screwed.By the way that special fixed frame 12 is configured so that when the fixed frame 12 is damaged, such as by
In dismount number it is excessive and when leading to not continue firm assembling, directly the fixed frame 12 can be removed and replaced for, and
Without being replaced to entire cradle head structure 1, it is possible to prevente effectively from the waste of vast resources.
By fixed frame 12, holder ontology 11 can be bonded to the bottom of aircraft body shown in Fig. 2, so as to
The operations such as take photo by plane can be realized by the cradle head structure 1.The structure of fixed frame 12 is discussed in detail with reference to Fig. 3-5, with
And the fit structure on aircraft body 2；Wherein, Fig. 3 is showing according to a kind of fixed frame 12 shown in an exemplary embodiment
It is intended to, Fig. 4 is according to the schematic diagram of the aircraft body 2 under a kind of first visual angle shown in an exemplary embodiment, and Fig. 5 is root
A kind of schematic diagram of the aircraft body 2 under second visual angle shown according to an exemplary embodiment.
As shown in figure 3, being equipped with fixed card buckle 121 at a side at the top of fixed frame 12, which can be with
For the convex rib structure that fixed frame 12 is outwardly formed, to ensure that the fixed card buckle 121 has sufficient intensity.Correspondingly, such as Fig. 4 institutes
Show, the bottom of aircraft body 2 formed can accommodate cradle head structure 1 fixed frame 12 groove 20, the depth of the groove 20 with
The thickness of fixed frame 12 matches, and fixed frame 12 is enable to be contained in substantially in the groove 20.At the side inner wall of groove 20
Equipped with default card slot 21, then the clasp of above-mentioned fixed card buckle 121 can be stretched into the default card slot 21, so as to make the default card
Slot 21 is connected with fixed card buckle 121.
Further, as shown in figure 3, relative to the another of above-mentioned a side equipped with fixed card buckle 121 on fixed frame 12
When left side is equipped with the fixed card buckle 121 in a side, such as Fig. 3, at least one block button hole 122 can be equipped in right edge；
Correspondingly, as shown in figure 5, when groove 20 inner left wall be equipped with above-mentioned default card slot 21 when, in the right side of the groove 20
Wall can be equipped at least one lock 22, then the lock 22 can be stretched into the block button hole 122 on fixed frame 12, so as to make lock
Button 22 is connected with corresponding block button hole 122.
In the above-described embodiments, it is by realizing being connected together between fixed frame 12 and groove 20 from both sides respectively, i.e., solid
Surely buckle 121 and default card slot 21 between be connected together, block button hole 122 and lock 22 between being connected together, can realize
Being bonded between fixed frame 12 and aircraft body 2.
As shown in figure 3, the side (i.e. right edge in Fig. 3) that fixed frame 12 is equipped with block button hole 122 can be fixed to this
The inside of frame 12 slightly tilts so that and when fixed frame 12 is embedded in groove 20, the section of embedded groove 20 gradually increases on fixed frame 12,
On the one hand contribute to the accurate positionin between fixed frame 12 and groove 20, on the other hand formed by the inclination respective side edge
One gentle slope, the lock 22 contributed in groove 20 more slip into block button hole 122 glibly along the gentle slope.
In one embodiment, above-mentioned lock 22 can be sliding shackle, which can be in fixed frame 12 to groove
20 when being assembled to the internal slide of the aircraft body 2, i.e., in the accommodating chamber that 20 inner wall of retraction groove is inwardly formed, make solid
Determining frame 12 can smoothly be inserted into groove 20；Especially, when the side that fixed frame 12 is equipped with block button hole 122 is formed shown in Fig. 3
Above-mentioned gentle slope when, the gentle slope can fixed frame 12 be embedded in groove 20 during sliding shackle is pushed, so as to will
The sliding shackle is pushed into above-mentioned accommodating chamber, is promoted in the smooth embedded groove 20 of fixed seat 12.
Wherein, it is also provided with being matched with the spring (not shown) of the sliding shackle in aircraft body 2, such as should
Spring can be located in above-mentioned accommodating chamber so that and when sliding shackle is pushed into accommodating chamber, the spring can be caused to deform upon,
And generate the active force that sliding shackle is released to accommodating chamber.During fixed frame 12 is embedded in groove 20, when on fixed frame 12
122 misalignment sliding shackle of block button hole when, which will be butted under the promotion of spring on the side wall of fixed frame 12, directly
To after fixed frame 12 is assembled to groove 20 completely, block button hole 122 is directed at sliding shackle, which can be under the promotion of spring
It stretches into and is matched on the fixed frame 12 corresponding block button hole 122.
