CN104960662A - Landing gear and unmanned aerial vehicle using the same - Google Patents
Landing gear and unmanned aerial vehicle using the same Download PDFInfo
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- CN104960662A CN104960662A CN201510291606.XA CN201510291606A CN104960662A CN 104960662 A CN104960662 A CN 104960662A CN 201510291606 A CN201510291606 A CN 201510291606A CN 104960662 A CN104960662 A CN 104960662A
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- buffer part
- attaching parts
- damper element
- joint
- alighting gear
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Abstract
The invention discloses a landing gear applied to an unmanned aerial vehicle. The landing gear comprises supporting legs which comprise connecting pieces. The connecting pieces comprise mounting ends used for fixing the landing gear on the unmanned aerial vehicle. The supporting legs further comprise buffering pieces arranged on the connecting pieces. The buffering pieces comprise buffering parts on which buffering areas are arranged, wherein through the buffering areas, the buffering parts are enabled to generate elastic deformations relative to the connecting pieces under external force. The invention further provides the unmanned aerial vehicle using the landing gear. The landing gear for the unmanned aerial vehicle has a good buffering effect while the unmanned aerial vehicle is landing.
Description
Technical field
The present invention relates to a kind of alighting gear and use the unmanned vehicle of this alighting gear.
Background technology
Unmanned vehicle generally comprises fuselage and is installed in the alighting gear on described fuselage, and described alighting gear comprises at least two feets.For alleviating the weight of described unmanned vehicle entirety, and ensure the stability of described unmanned vehicle when flying, described feet is generally multiple strut bar be made up of carbon fiber and is mutually rigidly connected and forms, described strut bar is connected on described fuselage, as support during described unmanned vehicle landing.But the rigidity of described feet is comparatively large, when described unmanned vehicle landing, its buffer action is limited.If described unmanned vehicle needs to land on the comparatively complicated ground of landform, or when dropping to ground from low latitude, described feet is difficult to deformation buffering occurs, and making the vibrations when landing of described unmanned vehicle comparatively large, even dropping and causing damage.
Summary of the invention
In view of above content, be necessary the alighting gear that a kind of good buffer effect is provided, and use the unmanned vehicle of this alighting gear.
A kind of alighting gear, is applied in unmanned vehicle.Described alighting gear comprises feet, and described feet comprises attaching parts.Described attaching parts comprises the installation end for being fixed on by described alighting gear on described unmanned vehicle.Described feet also comprises the damper element be arranged on described attaching parts.Described damper element comprises buffer part, and described buffer part is provided with buffer zone, and described buffer zone makes described buffer part produce elastic deformation relative to described attaching parts under external force.
Further, described buffer zone is the buffering cavity structure be arranged in described buffer part;
Or described setting buffers, in described buffer part, described buffer zone offers multiple hole;
Or described setting buffers is in described buffer part, and the hardness of described buffer zone is less than the hardness of described joint and described buffer part.
Further, described damper element also comprises being arranged at described buffer part plugs portion, described in the portion of plugging be inserted in the end of described attaching parts.
Further, described damper element also comprises holding parts, and described holding parts plugs outside portion described in being arranged at, and is connected in described buffer part.
Further, described holding parts and described plugging between portion are provided with gap, described in the portion of plugging when being inserted in the end of described attaching parts, the end of described attaching parts is contained in described gap.
Further, described damper element also comprises the carrier be arranged in described buffer part, and described feet also comprises strut member, and described strut member is inserted on described carrier.
Further, described buffer zone is the dashpot running through the setting of described buffer part, and described buffer zone enables described buffer part change relative to the position of described attaching parts under external force;
Or described buffer zone offers multiple through hole, and described buffer zone enables described buffer part change relative to the position of described attaching parts under external force;
Or the hardness of described buffer zone is less than the hardness of described joint and described buffer part, described buffer zone enables described buffer part change relative to the position of described attaching parts under external force.
Further, described damper element also comprises the joint be connected on described attaching parts, and described buffer part is connected on described joint, and described setting buffers is between described joint and described buffer part.
Further, described joint is two pass joints, and described feet also comprises strut member, and described attaching parts is connected to one end of described joint, described strut member is arranged at the other end of described joint, and described buffer part is arranged at the side away from described strut member on described joint.
