CN205113689U - Aircraft, aircraft main part and foot rest - Google Patents
Aircraft, aircraft main part and foot rest Download PDFInfo
- Publication number
- CN205113689U CN205113689U CN201520438515.XU CN201520438515U CN205113689U CN 205113689 U CN205113689 U CN 205113689U CN 201520438515 U CN201520438515 U CN 201520438515U CN 205113689 U CN205113689 U CN 205113689U
- Authority
- CN
- China
- Prior art keywords
- communication port
- aircraft
- foot rest
- hole
- joint pin
- Prior art date
- 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.)
- Active
Links
Landscapes
- Connection Of Plates (AREA)
Abstract
This has openly revead an aircraft, aircraft main part and foot rest, belongs to mechanical technical field. This aircraft includes: aircraft main part and foot rest, the week side of aircraft main part is provided with first connector, the top side of foot rest is provided with the second connector, aircraft main part and foot rest are twisted the screw through the hand that runs through first connector and second connector and are docked fixedly, under butt joint fixed status, formation has elastic column bearing structure between first connector and the second connector. This has openly been solved volume of aircraft foot rest and great and can not dismantle, leads to the inconvenient problem of carrying of aircraft, installation and the dismantlement that to accomplish the foot rest through the interface of setting on aircraft main part and foot rest have fast been reached to improve the portable effect of aircraft.
Description
Technical field
The disclosure relates to field of mechanical technique, particularly a kind of aircraft, aircraft body and foot rest.
Background technology
Aircraft as a kind of novel instrument of taking photo by plane, have higher can be handling, and manipulation is more convenient.
In order to avoid aircraft fall time, the direct kiss the earth of aircraft body causes intraware to damage, and the bottom of aircraft body is all provided with foot rest usually.But the volume due to aircraft foot rest is comparatively large and can not dismantle, aircraft is caused to be inconvenient to carry.
Utility model content
The disclosure provides a kind of aircraft, aircraft body and foot rest.Described technical scheme is as follows:
According to the first aspect of disclosure embodiment, provide a kind of aircraft, this aircraft comprises: aircraft body and foot rest;
All sides of aircraft body are provided with the first communication port;
The top side of foot rest is provided with the second communication port;
Aircraft body and foot rest carry out docking by the hand tighten screw running through the first communication port and the second communication port to be fixed;
Under docking stationary state, formed between the first communication port and the second communication port and there is elastomeric columnar stays structure.
In a kind of possible embodiment, the first communication port is provided with the n parallel with direction and has elastomeric joint pin, n is positive integer;
Second communication port is provided with the n parallel with an abutting direction accommodation hole, the diameter of joint pin is not more than the internal diameter of accommodation hole;
Under docking stationary state, one end of joint pin inserts in corresponding accommodation hole to be formed has elastomeric columnar stays structure.
In a kind of possible embodiment, the first communication port is provided with the n parallel with an abutting direction accommodation hole, n is positive integer;
Second communication port is provided with the n parallel with abutting direction and has elastomeric joint pin, the diameter of joint pin is not more than the internal diameter of accommodation hole;
Under docking stationary state, one end of joint pin inserts in corresponding accommodation hole to be formed has elastomeric columnar stays structure.
In a kind of possible embodiment, the boundary position of the second communication port is provided with m through hole, and the inwall of through hole is without screw thread, and m is positive integer;
The boundary position correspondence of the first communication port is provided with m tapped bore, and the screw thread of tapped bore mates with the screw thread of hand tighten screw;
Under docking stationary state, hand tighten screw runs through the through hole of the second communication port, and agrees with the tapped bore of the first communication port.
In a kind of possible embodiment, the boundary position of the first communication port is provided with m through hole, and the inwall of through hole is without screw thread, and m is positive integer;
The boundary position correspondence of the second communication port is provided with m tapped bore, and the screw thread of tapped bore mates with the screw thread of hand tighten screw;
Under docking stationary state, hand tighten screw runs through the through hole of the first communication port, and agrees with the tapped bore of the second communication port.
