CN215436955U

CN215436955U - Aircraft

Info

Publication number: CN215436955U
Application number: CN202120345872.7U
Authority: CN
Inventors: 敬鹏生; 胡海
Original assignee: Hanwang Technology Co Ltd
Current assignee: Hanwang Technology Co Ltd
Priority date: 2021-02-07
Filing date: 2021-02-07
Publication date: 2022-01-07
Anticipated expiration: 2031-02-07

Abstract

The utility model relates to an aircraft comprising: the nose is arranged at the front end of the aircraft and used for pointing to the flight direction of the aircraft; the machine body is connected with the machine head, and a mounting hole for mounting the battery pack is formed in the machine body; the battery component is detachably arranged on the aircraft body through the mounting hole and used for supplying power to the aircraft; wherein the battery pack includes a battery and a case, at least one outer surface of the case becomes a portion of a corresponding one of outer surfaces of the body when the battery pack is mounted to the body through the mounting hole.

Description

Aircraft

Technical Field

The utility model relates to the field of aircrafts, in particular to an aircraft with a battery assembly capable of being replaced conveniently.

Background

In recent years, aircraft have become more and more popular. Existing aircraft are largely classified into winged aircraft and wingless aircraft. Winged aircraft include fixed-wing aircraft, such as gliders, and moving-wing aircraft, such as rotary-wing aircraft and ornithopters. The existing aircraft generally welds the battery for supplying power to the aircraft directly on the circuit board in the aircraft, and although the battery assembly mode ensures the stable connection between the battery and the circuit board and the integrity of the appearance of the aircraft, the battery cannot be replaced by a new battery when the battery is exhausted or damaged, thereby affecting the experience of consumers.

Disclosure of Invention

Based on the above, the utility model provides an aircraft, which is convenient for replacing a battery on the basis of ensuring the complete appearance of the aircraft.

The utility model discloses an aircraft, comprising: the nose is arranged at the front end of the aircraft and used for pointing to the flight direction of the aircraft; the machine body is connected with the machine head, and a mounting hole for mounting the battery pack is formed in the machine body; the battery component is detachably arranged on the aircraft body through the mounting hole and used for supplying power to the aircraft; wherein the battery pack includes a battery and a case, at least one outer surface of the case becomes a portion of a corresponding one of outer surfaces of the body when the battery pack is mounted to the body through the mounting hole.

According to the aircraft provided by the utility model, the battery assembly is arranged on the fuselage through the mounting hole, and at least one outer surface of the shell of the battery assembly can be part of one corresponding outer surface of the fuselage, so that the aircraft provided by the utility model can ensure the complete appearance of the aircraft and can be used for conveniently replacing the battery, and the service life of the aircraft is prolonged.

Drawings

The above and other objects, features and advantages of the present invention will become more apparent by describing in more detail embodiments of the present invention with reference to the attached drawings. The accompanying drawings are included to provide a further understanding of embodiments of the utility model, and are incorporated in and constitute a part of this specification. The drawings together with the embodiments of the utility model serve to explain the utility model, but do not constitute a limitation of the utility model. In the drawings, like reference numerals refer to like parts, steps or elements unless otherwise explicitly indicated. In the drawings, there is shown in the drawings,

FIG. 1 illustrates an example of an aircraft according to an embodiment of the utility model;

FIG. 2 shows a view in which at least one exterior surface of a battery assembly and an exterior surface opposite thereto are both integral with an exterior surface of an aircraft, according to an embodiment of the utility model;

fig. 3 shows an example of a battery assembly according to an embodiment of the utility model;

FIG. 4 illustrates another example of an aircraft according to an embodiment of the utility model.

Detailed Description

The technical scheme of the utility model is clearly and completely described in the following with reference to the accompanying drawings. It is to be understood that the embodiments described are only a few embodiments of the present invention, and not all embodiments. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, belong to the scope of the present invention.

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 orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element being referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance. Also, the use of the terms "a," "an," or "the" and similar referents do not denote a limitation of quantity, but rather denote the presence of at least one. The word "comprising" or "comprises", and the like, means that the element or item appearing before the word covers the element or item listed after the word and its equivalents, but 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.

In the description of the present invention, it is to be noted that the terms "mounted," "connected," and "connected" are to be construed broadly unless otherwise specifically stated or limited. For example, the connection can be fixed, detachable or integrated; 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 meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.

In addition, the technical features involved in the different embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.