Further, described joint comprises the first connecting portion and is arranged at second connecting portion of described first connecting portion one end, the end of described attaching parts is inserted in described first connecting portion, described strut member is arranged at one end of described second connecting portion, and described buffer part is arranged at the other end of described second connecting portion.
Further, described buffer part is provided with groove, described groove extends and the through other end to described buffer part from described buffer part near one end of described second connecting portion.
Further, described buffer part also offers through hole, described through hole is communicated with described groove, and described through hole provides deformation space for the elastic deformation of described buffer part.
Further, the quantity of described attaching parts is identical with the quantity of described damper element, and the described joint of each described damper element is arranged on each described attaching parts; The two ends of described strut member are connected with the described joint in two described damper elements respectively.
Further, the quantity of described feet is two, support when two described feets are for being arranged on symmetrically on described unmanned vehicle and land as described unmanned vehicle.
Further, described damper element is the hollow structure with cavity, is filled with rubber in the cavity of described damper element.
A kind of unmanned vehicle, it comprises fuselage and the alighting gear as above described in any one, and described attaching parts is arranged on described fuselage, and described damper element is arranged at described attaching parts one end away from described fuselage.
Further, described unmanned vehicle also comprises the horn be arranged on described fuselage and the engine installation be arranged on described horn, and described engine installation is with thinking that described unmanned vehicle provides flying power.
Further, described horn is multiple, and arranges around described fuselage.
Further, described horn comprises a principal arm and is arranged at two support arms on described principal arm, one end of described principal arm is arranged on described fuselage, and two described support arms are all connected to described principal arm one end away from described fuselage, and described engine installation is arranged on described support arm.
Further, described fuselage is provided with the automatically controlled module for controlling described engine installation.
Unmanned vehicle of the present invention, the described setting buffers of its alighting gear is between described joint and described buffer part, elastic deformation for described damper element provides space and the distortion allowance of distortion, make described buffer part and described joint under the effect of external force, therebetween can there is the change of temporary transient relative position and not damage the integral structure of described damper element, improve the buffering effect of described alighting gear.
Accompanying drawing explanation
The lateral plan of the unmanned vehicle that Fig. 1 provides for first embodiment of the invention.
Fig. 2 is the upward view of unmanned vehicle shown in Fig. 1.
Fig. 3 is the lateral plan of the damper element of the alighting gear of unmanned vehicle shown in Fig. 1.
Fig. 4 is the birds-eye view of the damper element of the alighting gear of unmanned vehicle shown in Fig. 3.
The schematic diagram of the feet of the unmanned vehicle that Fig. 5 provides for second embodiment of the invention.
Fig. 6 is the lateral plan of the damper element of the feet of unmanned vehicle shown in Fig. 5.
Fig. 7 is the generalized section of the damper element of the feet of unmanned vehicle shown in Fig. 6.
The lateral plan at another visual angle of damper element that Fig. 8 is the feet of unmanned vehicle shown in Fig. 6.
Main element nomenclature
| Unmanned vehicle | 100 |
| Fuselage | 20 |
| Horn | 40 |
| Principal arm | 42 |
| Support arm | 44 |
| Engine installation | 60 |
| Actuator | 62 |
| Screw propeller | 64 |
| Alighting gear | 80 |
| Feet | 82，92 |
| Attaching parts | 83，93 |
| Installation end | 831 |
| Damper element | 85，95 |
| Joint | 851 |
| First connecting portion | 8511 |
| Second connecting portion | 8513 |
| Buffer part | 853，9511 |
| Groove | 8531 |
| Through hole | 8533 |
| Buffer zone | 855，952 |
| Strut member | 87，97 |
| Plug Division | 951 |
| Holding parts | 9513 |
| Plug portion | 9515 |
| Gap | 9517 |
| Transition region | 953 |
| Carrier | 955 |
Following detailed description of the invention will further illustrate the present invention in conjunction with above-mentioned accompanying drawing.