In a kind of possible embodiment, joint pin is quality of rubber materials.
According to the second aspect of disclosure embodiment, provide a kind of aircraft body, all sides of this aircraft body are provided with the first communication port;
First communication port is provided with n parallel with abutting direction there is elastomeric joint pin, n is positive integer; Or, the first communication port is provided with the n parallel with an abutting direction accommodation hole; Abutting direction is the direction towards foot rest when docking fixing with foot rest;
The boundary position of the first communication port is provided with the m parallel with an abutting direction through hole, and the inwall of through hole is without screw thread, and through hole is used for running through hand tighten screw, and m is positive integer; Or the boundary position of the first communication port is provided with the m parallel with an abutting direction tapped bore, and the screw thread of tapped bore mates with the screw thread of hand tighten screw.
In a kind of possible embodiment, joint pin is quality of rubber materials.
According to the third aspect of disclosure embodiment, provide a kind of foot rest, the top side of this foot rest is provided with the second communication port;
Second communication port is provided with the n parallel with abutting direction and has elastomeric joint pin, n is positive integer; Or, the first communication port is provided with the n parallel with an abutting direction accommodation hole; Abutting direction is the direction towards aircraft body when docking fixing with aircraft body;
The boundary position of the second communication port is provided with the m parallel with an abutting direction through hole, and the inwall of through hole is without screw thread, and through hole is used for running through hand tighten screw, and m is positive integer; Or the boundary position of the second communication port is provided with the m parallel with an abutting direction tapped bore, and the screw thread of tapped bore mates with the screw thread of hand tighten screw.
In a kind of possible embodiment, joint pin is quality of rubber materials.
The technical scheme that embodiment of the present disclosure provides can comprise following beneficial effect:
By arranging the first communication port in all sides of aircraft body, the top side of foot rest is provided with the second communication port, and it is fixing to use hand tighten screw the first communication port and the second communication port to be carried out docking; The volume solving aircraft foot rest is comparatively large and can not dismantle, and causes aircraft to be inconvenient to the problem of carrying; Reach the Assembly &Disassembly that can be completed foot rest by the interface be arranged on aircraft body and foot rest fast, thus improve the effect of aircraft portability.
Should be understood that, it is only exemplary that above general description and details hereinafter describe, and can not limit the disclosure.
Accompanying drawing explanation
Accompanying drawing to be herein merged in specification sheets and to form the part of this specification sheets, shows and meets embodiment of the present disclosure, and is used from specification sheets one and explains principle of the present disclosure.
Figure 1A (1), Figure 1A (2) and Figure 1A (3) are the schematic diagrams of the first communication port arrangement mode in the aircraft body according to an exemplary embodiment;
Figure 1B is the local structure schematic diagram that columnar stays structure is shown according to an exemplary embodiment;
Fig. 2 is the local structure schematic diagram of the first communication port according to an exemplary embodiment and the second communication port;
Fig. 3 is the local structure schematic diagram of the first communication port according to another exemplary embodiment and the second communication port;
Fig. 4 is the local structure schematic diagram of the first communication port Gen Ju an exemplary embodiment again and the second communication port;
Fig. 5 is the local structure schematic diagram of the first communication port according to another exemplary embodiment and the second communication port;
Fig. 6 is the sectional perspective schematic diagram of the first communication port according to an exemplary embodiment and the second communication port.
Detailed description of the invention
Here will be described exemplary embodiment in detail, its sample table shows in the accompanying drawings.When description below relates to accompanying drawing, unless otherwise indicated, the same numbers in different accompanying drawing represents same or analogous key element.Embodiment described in following exemplary embodiment does not represent all embodiments consistent with the disclosure.On the contrary, they only with as in appended claims describe in detail, example that aspects more of the present disclosure are consistent.