FIG. 1 illustrates an example of an aircraft according to an embodiment of the utility model. As shown in fig. 1, an aircraft (e.g., an ornithopter) according to an embodiment of the utility model may include: a nose 110 disposed at a front end of the aircraft for pointing in a flight direction of the aircraft; the machine body 120 is connected with the machine head 110, and the machine body 120 is provided with a mounting hole 121 for mounting a battery pack; and a battery assembly 130 detachably mounted to the fuselage 120 through the mounting hole 121 for supplying power to the aircraft. The battery assembly 130 includes a battery (not shown) and a housing 131. When the battery assembly 130 is mounted on the body 120 through the mounting hole 121, at least one outer surface of the housing 131, for example, the first outer surface 131_1 in fig. 1, becomes a portion of a corresponding one of the outer surfaces of the body 120, and as described in fig. 2, after the battery assembly 130 is mounted on the body 120 through the mounting hole 121, the first outer surface 131_1 and/or the second outer surface 131_2 of the housing 131 become a portion of the outer surface of the body 120.

According to the aircraft disclosed by the utility model and described in connection with fig. 1 and 2, as the battery assembly can be mounted on the fuselage through the mounting hole and at least one outer surface of the housing of the battery assembly can be a part of a corresponding outer surface of the fuselage, the aircraft provided by the utility model can ensure complete appearance of the aircraft and can be conveniently replaced with batteries, and user experience is increased. In addition, the service life of the aircraft can be prolonged, because the batteries welded inside the aircraft are aged with the increase of charging times relative to the aircraft with the batteries welded on the circuit board, so that the stored electricity of the batteries is reduced, the flying time of the aircraft is shortened, common consumers cannot replace the batteries by themselves, and the service life of the batteries is the service life of the aircraft. In addition, compared with a common battery mounting hole with a shell, the battery assembly of the aircraft is directly mounted on the aircraft through the mounting hole without the shell on the aircraft body, so that the aircraft is convenient to manufacture (namely, the complicated battery mounting hole does not need to be manufactured in the manufacturing process) and a user can conveniently replace the battery.

Regarding the mounting hole 121, in one embodiment, the mounting hole 121 may include a groove provided on the body 120 to fit the shape and size of the battery assembly 130, and the battery assembly 130 is placed in the groove. In another embodiment, the mounting hole 121 may include a through-hole slot extending through the fuselage 120 in a direction perpendicular to the axis of the fuselage 120, the through-hole slot being sized to fit the battery assembly 130, the battery assembly 130 being disposed within the through-hole slot, and at least one outer surface of the battery assembly 130 and an outer surface opposite thereto, such as the first outer surface 131_1 and the second outer surface 131_2 shown in fig. 2, may be integral with the outer surface of the aircraft. This arrangement may facilitate removal of the battery. Specifically, for example, the battery assembly 130 can be easily removed by pressing the pressing position 200 shown in fig. 2, in this embodiment, the pressing position 200 is the second outer surface 131_2 of the battery assembly 130.

In one embodiment, at least one outer surface of the housing 131, for example, the first outer surface 131_1 illustrated in fig. 1, or the edge structure of both the first outer surface 131_1 and the second outer surface 131_2 illustrated in fig. 2, may be adapted to the opening of the mounting hole 121, such that the at least one outer surface of the housing 131 is integrated with the outer surface of the body 120 where the opening of the mounting hole 121 is located. This further increases the integrity of the outer shape of the aircraft. Further, the battery assembly 130 and the mounting hole 121 may be zero-clearance fitted, which may allow the battery assembly 130 to be more stably mounted to the body 120.

Furthermore, in one embodiment, at least one outer surface of the housing 131 of the battery assembly 130, such as the first outer surface 131_1 shown in fig. 1, is non-rotationally symmetric. For example, two end surfaces of the first outer surface 131_1 of the housing 131 in the axial direction of the body 120 are non-rotationally symmetric, for example, the first end surface 131_1a and the second end surface 131_1b shown in fig. 1 are different in size, so that the first outer surface 131_1 is non-rotationally symmetric. In the present invention, non-rotational symmetry means that, for a rotation of 0 ° -360 ° (including 0 ° and 360 °), the rotation is not coincident with the rotation before, unless rotated by 0 ° or 360 °. For example, a trapezoid is not rotationally symmetric, whereas a rectangle is rotationally symmetric, and when the rectangle is rotated by 180 °, the rotated rectangle coincides with the rotated rectangle before rotation. The non-rotational symmetrical form of at least one outer surface of the case 131 of the battery pack 130 may allow the battery pack to be mounted without a wrong mounting direction, and thus may further facilitate the mounting of the battery by a user.

