阅读说明：本技术 无人机 (Unmanned plane ) 是由 于建方 王坤殿 李璐鑫 莫颂权 于 2018-09-17 设计创作，主要内容包括：一种无人机(100),包括机身(10),所述机身(10)上设有用于收容电子元件(90)的收容腔(20),所述收容腔(20)的开口可拆卸地盖设有舱盖(30),所述舱盖(30)的内壁设有衬板(40),所述衬板(40)部分凸出于所述舱盖(30)。通过在舱盖(30)的内壁设置部分凸出于舱盖(30)的衬板(40),可以增大舱盖(30)与机身(10)之间的连接面积。当舱盖(30)与机身(10)连接后,衬板(40)凸出于舱盖(30)的部分可以填充在舱盖(30)与机身(10)之间的间隙处形成止挡,进而保证舱盖(30)与机身(10)之间在安装后无断差,以避免舱盖(30)在无人机(100)飞行过程中脱离机身(10)。(The utility model provides an unmanned aerial vehicle (100), includes fuselage (10), be equipped with on fuselage (10) and be used for acceping chamber (20) of acceping electronic component (90), the opening detachably lid of acceping chamber (20) is equipped with cabin cover (30), the inner wall of cabin cover (30) is equipped with welt (40), welt (40) part protrusion in cabin cover (30). The connection area between the hatch cover (30) and the fuselage (10) can be increased by arranging a lining plate (40) on the inner wall of the hatch cover (30), the part of which protrudes from the hatch cover (30). After the cabin cover (30) is connected with the fuselage (10), the part of the lining plate (40) protruding out of the cabin cover (30) can be filled in a gap between the cabin cover (30) and the fuselage (10) to form a stop, so that no break difference exists between the cabin cover (30) and the fuselage (10) after installation, and the cabin cover (30) is prevented from being separated from the fuselage (10) in the flying process of the unmanned aerial vehicle (100).)

1. The unmanned aerial vehicle is characterized by comprising a body, wherein an accommodating cavity for accommodating electronic elements is formed in the body, a hatch cover is detachably covered on an opening of the accommodating cavity, a lining plate is arranged on the inner wall of the hatch cover, and part of the lining plate protrudes out of the hatch cover.

2. The unmanned aerial vehicle of claim 1, wherein symmetrical lining plates are arranged on two sides of the inner wall of the hatch cover, and the shape of the lining plates is matched with the shape of the profile of the side part of the hatch cover.

3. The drone of claim 1, wherein the hatch is an arched structure, the middle of the hatch being arched outward forming an arch.

4. The drone of claim 1, wherein the hatch is provided with a first mounting portion and the patch is provided with a second mounting portion that mates with the first mounting portion.

5. Unmanned aerial vehicle according to claim 4, characterized in that the first assembly part is provided with a pin/box and the second assembly part is provided with a box/pin.

6. The drone of claim 4, wherein the first fitting portion is plural, arranged at intervals along a side profile of the hatch.

7. The unmanned aerial vehicle of claim 1, wherein a side wall of the housing cavity is provided with a first boss portion, and a side portion of the hatch is provided with a second boss portion that mates with the first boss portion.

8. Unmanned aerial vehicle according to claim 1, wherein the hatch is provided with a locking structure comprising a lock cooperating with the fuselage.

9. The drone of claim 8, wherein the locking member is rotatably disposed on an inner wall of the hatch.

10. The unmanned aerial vehicle of claim 9, wherein a through hole is formed in a surface of the hatch, the locking structure further comprises a rotating member inserted into the through hole, the rotating member is rotatable relative to the through hole, and a side of the rotating member close to an inner wall of the hatch is connected with the locking member.

11. The drone of claim 10, wherein a side of the rotating member proximate the hatch outer wall is provided with a rotating portion.

Technical Field

The embodiment of the invention relates to the technical field of unmanned flight, in particular to an unmanned aerial vehicle.

Background

Usually unmanned aerial vehicle's top all can set up the hatch cover, and the hatch cover can arouse forming great disconnected difference or even break away from the fuselage between hatch cover and the organism because the deformation of fuselage in the in-process that unmanned aerial vehicle flies, is the long-term problem that exists in this field.

It is now common practice to provide several spot-mounted fasteners on the deck lid, which forcibly fasten the deck lid to the body. However, this approach has the following disadvantages: (1) the installed fastener can inevitably protrude out of the machine body, the consistency of the surface of the machine body is damaged, and the appearance is influenced. (2) The fastener protrudes out of the airframe, so that the aerodynamic layout of the airframe is damaged, and the flight performance of the airplane is affected.

