阅读说明：本技术 起落架结构及无人机 (Undercarriage structure and unmanned aerial vehicle ) 是由 王坤殿 于建方 张圣鑫 陈旭东 于 2018-09-18 设计创作，主要内容包括：一种起落架结构及无人机。起落架结构(100)包括起落架(10)和快拆组件(20)；起落架(10)包括主体部(14)和设于主体部(14)的插接部(11),快拆组件(20)包括用于与外部主体结构连接的第一安装部(21)和与第一安装部(21)连接的第二安装部(22),第二安装部(22)设有与插接部(11)相配合的插槽(23)和固定件(24)；插接部(11)插设于插槽(23)内,并通过固定件(24)与第二安装部(22)固定。起落架(10)通过插接部插设在快拆组件的插槽内,通过固定件与快拆组件连接,通过快拆组件的第一安装部与外部主体结构连接,进而将起落架(10)安装到外部主体结构上。结构简单可靠性高,并且易于拆装。(Provided are an undercarriage structure and an unmanned aerial vehicle. The landing gear structure (100) comprises a landing gear (10) and a quick release assembly (20); the landing gear (10) comprises a main body part (14) and an insertion part (11) arranged on the main body part (14), the quick release assembly (20) comprises a first mounting part (21) used for being connected with an external main body structure and a second mounting part (22) connected with the first mounting part (21), and the second mounting part (22) is provided with a slot (23) and a fixing part (24) which are matched with the insertion part (11); the insertion part (11) is inserted into the slot (23) and is fixed with the second installation part (22) through a fixing part (24). The undercarriage (10) is inserted into a slot of the quick-release assembly through the insertion part, connected with the quick-release assembly through the fixing part, and connected with an external main structure through a first installation part of the quick-release assembly, so that the undercarriage (10) is installed on the external main structure. Simple structure, high reliability and easy disassembly and assembly.)

1. A landing gear structure, comprising: landing gear and quick release assembly;

the undercarriage comprises a main body part and an inserting part arranged on the main body part, the quick-release assembly comprises a first mounting part used for being connected with an external main body structure and a second mounting part connected with the first mounting part, and the second mounting part is provided with a slot and a fixing part which are matched with the inserting part;

the inserting part is inserted into the slot and is fixed with the second mounting part through the fixing part.

2. The landing gear structure of claim 1, wherein the first mounting portion includes a socket portion that is socket-connected to the outer body structure, and an outer sidewall of the socket portion is connected to the second mounting portion.

3. A landing gear structure according to claim 1, wherein the second mounting portion comprises two stop portions and a connecting portion between the two stop portions; the fixing piece is arranged on the limiting portion, and the slot is formed in the connecting portion.

4. A landing gear structure according to claim 3, wherein the two stop portions are spaced from the connection portion.

5. A landing gear structure according to claim 3, wherein the spacing between the two stop portions is equal to the width of the spigot portion.

6. The landing gear structure according to claim 3, wherein connecting holes are formed in side walls of the two limiting portions, the connecting holes of the two limiting portions are coaxially arranged, and the fixing member is inserted into each of the two connecting holes.

7. A landing gear structure according to claim 3, wherein the fixing is a ball plunger.

8. A landing gear structure according to claim 7, wherein the spigot portion is symmetrically provided with arcuate recesses adjacent both side ends of the two limiting portions, for engaging with the fixing members.

9. A landing gear structure according to claim 3, wherein the side of the connection portion is provided with a reinforcing wing plate connected to the first mounting portion.

10. A landing gear structure according to claim 1, wherein the landing gear is a swept back landing gear.

11. The landing gear structure of claim 1, wherein the main body portion is provided with a plurality of hollowed-out portions along a length direction thereof.

12. The utility model provides an unmanned aerial vehicle, its characterized in that, including the fuselage, set up in the horn of fuselage and undercarriage structure, its characterized in that includes: landing gear and quick release assembly;

the undercarriage comprises a main body part and an inserting part arranged on the main body part, the quick-release assembly comprises a first mounting part used for being connected with an external main body structure and a second mounting part connected with the first mounting part, and the second mounting part is provided with a slot and a fixing part which are matched with the inserting part;

the inserting part is inserted into the inserting groove and fixed with the second installation part through the fixing part, and the first installation part of the quick-release assembly of the undercarriage structure is connected with the horn.

13. The unmanned aerial vehicle of claim 12, wherein the first mounting portion comprises a sleeve portion sleeved on the outer main body structure, and the outer side wall of the sleeve portion is connected with the second mounting portion.