Fig. 3 shows an example of a battery assembly according to an embodiment of the present invention. As shown in fig. 3, the case 131 of the battery assembly 130 according to the present invention may include a first case 131_3 and a second case 131_4 that are separable. One surface of the first housing 131_3 may correspond to the first outer surface 131_1 described above, and one surface of the first housing 131_3 becomes a portion of the corresponding outer surface of the body 120 when the battery assembly 130 is installed on the aircraft. One surface of the second housing 131_4 may correspond to the second outer surface 131_2 described above. When the battery pack 130 is mounted on the aircraft, one surface of the second housing 131_4 becomes a portion of the corresponding outer surface of the body 120. For example, when the mounting hole 121 includes a through hole penetrating the body 120 in a direction perpendicular to the axial direction of the body 120, one surface of the first housing 131_3 and one surface of the second housing 131_4 become a part of the outer surface of the body 120.

In one embodiment, the first housing 131_3 and the second housing 131_4 are combined to form a closed space, for example, the first housing 131_3 and the second housing 131_4 include screw holes corresponding to positions, the first housing 131_3 and the second housing 131_4 are combined and fixed by bolts matched with the screw holes, and a battery (not shown) is disposed in the closed space. The battery pack 130 may include a connector plug 131_5, and the connector plug 131_5 is connected to a battery. Alternatively, a part of the connector plug 131_5 is exposed outside the second housing 131_4, as shown in fig. 3. Accordingly, the aircraft may include a connector receptacle, such as connector receptacle 122_1 shown in fig. 4, disposed within mounting hole 121 and mated with connector plug 131_ 5. The position of the connector receptacle 122_1 corresponds to the position of the connector plug 131_5 of the battery assembly 130. In one embodiment, the connector plug 131_5 and the connector receptacle 122_1 may be an sh1.0mm connector plug and its stand-off receptacle. By using the SH1.0mm connector plug and the vertical-pasting socket thereof, the battery can not easily loosen and slide out due to vibration in the flying process of the aircraft, and the user experience is improved.

Further, the housing 131 may include a first fixing member 131_ 6. Accordingly, the aircraft may include a second fixing member 122_2 provided in the mounting hole 121 to be engaged with the first fixing member 131_6, as shown in fig. 4. The position of the first fixing member 131_6 corresponds to the position of the second fixing member 122_ 2. The battery assembly 130 is fixed in the aircraft by the cooperation of at least the first fixing member 131_6 and the second fixing member 122_ 2. This arrangement may further enhance the securement between the battery assembly 130 and the aircraft, increasing the safety of the user in using the aircraft. In one embodiment, the first fixing member 131_6 may include a limit protrusion, which may be disposed on an outer surface of the housing 131 in an axial direction of the body 120 and away from the handpiece. The second fixing member 122_2 may include a limiting groove, and the groove may be disposed in the mounting hole 121 along the axial direction of the body 120 and away from the inner surface of the head. The limiting protrusion is matched with the limiting groove, and the size of the limiting groove is smaller than that of the mounting hole 121 along the axis direction perpendicular to the machine body 120, so that the occupied space of the limiting protrusion and the limiting groove for the mounting hole 121 is saved. It should be understood that the foregoing description of the first fixing member 131_6 and the second fixing member 122_2 is only an example, and not a limitation of the present invention. Those skilled in the art may arrange suitable fasteners and install them in suitable locations, such as by the engagement of nuts and bolts, depending on the characteristics of the aircraft and design requirements, etc.

Alternatively, as shown in fig. 3, the first housing 131_3 and the second housing 131_4 are not exactly the same size. For example, the second housing 131_4 is sized to accommodate a battery, and a portion of the first housing 131_3 and the second housing 131_4 are sized to constitute an enclosed space for accommodating the battery in combination with the second housing 131_ 4. In this embodiment, the connector plug 131_5 is disposed at one end of the first housing 131_3 close to the handpiece 110, and the first fixing member 131_6 is disposed at one end of the first housing 131_3 away from the handpiece 110, so that the length of the first housing 131_3 is greater than that of the second housing 131_4 in the axial direction of the body 120, and this design can prevent the front and back sides (the sides where the first housing 131_3 and the second housing 131_4 are located) from being erroneously mounted when the battery pack 130 is mounted in the mounting hole 121, thereby facilitating accurate mounting of the battery pack 130. Accordingly, the size of the mounting hole 121 fitted with the first and second cases 131_3 and 131_4 of the battery assembly 130 is also adjusted. The above-mentioned structural arrangement form that the sizes of the first housing 131_3 and the second housing 131_4 are not exactly the same is only an example, and is not a limitation of the present invention.

