CN203793654U - Aircraft loading bracket and aircraft - Google Patents
Aircraft loading bracket and aircraft Download PDFInfo
- Publication number
- CN203793654U CN203793654U CN201420007577.0U CN201420007577U CN203793654U CN 203793654 U CN203793654 U CN 203793654U CN 201420007577 U CN201420007577 U CN 201420007577U CN 203793654 U CN203793654 U CN 203793654U
- Authority
- CN
- China
- Prior art keywords
- aircraft
- loading dock
- carrying platform
- absorption device
- assembly
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
- 230000035939 shock Effects 0.000 claims description 69
- 238000009434 installation Methods 0.000 claims description 54
- 238000010521 absorption reaction Methods 0.000 claims description 48
- 230000005540 biological transmission Effects 0.000 claims description 5
- 230000000694 effects Effects 0.000 abstract description 11
- 238000013016 damping Methods 0.000 abstract description 7
- 230000000703 anti-shock Effects 0.000 abstract 1
- 238000005516 engineering process Methods 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 230000000007 visual effect Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
Abstract
The utility model discloses an aircraft loading bracket and an aircraft. The aircraft loading bracket is used for being connected with a rack component of the aircraft through a damping component. The aircraft loading bracket comprises a carrying platform component and an element mounting position, wherein the carrying platform component is provided with a shooting device, and an element arranged on the element mounting position and the carrying platform component are fixedly connected into a whole. In this way, the anti-shock performance of the aircraft loading bracket can be improved, and therefore the aerial photography effect of the aircraft can be improved.
Description
Technical field
The utility model relates to aeronautical technology field, particularly relates to a kind of loading dock and aircraft of aircraft.
Background technology
Along with scientific and technical development, with the aircraft that is loaded with camera, carry out Aerial photography more and more general.Aircraft, in flight course, can produce vibrations because of the rotation of rotor, affects the shooting effect of camera, need to carry out aseismatic design.The shockproof scheme of prior art is for arranging shock absorption device between the The Cloud Terrace at carrying camera and frame.But this shockproof scheme can be limited to the performance of shock absorption device, shockproof effect is not obvious.
Utility model content
The technical matters that the utility model embodiment mainly solves is to provide a kind of loading dock and aircraft of aircraft, can improve damping effect, thereby improves the effect of taking photo by plane.
For solving the problems of the technologies described above, the technical scheme that the utility model embodiment adopts is: the loading dock that a kind of aircraft is provided, this loading dock is for being connected with the housing assembly of aircraft by dampening assembly, loading dock comprises carrying platform assembly and the element installation position that is provided with filming apparatus, wherein, the element and the carrying platform assembly that are arranged on element installation position are fixedly connected into an integral body.
Wherein, the element being arranged on element installation position comprises battery and/or foot rest, and wherein, battery provides electric energy for the power plant to aircraft.
Wherein, the element being arranged on element installation position comprises Image transmission equipment and/or cradle head control unit.
Wherein, carrying platform assembly comprises carrying platform, filming apparatus and the relative both sides that are arranged on element on element installation position and are separately positioned on carrying platform.
Wherein, filming apparatus is camera or pick up camera, and carrying platform comprises at least one turning cylinder, for changing the shooting angle of camera or pick up camera.
For solving the problems of the technologies described above, another technical scheme that the utility model embodiment adopts is: a kind of aircraft is provided, this aircraft comprises housing assembly, loading dock and dampening assembly, dampening assembly is connected to housing assembly by loading dock, wherein, loading dock comprises loading dock above.
Wherein, dampening assembly comprises shock mount and spaced at least one the first shock absorption device and the second shock absorption device, carrying platform assembly is connected with shock mount respectively with the element being arranged on element installation position with phase the same side and carrying platform assembly that element installation position is positioned at shock mount, and housing assembly is located at respectively between housing assembly and shock mount at the opposite side of shock mount and the first shock absorption device and the second shock absorption device.
Wherein, dampening assembly comprises the first shock absorption device and the second shock absorption device, and the first shock absorption device is connected to housing assembly by carrying platform, and the second shock absorption device is connected to housing assembly by the element being arranged on element installation position.
Wherein, the first shock absorption device and the second shock absorption device are respectively shock-absorbing ball.
Wherein, housing assembly comprises frame main body and from the outward extending a plurality of extension arms of frame main body, dampening assembly is connected to loading dock the below of frame main body.