A kind of aircraft that the disclosure discloses, this aircraft comprises: aircraft body and foot rest.This aircraft can be single shaft aircraft or Multi-axis aircraft etc.
Wherein, all sides of aircraft body are provided with the first communication port, and this first communication port is arranged on the bottom week side of aircraft usually.The quantity of the first communication port of all sides of aircraft body is at least two, and at least two the first communication ports at the arrangement mode of all sides of aircraft body can be: with the center shaft of aircraft body for axis of symmetry does rotational symmetry distribution.
Such as, as shown in (1) in Figure 1A, all sides of aircraft body 11 can arrange 2 the first communication ports 12; As shown in (2) in Figure 1A, all sides of aircraft body 11 can arrange 3 the first communication ports 12; As shown in (3) in Figure 1A, all sides of aircraft body 11 can arrange 4 the first communication ports 12.Corresponding, the arrangement mode of the first communication port 12 can schematically as shown in Figure 1A (1), Figure 1A (2) and Figure 1A (3).The disclosure not to aircraft body week side the number of the first communication port and arrangement mode limit.
According to the quantity of the first communication port of all sides of aircraft body, be provided with the foot rest of respective numbers.The top side of this foot rest is provided with the second communication port, the shape of this second communication port and the form fit of the first communication port, and the second communication port and the first communication port can comprise following two kinds of possible abutting directions.
The first possible docking mode, abutting direction are horizontal direction, and namely the second communication port inserts the first communication port in the horizontal direction;
The possible docking mode of the second, abutting direction are vertical direction, and the second communication port vertically inserts the first communication port.
For convenience of description, in each embodiment following, be that vertical direction is described for example with abutting direction, the disclosure do not formed and limit.
When aircraft body and foot rest carry out docking fixing, hand tighten screw is used to run through the first communication port and the second communication port.It should be noted that, in this foot rest, can also buffer structure be provided with, the impulsive force produced during for absorbing foot rest and earth surface.This buffer structure can be spring buffer structure, hydraulic cushion structure, cylinder buffering structure etc., and the disclosure does not limit the buffer structure of foot rest.
As shown in Figure 1B, under docking stationary state, formed between the first communication port 12 and the second communication port 13 and there is elastomeric columnar stays structure.This columnar stays structure is made up of the accommodation hole 15 having elastomeric joint pin 14 and hold this joint pin 14, and this joint pin 14 is corresponding with accommodation hole 15 arranges, the shape of joint pin 14 and the form fit of accommodation hole 15.In addition, the shape of this joint pin 14 can be cylinder or cube etc., in following embodiment, only can be described for cylinder with the shape of this joint pin 14, does not form the disclosure and limits.
In sum, the aircraft that this exemplary embodiment provides, by arranging the first communication port in all sides of aircraft body, the top side of foot rest is provided with the second communication port, and it is fixing to use hand tighten screw the first communication port and the second communication port to be carried out docking; The volume solving aircraft foot rest is comparatively large and can not dismantle, and causes aircraft to be inconvenient to the problem of carrying; Reach the Assembly &Disassembly that can be completed foot rest by the interface be arranged on aircraft body and foot rest fast, thus improve the effect of aircraft portability.
Those skilled in the art are scrutable, and aircraft body also includes other for realizing the ordinary elements of aircraft, repeats no longer one by one in the present embodiment.
Those skilled in the art are scrutable, and foot rest also includes other for realizing the ordinary elements of foot rest, repeats no longer one by one in the present embodiment.
Formed between first communication port and the second communication port and there is elastomeric columnar stays structure, can be made up of the joint pin be arranged in first interface and the accommodation hole be arranged in the second interface, also can be made up of the joint pin be arranged in the second interface and the accommodation hole be arranged in first interface.Conveniently understand, adopt two exemplary embodiments to be described below.