Disclosure of Invention

The embodiment of the invention provides an unmanned aerial vehicle, which can ensure that no offset exists between a cabin cover and a body of the unmanned aerial vehicle after installation, so as to prevent the cabin cover from separating from the body in the flight process of the unmanned aerial vehicle.

The unmanned aerial vehicle provided by the embodiment of the invention comprises a body, wherein an accommodating cavity for accommodating electronic components is arranged on the body, a hatch cover is detachably covered on an opening of the accommodating cavity, a lining plate is arranged on the inner wall of the hatch cover, and the lining plate partially protrudes out of the hatch cover.

Furthermore, the two sides of the inner wall of the hatch cover are provided with the symmetrical lining plates, and the shape of the lining plates is matched with the shape of the profile of the side part of the hatch cover.

Further, the hatch cover is of an arched structure, and the middle of the hatch cover is arched outwards to form an arched part.

Further, the inner wall of the hatch cover is provided with a first assembling portion, and the lining plate is provided with a second assembling portion matched with the first assembling portion.

Further, the first assembling portion is provided with a male buckle/female buckle, and the second assembling portion is provided with a female buckle/male buckle.

Further, the first assembling portion is a plurality of, and is arranged at intervals along the side profile of the hatch cover.

Further, a first boss portion is arranged on the side wall of the accommodating cavity, and a second boss portion matched with the first boss portion is arranged on the side portion of the hatch cover.

Further, the hatch is provided with a locking structure comprising a locking element cooperating with the fuselage.

Further, the locking piece is rotatably arranged on the inner wall of the hatch cover.

Furthermore, a through hole is formed in the surface of the hatch cover, the locking structure further comprises a rotating piece which is arranged in the through hole in a penetrating mode, the rotating piece can rotate relative to the through hole, and one side, close to the inner wall of the hatch cover, of the rotating piece is connected with the locking piece.

Further, a rotating part is arranged on one side, close to the outer wall of the hatch cover, of the rotating part.

According to the unmanned aerial vehicle disclosed by the embodiment of the invention, the lining plate partially protruding out of the hatch cover is arranged on the inner wall of the hatch cover, so that the connection area between the hatch cover and the vehicle body can be increased. After the hatch cover is connected with the fuselage, the part of the lining plate protruding out of the hatch cover can be filled in the gap between the hatch cover and the fuselage to form a stop, so that no offset exists between the hatch cover and the fuselage after installation, and the hatch cover is prevented from being separated from the fuselage in the flight process of the unmanned aerial vehicle.

Drawings

Fig. 1 is a schematic perspective view of an unmanned aerial vehicle according to an embodiment of the present invention.

Fig. 2 is an exploded schematic view of an unmanned aerial vehicle according to an embodiment of the present invention.

Fig. 3 is a top view of an unmanned aerial vehicle according to an embodiment of the present invention.

Fig. 4 is an enlarged schematic view of the hatch and fuselage of the drone shown in fig. 3.

Fig. 5 is a side view of the utility model discloses an unmanned aerial vehicle is shown.

Fig. 6 is an exploded schematic view of the drone shown in fig. 5.

Fig. 7 is a front view of a drone according to an embodiment of the present invention.

Fig. 8 is an exploded schematic view of the drone shown in fig. 7.

Fig. 9 is an enlarged schematic view of the hatch and fuselage of the drone shown in fig. 7.

Fig. 10 is a partially enlarged schematic view of the drone shown in fig. 9.

Fig. 11 is a schematic structural diagram of a locking structure of an unmanned aerial vehicle according to an embodiment of the present invention.

Fig. 12 is a schematic view of a locking structure of a hatch cover of an unmanned aerial vehicle when connected with a fuselage according to an embodiment of the invention.

Fig. 13 is a schematic view of a locking structure of an unmanned aerial vehicle when a hatch cover is separated from a fuselage according to an embodiment of the invention.

Fig. 14 is a schematic structural diagram of a landing gear of an unmanned aerial vehicle according to an embodiment of the present invention.

Fig. 15 is an exploded view of a landing gear of a drone 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 unmanned aerial vehicle, which can ensure that no offset exists between a cabin cover and a body of the unmanned aerial vehicle after installation, so as to prevent the cabin cover from separating from the body in the flight process of the unmanned aerial vehicle. The unmanned aerial vehicle according to the embodiment of the invention is 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 8, an embodiment of the present invention provides a drone 100, 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 figure, the drone 100 is a vertical take-off and landing fixed wing drone, the drone 100 includes a fuselage 10, a fixed wing 11 disposed on the fuselage 10, and two arms 12 symmetrically disposed on the fuselage 10, a plurality of rotors 13 and a plurality of landing gears 14 may be disposed on the arms 12, and a propeller 15 is further disposed at the tail of the fuselage 10 as a power device for the fixed wing 11. Alternatively, the stationary vane 11 is detachably mounted on the body 10.