The beneficial effect of the utility model embodiment is: the situation that is different from prior art, the loading dock of the aircraft of the utility model embodiment comprises carrying platform assembly and the element installation position that is provided with filming apparatus, wherein, the element and the carrying platform assembly that are arranged on element installation position are fixedly connected into an integral body, and loading dock is connected with the housing assembly of aircraft by dampening assembly.By the way, the utility model embodiment is without the overall weight of change of flight device, but by the weight that element increases loading dock is set on element installation position, thereby increased the inertia of loading dock, make it have better stability, improve its anti-seismic performance, thereby improve the effect of taking photo by plane of aircraft.
Accompanying drawing explanation
Fig. 1 is the birds-eye view of the aircraft of the utility model embodiment;
Fig. 2 is that the aircraft shown in Fig. 1 is along the cutaway view of dotted line A-A ';
Fig. 3 is the diagram of circuit of shock-dampening method of the aircraft of the utility model embodiment.
The specific embodiment
Please also refer to Fig. 1 and Fig. 2, Fig. 1 is the birds-eye view of the aircraft of the utility model embodiment, and Fig. 2 is that the aircraft shown in Fig. 1 is along the cutaway view of dotted line A-A '.
As depicted in figs. 1 and 2, aircraft 10 of the present utility model comprises housing assembly 11, loading dock 12 and dampening assembly 13.Wherein, loading dock 12 comprises carrying platform assembly 121 and the element installation position 122 that filming apparatus 123 is set, and the element and the carrying platform assembly 121 that are arranged on element installation position 122 are fixedly connected into an integral body.Loading dock 12 is connected with the housing assembly 11 of aircraft 10 by dampening assembly 13.
It should be noted that, the loading dock 12 of the present embodiment can be by being spirally connected or the mode such as riveted joint is connected to dampening assembly 13, and further, dampening assembly 13 is by being spirally connected or the mode such as riveted joint is connected to housing assembly 11.
In the present embodiment, the overall weight of aircraft 10 does not change, and by the element on the element installation position 122 of loading dock 12 and carrying platform assembly 121 are fixedly connected into an integral body, increase the overall weight of loading dock 12, thereby increased the inertia of loading dock 12, make it have better stability, improve its anti-seismic performance, thereby improve the effect of taking photo by plane of aircraft 10.
Alternatively, element installation position 122 specifically can be a concrete element mount pad, can be also the component installation location in a space.When it is an element mount pad, element is directly installed on this element mount pad, further by this mount pad, is connected with carrying platform assembly 121; When it is the component installation location in a space, element is arranged in this component installation location, is further connected with carrying platform assembly 121.
Alternatively, the element being arranged on element installation position 122 comprises battery or foot rest, or battery and foot rest.Wherein, battery provides electric energy for the power plant to aircraft 10, and foot rest is the telescopic foot stool of aircraft 10.
Further, the element being arranged on element installation position 122 can also comprise Image transmission equipment or cradle head control unit, or Image transmission equipment and cradle head control unit.
In the utility model embodiment, as long as can be installed to the element on element installation position 122, all can be arranged on element installation position 122, to increase the weight of loading dock 12.
Alternatively, carrying platform assembly 121 comprises carrying platform 1211, wherein, and filming apparatus 123 and the relative both sides that are arranged on element on element installation position 122 and are separately positioned on carrying platform 1211, stressed with balance carrying platform 1211.
Alternatively, filming apparatus 123 is camera or pick up camera, and carrying platform 1211 also comprises at least one turning cylinder (not shown), for changing the shooting angle of the filming apparatus 123 such as camera or pick up camera.For example carrying platform 1211 comprises three turning cylinders, provides rotating freely at any angle of three degree of freedom to take.
Alternatively, dampening assembly 13 comprises at least one first shock absorption device 131 and at least one second shock absorption device 132.The present embodiment is only illustrated with first shock absorption device 131 and second shock absorption device 132.The first shock absorption device 131 is connected to housing assembly 11, the second shock absorption devices 132 by carrying platform 1211 element being arranged on element installation position 122 is connected to housing assembly 11.
In other preferred embodiments, dampening assembly 13 comprises shock mount (not shown) and spaced at least one first shock absorption device 131 and the second shock absorption device 132, at this with first shock absorption device 131 and the second shock absorption device 132 casehistorys.Carrying platform assembly 121 is connected with shock mount respectively with the element being arranged on element installation position 122 with phase the same side and carrying platform assembly 121 that element installation position 122 is positioned at shock mount, and housing assembly 11 is located at respectively between housing assembly 11 and shock mount at the opposite side of shock mount and the first shock absorption device 131 and the second shock absorption device 132.
Further, the upper surface of carrying platform 1211 and the upper surface flush that is arranged on the element of element installation position 122, it is identical making the damping dynamics of 131 pairs of carrying platforms 1211 of the first shock absorption device and damping dynamics that 132 pairs of the second shock absorption devices are arranged on the element of element installation position 122, guarantees the damping effect of aircraft 10.