14. The drone of claim 12, wherein the second mounting portion includes two stop portions and a connecting portion between the two stop portions; the fixing piece is arranged on the limiting portion, and the slot is formed in the connecting portion.

15. The drone of claim 14, wherein the two stop portions are spaced from the connecting portion.

16. The drone of claim 14, wherein a separation distance between the two stop portions is equal to a width of the docking portion.

17. The unmanned aerial vehicle of claim 14, wherein the side walls of the two limiting portions are both provided with connecting holes, the connecting holes of the two limiting portions are coaxially arranged, and the fixing members are arranged in the two connecting holes.

18. The drone of claim 14, wherein the mount is a ball plunger.

19. An unmanned aerial vehicle according to claim 18, wherein the insertion part is symmetrically provided with arc-shaped concave parts close to the two side ends of the two limiting parts, and the arc-shaped concave parts are matched with the fixing part.

20. The unmanned aerial vehicle of claim 14, wherein a side portion of the connecting portion is provided with a reinforcing wing plate connected with the first mounting portion.

21. The drone of claim 12, wherein the landing gear is a swept back landing gear.

22. The unmanned aerial vehicle of claim 12, wherein the main body portion is provided with a plurality of hollowed-out portions along a length direction thereof.

Technical Field

The embodiment of the invention relates to the technical field of unmanned aerial vehicles, in particular to an undercarriage structure and an unmanned aerial vehicle.

Background

The undercarriage must adapt to with the holistic design of unmanned aerial vehicle as the important mechanism on the unmanned aerial vehicle equipment, still needs to satisfy safe and reliable's requirement simultaneously.

And present ordinary unmanned aerial vehicle's undercarriage has two problems usually, and the sturdy and durable of structure is first, and the lightweight of structure is second. Some landing gears strengthen the structure but also increase the weight, and some landing gears reduce the weight but also weaken the structure, often considering that. The existing quick-release structure is often complex in manufacture, the weight is further increased, and the reliability of the mechanism is reduced. Or some undercarriage does not have a quick-release structure at all, and a lot of inconvenience is brought to packing transportation.

Disclosure of Invention

The embodiment of the invention provides an undercarriage structure which is reliable in structure and can be quickly disassembled and assembled and an unmanned aerial vehicle.

According to a first aspect of embodiments of the present invention, there is provided a landing gear structure comprising: landing gear and quick release assembly;

the undercarriage comprises a main body part and an inserting part arranged on the main body part, the quick-release assembly comprises a first mounting part used for being connected with an external main body structure and a second mounting part connected with the first mounting part, and the second mounting part is provided with a slot and a fixing part which are matched with the inserting part;

the inserting part is inserted into the slot and is fixed with the second mounting part through the fixing part.

Further, first installation department including cup joint in the portion of cup jointing of outside major structure, the lateral wall of the portion of cup jointing is connected with the second installation department.

Further, the second mounting part comprises two limiting parts and a connecting part positioned between the two limiting parts; the fixing piece is arranged on the limiting portion, and the slot is formed in the connecting portion.

Further, the two limiting parts and the connecting part are arranged at intervals.

Further, the spacing distance between the two limiting parts is equal to the width of the inserting part.

Furthermore, the connecting holes are formed in the side walls of the two limiting portions, the connecting holes of the two limiting portions are coaxially arranged, and the fixing pieces are arranged in the connecting holes in a penetrating mode.

Further, the fixing piece is a ball plunger.

Furthermore, the insertion part is provided with arc-shaped concave parts close to the end parts of the two sides of the two limiting parts, and the arc-shaped concave parts are matched with the fixing part.

Furthermore, a reinforcing wing plate connected with the first mounting part is arranged on the side part of the connecting part.

Further, the landing gear is a swept back landing gear.

Furthermore, the main body part is provided with a plurality of hollow parts along the length direction.

According to a second aspect of the embodiment of the invention, an unmanned aerial vehicle is provided, which comprises a fuselage, a horn arranged on the fuselage, and the undercarriage structure of any one of the embodiments, wherein the first mounting part of the quick release assembly of the undercarriage structure is connected with the horn.

According to the undercarriage structure provided by the embodiment of the invention, the undercarriage is inserted into the slot of the second mounting part of the quick-release assembly through the insertion part, is fixedly connected with the second mounting part through the fixing part, so as to be connected with the quick-release assembly, and is connected with the external main body structure through the first mounting part of the quick-release assembly, so that the undercarriage is mounted on the external main body structure. Simple structure, high reliability and easy disassembly and assembly.

Drawings

FIG. 1 is a schematic structural view of a landing gear configuration according to an embodiment of the present invention.

FIG. 2 is an exploded schematic view of a landing gear configuration shown in an embodiment of the present invention.

FIG. 3 is an exploded isometric view of a landing gear configuration according to an embodiment of the present invention.

Fig. 4 is a schematic perspective view of an unmanned aerial vehicle according to an embodiment of the present invention.

Fig. 5 is a side view of a drone according to an embodiment of the present invention.

Fig. 6 is a front view of a drone according to an embodiment of the present invention.

Fig. 7 is an enlarged schematic view of a hatch cover and a fuselage of an unmanned aerial vehicle according to an embodiment of the present invention.

Detailed Description

Reference will now be made in detail to the exemplary embodiments, examples of which are illustrated in the accompanying drawings. When the following description refers to the accompanying drawings, like numbers in different drawings represent the same or similar elements unless otherwise indicated. The implementations described in the following exemplary embodiments do not represent all implementations consistent with embodiments of the invention. Rather, they are merely examples of apparatus and methods consistent with certain aspects of embodiments of the invention, as detailed in the following claims.

The terminology used in the embodiments of the invention is for the purpose of describing particular embodiments only and is not intended to be limiting of the embodiments of the invention. As used in the examples of the present invention and the appended claims, the singular forms "a," "an," and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. It should also be understood that the term "and/or" as used herein refers to and encompasses any and all possible combinations of one or more of the associated listed items.

It should be understood that the terms "first," "second," and the like as used in the description and in the claims, do not denote any order, quantity, or importance, but rather are used to distinguish one element from another. Also, the use of the terms "a" or "an" and the like do not denote a limitation of quantity, but rather denote the presence of at least one. Unless otherwise indicated, "front", "rear", "lower" and/or "upper" and the like are for convenience of description and are not limited to one position or one spatial orientation. The word "comprising" or "comprises", and the like, means that the element or item listed as preceding "comprising" or "includes" covers the element or item listed as following "comprising" or "includes" and its equivalents, and does not exclude other elements or items. The terms "connected" or "coupled" and the like are not restricted to physical or mechanical connections, but may include electrical connections, whether direct or indirect.

The embodiment of the invention provides an undercarriage structure which is reliable in structure and can be quickly disassembled and assembled and an unmanned aerial vehicle. The landing gear structure and the unmanned aerial vehicle according to the embodiment of the invention are described in detail below with reference to the accompanying drawings. The features of the following examples and embodiments may be combined with each other without conflict.

Referring to fig. 1 to 3, an embodiment of the invention provides a landing gear structure 100 for mounting on an outer body structure, which in this embodiment may be the horn of an unmanned aerial vehicle. The landing gear structure 100 includes: landing gear 10 and quick release assembly 20, landing gear 10 is detachably connected with quick release assembly 20.

The landing gear 10 comprises a main body portion 14 and an insertion portion 11 arranged on the main body portion 14, the quick release assembly 20 comprises a first mounting portion 21 and a second mounting portion 22, the first mounting portion 21 is used for being connected with an external main body structure, the second mounting portion 22 is connected with the first mounting portion 21, and the second mounting portion 22 is provided with a slot 23 and a fixing piece 24, the slot 23 is matched with the insertion portion 11. The insertion part 11 of the landing gear 10 is inserted into the insertion slot 23 of the second mounting part 22 of the quick release assembly 20, and is fixed with the second mounting part 22 through the fixing part 24.

As can be seen from the above embodiments, in the landing gear structure 100 according to the embodiment of the invention, the landing gear 10 is inserted into the insertion slot 23 of the second mounting portion 22 of the quick release assembly 20 through the insertion portion 11, and is then fixedly connected to the second mounting portion 22 through the fixing member 24, so as to be connected to the quick release assembly 20, and then is connected to the external main structure through the first mounting portion 21 of the quick release assembly 20, so as to mount the landing gear 10 on the external main structure. When the landing gear 10 needs to be disassembled, the insertion part 11 of the landing gear 10 is pulled out from the insertion groove 23 of the second mounting part 22 of the quick release assembly 20, so that the landing gear 10 and the external main structure are disassembled. Simple structure, high reliability and easy disassembly and assembly.