The electronic component protection device is characterized in that a containing cavity 20 for containing an electronic component 90 is arranged on the machine body 10, a hatch 30 is detachably covered on an opening of the containing cavity 20, a lining plate 40 is arranged on the inner wall of the hatch 30, and part of the lining plate 40 protrudes out of the hatch 30. The hatch 30 is attached to the body 10 to cover the accommodation chamber 20, so as to enclose the electronic component 90 inside the body 10. Optionally, the housing cavity 20 is located at the top of the fuselage 10. The electronic components 90 may include a battery, a GPS module, a 4G module, a satellite module, a master control module, and the like.

According to the unmanned aerial vehicle 100 provided by the embodiment of the invention, the lining plate 40 partially protruding out of the hatch cover 30 is arranged on the inner wall of the hatch cover 30, so that the connection area between the hatch cover 30 and the vehicle body 10 can be increased. After the hatch cover 30 is connected with the fuselage 10, the part of the lining plate 40 protruding out of the hatch cover 30 can be filled in the gap between the hatch cover 30 and the fuselage 10 to form a stop, so that no break difference exists between the hatch cover 30 and the fuselage 10 after installation, and the hatch cover 30 is prevented from being separated from the fuselage 10 in the flying process of the unmanned aerial vehicle 100.

In an alternative embodiment, the lining plate 40 is a whole carbon fiber plate with a thickness of 0.5mm and is fixed on the inner side of the hatch cover 30, and the carbon fiber plate with a thickness of 0.5mm can ensure sufficient flexibility in the longitudinal direction while ensuring the transverse strength, and can be easily attached to the hatch cover 30 with a three-dimensional curved surface structure. The portion of the edge of the liner 40 protruding from the hatch 30 has a sufficient contact area to ensure that no break occurs between the hatch 30 and the fuselage 10.

In an alternative embodiment, as shown in fig. 2 and 4, the inner wall of the hatch 30 is provided with symmetrical lining plates 40 on both sides, and the shape of the lining plates 40 is adapted to the shape of the side profile of the hatch 30 to ensure complete filling of the gap between the hatch 30 and the fuselage 10.

Further, as shown in fig. 8, the hatch 30 has an arched structure, and an arched portion 31 is formed at the middle of the hatch 30 and arched outward, so that the hatch 30 has a smooth and rounded surface, is full of dynamic feeling, and has good aerodynamic performance.

In the present embodiment, the hatch 30 includes a middle portion 302, and a front end portion 301 and a rear end portion 303 located on both sides of the middle portion 302, wherein a portion of the front end portion 301 close to the middle portion 302, and the rear end portion 303 are all similar rectangular structures, a width of the middle portion 302 is greater than a width of a portion of the front end portion 301 close to the middle portion 302 and a width of the rear end portion 303, and a portion of the front end portion 301 far from the middle portion 302 is a similar tapered structure with a gradually decreasing width. Two liner plates 40 are symmetrically arranged on both sides of the front end portion 301 of the hatch 30, and the shape of the liner plates 40 is adapted to the side profile shape of the front end portion 301 of the hatch 30.

In an alternative embodiment, the hatch 30 is provided with a first fitting part 32 and the lining 40 is provided with a second fitting part 41 cooperating with the first fitting part 32. The hatch 30 and the lining panel 40 are connected to each other by the mutual cooperation of the first fitting portion 32 and the second fitting portion 41. In the example shown in the figure, the first fitting portions 32 are plural, are arranged on the hatch 30 at intervals along the side profile of the front end portion 301 of the hatch 30, and the second fitting portions 41 are identical in number to the first fitting portions 32 and are correspondingly arranged on the liner 40 to ensure the connection strength between the hatch 30 and the liner 40.

Further, the first assembling portion 32 is provided with a male/female buckle, and the second assembling portion 41 is provided with a corresponding female/male buckle, so that the hatch 30 and the lining board 40 are connected to each other by mutually buckling the male buckle and the female buckle (i.e. corresponding to the structural form of the male buckle and the female buckle). In this embodiment, first assembly portion 32 with second assembly portion 41 is the through-hole, the built-in pin thread 34 that is equipped with of first assembly portion 32, the built-in box thread 42 that is equipped with of second assembly hole 41, with pin thread 34 and the mutual lock of box thread 42, can be with hatch cover 30 and welt 40 interconnect, easy and simple to handle, simple structure to the structural style of box can flush with the surface of hatch cover 30 to the at utmost, consequently can not avoid influencing aesthetic property and the aerodynamic performance on fuselage 10 surface. Optionally, the snap fastener is made of a plastic material to meet the requirement of light weight. Of course, the first mounting portion 32 and the second mounting portion 41 can be connected to each other by other rivet-like connecting structures, and the description is not limited thereto.