Further, as shown in figure 5, being also provided on aircraft body 2：The lock that can be synchronized with the movement with sliding shackle
Push button 23.Wherein, when the lock push button 23 is located at default solution lock-bit, which corresponding on the fixed frame 12 can block
Button hole 122 is detached from, for example the lock push button 23 can drive sliding shackle to be slided into above-mentioned accommodating chamber, so that fixed frame 12
It can be smoothly detached from out of groove 20；And when the lock push button 23 is located at default locking bit, which can stretch into and match
Together in block button hole 122 corresponding on the fixed frame 12, and when latching push button 23 positioned at default solution lock-bit, above-mentioned spring can be sent out
Raw deformation simultaneously generates the active force for being pushed outwardly sliding shackle so that fixed frame 12 is removed and latches push button 23 not by user
When force pushes, sliding shackle from receiving intracavitary can be released automatically and automatically reset lock push button 23 to above-mentioned
Default locking bit.
In one embodiment, as shown in figure 3, the top of fixed frame 12 can be equipped with connector base 123；Meanwhile as schemed
Shown in 4-5, the connector female seat 24 being located in groove 20 can be included on aircraft body 2.So, pass through in cradle head structure 1
When fixed frame 12 is assembled to 2 bottom of aircraft body, which can be with the connection of 2 bottom of aircraft body
Device female seat 24 is connected, so that the holder ontology 11 of the cradle head structure 1 is electrically connected to the aircraft body 2, for example realizes number
According to transmission, power supply etc..
Wherein, when the connector base 123 is blade type terminal structure, connector female seat 24 can be equipped with and be respectively used to
One group of shrapnel of each blade type terminal is inserted into, and the shrapnel is equipped with salient point.So, the blade type end of connector base 123
After son is inserted into connector female seat 24, though the blade type terminal to any direction light exercise, on 24 shrapnel of connector female seat
Salient point can touch the blade type terminal, so as to when aircraft body 2, cradle head structure 1 are given a shock, can be ensured that always
Good contact between connector base 123 and connector female seat 24.Simultaneously as not using external cabling, even if thus
In the presence of more strong vibrations, the problems such as incidental circuit disconnects during connection female using such as row's needle row can also be avoided,
With extremely strong stability.
In addition, as illustrated in figures 4-5, aircraft body 2 can also include：At least one piece of elastomeric pad 25, can be set to
The bottom surface of the groove 20.So, when fixed seat 12 is embedded in and is assemblied in groove 20, which can fill fixation
Gap between seat 12 and groove 20, plays pressuring action；Meanwhile in the case where shaking, which may be used also
To provide effective elastic shock attenuation effect, to protect aircraft.
Those skilled in the art will readily occur to the disclosure its after considering specification and putting into practice disclosure disclosed herein
Its embodiment.This application is intended to cover any variations, uses, or adaptations of the disclosure, these modifications, purposes or
Person's adaptive change follows the general principle of the disclosure and including the undocumented common knowledge in the art of the disclosure
Or conventional techniques.Description and embodiments are considered only as illustratively, and the true scope and spirit of the disclosure are by following
Claim is pointed out.
It should be understood that the present disclosure is not limited to the precise structures that have been described above and shown in the drawings, and
And various modifications and changes may be made without departing from the scope thereof.The scope of the present disclosure is only limited by appended claim.
Claims (5)
1. a kind of aircraft, which is characterized in that including aircraft body and cradle head structure；The cradle head structure includes holder ontology
And fixed frame, the bottom of the fixed frame can be fixedly attached to the holder ontology top of the cradle head structure；The fixed frame
Fixed card buckle is equipped at a side at top, can be connected with the default card slot of aircraft body bottom；The fixation
At least one block button hole is equipped with relative to another side edge of described a side on frame, it can be pre- with the aircraft body bottom
If lock is connected；Another side of the fixed frame is slightly tilted to the inside of the fixed frame；The fixed card buckle
It is formed by the top of the fixed frame in the outwardly directed convex ribs of described a side；
The bottom of the aircraft body is equipped with the groove for the fixed frame that can accommodate cradle head structure；At the side inner wall of the groove
Equipped with default card slot, can be connected with the fixed card buckle at a side at the top of the fixed frame；Phase on the groove
For at the opposite side inner wall of the side inner wall be equipped at least one lock, can on the fixed frame relative to the side
The default block button hole of another side edge on side is connected；Wherein, the lock is sliding shackle, can be in the fixed frame
To the internal slide of the aircraft body when being assembled to the groove；It is additionally provided in the aircraft body and is matched with institute
The spring of sliding shackle is stated, the spring can pop up the sliding shackle after the fixed frame is assembled to the groove, with
It stretches into and is matched with corresponding block button hole on the fixed frame.
