CN210416962U - Foldable unmanned aerial vehicle buffering undercarriage - Google Patents
Foldable unmanned aerial vehicle buffering undercarriage Download PDFInfo
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- CN210416962U CN210416962U CN201922094114.8U CN201922094114U CN210416962U CN 210416962 U CN210416962 U CN 210416962U CN 201922094114 U CN201922094114 U CN 201922094114U CN 210416962 U CN210416962 U CN 210416962U
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Abstract
The utility model provides a folding type buffering undercarriage for an unmanned aerial vehicle, which comprises a horn fixing structure, a connecting component, a limiting component and a landing frame rod, wherein the horn fixing structure compresses a horn; the lower end of the machine arm fixing structure is rotatably connected with the landing gear rod through the connecting component; the limiting assembly is sleeved outside the connecting assembly to limit the machine arm fixing structure and the connecting assembly to rotate mutually. Convenient folding and expansion save the storage space, can realize deploying fast, and the light is high-efficient, satisfies unmanned aerial vehicle's portability demand, is favorable to the user demand of guarantee aircraft safety take off and land.
Description
Technical Field
The utility model relates to an unmanned aerial vehicle cushions undercarriage, especially relates to a foldable unmanned aerial vehicle cushions undercarriage.
Background
The small unmanned aerial vehicle has strong environmental adaptability and excellent portability, and is widely applied to the task fields of reconnaissance, detection and the like. The undercarriage guarantees that unmanned aerial vehicle takes off and land smoothly and carries out the basis of the task of flying, and unmanned aerial vehicle's design also need satisfy fast expansion, light efficient requirement, will guarantee unmanned aerial vehicle's safe take off and land moreover, and this has proposed higher requirement to the design of undercarriage.
Among the prior art, the undercarriage that unmanned aerial vehicle adopted mainly has two kinds, one kind is bow-shaped undercarriage, and this kind of undercarriage not only the volume is great to occupy more space of taking, has lost the portability, and unmanned aerial vehicle's expansion is inconvenient in addition, weight is heavier, is not conform to unmanned aerial vehicle's design service features, can't satisfy unmanned aerial vehicle and deploy fast, light efficient requirement. The other type is a split type screwed landing gear which has simple structure and light weight, but can generate shaking conditions due to the vibration of a propeller during the flight, and the landing gear is easy to lose after the airplane is retracted.
SUMMERY OF THE UTILITY MODEL
The to-be-solved first technical problem of the utility model is to provide a foldable unmanned aerial vehicle buffering undercarriage, convenient folding and expansion save storage space, can realize deploying fast, and the light is high-efficient, satisfies unmanned aerial vehicle's portability demand, is favorable to the user demand of ensureing the safe take off and land of aircraft.
In order to solve the technical problem, foldable unmanned aerial vehicle cushions undercarriage, including horn fixed knot structure, horn fixed knot structure compresses tightly the horn, still includes coupling assembling, spacing subassembly and the hack lever that plays.
The lower end of the machine arm fixing structure is rotatably connected with the landing gear rod through the connecting assembly.
The limiting assembly is sleeved outside the connecting assembly to limit the machine arm fixing structure and the connecting assembly to rotate mutually.
The connecting assembly comprises a first connecting piece and a second connecting piece.
The bottom of the machine arm fixing structure is fixedly connected with the upper end of the first connecting piece.
The lower end of the first connecting piece is rotatably connected with the upper end of the second connecting piece.
The limiting assembly comprises an elastic piece, a clamp and a limiting block.
The elastic piece is sleeved outside the first connecting piece.
The clamp sleeve is arranged on the outer side of the first connecting piece.
The upper end of the elastic piece is abutted to the horn fixing structure.
The clamp supports the lower end of the elastic piece.
The lower extreme of first connecting piece is provided with first arch, the bearing the lower extreme of clamp.
The limiting block is fixedly connected with the upper end of the second connecting piece.
The limiting block exceeds the upper end of the second connecting piece.
The stopper surpasss the part of second connecting piece upper end stretches into the lower extreme of clamp.
The inner side of the hoop protrudes inwards along the radial direction to form a circle of convex ring.
The convex ring supports the lower end of the elastic piece.
The first bulge is provided with a pin hole.
And a second bulge is arranged at the upper end of the second connecting piece.
The second protrusion is provided with a pin hole.
The bayonet pin penetrates through the first protrusion and the second protrusion, so that the first connecting piece and the second connecting piece are rotatably connected.
The second connecting piece is provided with a through hole along the axial direction.
The through hole is used for the landing gear rod to be inserted.
The second connecting piece and the landing gear rod are screwed tightly through threads to realize compression. The device further comprises a sleeve, a buffer piece, a bolt and a base.
The sleeve is sleeved at the bottom end of the landing gear rod.
Two hole sites are arranged on the sleeve.
The two hole sites are located on the same cross section of the sleeve.
The base is sleeved at the bottom end of the sleeve.
Two grooves are formed in the base corresponding to the two hole positions.
The bolt is inserted into the two grooves and the two hole positions, so that the base can move up and down along the sleeve.
The buffer is disposed inside the sleeve.
When the bolt is located when the slot is topmost, the upper end butt of bolster the outside bottom of base, the lower extreme butt of bolster the telescopic inside bottom.
The utility model discloses a foldable unmanned aerial vehicle buffering undercarriage compares with prior art and has following beneficial effect:
(1) convenient folding and expansion save the storage space, can realize deploying fast, and the light is high-efficient, satisfies unmanned aerial vehicle's portability demand, is favorable to the user demand of guarantee aircraft safety take off and land.
(2) The landing gear is in a freely foldable state through the deformation of the elastic part after compression, so that the folding function is realized; meanwhile, the clamp hoop plays a limiting role on the second connecting piece through the elasticity of the elastic piece, and the second connecting piece is prevented from being freely folded and unfolded under the condition of not being manually intervened.
(3) This folding direction of foldable unmanned aerial vehicle buffering undercarriage is the same with the horn direction, and the horn after folding occupies with the undercarriage volume and changes little, saves storage space, satisfies unmanned aerial vehicle's portability demand.
(4) The bolster of undercarriage tail end can absorb the energy, plays the cushioning effect when small unmanned aerial vehicle descends through the location fit with telescopic, prevents that the aircraft from descending to touch to ground and produce the damage to organism structure.
(5) The folding type buffering undercarriage structure of the unmanned aerial vehicle is simple and reliable, the structure has good machinability, the machining process is easy to realize, lower machining cost and machining period are guaranteed, and the folding type buffering undercarriage structure is particularly suitable for the production and use requirements of small unmanned aerial vehicles.
Drawings
The present invention will be described in further detail with reference to the accompanying drawings and specific embodiments.
Fig. 1 is a schematic view of the overall structure of the buffering undercarriage of the folding unmanned aerial vehicle;
fig. 2 is a schematic structural view of the connection between the buffering undercarriage and the horn of the foldable unmanned aerial vehicle of the present invention;
fig. 3 is a schematic structural view of a foldable part of the buffering undercarriage of the folding unmanned aerial vehicle;
fig. 4 is a schematic diagram of an explosive structure of the foldable portion of the buffering undercarriage for foldable unmanned aerial vehicles according to the present invention;
fig. 5 is a schematic diagram of a second explosion structure of the foldable portion of the buffering undercarriage for foldable unmanned aerial vehicles according to the present invention;
fig. 6 is a schematic diagram of a third explosion structure of the foldable portion of the buffering undercarriage for foldable unmanned aerial vehicles according to the present invention;
fig. 7 is a schematic diagram of a fourth explosive structure of the foldable portion of the buffering undercarriage for foldable unmanned aerial vehicles according to the present invention;
fig. 8 is the utility model discloses the buffer part structure schematic diagram of foldable unmanned aerial vehicle buffering undercarriage.
In the figure: 1-a fixed seat on the machine arm; 2-first connection screw; 3-a lower fixed seat of the machine arm; 4-an elastic member; 5-a first connecting member; 6, clamping a hoop; 7-a bayonet lock; 8-a second connector; 9-a machine arm; 10-a third connection screw; 11-a second connection screw; 12-a landing gear lever; 13-a sleeve; 14-a latch; 15-a buffer; 16-a base; 17-a limiting block.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. The components of the embodiments of the present invention, as generally described and illustrated in the figures herein, can be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the present invention, presented in the accompanying drawings, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative efforts belong to the protection scope of the present invention.
It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", and the like indicate the position or positional relationship based on the position or positional relationship shown in the drawings, or the position or positional relationship which is usually placed when the product of the present invention is used, and are only for convenience of description and simplification of the description, but do not indicate or imply that the device or element referred to must have a specific position, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," "third," and the like are used solely to distinguish one from another and are not to be construed as indicating or implying relative importance.
Furthermore, the terms "horizontal", "vertical", "overhang" and the like do not imply that the components are required to be absolutely horizontal or overhang, but may be slightly inclined. For example, "horizontal" merely means that the direction is more horizontal than "vertical" and does not mean that the structure must be perfectly horizontal, but may be slightly inclined.
In the description of the present invention, it should also be noted that, unless otherwise explicitly specified or limited, the terms "disposed," "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.
Some embodiments of the present invention will be described in detail below with reference to the accompanying drawings. The embodiments described below and the features of the embodiments can be combined with each other without conflict.
The utility model discloses an embodiment is as shown in fig. 1 to fig. 8, and this embodiment provides a foldable unmanned aerial vehicle buffering undercarriage, including horn fixed knot structure, horn fixed knot structure compresses tightly horn 9, still includes coupling assembling, spacing subassembly and plays undercarriage pole 12.
The lower end of the horn fixed structure is rotatably connected with the landing gear rod 12 through the connecting component.
The limiting assembly is sleeved outside the connecting assembly to limit the machine arm fixing structure and the connecting assembly to rotate mutually.
The horn fixed knot constructs including fixing base 1 and horn lower fixing base 3 on the horn.
The upper fixed seat 1 of the machine arm and the lower fixed seat 3 of the machine arm are locked through a group of first connecting screws 2.
The upper fixed seat 1 and the lower fixed seat 3 of the horn are main stressed parts of the airplane and are made of metal materials with strength and rigidity.
The connecting assembly comprises a first connecting piece 5 and a second connecting piece 8.
The bottom of the lower arm fixing seat 3 is locked with the upper end of the first connecting piece 5 through a second connecting screw 11.
The lower end of the first connecting piece 5 is rotatably connected with the upper end of the second connecting piece 8.
The limiting assembly comprises an elastic piece 4, a clamp 6 and a limiting block 17.
The elastic piece 4 is sleeved outside the first connecting piece 5.
The clamp 6 is sleeved on the outer side of the first connecting piece 5.
The clamp 6 supports the lower end of the elastic member 4.
The upper end of the elastic piece 4 is abutted to the horn fixing structure.
The lower extreme of first connecting piece 5 is provided with first arch, the bearing the lower extreme of clamp 6.
The limiting block 17 is fixedly connected with the upper end of the second connecting piece 8.
The limiting block 17 and the second connecting piece 8 are integrally formed.
The limiting block 17 exceeds the upper end of the second connecting piece 8.
The part that stopper 17 surpasss second connecting piece 8 upper end stretches into the lower extreme of clamp 6.
The inner side of the hoop 6 protrudes inwards along the radial direction to form a circle of convex rings.
The raised ring supports the lower end of the elastic member 4.
The first bulge is provided with a pin hole.
And a second bulge is arranged at the upper end of the second connecting piece 8.
The second protrusion is provided with a pin hole.
The bayonet 7 penetrates through the first projection and the second projection, so that the first connecting piece 5 and the second connecting piece 8 are rotatably connected.
The second connecting piece 8 is provided with a through hole along the axial direction.
The through hole is for the landing gear rod 12 to be inserted.
And third bulges are arranged at the two ends of the through hole at the lower end of the second connecting piece 8.
The third bulge is provided with a pin hole.
And a third connecting screw 10 penetrates through the pin hole, and the second connecting piece 8 and the landing gear rod 12 are screwed tightly to realize compression.
The landing gear rod 12 is made of a carbon fiber material with a hollow structure, and meets the strength requirement.
The included angle between the connecting assembly, the limiting assembly, the landing gear rod 12 and the horn is 110 degrees, so that the unmanned aerial vehicle can be ensured not to turn on one's side when descending at a large angle and land stably.
The device also comprises a sleeve 13, a buffer piece 15, a bolt 14 and a base 16.
The sleeve 13 is sleeved at the bottom end of the landing gear rod 12.
Two hole sites are provided on the sleeve 13.
Both said holes are located in the same cross section of the sleeve 13.
The base 16 is sleeved at the bottom end of the sleeve 13.
Two grooves are arranged on the base 16 corresponding to the two hole positions.
The pins 14 are inserted into the two grooves and the two holes, so that the base 16 can move up and down along the sleeve 13.
The buffer 15 is arranged inside the sleeve 13.
When the bolt 14 is located at the topmost end of the groove, the upper end of the buffer member 15 abuts against the outer bottom end of the base 16, and the lower end of the buffer member 15 abuts against the inner bottom end of the sleeve 13.
The whole material mainly adopts high-strength plastic materials and carbon fiber materials, and the weight of the undercarriage is reduced on the premise of meeting the requirements for strength and rigidity.
The utility model discloses a another embodiment is as shown in fig. 1 to fig. 8, and this embodiment provides a foldable unmanned aerial vehicle buffering undercarriage, including horn fixed knot structure, horn fixed knot structure compresses tightly horn 9, still includes coupling assembling, spacing subassembly and plays undercarriage pole 12.
The lower end of the horn fixed structure is rotatably connected with the landing gear rod 12 through the connecting component.
The limiting assembly is sleeved outside the connecting assembly to limit the machine arm fixing structure and the connecting assembly to rotate mutually.
The horn fixed knot constructs including fixing base 1 and horn lower fixing base 3 on the horn.
The upper fixed seat 1 of the machine arm and the lower fixed seat 3 of the machine arm are locked through four first connecting screws 2.
The upper fixed seat 1 and the lower fixed seat 3 of the horn are main stressed parts of the airplane and are made of metal materials with strength and rigidity.
The connecting assembly comprises a first connecting piece 5 and a second connecting piece 8.
The bottom of the lower arm fixing seat 3 is locked with the upper end of the first connecting piece 5 through a second connecting screw 11.
The lower end of the first connecting piece 5 is rotatably connected with the upper end of the second connecting piece 8.
The limiting assembly comprises an elastic piece 4, a clamp 6 and a limiting block 17.
The elastic piece 4 is sleeved outside the first connecting piece 5.
The elastic member 4 is a compression spring.
The clamp 6 is sleeved on the outer side of the first connecting piece 5.
The clamp 6 supports the lower end of the elastic member 4.
The upper end of the elastic piece 4 is abutted to the horn fixing structure.
The lower extreme of first connecting piece 5 is provided with first arch, the bearing the lower extreme of clamp 6.
The limiting block 17 is fixedly connected with the upper end of the second connecting piece 8.
The limiting block 17 exceeds the upper end of the second connecting piece 8.
The part that stopper 17 surpasss second connecting piece 8 upper end stretches into the lower extreme of clamp 6.
The inner side of the hoop 6 protrudes inwards along the radial direction to form a circle of convex rings.
The raised ring supports the lower end of the elastic member 4.
The first bulge is provided with a pin hole.
And a second bulge is arranged at the upper end of the second connecting piece 8.
The second protrusion is provided with a pin hole.
The bayonet 7 penetrates through the first projection and the second projection, so that the first connecting piece 5 and the second connecting piece 8 are rotatably connected.
The second connecting piece 8 is provided with a through hole along the axial direction.
The through hole is for the landing gear rod 12 to be inserted.
And third bulges are arranged at the two ends of the through hole at the lower end of the second connecting piece 8.
The third bulge is provided with a pin hole.
And a third connecting screw 10 penetrates through the pin hole, and the second connecting piece 8 and the landing gear rod 12 are screwed tightly to realize compression.
The landing gear rod 12 is made of a carbon fiber material with a hollow structure, and meets the strength requirement.
The included angle between the connecting assembly, the limiting assembly, the landing gear rod 12 and the horn is 110 degrees, so that the unmanned aerial vehicle can be ensured not to turn on one's side when descending at a large angle and land stably.
The device also comprises a sleeve 13, a buffer piece 15, a bolt 14 and a base 16.
The sleeve 13 is sleeved at the bottom end of the landing gear rod 12.
Two hole sites are provided on the sleeve 13.
Both said holes are located in the same cross section of the sleeve 13.
The base 16 is sleeved at the bottom end of the sleeve 13.
Two grooves are arranged on the base 16 corresponding to the two hole positions.
The pins 14 are inserted into the two grooves and the two holes, so that the base 16 can move up and down along the sleeve 13.
The buffer 15 is arranged inside the sleeve 13.
The buffer member 15 is a buffer spring.
When the bolt 14 is located at the topmost end of the groove, the upper end of the buffer member 15 abuts against the outer bottom end of the base 16, and the lower end of the buffer member 15 abuts against the inner bottom end of the sleeve 13.
The whole material mainly adopts high-strength plastic materials and carbon fiber materials, and the weight of the undercarriage is reduced on the premise of meeting the requirements for strength and rigidity.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (6)
1. A foldable buffering undercarriage of an unmanned aerial vehicle comprises a horn fixing structure, wherein the horn fixing structure presses a horn tightly, and the foldable buffering undercarriage is characterized by further comprising a connecting assembly, a limiting assembly and a landing frame rod;
the lower end of the machine arm fixing structure is rotatably connected with the landing gear rod through the connecting component;
the limiting assembly is sleeved outside the connecting assembly to limit the machine arm fixing structure and the connecting assembly to rotate mutually.
2. The folding unmanned aerial vehicle cushioned landing gear of claim 1,
the connecting assembly comprises a first connecting piece and a second connecting piece;
the bottom of the machine arm fixing structure is fixedly connected with the upper end of the first connecting piece;
the lower end of the first connecting piece is rotatably connected with the upper end of the second connecting piece;
the limiting assembly comprises an elastic piece, a clamp and a limiting block;
the elastic piece is sleeved outside the first connecting piece;
the clamp is sleeved on the outer side of the first connecting piece;
the upper end of the elastic piece is abutted against the machine arm fixing structure;
the hoop supports the lower end of the elastic piece;
the lower end of the first connecting piece is provided with a first bulge for supporting the lower end of the hoop;
the limiting block is fixedly connected with the upper end of the second connecting piece;
the limiting block exceeds the upper end of the second connecting piece;
the stopper surpasss the part of second connecting piece upper end stretches into the lower extreme of clamp.
3. The folding unmanned aerial vehicle cushioned landing gear of claim 2,
the inner side of the hoop protrudes inwards along the radial direction to form a circle of convex ring;
the convex ring supports the lower end of the elastic piece.
4. The folding unmanned aerial vehicle cushioned landing gear of claim 2,
the first bulge is provided with a pin hole;
a second bulge is arranged at the upper end of the second connecting piece;
the second bulge is provided with a pin hole;
the bayonet pin penetrates through the first protrusion and the second protrusion, so that the first connecting piece and the second connecting piece are rotatably connected.
5. The folding unmanned aerial vehicle cushioned landing gear of claim 2,
the second connecting piece is provided with a through hole along the axial direction;
the through hole is used for the landing gear rod to be inserted;
the second connecting piece and the landing gear rod are screwed tightly through threads to realize compression.
6. The folding unmanned aerial vehicle cushioned landing gear of claim 1, further comprising a sleeve, a cushion, a pin, and a base;
the sleeve is sleeved at the bottom end of the landing gear rod;
two hole sites are arranged on the sleeve;
the two hole sites are positioned on the same cross section of the sleeve;
the base is sleeved at the bottom end of the sleeve;
two grooves are formed in the base corresponding to the two hole sites;
the bolt is inserted into the two grooves and the two hole sites, so that the base can move up and down along the sleeve;
the buffer piece is arranged inside the sleeve;
when the bolt is located when the slot is topmost, the upper end butt of bolster the outside bottom of base, the lower extreme butt of bolster the telescopic inside bottom.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922094114.8U CN210416962U (en) | 2019-11-28 | 2019-11-28 | Foldable unmanned aerial vehicle buffering undercarriage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922094114.8U CN210416962U (en) | 2019-11-28 | 2019-11-28 | Foldable unmanned aerial vehicle buffering undercarriage |
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| CN210416962U true CN210416962U (en) | 2020-04-28 |
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| CN201922094114.8U Active CN210416962U (en) | 2019-11-28 | 2019-11-28 | Foldable unmanned aerial vehicle buffering undercarriage |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112455645A (en) * | 2020-12-14 | 2021-03-09 | 珠海紫燕新科技有限公司 | Collapsible unmanned aerial vehicle |
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2019
- 2019-11-28 CN CN201922094114.8U patent/CN210416962U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112455645A (en) * | 2020-12-14 | 2021-03-09 | 珠海紫燕新科技有限公司 | Collapsible unmanned aerial vehicle |
| CN112455645B (en) * | 2020-12-14 | 2022-11-29 | 珠海紫燕新科技有限公司 | Collapsible unmanned aerial vehicle |
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