Detailed description of the invention
Below in conjunction with the accompanying drawing in the embodiment of the present invention, be clearly and completely described the technical scheme in the embodiment of the present invention, obviously, described embodiment is only the present invention's part embodiment, instead of whole embodiments.Based on the embodiment in the present invention, those of ordinary skill in the art, not making the every other embodiment obtained under creative work prerequisite, belong to the scope of protection of the invention.
It should be noted that, when assembly is called as " being fixed on " another assembly, directly can there is assembly placed in the middle in it on another assembly or also.When an assembly is considered to " connection " another assembly, it can be directly connected to another assembly or may there is assembly placed in the middle simultaneously.When an assembly is considered to " being arranged at " another assembly, it can be set directly on another assembly or may there is assembly placed in the middle simultaneously.Term as used herein " vertical ", " level ", "left", "right" and similar statement are just for illustrative purposes.
Unless otherwise defined, all technology used herein and scientific terminology are identical with belonging to the implication that those skilled in the art of the present invention understand usually.The object of term used in the description of the invention herein just in order to describe specific embodiment, is not intended to be restriction the present invention.Term as used herein " and/or " comprise arbitrary and all combinations of one or more relevant Listed Items.
Below in conjunction with accompanying drawing, some embodiments of the present invention are elaborated.When not conflicting, the feature in following embodiment and embodiment can combine mutually.
Please refer to Fig. 1 and Fig. 2, first embodiment of the invention provides a kind of unmanned vehicle 100, described unmanned vehicle 100 comprises fuselage 20, the horn 40 be arranged on described fuselage 20, the engine installation 60 be arranged on described horn 40, and is arranged at the alighting gear 80 on described fuselage 20.Described engine installation 60 flies for driving described unmanned vehicle 100, is also provided with the automatically controlled module for controlling described engine installation 60 in described fuselage 20.Described alighting gear 80 is arranged at bottom described fuselage 20, buffering when landing as described unmanned vehicle 100 and support.
In the present embodiment, the quantity of described horn 40 is four, and four described horns 40 are arranged around described fuselage 20, and extends towards the direction deviating from described fuselage 20.Each described horn 40 is all roughly shaft-like in " Y " shape, and includes a principal arm 42 and be connected to two support arms 44 on described principal arm 42.
The described principal arm 42 of four described horns 40 is evenly distributed in the surrounding of described fuselage 20, and extends towards the direction deviating from described fuselage 20.Each described support arm 44 is arranged at the one end away from described fuselage 20 on corresponding principal arm 42, two described support arms 44 of each described horn 40 are mutually certain angle and arrange, and extend towards the direction deviating from described principal arm 42, make each described horn 40 all roughly in " Y " shape.
In the present embodiment, the quantity of described engine installation 60 is eight, and each described engine installation 60 is arranged at the end of a described support arm 44.Described engine installation 60 comprises the actuator 62 be arranged on described support arm 44 and the screw propeller 64 be arranged on described actuator 62, described actuator 62 can drive described screw propeller 64 to rotate under the driving of described automatically controlled module, thus drives described unmanned vehicle 100 to fly.Described actuator 62 can be the rotary drive such as brush motor, brushless motor, rotates to drive described screw propeller 64.
In embodiments of the present invention, the quantity of described horn 40 is individual arbitrarily.Such as: two, three, five, six, seven, eight etc., can assemble according to designer's demand.
Described alighting gear 80 is arranged on described fuselage 20, and is positioned at described fuselage 20 relatively away from the side of described engine installation 60.In the present embodiment, described alighting gear 80 comprises two feets 82.Two feets 82 are arranged substantially symmetrically in the bottom of fuselage 20, and mutually in "eight" shape when described two feets 82 launch.The strut member 87 that each feet 82 includes the attaching parts 83 be connected on described fuselage 20, is connected to the damper element 85 on described attaching parts 83 and is arranged on described damper element 85.
In the present embodiment, described in each described feet 82, the quantity of attaching parts 83 is two.Two described attaching partss 83 all roughly in shaft-like, and are arranged on described fuselage 20 roughly in parallel to each other, and relatively described fuselage 20 tilts.Each described attaching parts 83 is provided with installation end 831, and described installation end 831 is fixed on described fuselage 20, and it is for being installed in described fuselage 20 by described alighting gear 80.
In the present embodiment, described in each described feet 82, the quantity of damper element 85 is two.Each described damper element 85 is arranged on the one end away from described fuselage 20 on a described attaching parts 83.
Please refer to Fig. 3 and Fig. 4, described damper element 85 comprises joint 851 and is arranged at the buffer part 853 on described joint 851, is provided with buffer zone 855 between described joint 851 and described buffer part 853.
In the present embodiment, described joint 851 is roughly two and connects head, and it comprises the first connecting portion 8511 and the second connecting portion 8513, and the axis of described first connecting portion 8511 and the axis of described second connecting portion 8513 are roughly mutually vertical.Described first connecting portion 8511 is sheathed on the end of corresponding described attaching parts 83.Described second connecting portion 8513 is formed at the end of described first connecting portion 8511, and its axis is roughly parallel to described fuselage 20.Described second connecting portion 8513 is for installing described strut member 87.
Described buffer part 853 is roughly the rectangular shaft-like of hollow, and it is arranged at one end of described second connecting portion 8513, and extends along the axis of described second connecting portion 8513 towards the direction deviating from described first connecting portion 8511.Described buffer zone 855 is arranged between described buffer part 853 and described second connecting portion 8513, and is positioned at the side of described second connecting portion 8513 near described first connecting portion 8511.In the present embodiment, described buffer zone 855 is for running through the dashpot of the side setting of described second connecting portion 8513.
Described buffer part 853 offers groove 8531 towards the side of described fuselage 20, described groove 8531 is roughly strip shape groove, its sidewall running through described buffer part 853 is offered, and extends and the through other end to described buffer part 853 from described buffer part 853 near one end of described second connecting portion 8513.While described groove 8531 and described buffer zone 855 make the overall weight of described damper element 85 alleviate, described buffer part 853 is made to have certain toughness and elasticity, when described buffer part 853 is when being subject to external impacts, can there is elastic deformation in it, thus cushion the impact that described external force causes described unmanned vehicle 100 entirety.
The side that described buffer part 853 deviates from described groove 8531 offers through hole 8533, and described through hole 8533 runs through the sidewall of described buffer part 853, and is communicated with described groove 8531.While described through hole 8533 makes the overall weight of described damper element 85 alleviate, the rigidity making described damper element 85 is relatively strong, and provides deformation space for the elastic deformation of described damper element 85.Simultaneously, described through hole 8533 makes described damper element 85 increase with the roughness of the side of earth surface, improve the adaptive capacity on the ground of described alighting gear 80 pairs of different terrain, even if described unmanned vehicle 100 lands on comparatively complicated coarse ground, described alighting gear 80 also can adaptation to the ground, makes described unmanned vehicle 100 can stable landing.
In the present embodiment, described damper element 85 entirety is the buffer body be made up of nylon plastic material, described damper element 85 is made to have relatively large elasticity and plasticity, described unmanned vehicle 100 is landed on the comparatively complicated ground of landform, or when dropping to bottom surface from low latitude, elastic deformation can be there is with the impact of attenuate ground in described damper element 85, avoid the situation that described alighting gear 80 fractures because of excessive impulsive force, thus the infringement that reduction drop impact causes described unmanned vehicle 100 entirety.
Further, described damper element 85 is for having the hollow structure of cavity, and its central cavity position can filled rubber, to improve toughness and the plasticity of described damper element 85 further.
Please again consult Fig. 1 and Fig. 2, two described damper elements 85 are separately positioned on two described attaching partss 83, and two described buffer part 853 deviate from setting mutually.Described strut member 87 is arranged between two described damper elements 85, and the two ends of described strut member 87 are plugged in two damper elements 85 respectively.
Described strut member 87 is roughly in shaft-like, and it is for strengthening the bulk strength of described feet 82.In the present embodiment, described strut member 87 and the strut bar of described attaching parts 83 all for being made up of carbon fiber, while making described alighting gear 80 entirety have larger rigidity, have certain elasticity and lighter in weight.
Unmanned vehicle 100 of the present invention, its alighting gear 80 have employed the described strut member 87 be made up of carbon fiber and described attaching parts 83 builds keystone configuration, and the described damper element 85 adopting nylon plastic cement to make connects described strut member 87 and described attaching parts 83, while making described alighting gear 80 entirety have larger rigidity, there is certain elasticity and lighter in weight.Described unmanned vehicle 100 drops on the comparatively complicated ground of landform and lands, or when dropping to bottom surface from low latitude, elastic deformation can be there is with the impact of attenuate ground in described damper element 85, avoid the situation that described alighting gear 80 fractures because of excessive impulsive force, thus the infringement that reduction drop impact causes described unmanned vehicle 100 entirety.
Further, described buffer zone 855 is arranged between described joint 851 and described buffer part 853, elastic deformation for described damper element 85 provides space and the distortion allowance of distortion, make described buffer part 853 and described joint 851 under the effect of external force, therebetween can there is the change of temporary transient relative position and not damage the integral structure of described damper element 85, improve the buffering effect of described alighting gear 80.
In addition, the joint 851 of described damper element 85 is two pass joint structures, and it can be installed in rapidly on described attaching parts 83 and to connect described strut member 87, makes described alighting gear 80 disassembling, assembling and replacing more convenient.
Be appreciated that the quantity of described horn 40 can be one or more, such as, two, three, six etc.Similarly, the quantity of described engine installation 60 also can be one or more.
Be appreciated that the quantity of support arm 44 in each described horn 40 can for one or more.Even, described support arm 44 can omit, and is directly installed on described principal arm 42 by described engine installation 60.
Be appreciated that the structure of described groove 8531 is not limited to strip shape groove as described above, it can be the groove of other shapes.Such as, described groove 8531 can for being opened in the multiple grooves in described buffer part 853, and described multiple groove makes described buffer part 853 in engraved structure, thinks that the elastic deformation of described damper element 85 provides deformation space.Similarly, the structure of described through hole 8533 can be not limited to structure as described above, and it for being opened in the multiple grooves in described buffer part 853, can also think that the elastic deformation of described damper element 85 provides deformation space.
Be appreciated that the structure of described joint 851 is not limited to two pass joint structures as described above, it can also be the joint of other structures.Such as, when the quantity of the strut member 87 of described alighting gear 80 be three or four time, described joint 851 can be T-pipe joint, and an interface of described T-pipe joint is for connecting described attaching parts 83, and all the other two interfaces are for connecting described strut member 87.Or when the connection between described damper element 85 and described attaching parts 83 and described strut member 87 does not connect for pipe, the joint 851 of described damper element 85 can be other connection structures.Such as, can be connected together by threaded fastenerss such as screws between described damper element 85 and described attaching parts 83 and described strut member 87, now described damper element 85 is without the need to being designed to two pass joint structures.
Be appreciated that described buffer zone 855 can be not limited to dashpot structure as described above, it can be other buffer structure.Such as, described buffer zone 855 is for offering the buffer zone of multiple through hole, or the buffer zone etc. that the flexible material being less than described joint 851 and described buffer part 853 for other hardness is made as rubber, foam etc., make described buffer part 853 and described joint 851 under the effect of external force, therebetween can there is the change of temporary transient relative position and not damage the integral structure of described damper element 85, that is, described buffer zone 855 is space and the distortion allowance that the elastic deformation of described damper element 85 provides distortion.
It is the schematic diagram of the feet 92 of the unmanned vehicle (not shown) of second embodiment of the invention please refer to Fig. 5, Fig. 5.The structure of the unmanned vehicle of described second embodiment is roughly the same with the structure of the unmanned vehicle 100 of the first embodiment, the structure of the feet 92 of the unmanned vehicle of described second embodiment is roughly the same with the structure of the feet 82 of described first embodiment unmanned vehicle 100, its strut member 97 comprising attaching parts 93 equally, be arranged at the damper element 95 on described attaching parts 93 and be arranged on described damper element 95, its difference is: described damper element 95 is roughly T-pipe joint shape.
Please refer to Fig. 6 to Fig. 8, described damper element 95 comprises Plug Division 951 and carrier 955, and the axis of described Plug Division 951 and the axis of carrier 955 are roughly mutually vertical.
Described Plug Division 951 comprises buffer part 9511, holding parts 9513 and plugs portion 9515.Described buffer part 9511 is roughly in column.Described holding parts 9513 is roughly in cylindrical toroidal, and it is arranged at one end of described buffer part 9511.Described one end plugging portion 9515 is arranged in described holding parts 9513, and is connected with described buffer part 9511.The described other end plugging portion 9515 extends towards the direction deviating from described buffer part 9511.The described overall diameter plugging portion 9515 is less than the interior diameter of described holding parts 9513, described holding parts 9513 is made to plug outside portion 9515 described in being arranged at, and plug described in making between portion 9515 and described holding parts 9513 and form a gap 9517, described gap 9517 is for accommodating described attaching parts 93.Plug the end that portion 9515 is inserted in described attaching parts 93 described in described damper element 95 passes through, a part for attaching parts 93 protrudes in described gap 9517, described damper element 95 entirety to be installed in securely on described attaching parts 93.
Buffer zone 952 and transition region 953 is provided with in described Plug Division 951.In the present embodiment, described buffer zone 952 is a spherical buffering cavity structure, and it is opened in described buffer part 9511.Described transition region 953 is pore structure, its be arranged at described in plug the end in portion 9515, and to extend to described buffer zone 952, and be connected with described buffer zone 952.While described buffer zone 952 and described transition region 953 make the overall weight of described damper element 95 alleviate, make described buffer part 9511 have certain toughness and elasticity, the elastic deformation for described damper element 95 provides space and the distortion allowance of distortion.When described buffer part 9511 is when being subject to external impacts, can there is elastic deformation in it, thus cushion described external force to the overall impact caused of described unmanned vehicle.
Described carrier 955 is arranged in described buffer part 9511, and be positioned at described buffer part 9511 deviate from described in plug the side in portion 9515.In the present embodiment, described carrier 955 is cylindrical tube shape, and it is for connecting described strut member 97.Described damper element 95 is sheathed on described strut member 97 by described carrier 955, to be connected together with described strut member 97 by described attaching parts 93.In the present embodiment, described damper element 95 is positioned at the approximate mid-section position of described strut member 97.Be appreciated that described damper element 95 can also be arranged on other positions of described strut member 97, such as, described damper element 95 can be arranged on the two ends of described strut member 97.
Be appreciated that described buffer zone 952 can be not limited to buffering cavity structure as described above, it can be other buffer structure.Such as, described buffer zone 855 is for offering the buffer zone in multiple hole, or the buffer zone etc. that the flexible material being less than described Plug Division 951 and carrier 955 for other hardness is made as rubber, foam etc., make Plug Division 951 and carrier 955 under the effect of external force, can elastic deformation be there is and not damage the integral structure of described damper element 95 in Plug Division 951, that is, described buffer zone 952 is space and the distortion allowance that the elastic deformation of described damper element 85 provides distortion.
Be appreciated that described buffer zone 952 can be the buffering cavity structure of other shapes except spherical, such as, described buffer zone 952 can be the buffering such as elliposoidal, box-shaped cavity structure, or other erose buffering cavity structures.
Above embodiment is only in order to illustrate technical scheme of the present invention and unrestricted, although with reference to above embodiment to invention has been detailed description, those of ordinary skill in the art should be appreciated that and can modify to technical scheme of the present invention or be equal to the spirit and scope of replacing and should not depart from technical solution of the present invention.
Claims (20)
1. an alighting gear, be applied in unmanned vehicle, described alighting gear comprises feet, described feet comprises attaching parts, it is characterized in that: described attaching parts comprises the installation end for being fixed on by described alighting gear on described unmanned vehicle, and described feet also comprises the damper element be arranged on described attaching parts, and described damper element comprises buffer part, described buffer part is provided with buffer zone, and described buffer zone makes described buffer part produce elastic deformation relative to described attaching parts under external force.
2. alighting gear as claimed in claim 1, is characterized in that: described buffer zone is the buffering cavity structure be arranged in described buffer part;
Or described setting buffers, in described buffer part, described buffer zone offers multiple hole;
Or described setting buffers is in described buffer part, and the hardness of described buffer zone is less than the hardness of described joint and described buffer part.
3. alighting gear as claimed in claim 2, is characterized in that: described damper element also comprises being arranged at described buffer part plugs portion, described in the portion of plugging be inserted in the end of described attaching parts.
4. alighting gear as claimed in claim 3, it is characterized in that: described damper element also comprises holding parts, described holding parts plugs outside portion described in being arranged at, and is connected in described buffer part.
5. alighting gear as claimed in claim 4, is characterized in that: described holding parts and described plugging between portion are provided with gap, described in the portion of plugging when being inserted in the end of described attaching parts, the end of described attaching parts is contained in described gap.
6. alighting gear as claimed in claim 3, it is characterized in that: described damper element also comprises the carrier be arranged in described buffer part, described feet also comprises strut member, and described strut member is inserted on described carrier.
7. alighting gear as claimed in claim 1, is characterized in that: described buffer zone is the dashpot running through the setting of described buffer part, and described buffer zone enables described buffer part change relative to the position of described attaching parts under external force;
Or described buffer zone offers multiple through hole, and described buffer zone enables described buffer part change relative to the position of described attaching parts under external force;
Or the hardness of described buffer zone is less than the hardness of described joint and described buffer part, described buffer zone enables described buffer part change relative to the position of described attaching parts under external force.
8. alighting gear as claimed in claim 7, it is characterized in that: described damper element also comprises the joint be connected on described attaching parts, described buffer part is connected on described joint, and described setting buffers is between described joint and described buffer part.
9. alighting gear as claimed in claim 8, it is characterized in that: described joint is two pass joints, described feet also comprises strut member, described attaching parts is connected to one end of described joint, described strut member is arranged at the other end of described joint, and described buffer part is arranged at the side away from described strut member on described joint.
10. alighting gear as claimed in claim 9, it is characterized in that: described joint comprises the first connecting portion and is arranged at second connecting portion of described first connecting portion one end, the end of described attaching parts is inserted in described first connecting portion, described strut member is arranged at one end of described second connecting portion, and described buffer part is arranged at the other end of described second connecting portion.
11. alighting gears as claimed in claim 10, is characterized in that: described buffer part is provided with groove, and described groove extends and the through other end to described buffer part from described buffer part near one end of described second connecting portion.
12. alighting gears as claimed in claim 11, it is characterized in that: described buffer part also offers through hole, described through hole is communicated with described groove, and described through hole provides deformation space for the elastic deformation of described buffer part.
13. alighting gears as claimed in claim 9, is characterized in that: the quantity of described attaching parts is identical with the quantity of described damper element, and the described joint of each described damper element is arranged on each described attaching parts; The two ends of described strut member are connected with the described joint in two described damper elements respectively.
14. alighting gears as claimed in claim 13, is characterized in that: the quantity of described feet is two, support when two described feets are for being arranged on symmetrically on described unmanned vehicle and land as described unmanned vehicle.
15. alighting gears according to any one of claim 1 ~ 14, is characterized in that: described damper element is the hollow structure with cavity, is filled with rubber in the cavity of described damper element.
16. 1 kinds of unmanned vehicles, it comprises fuselage, it is characterized in that: described unmanned vehicle also comprises the alighting gear according to any one of claim 1 ~ 15, described attaching parts is arranged on described fuselage, and described damper element is arranged at described attaching parts one end away from described fuselage.
17. unmanned vehicles as claimed in claim 16, it is characterized in that: described unmanned vehicle also comprises the horn be arranged on described fuselage and the engine installation be arranged on described horn, described engine installation is with thinking that described unmanned vehicle provides flying power.
18. unmanned vehicles as claimed in claim 17, is characterized in that: described horn is multiple, and arranges around described fuselage.
19. unmanned vehicles as claimed in claim 17, it is characterized in that: described horn comprises a principal arm and is arranged at two support arms on described principal arm, one end of described principal arm is arranged on described fuselage, two described support arms are all connected to described principal arm one end away from described fuselage, and described engine installation is arranged on described support arm.
20. unmanned vehicles as claimed in claim 17, is characterized in that: described fuselage is provided with the automatically controlled module for controlling described engine installation.
Priority Applications (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510291606.XA CN104960662B (en) | 2015-06-01 | 2015-06-01 | Undercarriage and the unmanned vehicle using the undercarriage |
| CN201810182398.3A CN108482654B (en) | 2015-06-01 | 2015-06-01 | Undercarriage and use unmanned vehicles of this undercarriage |
| CN201810182585.1A CN108482650B (en) | 2015-06-01 | 2015-06-01 | Undercarriage and use unmanned vehicles of this undercarriage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510291606.XA CN104960662B (en) | 2015-06-01 | 2015-06-01 | Undercarriage and the unmanned vehicle using the undercarriage |
Related Child Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810182398.3A Division CN108482654B (en) | 2015-06-01 | 2015-06-01 | Undercarriage and use unmanned vehicles of this undercarriage |
| CN201810182585.1A Division CN108482650B (en) | 2015-06-01 | 2015-06-01 | Undercarriage and use unmanned vehicles of this undercarriage |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104960662A true CN104960662A (en) | 2015-10-07 |
| CN104960662B CN104960662B (en) | 2018-04-10 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510291606.XA Expired - Fee Related CN104960662B (en) | 2015-06-01 | 2015-06-01 | Undercarriage and the unmanned vehicle using the undercarriage |
| CN201810182398.3A Expired - Fee Related CN108482654B (en) | 2015-06-01 | 2015-06-01 | Undercarriage and use unmanned vehicles of this undercarriage |
| CN201810182585.1A Expired - Fee Related CN108482650B (en) | 2015-06-01 | 2015-06-01 | Undercarriage and use unmanned vehicles of this undercarriage |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201810182398.3A Expired - Fee Related CN108482654B (en) | 2015-06-01 | 2015-06-01 | Undercarriage and use unmanned vehicles of this undercarriage |
| CN201810182585.1A Expired - Fee Related CN108482650B (en) | 2015-06-01 | 2015-06-01 | Undercarriage and use unmanned vehicles of this undercarriage |
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| CN (3) | CN104960662B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110816836A (en) * | 2019-12-06 | 2020-02-21 | 沈阳旋飞航空技术有限公司 | Support arm folding mechanism for unmanned aerial vehicle |
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| CN202863761U (en) * | 2012-10-25 | 2013-04-10 | 北京化工大学 | Airplane wheel system with combination of rigid solid tyre and buffering bracket |
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| CN204096084U (en) * | 2014-09-16 | 2015-01-14 | 河北雷肯农业机械有限公司 | A kind of alighting gear on 15kg remotely pilotless pesticide applicator |
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- 2015-06-01 CN CN201510291606.XA patent/CN104960662B/en not_active Expired - Fee Related
- 2015-06-01 CN CN201810182398.3A patent/CN108482654B/en not_active Expired - Fee Related
- 2015-06-01 CN CN201810182585.1A patent/CN108482650B/en not_active Expired - Fee Related
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| US4196878A (en) * | 1976-11-24 | 1980-04-08 | Societe Nationale Industrielle Aerospatiale | Aircraft landing-gear with skids |
| CN103062543A (en) * | 2011-10-20 | 2013-04-24 | 霍尼韦尔国际公司 | O-ring shield system and method |
| CN202642095U (en) * | 2012-04-10 | 2013-01-02 | 深圳市大疆创新科技有限公司 | Undercarriage of aircraft and aircraft with undercarriage |
| EP2679490A1 (en) * | 2012-06-26 | 2014-01-01 | Bell Helicopter Textron Inc. | Lightweight landing gear skid shoe assembly |
| CN102874403A (en) * | 2012-10-25 | 2013-01-16 | 北京化工大学 | Airplane wheel system with combination of rigid solid tires and buffer support |
| CN203806137U (en) * | 2013-12-30 | 2014-09-03 | 广州供电局有限公司 | Multi-rotor shock-absorbing landing stand |
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| CN110816836A (en) * | 2019-12-06 | 2020-02-21 | 沈阳旋飞航空技术有限公司 | Support arm folding mechanism for unmanned aerial vehicle |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108482650B (en) | 2020-05-29 |
| CN104960662B (en) | 2018-04-10 |
| CN108482650A (en) | 2018-09-04 |
| CN108482654A (en) | 2018-09-04 |
| CN108482654B (en) | 2020-06-02 |
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