In an optional embodiment, the first mounting portion 21 of the quick release assembly 20 includes a sleeve portion 212 sleeved on the outer main body structure, and the outer sidewall of the sleeve portion 212 is connected to the second mounting portion 22. In this embodiment, the first mounting portion 21 is a sleeve member, and the side wall of the sleeve portion 212 is provided with a slit portion 213, so that the sleeve portion 212 has a certain expansion margin, and is more convenient to sleeve on the external main body structure.

In this embodiment, outside major structure is unmanned aerial vehicle's horn, a plurality of hole sites have been seted up on this horn, the lateral wall of cup joint portion 212 can also set up with this hole site matched with mounting hole 214 (use two mounting holes 214 as the example in the figure), cup joint portion 212 cover is established back on the horn, adjust cup joint portion 212 to suitable position, can wear to establish in corresponding hole site and mounting hole 214 through fastener 215 (for example screw), realize cup joint portion 212 and outside major structure reciprocal anchorage, and then install the first installation department 21 of quick detach subassembly 20 on outside major structure, and also be convenient for dismantle quick detach subassembly 20 and outside major structure through such connected mode. Of course, the first mounting portion 21 of the quick release assembly 20 may also be connected to the external main structure by other connection methods (which may be fixed connection or detachable connection), and the embodiment of the invention is not limited thereto.

In an alternative embodiment, the second mounting portion 22 of the quick release assembly 20 includes two position-limiting portions 25 and a connecting portion 26 located between the two position-limiting portions 25. The fixing member 24 is installed on the limiting portion 25, and the slot 23 is opened on the connecting portion 26. In this embodiment, the two limiting portions 25 and the connecting portion 26 are arranged at an interval, when the slot 23 is machined, a round corner is formed at the bottom of the slot 23, which may prevent the insertion portion 11 from being inserted into the slot 23, and the round corner may be milled away at an interval between the two limiting portions 25 and the connecting portion 26 in the process, so as to facilitate the insertion of the insertion portion 11 into the slot 23 and the close fit with the slot 23, and facilitate the observation of the position of the insertion portion 11 from the gap between the limiting portions 25 and the connecting portion 26, so as to insert the insertion portion 11 into the slot 23. And the spacing distance between the two limiting parts 25 is equal to the width of the insertion part 11, so that the insertion part 11 can be guided, and the insertion part 11 can be more conveniently inserted into the slot 23. Of course, in other examples, the two stopper portions 25 and the connecting portion 26 may be integrally formed. In addition, the width of the part of the main body part 14 of the landing gear 10 adjacent to the insertion part 11 is larger than that of the insertion part 11, and after the insertion part 11 is inserted into the insertion groove 23 of the connecting part 26, the main body part 14 can be abutted against the limiting part 25, so that the landing gear 10 is more firmly installed.

In an optional embodiment, the side walls of the two position-limiting portions 25 are both provided with a connecting hole 251, the connecting holes 251 of the two position-limiting portions 25 are coaxially arranged, and the fixing member 24 is inserted into both the two connecting holes 251. In this embodiment, the fixing member 24 is a ball plunger, and the insertion part 11 is symmetrically provided with arc-shaped concave parts 12 which are matched with the fixing member 24 using the ball plunger, near the two side end parts of the two limiting parts 25. Further, in order to enhance the structural strength of the second mounting portion 22, a reinforcing wing 27 connected to the first mounting portion 21 is provided at a side portion of the connecting portion 26.

Normally, the ball head portion of the ball plunger partially protrudes from the side wall of the limiting portion 25, when the insertion portion 11 of the landing gear 10 is inserted into the slot 23 of the connecting portion 26, the insertion portion 11 first presses the ball head portion of the ball plunger to press the ball head portion into the connecting hole 251 of the side wall of the limiting portion 25, and when the arc-shaped recessed portion 12 of the insertion portion 11 moves to a position corresponding to the connecting hole 251, the ball head portion of the ball plunger gradually pops out of the connecting hole 251 until being completely engaged with the arc-shaped recessed portion 12, so that both sides of the insertion portion 11 are engaged with the corresponding fixing members 24, and the landing gear 10 and the second mounting portion 22 of the quick release assembly 20 are fixed to each other. When the landing gear 10 needs to be disassembled, the insertion part 11 is only required to be pulled out of the insertion groove 23 of the connecting part 26, so that the landing gear 10 and the quick disassembling component 20 can be quickly disassembled.