2. aircraft according to claim 1, which is characterized in that connector base is additionally provided at the top of the fixed frame,
When the cradle head structure is assembled to the aircraft body bottom by the fixed frame, the connector base can with it is described
The connector female seat of aircraft body bottom is connected, so that the holder ontology of the cradle head structure is electrically connected to the flight
Device ontology.
3. aircraft according to claim 1, which is characterized in that the aircraft body further includes：
The lock push button that can be synchronized with the movement with the sliding shackle；When the lock push button is located at default solution lock-bit, the cunning
Dynamic lock block button hole corresponding on the fixed frame is detached from, when the lock push button is located at default locking bit, the slip
Lock can stretch into and be matched with corresponding block button hole on the fixed frame.
4. aircraft according to claim 1, which is characterized in that the aircraft body further includes：
Connector female seat in the groove is assembled to the aircraft sheet in the cradle head structure by the fixed frame
During the bottom of body, the connector female seat can be connected with the connector base at the top of the fixed frame, so that the holder
The holder ontology of structure is electrically connected to the aircraft body；
Wherein, when the connector base is blade type terminal structure, the connector female seat, which is equipped with, to be respectively for insertion into often
One group of shrapnel of a blade type terminal, and the shrapnel is equipped with salient point.
5. aircraft according to claim 1, which is characterized in that the aircraft body further includes：
At least one piece of elastomeric pad is set to the bottom surface of the groove.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610355180.4A CN105889725B (en) | 2016-05-25 | 2016-05-25 | Cradle head structure and its fixed frame, aircraft body and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610355180.4A CN105889725B (en) | 2016-05-25 | 2016-05-25 | Cradle head structure and its fixed frame, aircraft body and aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105889725A CN105889725A (en) | 2016-08-24 |
| CN105889725B true CN105889725B (en) | 2018-06-12 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610355180.4A Active CN105889725B (en) | 2016-05-25 | 2016-05-25 | Cradle head structure and its fixed frame, aircraft body and aircraft |
Country Status (1)
| Country | Link |
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Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2018076347A1 (en) * | 2016-10-31 | 2018-05-03 | 深圳一电航空技术有限公司 | Unmanned aerial vehicle for aerial photography |
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| CN1520128A (en) * | 2003-01-24 | 2004-08-11 | 华冠通讯股份有限公司 | Clip buckle structure in battery seat |
| CN1627769A (en) * | 2003-12-10 | 2005-06-15 | 乐金电子(中国)研究开发中心有限公司 | Cell latch of portable terminal |
| US8241777B2 (en) * | 2008-09-11 | 2012-08-14 | Shenzhen Futaihong Precision Industry Co., Ltd. | Battery cover mechanism |
| CN205098486U (en) * | 2015-10-13 | 2016-03-23 | 深圳一电科技有限公司 | Unmanned aerial vehicle |
| CN105539872A (en) * | 2016-01-29 | 2016-05-04 | 北京小米移动软件有限公司 | Pan-tilt of unmanned aerial vehicle and bearing support of pan-tilt |
| CN205781864U (en) * | 2016-05-25 | 2016-12-07 | 北京小米移动软件有限公司 | Cradle head structure and fixed mount, aircraft body and aircraft |
-
2016
- 2016-05-25 CN CN201610355180.4A patent/CN105889725B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1520128A (en) * | 2003-01-24 | 2004-08-11 | 华冠通讯股份有限公司 | Clip buckle structure in battery seat |
| CN1627769A (en) * | 2003-12-10 | 2005-06-15 | 乐金电子(中国)研究开发中心有限公司 | Cell latch of portable terminal |
| US8241777B2 (en) * | 2008-09-11 | 2012-08-14 | Shenzhen Futaihong Precision Industry Co., Ltd. | Battery cover mechanism |
| CN205098486U (en) * | 2015-10-13 | 2016-03-23 | 深圳一电科技有限公司 | Unmanned aerial vehicle |
| CN105539872A (en) * | 2016-01-29 | 2016-05-04 | 北京小米移动软件有限公司 | Pan-tilt of unmanned aerial vehicle and bearing support of pan-tilt |
| CN205781864U (en) * | 2016-05-25 | 2016-12-07 | 北京小米移动软件有限公司 | Cradle head structure and fixed mount, aircraft body and aircraft |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105889725A (en) | 2016-08-24 |
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