Fig. 2 is the local structure schematic diagram of the first communication port according to an exemplary embodiment and the second communication port.The present embodiment has elastomeric joint pin this first interface to be provided with 2, and on the second interface, correspondence is provided with 2 accommodation holes is that example is described.
When the abutting direction of the first communication port and the second communication port is vertical direction, the first communication port in the vertical direction is provided with has elastomeric joint pin; When the abutting direction of the first communication port and the second communication port is horizontal direction, the first communication port is provided with in the horizontal direction has elastomeric joint pin.As shown in Figure 2, because the abutting direction of the first communication port 21 and the second communication port 22 is vertical direction, so the first communication port 21 in the vertical direction is provided with 2 have elastomeric joint pin 211, and 2 joint pins 211 are symmetric on the first communication port 21.The material that this joint pin 211 adopts can be elastomeric material, such as elastomeric material, and the diameter of this joint pin is comparatively large, thus makes first interface and the second interface reach better buffering effect.
It should be noted that, in order to ensure first interface 21 dock with the second interface 22 after stability, this joint pin 211 is usually symmetrical on the first communication port 21.
As shown in Figure 2, corresponding with the joint pin 211 on the first communication port 21, second communication port 22 is provided with 2 for holding the accommodation hole 221 of joint pin 211, the diameter of this joint pin 211 is not more than the diameter of accommodation hole 221, and 2 accommodation holes 221 are also symmetric on the second communication port 22.
In order to ensure under docking stationary state, one end of joint pin 211 inserts in corresponding accommodation hole 221 to be formed to be had elastomeric columnar stays structure thus absorbs the impulsive force produced when aircraft lands, as shown in Figure 2, the length of joint pin 211 need slightly larger than the hole depth of accommodation hole 221, when making joint pin 211 insert accommodation hole 221, between the first communication port 21 and the second communication port 22, there is gap.When aircraft lands generation impulsive force, by joint pin 211 and accommodation hole 221, this impulsive force is absorbed, thus play the effect of buffering, effectively can reduce the impact of impulsive force on aircraft body intraware.
In order to ensure the reliability that aircraft body is connected with foot rest, prevent in flight course, joint pin 211 and accommodation hole 221 depart from and cause foot rest to drop, the boundary position of the second communication port 22 is provided with 2 through holes 222, corresponding, the boundary position correspondence of the first communication port 21 is provided with 2 tapped bore 212, and user uses hand tighten screw 23 to run through this through hole 222, and rotate hand tighten screw 23 itself and tapped bore 212 are agreed with, realize the fixing of the first communication port 21 and the second communication port 22.
Wherein, the diameter of this through hole 222 is not less than the diameter in hand tighten screw 23 bar portion and is not more than the diameter of hand tighten screw 23 head, and the screw thread of tapped bore 212 mates with the screw thread of hand tighten screw 23.
After use hand tighten screw 23 is fixed, because hand tighten screw 23 only agrees with tapped bore 212, do not agree with through hole 222, so the impulsive force produced when aircraft falls can not act on hand tighten screw 23 and tapped bore 212 agree with place, thus ensure that the stability that hand tighten screw 23 and tapped bore 212 agree with.
When user installs foot rest in aircraft body, only need the accommodation hole inserted successively by the joint pin of aircraft body all sides first communication port in the communication port of foot rest top second, and use hand tighten screw to run through the through hole of the second communication port boundary position, and rotate this hand tighten screw the tapped bore on itself and the first communication port is agreed with, can installation be completed; And when dismantling foot rest, only needing to rotate hand tighten screw makes it be separated with tapped bore, then be separated with accommodation hole joint pin, whole Assembly &Disassembly process does not need to use extra special tool, and simple and quick.
In sum, the aircraft that this exemplary embodiment provides, by arranging the first communication port in all sides of aircraft body, the top side of foot rest is provided with the second communication port, and it is fixing to use hand tighten screw the first communication port and the second communication port to be carried out docking; The volume solving aircraft foot rest is comparatively large and can not dismantle, and causes aircraft to be inconvenient to the problem of carrying; Reach the Assembly &Disassembly that can be completed foot rest by the interface be arranged on aircraft body and foot rest fast, thus improve the effect of aircraft portability.
As a kind of possible implementation, as shown in Figure 3, the through hole 312 that hand tighten screw 33 runs through can be arranged on the edge of the first communication port 31, and accordingly, tapped bore 322 can be arranged on the boundary position of the second communication port 32 correspondence.
Wherein, the boundary position of the first communication port 31 is provided with 2 through holes 312, and the inwall of through hole 312 is without screw thread;
The boundary position correspondence of the second communication port 32 is provided with 2 tapped bore 322, and the screw thread of tapped bore 322 mates with the screw thread of hand tighten screw 33;
Under docking stationary state, hand tighten screw 33 runs through the through hole 312 of the first connection 31 mouthfuls, and agrees with the tapped bore 322 of the second communication port 32.
Fig. 4 is the local structure schematic diagram of the first communication port Gen Ju an exemplary embodiment again and the second communication port.The present embodiment is this first interface to be provided with 2 accommodation holes, and on the second interface, correspondence is provided with 2 to have elastomeric joint pin be that example is described.
When the abutting direction of the first communication port and the second communication port is vertical direction, the first communication port in the vertical direction is provided with accommodation hole; When the abutting direction of the first communication port and the second communication port is horizontal direction, the first communication port is provided with accommodation hole in the horizontal direction.As shown in Figure 4, because the abutting direction of the first communication port 41 and the second communication port 42 is vertical direction, so the first communication port 41 in the vertical direction is provided with 2 accommodation holes 411.It should be noted that, in order to ensure first interface 41 dock with the second interface 42 after stability, this accommodation hole 411 is usually symmetrical on the first communication port 41.
Corresponding, as shown in Figure 4, corresponding with the accommodation hole 411 on the first communication port 41, the second communication port 42 is provided with 2 joint pins 421, and 2 joint pins 421 are also symmetric on the second communication port 42.
The material that joint pin 421 adopts can be elastomeric material, such as elastomeric material, and the diameter of this joint pin 421 is comparatively large, thus makes first interface 41 and the second interface 42 place reach better buffering effect.It should be noted that, the diameter of this joint pin 421 is not more than the internal diameter of accommodation hole 411.
In order to ensure under docking stationary state, one end of joint pin 421 inserts in corresponding accommodation hole 411 to be formed to be had elastomeric columnar stays structure thus absorbs the impulsive force produced when aircraft lands, as shown in Figure 4, the length of joint pin 421 need slightly larger than the hole depth of accommodation hole 411, when making joint pin 421 insert accommodation hole 411, between the first communication port 41 and the second communication port 42, there is gap.When aircraft lands generation impulsive force, by joint pin 421 and accommodation hole 411, this impulsive force is absorbed, thus play the effect of buffering, effectively can reduce the impact of impulsive force on aircraft body intraware.
In order to ensure the reliability that aircraft body is connected with foot rest, prevent in flight course, joint pin 421 and accommodation hole 411 depart from and cause foot rest to drop, the boundary position of the second communication port 42 is provided with 2 through holes 422, corresponding, the boundary position correspondence of the first communication port 41 is provided with 2 tapped bore 412, and user uses hand tighten screw 43 to run through this through hole 422, and rotate hand tighten screw 43 itself and tapped bore 412 are agreed with, realize the fixing of the first communication port 41 and the second communication port 42.
Wherein, the diameter of this through hole 422 is not less than the diameter in hand tighten screw 43 bar portion and is not more than the diameter of hand tighten screw 43 head, and the screw thread of tapped bore 412 mates with the screw thread of hand tighten screw 43.
After use hand tighten screw 43 is fixed, because hand tighten screw 43 only agrees with tapped bore 412, do not agree with through hole 422, so the impulsive force produced when aircraft falls can not act on hand tighten screw 43 and tapped bore 412 agree with place, thus ensure that the stability that hand tighten screw 43 and tapped bore 412 agree with.
When user installs foot rest in aircraft body, only need the accommodation hole inserted successively by the joint pin of aircraft body all sides second communication port in the communication port of foot rest top first, and use hand tighten screw to run through the through hole of the second communication port boundary position, and rotate this hand tighten screw the tapped bore on itself and the first communication port is agreed with, can installation be completed; And when dismantling foot rest, only needing to rotate hand tighten screw makes it be separated with tapped bore, then be separated with accommodation hole joint pin, whole Assembly &Disassembly process does not need to use extra special tool, and simple and quick.
In sum, the aircraft that this exemplary embodiment provides, by arranging the first communication port in all sides of aircraft body, the top side of foot rest is provided with the second communication port, and it is fixing to use hand tighten screw the first communication port and the second communication port to be carried out docking; The volume solving aircraft foot rest is comparatively large and can not dismantle, and causes aircraft to be inconvenient to the problem of carrying; Reach the Assembly &Disassembly that can be completed foot rest by the interface be arranged on aircraft body and foot rest fast, thus improve the effect of aircraft portability.
As a kind of possible implementation, as shown in Figure 5, the through hole 512 that hand tighten screw 53 runs through can be arranged on the edge of the first communication port 51, and accordingly, tapped bore 522 can be arranged on the boundary position of the second communication port 52 correspondence.
Wherein, the boundary position of the first communication port 51 is provided with 2 through holes 512, and the inwall of through hole 512 is without screw thread;
The boundary position correspondence of the second communication port 52 is provided with 2 tapped bore 522, and the screw thread of tapped bore 522 mates with the screw thread of hand tighten screw 53;
Under docking stationary state, hand tighten screw 53 runs through the through hole 512 of the first connection 51 mouthfuls, and agrees with the tapped bore 522 of the second communication port 52.
Fig. 6 is the sectional perspective schematic diagram of the first communication port according to an exemplary embodiment and the second communication port.
First communication port 61 is positioned at all sides of aircraft body, and the second communication port 62 is positioned at the top of foot rest.
Be symmetrically arranged with two in first communication port 61 and there is elastomeric joint pin 611; Two tapped bore 612 are symmetrically arranged with, for agreeing with hand tighten screw 63 at the boundary position of the first communication port 61.
Corresponding with the first communication port 61, be symmetrically arranged with two accommodation holes 621 in the second communication port 62, for holding joint pin 611; Two through holes 622 are symmetrically arranged with at the boundary position of the second communication port 62.
When foot rest is installed to aircraft body by user, first the second communication port 62 is inserted the inside of the first communication port 61, now, joint pin 611 inserts corresponding accommodation hole 621 respectively; Again hand tighten screw 63 is passed through hole 622, and rotate this hand tighten screw 63, itself and tapped bore 612 are agreed with, the first communication port 61 can be completed and fix with the second docking of communication port 62.
When user removes foot rest from aircraft body, rotate hand tighten screw 63 and make it be separated with tapped bore 612, then the second communication port 62 to be extracted from the first communication port 61 inside, being separated of the first communication port 61 and the second communication port 62 can be completed.
Apparent, whole Assembly &Disassembly process does not need to use extra special tool, and simple and quick.
In sum, the aircraft that this exemplary embodiment provides, by arranging the first communication port in all sides of aircraft body, the top side of foot rest is provided with the second communication port, and it is fixing to use hand tighten screw the first communication port and the second communication port to be carried out docking; The volume solving aircraft foot rest is comparatively large and can not dismantle, and causes aircraft to be inconvenient to the problem of carrying; Reach the Assembly &Disassembly that can be completed foot rest by the interface be arranged on aircraft body and foot rest fast, thus improve the effect of aircraft portability.
Those skilled in the art, at consideration specification sheets and after putting into practice invention disclosed herein, will easily expect other embodiment of the present disclosure.The application is intended to contain any modification of the present disclosure, purposes or adaptations, and these modification, purposes or adaptations are followed general principle of the present disclosure and comprised the undocumented common practise in the art of the disclosure or conventional techniques means.Specification sheets and embodiment are only regarded as exemplary, and true scope of the present disclosure and spirit are pointed out by claim below.
Should be understood that, the disclosure is not limited to precision architecture described above and illustrated in the accompanying drawings, and can carry out various amendment and change not departing from its scope.The scope of the present disclosure is only limited by appended claim.
Claims (10)
1. an aircraft, is characterized in that, described aircraft comprises: aircraft body and foot rest;
All sides of described aircraft body are provided with the first communication port;
The top side of described foot rest is provided with the second communication port;
Described aircraft body and described foot rest carry out docking by the hand tighten screw running through described first communication port and described second communication port to be fixed;
Under docking stationary state, formed between described first communication port and described second communication port and there is elastomeric columnar stays structure.
2. aircraft according to claim 1, is characterized in that,
Described first communication port is provided with the n parallel with abutting direction and has elastomeric joint pin, n is positive integer;
Described second communication port is provided with the n parallel with a described abutting direction accommodation hole, the diameter of described joint pin is not more than the internal diameter of described accommodation hole;
Under described docking stationary state, one end of described joint pin is inserted in corresponding described accommodation hole has elastomeric columnar stays structure described in formation.
3. aircraft according to claim 1, is characterized in that,
Described first communication port is provided with the n parallel with an abutting direction accommodation hole, n is positive integer;
Described second communication port is provided with the n parallel with described abutting direction and has elastomeric joint pin, the diameter of described joint pin is not more than the internal diameter of described accommodation hole;
Under described docking stationary state, one end of described joint pin is inserted in corresponding described accommodation hole has elastomeric columnar stays structure described in formation.
4., according to the arbitrary described aircraft of claims 1 to 3, it is characterized in that,
The boundary position of described second communication port is provided with m through hole, and the inwall of described through hole is without screw thread, and m is positive integer;
The boundary position correspondence of described first communication port is provided with m tapped bore, and the screw thread of described tapped bore mates with the screw thread of described hand tighten screw;
Under described docking stationary state, described hand tighten screw runs through the described through hole of described second communication port, and agrees with the described tapped bore of described first communication port.
5., according to the arbitrary described aircraft of claims 1 to 3, it is characterized in that,
The boundary position of described first communication port is provided with m through hole, and the inwall of described through hole is without screw thread, and m is positive integer;
The boundary position correspondence of described second communication port is provided with m tapped bore, and the screw thread of described tapped bore mates with the screw thread of described hand tighten screw;
Under described docking stationary state, described hand tighten screw runs through the described through hole of described first communication port, and agrees with the described tapped bore of described second communication port.
6. the aircraft according to Claims 2 or 3, is characterized in that, described joint pin is quality of rubber materials.
7. an aircraft body, is characterized in that, all sides of described aircraft body are provided with the first communication port;
Described first communication port is provided with n parallel with abutting direction there is elastomeric joint pin, n is positive integer; Or, described first communication port is provided with the n parallel with a described abutting direction accommodation hole; Described abutting direction is the direction towards described foot rest when docking fixing with foot rest;
The boundary position of described first communication port is provided with the m parallel with a described abutting direction through hole, and the inwall of described through hole is without screw thread, and described through hole is used for running through hand tighten screw, and m is positive integer; Or the boundary position of described first communication port is provided with the m parallel with a described abutting direction tapped bore, and the screw thread of described tapped bore mates with the screw thread of described hand tighten screw.
8. aircraft body according to claim 7, is characterized in that, described joint pin is quality of rubber materials.