So far, the aircraft according to the present invention has been described with reference to fig. 1 to 4, and according to the aircraft according to the embodiment of the present invention, since the battery assembly is mounted on the fuselage through the mounting hole, and at least one outer surface of the housing of the battery assembly can become a part of a corresponding one of the outer surfaces of the fuselage, after the battery assembly is mounted on the aircraft, the housing of the battery assembly becomes a part of the outer surface of the aircraft, and there is no height difference at the junction with the fuselage of the aircraft, so that the outer surface of the whole housing of the aircraft after the battery assembly is mounted is smooth, which can ensure the complete appearance of the aircraft and facilitate battery replacement, thereby increasing the service life of the aircraft.

It is also to be understood that the above description is only exemplary of the embodiments of the utility model and is intended as a definition of the limits of the utility model. It will be appreciated by those skilled in the art that the scope of the disclosure herein is not limited to the particular combination of features described above, but also encompasses other embodiments in which any combination of the features described above or their equivalents is encompassed without departing from the spirit of the disclosure. For example, the above features and (but not limited to) features having similar functions disclosed in the present invention are mutually replaced to form the technical solution.

Further, while operations are depicted in a particular order, this should not be understood as requiring that such operations be performed in the particular order shown or in sequential order. Under certain circumstances, multitasking and parallel processing may be advantageous. Likewise, while several specific implementation details are included in the above discussion, these should not be construed as limitations on the scope of the utility model. Certain features that are described in the context of separate embodiments can also be implemented in combination in a single embodiment. Conversely, various features that are described in the context of a single embodiment can also be implemented in multiple embodiments separately or in any suitable subcombination.

Although the subject matter has been described in language specific to structural features and/or methodological acts, it is to be understood that the subject matter defined in the appended claims is not necessarily limited to the specific features or acts described above. Rather, the specific features and acts described above are disclosed as example forms of implementing the claims.

Claims

1. An aircraft, characterized in that it comprises:

the nose is arranged at the front end of the aircraft and used for pointing to the flight direction of the aircraft;

the machine body is connected with the machine head, and a mounting hole for mounting a battery assembly is formed in the machine body;

the battery assembly is detachably arranged on the aircraft body through the mounting hole and is used for supplying power to the aircraft; wherein,

the battery pack includes a battery and a case, and at least one outer surface of the case becomes a part of a corresponding one of outer surfaces of the body when the battery pack is mounted on the body through the mounting hole.

2. The aircraft of claim 1, wherein the edge structure of the at least one outer surface of the skin is adapted to the opening of the mounting hole such that the at least one outer surface of the skin is integral with an outer surface of the fuselage in which the opening of the mounting hole is located.

3. The aircraft of claim 1, wherein the at least one outer surface of the outer shell is non-rotationally symmetric.

4. The aircraft of claim 3, wherein two end faces of the skin in the axial direction of the fuselage are of different sizes.

5. The aircraft of claim 1, wherein the enclosure comprises first and second separable enclosures, the first and second enclosures combining to form an enclosed space, the battery being disposed within the enclosed space, and an exterior surface of the first enclosure being a portion of the corresponding exterior surface of the fuselage.

6. The aircraft of claim 5, wherein the battery assembly comprises a connector plug connected to the battery and having a portion thereof exposed outside the second enclosure; the aircraft comprises a connector socket which is arranged in the mounting hole and matched with the connector plug, and the position of the connector socket corresponds to the position of the connector plug of the battery pack.

7. The aircraft of claim 1, wherein the battery assembly is a zero clearance fit with the mounting hole.

8. The aircraft of claim 1, wherein the outer shell comprises a first fastener, the aircraft comprises a second fastener disposed within the mounting hole that mates with the first fastener, the first fastener being positioned to correspond to the second fastener, and the battery assembly is secured to the aircraft by mating at least the first fastener with the second fastener.

9. The aircraft of claim 8, wherein the first fixing member comprises a limiting protrusion disposed on the outer shell along an axial direction of the fuselage and away from an outer surface of the nose, the second fixing member comprises a limiting groove disposed on the mounting hole along the axial direction of the fuselage and away from an inner surface of the nose, and a dimension of the limiting groove in a direction perpendicular to the axial direction is smaller than a dimension of the mounting hole.

10. The aircraft according to any one of claims 1 to 9, wherein said mounting hole comprises a recess provided on said fuselage, adapted to the shape and size of said battery assembly, said battery assembly being placed in said recess.

11. The aircraft of any one of claims 1 to 9, wherein the mounting hole comprises a through-slot extending through the fuselage in a direction perpendicular to an axis of the fuselage, the through-slot being shaped and dimensioned to accommodate the battery assembly, the battery assembly being disposed within the through-slot, and the at least one outer surface of the battery assembly and an outer surface opposite thereto each being integral with an outer surface of the aircraft.