Referring to fig. 9 and 10, in an alternative embodiment, the side wall of the receiving cavity 20 is provided with a first boss portion 21, and the side portion of the hatch 30 is provided with a second boss portion 33 which is matched with the first boss portion 21. The first boss portion 21 and the second boss portion 33 are engaged with each other, whereby the freedom of movement of the hatch 30 into the housing chamber 20 can be restricted. The liner 40 can be well attached to the inner side of the hatch 30 due to the deformability of the liner, and the hatch 30 is limited from moving freely in a direction away from the fuselage 10, so that the hatch 30 can be well attached to the fuselage 10. Furthermore, the corresponding boss surfaces formed between the first boss portion 21 and the second boss portion 33 can also serve as sliding grooves to enable the hatch 30 to be slidably fitted to the fuselage 10.

Referring to fig. 11 to 13, in an alternative embodiment, the hatch 30 is provided with a locking structure 50, the locking structure 50 includes a locking member 51 engaged with the fuselage 10, and the locking member 51 is rotatably provided on the inner wall of the hatch 30. The locking member 51 may be directly connected to and engaged with the main body 10, or a structure for engaging with the locking member 51 may be provided inside the main body 10.

In this embodiment, the inside of the body 10 may be provided with a slot to be engaged with the locking member 51. When it is necessary to attach the hatch 30 to the opening of the receiving cavity 20 and the fuselage 10, the locking member 51 may be rotated to the state shown in fig. 12, and the locking member 51 may be engaged in the slot inside the fuselage 10, thereby fixing the hatch 30 and the fuselage 10 to each other. When it is necessary to separate the hatch 30 from the fuselage 10, the locking piece 51 may be rotated to the state shown in fig. 13, so that the locking piece 51 is disengaged from the insertion groove inside the fuselage 10, and the hatch 30 may be separated from the fuselage 10, and the hatch 30 may be detached from the fuselage 10. Alternatively, the number of the locking structures 50 may be plural, and the locking structures are provided at intervals on the hatch 30. In the example shown in the figures, the locking structures 50 are three in number and are spaced apart on the rear end 303 of the deck lid 30.

Further, a through hole is formed in the surface of the hatch cover 30, the locking structure 50 further includes a rotating member 52 inserted into the through hole, the rotating member 52 can rotate relative to the through hole, one side of the rotating member 52 close to the inner wall of the hatch cover 30 is connected to the locking member 51, one side of the rotating member 52 close to the outer wall of the hatch cover 30 is provided with a rotating portion 53, and the rotating portion 53 can rotate relative to the through hole to drive the locking member 51 to rotate.

In other embodiments, the fuselage 10 may further have a mounting hole along the fuselage direction, and the hatch 30 may have a resilient structure that restores the deformed locking when the hatch 30 is to be locked by pulling the resilient structure toward the nose direction to mount the locking member 30 in the modified mounting hole. Alternatively, the interior of the fuselage 10 may also be provided with an assembly hole in the longitudinal direction, the locking structure 50 may also include an elastic member disposed on the inner wall of the hatch 30 and engaged with the assembly hole, and after the hatch 30 is assembled on the fuselage 10 in place, the hatch 30 may be pressed downward to engage the elastic member in the assembly hole, thereby fixing the hatch 30 and the fuselage 10 to each other.

Referring to fig. 14 and 15, in an alternative embodiment, the landing gear 14 includes: a landing gear body 141 and a quick release assembly 142, the landing gear 141 being detachably connected to the quick release assembly 142. The landing gear body 141 includes a main body portion 143 and an insertion portion 144 disposed on the main body portion 143, the quick release assembly 142 includes a first mounting portion 145 for connecting with the horn 12 and a second mounting portion 146 connected with the first mounting portion 145, and the second mounting portion 146 is provided with a slot 147 and a fixing member 148 matched with the insertion portion 144. The insertion portion 144 of the landing gear body 141 is inserted into the insertion slot 147 of the quick release assembly 142 and fixed to the second mounting portion 146 by the fixing member 148, thereby mounting the landing gear 14 to the horn 12.

Although the embodiments of the present invention have been disclosed with reference to the above-mentioned embodiments, the invention is not limited to the above-mentioned embodiments, and those skilled in the art can make various changes and modifications to the equivalent embodiments without departing from the scope of the embodiments of the present invention, but all changes, equivalents and modifications to the above-mentioned embodiments that do not depart from the technical spirit of the embodiments of the present invention are deemed to fall within the technical 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.