In an alternative embodiment, in order to ensure both the structural strength and the weight reduction requirements of the landing gear 10, the landing gear 10 is made of a carbon fiber material with a thickness of 4mm, which ensures the structural strength of the landing gear 10. The landing gear 10 is swept back as a whole, is full of dynamic feeling and has good aerodynamic performance. The main body portion 14 of the landing gear 10 is provided with a plurality of hollowed portions 13 along the length direction thereof, so that the requirement of light weight can be met. Each part of the quick release assembly 20 can be made of aluminum alloy materials, and the requirements of structural strength and light weight can be met.

Referring to fig. 4 and 5, an embodiment of the present invention further provides a drone 200, which may be a fixed-wing drone, a multi-rotor drone, a vertical take-off and landing fixed-wing drone, a hybrid-wing drone, or other model equipment. In the example shown in the figures, the drone 200 is a vertical take-off and landing fixed wing drone, and the drone 200 includes a fuselage 91, an arm 92 provided to the fuselage 91, a fixed wing 93, and a landing gear structure 100 mounted to the arm 92. Optionally, a propeller 94 is further provided at the rear of the body 91 as a power device for the fixed wing 93, and the fixed wing 93 is detachably mounted on the body 91. It should be noted that the description of the landing gear structure 100 in the above embodiments and embodiments also applies to the drone 200 according to the embodiment of the present invention. The first mounting portion 21 of the quick release assembly 20 of the landing gear structure 100 is connected to the horn 92.

In the unmanned aerial vehicle 200 according to the embodiment of the invention, the undercarriage 10 of the undercarriage structure 100 is inserted into the slot 23 of the second mounting portion 22 of the quick release assembly 20 through the insertion portion 11, and is fixedly connected with the second mounting portion 22 through the fixing member 24, so as to be connected with the quick release assembly 20, and then is connected with the horn 92 of the unmanned aerial vehicle 200 through the first mounting portion 21 of the quick release assembly 20, so as to mount the undercarriage 10 on the horn 92. When the landing gear 10 needs to be disassembled, the insertion part 11 of the landing gear 10 is pulled out from the insertion groove 23 of the second mounting part 22 of the quick release assembly 20, so that the landing gear 10 and the horn 92 are disassembled. Simple structure, high reliability and easy disassembly and assembly.

As described in conjunction with fig. 4 to 6, in an alternative embodiment, the number of the booms 92 is two, the booms are symmetrically disposed on two sides of the fuselage 91, two landing gear structures 100 are disposed on each of the booms 92, the two landing gear structures 100 are disposed on the corresponding booms 92 in tandem, and the landing gear structures 100 disposed on the two booms 92 are both disposed to be inclined outward relative to the axial direction of the fuselage 91, and are arranged in an overall shape like an outer "eight", so that when the unmanned aerial vehicle 200 is placed on the ground, the stability of the whole unmanned aerial vehicle can be greatly increased.

Referring to fig. 7, in an alternative embodiment, a top of the body 91 is provided with a receiving cavity for receiving electronic components, an opening of the receiving cavity is detachably covered with a hatch 95, an inner wall of the hatch 95 is provided with a lining plate 96, and the lining plate 96 partially protrudes from the hatch 95. The hatch 95 covers the accommodation chamber after being attached to the body 91, and can enclose the electronic components inside the body 91. The electronic components may include a battery, a GPS module, a 4G module, a satellite module, a master control module, and the like. Alternatively, the hatch 95 and the fuselage 91 may be removably attached using snap-fit structures such as snap-fit fasteners.

By providing the liner 96 at the inner wall of the hatch 95 so as to partially protrude from the hatch 95, the area of connection between the hatch 95 and the fuselage 91 can be increased. After the hatch 95 is connected with the fuselage 91, the part of the lining plate 96 protruding out of the hatch 95 can be filled in the gap between the hatch 95 and the fuselage 91 to form a stop, so that no break difference is generated between the hatch 95 and the fuselage 91 after installation, and the hatch 95 is prevented from separating from the fuselage 91 in the flying process of the unmanned aerial vehicle 200.

Although the embodiments of the present invention have been disclosed with reference to the above-mentioned embodiments, the present invention is not limited to the above-mentioned embodiments, and those skilled in the art can make various changes and modifications which are equivalent to those of the above-mentioned embodiments without departing from the scope of the embodiments of the present invention.

The disclosure of this patent document contains material which is subject to copyright protection. The copyright is owned by the copyright owner. The copyright owner has no objection to the facsimile reproduction by anyone of the patent document or the patent disclosure, as it appears in the patent and trademark office official records and records.