In other embodiments, also by bracing or strutting arrangements such as strut bars, the element that is arranged on element installation position 122 is supported to certain altitude, until the element that is arranged on element installation position 122 is supported to the position, space of housing assembly 11, or higher than the horizontal surface of carrying platform 1211, the element of avoiding being arranged on element installation position 122 hinders the shooting visual field of the filming apparatus 123 such as camera or pick up camera.
Wherein, set in advance the height threshold that supports the element that is arranged on element installation position 122, specifically having the restriction of two aspects, is to guarantee the gravity acting point and the carrying platform assembly 121 that are arranged on the element of element installation position 122 to be co-located on shock mount on the one hand.On the other hand for guaranteeing the shooting visual field of the filming apparatus 123 such as camera or pick up camera.
Alternatively, the first shock absorption device 131 and the second shock absorption device 132 are shock-absorbing ball.The present embodiment is only exemplified as two shock-absorbing balls, in actual applications, can be also a plurality of shock-absorbing balls, guarantees damping effect.The first shock absorption device 131 and the second shock absorption device 132 can also be for spring or gyroscope etc., as long as have the performance of damping.
Alternatively, housing assembly 11 comprises frame main body 111 and from the outward extending a plurality of extension arms 112 of frame main body 111, dampening assembly 13 is connected to loading dock 12 below of frame main body 111.
Aircraft 10 further comprises the main control module (not shown) being arranged in frame main body 111 and is arranged at the flying power module 114 on extension arm 112.The battery that is arranged on element installation position 122 is further electrically connected to main control module, and main control module is powered; Or the battery that is arranged on element installation position 122 is electrically connected to flying power module 114, and flying power module 114 is powered; Or the battery that is arranged on element installation position 122 is all electrically connected to main control module and flying power module 114, and main control module and flying power module 114 are powered.
Flying power module 114 comprises the rotor 1142 on the motor 1141 being arranged on extension arm 112 and the turning cylinder that is arranged at motor 1141.Rotor 1142 is 4 groups, is distributed in the surrounding of housing assembly 11 centered by housing assembly 11.Motor 1141 drives rotor 1142 to rotate by turning cylinder, and wherein, centered by housing assembly 11, the rotation direction of two groups of symmetrical rotors 1142 is consistent, and the direction of rotation of two groups of adjacent rotors 1142.
Therefore, the overall weight of the utility model aircraft 10 does not change, and by the weight that element increases loading dock 12 is set on element installation position 122, thereby increased the inertia of loading dock 12, make it have better stability, improve its anti-seismic performance, thereby improve the effect of taking photo by plane of aircraft 10.
In addition, the utility model embodiment also provides a kind of shock-dampening method of aircraft based on previously described aircraft 10, and as shown in Figure 3, the shock-dampening method of aircraft 10 comprises the following steps:
Step S1: on the carrying platform 1211 of carrying platform assembly 121, filming apparatus 123 is set, on element installation position 122, element is set.
In this step, filming apparatus 123 comprises camera or pick up camera.
The element arranging on element installation position 122 comprises battery and/or foot rest, also comprises Image transmission equipment and/or cradle head control unit.Wherein, battery provides electric energy for the power plant to aircraft 10, and foot rest is the telescopic foot stool of aircraft 10.
Step S2: carrying platform assembly 121 and the element being arranged on element installation position 122 are fixedly connected into an integral body, to form loading dock 12.
In this step, be specially by filming apparatus 123 and the relative both sides that are arranged on element on element installation position 122 and are separately positioned on carrying platform 1211 stressed with balance carrying platform 1211.Further, the upper surface of carrying platform 1211 and the upper surface flush that is arranged on the element of element installation position 122.
Step S3: loading dock 12 is connected to housing assembly 11 by dampening assembly 13.
In this step, dampening assembly 13 preferably includes shock mount, first shock absorption device 131 and second shock absorption device 132.Thus, this step is specially phase the same side and carrying platform assembly 121 that carrying platform assembly 121 and element installation position 122 are arranged on to shock mount and is connected with shock mount respectively with the element being arranged on element installation position 122, further housing assembly 121 is arranged on to the opposite side of shock mount, further the first shock absorption device 131 and the second shock absorption device 132 is separately positioned between housing assembly 11 and shock mount.
In other embodiments, dampening assembly 13 can also only include first shock absorption device 131 and second shock absorption device 132.Step S3 is specially by the first shock absorption device 131 carrying platform 121 is connected to housing assembly 11, further by the second shock absorption device 132, the element being arranged on element installation position 122 is connected to housing assembly 11.