9. a foot rest, is characterized in that, the top side of described foot rest is provided with the second communication port;
Described second communication port is provided with the n parallel with abutting direction and has elastomeric joint pin, n is positive integer; Or, described first communication port is provided with the n parallel with a described abutting direction accommodation hole; Described abutting direction is the direction towards described aircraft body when docking fixing with aircraft body;
The boundary position of described second communication port is provided with the m parallel with a described abutting direction through hole, and the inwall of described through hole is without screw thread, and described through hole is used for running through hand tighten screw, and m is positive integer; Or the boundary position of described second communication port is provided with the m parallel with a described abutting direction tapped bore, and the screw thread of described tapped bore mates with the screw thread of described hand tighten screw.
10. foot rest according to claim 9, is characterized in that, described joint pin is quality of rubber materials.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520438515.XU CN205113689U (en) | 2015-06-24 | 2015-06-24 | Aircraft, aircraft main part and foot rest |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520438515.XU CN205113689U (en) | 2015-06-24 | 2015-06-24 | Aircraft, aircraft main part and foot rest |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205113689U true CN205113689U (en) | 2016-03-30 |
Family
ID=55569322
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520438515.XU Active CN205113689U (en) | 2015-06-24 | 2015-06-24 | Aircraft, aircraft main part and foot rest |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205113689U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105083545A (en) * | 2015-06-24 | 2015-11-25 | 广州飞米电子科技有限公司 | Aircraft, aircraft body and foot stand |
-
2015
- 2015-06-24 CN CN201520438515.XU patent/CN205113689U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105083545A (en) * | 2015-06-24 | 2015-11-25 | 广州飞米电子科技有限公司 | Aircraft, aircraft body and foot stand |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN205113689U (en) | Aircraft, aircraft main part and foot rest | |
| CN103603858B (en) | A kind of miniature docking separating mechanism | |
| CN103802169A (en) | Wood drilling machine material platform with conveniently-adjustable inclination | |
| CN104375360A (en) | High-stable and semi-flexible supporting structure for secondary lens of space camera | |
| CN102305679B (en) | Positioning carrier for notebook computer keycap testing machine | |
| CN105083545A (en) | Aircraft, aircraft body and foot stand | |
| CN211033023U (en) | Damping device for wings of unmanned aerial vehicle | |
| CN204248011U (en) | Three direction rigs | |
| CN206740347U (en) | A kind of fixture of PCB backboards vibration test | |
| CN202162573U (en) | Floating support device | |
| CN102076173B (en) | Clamp for printed circuit board | |
| CN205036683U (en) | Cabinet board connection structure of assembled cabinet is taken to swift dress | |
| CN205798524U (en) | Stabiliser bar drill jig | |
| CN103323193A (en) | Assembly type horizontal sliding table | |
| CN103323194B (en) | A kind of assembled horizontal sliding table | |
| CN205166768U (en) | Mechanical model demonstration teaching fixing device | |
| CN216097595U (en) | Shaft machining quick-change clamp for horizontal machining center | |
| CN203864252U (en) | Teaching presentation board | |
| CN211399179U (en) | Fixing device of six-degree-of-freedom platform hydraulic telescopic device | |
| CN204481522U (en) | Charger and have this charger charging combination | |
| CN205516507U (en) | Children learn building blocks | |
| CN109621454A (en) | A kind of multifunctional building block pedestal | |
| CN203310595U (en) | Assembly-type horizontal slide platform | |
| CN204576962U (en) | Drill bit demonstration teaching aid | |
| CN204143698U (en) | A kind of square demonstration teaching aid |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: Aircraft, aircraft body and foot stand Effective date of registration: 20180305 Granted publication date: 20160330 Pledgee: Silicon Valley Bank Co., Ltd. Pledgor: GUANGZHOU FEIMI ELECTRONIC TECHNOLOGY CO., LTD. Registration number: 2018310000008 |