In sum, the overall weight of the utility model aircraft 10 does not change, and by the weight that element increases loading dock 12 is set on element installation position 122, then by dampening assembly 13, loading dock 12 is connected to housing assembly 11.Therefore, the utility model has increased the inertia of loading dock 12, makes it have better stability, improves its anti-seismic performance, thereby improves the effect of taking photo by plane of aircraft 10.
The foregoing is only embodiment of the present utility model; not thereby limit the scope of the claims of the present utility model; every equivalent structure or conversion of equivalent flow process that utilizes the utility model specification sheets and accompanying drawing content to do; or be directly or indirectly used in other relevant technical fields, be all in like manner included in scope of patent protection of the present utility model.
Claims (10)
1. the loading dock of an aircraft, it is characterized in that, described loading dock is for being connected with the housing assembly of aircraft by dampening assembly, described loading dock comprises carrying platform assembly and the element installation position that is provided with filming apparatus, wherein, the element and the described carrying platform assembly that are arranged on described element installation position are fixedly connected into an integral body.
2. loading dock according to claim 1, is characterized in that, the element being arranged on described element installation position comprises battery and/or foot rest, and wherein, described battery provides electric energy for the power plant to described aircraft.
3. loading dock according to claim 2, is characterized in that, the element being arranged on described element installation position comprises Image transmission equipment and/or cradle head control unit.
4. loading dock according to claim 1, is characterized in that, described carrying platform assembly comprises carrying platform, described filming apparatus and the relative both sides that are arranged on element on described element installation position and are separately positioned on described carrying platform.
5. loading dock according to claim 4, is characterized in that, described filming apparatus is camera or pick up camera, and described carrying platform comprises at least one turning cylinder, for changing the shooting angle of described camera or pick up camera.
6. an aircraft, it is characterized in that: described aircraft comprises housing assembly, loading dock and dampening assembly, described dampening assembly is connected to described housing assembly by described loading dock, and wherein, described loading dock comprises the loading dock as described in claim 1-5 any one.
7. aircraft according to claim 6, it is characterized in that, described dampening assembly comprises shock mount and spaced at least one the first shock absorption device and the second shock absorption device, described carrying platform assembly is connected with described shock mount respectively with the element being arranged on described element installation position with phase the same side and described carrying platform assembly that described element installation position is positioned at described shock mount, and described housing assembly is located at respectively between described housing assembly and described shock mount at the opposite side of described shock mount and described the first shock absorption device and the second shock absorption device.
8. aircraft according to claim 6, it is characterized in that, described dampening assembly comprises the first shock absorption device and the second shock absorption device, described the first shock absorption device is connected to described housing assembly by described carrying platform, and described the second shock absorption device is connected to described housing assembly by the element being arranged on described element installation position.
9. according to the aircraft described in claim 7 or 8 any one, it is characterized in that, described the first shock absorption device and described the second shock absorption device are respectively shock-absorbing ball.
10. aircraft according to claim 6, is characterized in that, described housing assembly comprises frame main body and from the outward extending a plurality of extension arms of described frame main body, described dampening assembly is connected to described loading dock the below of described frame main body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420007577.0U CN203793654U (en) | 2014-01-06 | 2014-01-06 | Aircraft loading bracket and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420007577.0U CN203793654U (en) | 2014-01-06 | 2014-01-06 | Aircraft loading bracket and aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203793654U true CN203793654U (en) | 2014-08-27 |
Family
ID=51375894
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420007577.0U Expired - Fee Related CN203793654U (en) | 2014-01-06 | 2014-01-06 | Aircraft loading bracket and aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203793654U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103738504A (en) * | 2014-01-06 | 2014-04-23 | 深圳市大疆创新科技有限公司 | Loading support for aircraft, aircraft and shock absorption method for aircraft |
-
2014
- 2014-01-06 CN CN201420007577.0U patent/CN203793654U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103738504A (en) * | 2014-01-06 | 2014-04-23 | 深圳市大疆创新科技有限公司 | Loading support for aircraft, aircraft and shock absorption method for aircraft |
| CN103738504B (en) * | 2014-01-06 | 2017-04-19 | 深圳市大疆创新科技有限公司 | Loading support for aircraft, aircraft and shock absorption method for aircraft |
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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: 20170627 Address after: 518057 Guangdong city of Shenzhen province Nanshan District Guangdong streets south four Road No. 18 building in the West SKYWORTH semiconductor design 12 Patentee after: SZ DJI OSMO TECHNOLOGY Co.,Ltd. Address before: 518057 Guangdong city of Shenzhen province Nanshan District high tech Industrial Park South Hing a 9 Hongkong branch of Shenzhen University Building 6 layer 613, 614 Patentee before: SZ DJI TECHNOLOGY Co.,Ltd. |
|
| TR01 | Transfer of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140827 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |