阅读说明：本技术 飞行器、飞行器的机套和用于更换飞行器的机套的方法 (Aircraft, aircraft holster and method for replacing aircraft holster ) 是由 王彦伟 于 2021-02-10 设计创作，主要内容包括：本公开涉及飞行器、飞行器的机套和用于更换飞行器的机套的方法,该飞行器包括：机头,设置在飞行器的前端,用于指向飞行器的飞行方向；机身,与机头连接,用于安装机翼和尾翼；机套,用于包覆机头和/或机身；其中,机套包括机头套和/或机身套；机头套设置有第一开口,通过该第一开口将机头套套装于机头,使得机头套包覆机头；机身套设置有第二开口,通过该第二开口将机身套套装于机身,使得机身套包覆机身。(The present disclosure relates to an aircraft, a holster of an aircraft and a method for replacing a holster of an aircraft, the 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 fuselage is connected with the nose and used for mounting wings and empennages; the machine sleeve is used for coating the machine head and/or the machine body; wherein the machine cover comprises a machine head cover and/or a machine body cover; the machine head sleeve is provided with a first opening, and the machine head sleeve is sleeved on the machine head through the first opening, so that the machine head sleeve covers the machine head; the fuselage sleeve is provided with a second opening, and the fuselage sleeve is sleeved on the fuselage through the second opening, so that the fuselage sleeve covers the fuselage.)

1. An aircraft, the 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 fuselage is connected with the nose and used for mounting wings and empennages;

the machine sleeve is used for coating the machine head and/or the machine body; wherein the content of the first and second substances,

the machine cover comprises a machine head cover and/or a machine body cover;

when the machine cover comprises a machine head cover, the machine head cover is provided with a first opening, and the machine head cover is sleeved on the machine head through the first opening, so that the machine head cover covers the machine head;

when the machine sleeve comprises a machine body sleeve, the machine body sleeve is provided with a second opening, and the machine body sleeve is sleeved on the machine body through the second opening, so that the machine body sleeve covers the machine body.

2. The aircraft of claim 1, wherein the holster is fixedly secured to the nose and/or the fuselage.

3. The aircraft of claim 2, wherein the fixed cladding of the holster to the nose and/or the fuselage comprises: the machine sleeve is fixedly coated on the machine head and/or the machine body in at least one of buckling, bonding, pressing, clamping and threaded connection.

4. The aircraft of claim 1, wherein the second opening is provided with an opening and closing structure, and the second opening is opened or closed through the opening and closing structure.

5. The aircraft of claim 4, wherein the opening and closing structure is at least one of a zipper, a hidden button, and a sticker.

6. The aircraft of claim 1, wherein the second opening corresponds to a battery mounting location of the aircraft through which battery replacement of the aircraft is enabled.

7. An aircraft according to claim 1, wherein one or both sides of the fuselage sleeve are provided with a third opening through which the wing is mounted to the fuselage.

8. The aircraft of claim 5, wherein a wing socket for the wing to be mounted on the fuselage is formed on the fuselage, the aircraft further comprises a fixing member disposed corresponding to the wing socket, an accommodating space is formed between an outer edge of the fixing member and the fuselage, the accommodating space is used for accommodating at least a part of an edge of the third opening, and the fixing member comprises an opening matched with the shape of the wing socket.

9. The aircraft of claim 8, wherein the mount comprises at least one first snap for snapping into the wing interface.

10. The aircraft of claim 1, wherein a position of the fuselage sleeve corresponding to the tail wing is provided with a fourth opening through which the tail wing is mounted to the fuselage.

11. The aircraft of claim 1, wherein the upper fuselage sleeve is provided with at least one opening, and at least one connection piece of the upper fuselage side for connection to a wing of the aircraft passes through the opening and is connected to the wing of the aircraft.

12. The aircraft of claim 1,

the front side of the fuselage is provided with at least one hole;

the machine body sleeve comprises at least one machine body sleeve hole at a position corresponding to the at least one hole; and is

The aircraft further comprising a shield comprising at least one plug element form-fitting to the at least one aperture,

wherein the at least one plug connector is inserted into the at least one hole through the at least one body sleeve hole.

13. The aircraft of claim 12 wherein the shield further comprises a protective strip that conforms to the front side of the fuselage sleeve, the protective strip sized and shaped to fit the area and shape of contact with the ground when the aircraft lands.

14. The aircraft of claim 12 wherein at least one of the at least one plug elements includes a second snap element for snapping into a corresponding aperture.

15. The aircraft of any one of claims 1 to 14, wherein the nose of the aircraft is integrally formed with the fuselage.

16. The aircraft of any one of claims 1 to 14, wherein at least one of the wing, the empennage, the airframe cover, and the airframe cover are detachable.

17. The aircraft of claim 16, wherein the nose cup is removably coupled to at least one of the nose, the fuselage, and the fuselage cup by a snap fastener.

18. The aircraft according to any one of claims 1 to 14, wherein the interior of the nose casing is filled with a filling, said filling being a material having a cushioning effect.

19. The aircraft of any one of claims 1 to 14, wherein the holster is made of a resilient wear resistant material.

20. The aircraft of any one of claims 1 to 14, wherein the holster is configured with at least one of a material, a shape, a color, a pattern, or a combination of at least two.

21. A holster for an aircraft, the holster intended to cover a nose and/or a fuselage of the aircraft; the machine cover comprises a machine head cover and/or a machine body cover;

when the machine cover comprises a machine head cover, the machine head cover is provided with a first opening, the machine head cover can be sleeved on the machine head through the first opening, and the machine head cover covers the machine head after the machine head cover is sleeved on the machine head; when the machine sleeve comprises a machine body sleeve, the machine body sleeve is provided with a second opening, the machine body sleeve can be sleeved on the machine body through the second opening, the machine body sleeve is sleeved behind the machine body, and the machine body sleeve covers the machine body.

22. The holster of claim 21, wherein the holster is a single color.

23. A method for replacing a holster of an aircraft, the aircraft nose and/or fuselage being covered by a first holster, the method for replacing a first holster covering the aircraft nose and/or fuselage with a second holster, the first holster comprising a first nose holster and/or a first fuselage holster, the second holster comprising a second nose holster and/or a second fuselage holster, the method comprising:

the first head cover which is sleeved on the aircraft head and covers the aircraft head is taken down at least through the first opening of the first head cover;

sleeving the second handpiece sleeve on the handpiece at least through the first opening of the second handpiece sleeve so that the second handpiece sleeve covers the handpiece;

and/or

The first fuselage sleeve which is sleeved on the fuselage of the aircraft and coats the fuselage is taken down at least through the second opening of the first fuselage sleeve;

and sleeving the second machine body sleeve on the machine body at least through a second opening of the second machine body sleeve, so that the machine body is wrapped by the second machine body sleeve.

24. The method of claim 23, wherein the second opening corresponds to a battery mounting location of the aircraft through which battery replacement of the aircraft is enabled.

25. The method of claim 23, wherein,

the first head cover and the second head cover have the same appearance, and/or the first body cover and the second body cover have the same appearance, or

The first machine head sleeve and the second machine head sleeve are different in appearance, and/or the first machine body sleeve and the second machine body sleeve are different in appearance.

26. The method of claim 23, wherein the forward side of the fuselage has at least one aperture, the aircraft further comprising a first or second protection element comprising at least one plug shaped to fit the at least one aperture, the at least one plug of the first or second protection element being inserted into the at least one aperture, the method further comprising:

removing the first protective part by removing the at least one plug-in part of the first protective part from the at least one opening before removing the first fuselage sleeve which is fitted to the fuselage of the aircraft and which encloses the fuselage at least via the second opening of the first fuselage sleeve; and

after the second fuselage sleeve is sleeved on the fuselage at least through the second opening of the second fuselage sleeve, so that the second fuselage sleeve covers the fuselage, the second protection part is installed by inserting the at least one plug connector of the second protection part into the at least one hole.

27. The method of claim 26, wherein the first guard further comprises a first guard bar, the second guard further comprises a second guard bar, the first guard bar conforms to a front side of the first fuselage sleeve, the first and second guard bars are sized and shaped to fit the contact area and shape, respectively, of the ground when the aircraft lands, wherein the first guard bar and the second guard bar are sized and shaped to fit the contact area and shape, respectively, of the ground when the aircraft lands

Removing the first guard further comprises peeling the first guard bar off the first body cover; and is

Mounting the second guard further comprises fitting the second guard bar to a front side of the first body shell or the second body shell.

28. The method of claim 26 or 27, wherein the first and second guard are the same guard.

29. The method of claim 23, wherein one or both sides of the first and second fuselage sleeves are provided with a third opening through which a wing of the aircraft is mounted to the fuselage and a wing receptacle opened in the fuselage, and wherein a fixture is provided at the wing receptacle, an outer edge of the fixture forming a receiving space with the fuselage for receiving at least a portion of an edge of the third opening, and the fixture including an opening shaped to fit the wing receptacle, the method further comprising:

removing at least a portion of an edge of the third opening of the first fuselage sleeve from the accommodation space before removing the first fuselage sleeve fitted to and enveloping the fuselage of the aircraft at least via the second opening of the first fuselage sleeve; and is

After the second fuselage sleeve is sleeved on the fuselage at least through the second opening of the second fuselage sleeve, at least one part of the edge of the third opening of the second fuselage sleeve is plugged into the accommodating space, so that the accommodating space accommodates at least one part of the edge of the third opening of the second fuselage sleeve; alternatively, the first and second electrodes may be,

before the first fuselage sleeve which is sleeved on the fuselage of the aircraft and coats the fuselage is taken down at least through the second opening of the first fuselage sleeve, the fixing piece is separated from the wing socket; and is

After the second fuselage sleeve is fitted to the fuselage at least via the second opening of the second fuselage sleeve, the securing element is arranged at the wing socket such that the receiving space receives at least a part of the edge of the third opening of the second fuselage sleeve.

Technical Field

The utility model relates to an aircraft field, concretely relates to aircraft with machine cover.

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. Current aircraft, shell are mostly hard material or foaming material, do not have the protection device to the aircraft structure when receiving external force, and the outward appearance is single, has influenced the popularization of current aircraft.

Disclosure of Invention

Based on the foregoing, the present disclosure provides a suite of 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 fuselage is connected with the nose and used for mounting wings and empennages; the machine sleeve is used for coating the machine head and/or the machine body; wherein the machine cover comprises a machine head cover and/or a machine body cover; the machine head sleeve is provided with a first opening, and the machine head sleeve is sleeved on the machine head through the first opening, so that the machine head sleeve covers the machine head; the fuselage sleeve is provided with a second opening, and the fuselage sleeve is sleeved on the fuselage through the second opening, so that the fuselage sleeve covers the fuselage.

The present disclosure also provides a holster for an aircraft for covering a nose and/or fuselage of the aircraft; the machine cover comprises a machine head cover and/or a machine body cover; when the machine cover comprises a machine head cover, the machine head cover is provided with a first opening, the machine head can be sleeved on the machine head through the first opening, and the machine head cover covers the machine head after the machine head is sleeved on the machine head; when the machine cover comprises the machine body cover, the machine body cover is provided with a second opening, the machine body can be sleeved on the machine body through the second opening, and the machine body is covered by the machine body cover after the machine body is sleeved on the machine body.

The present disclosure also provides a method for replacing a holster of an aircraft, a nose and/or a fuselage of the aircraft being covered by a first holster, the method for replacing the first holster covering the nose and/or the fuselage of the aircraft with a second holster, the first holster comprising a first nose holster and/or a first fuselage holster, the second holster comprising a second nose holster and/or a second fuselage holster, the method comprising: taking down a first head cover sleeved on a head of the aircraft and covering the head at least through a first opening of the first head cover; sleeving the second head sleeve on the head at least through the first opening of the second head sleeve, so that the second head sleeve covers the head; and/or a first fuselage sleeve which is sheathed on the fuselage of the aircraft and which coats the fuselage is removed at least via the second opening of the first fuselage sleeve; the second fuselage sleeve is sleeved to the fuselage at least through the second opening of the second fuselage sleeve, so that the second fuselage sleeve covers the fuselage.

According to the aircraft of the embodiment of this disclosure, it has the aircraft casing for the outward appearance of aircraft, structure are not fragile, and can play the buffering guard action when the aircraft takes place to strike, thereby factor of safety when having improved the aircraft collision, the part of the aircraft of being convenient for simultaneously is changed, also makes the outward appearance of aircraft more diversified, can change the molding design of aircraft surface at any time according to the demand.

Drawings

The above and other objects, features and advantages of the present disclosure will become more apparent by describing in more detail embodiments of the present disclosure with reference to the attached drawings. The accompanying drawings are included to provide a further understanding of embodiments of the disclosure, and are incorporated in and constitute a part of this specification. The drawings, together with the embodiments of the disclosure, serve to explain the disclosure, but do not constitute a limitation of the disclosure. 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 present disclosure;

FIG. 2 further illustrates an example of a holster of an aircraft according to an embodiment of the present disclosure;

FIG. 3 illustrates an example of a second opening on a fuselage sleeve according to an embodiment of the present disclosure;

FIG. 4 illustrates an example of a third opening, a fourth opening, and an aperture on a fuselage sleeve according to an embodiment of this disclosure;

FIG. 5 illustrates an example of a connection for connecting a headgear cover and an aircraft according to an embodiment of the present disclosure;

FIG. 6 illustrates a mount and a shield for an aircraft according to an embodiment of the disclosure;

FIG. 7 illustrates another fastener disposed on an aircraft according to an embodiment of the disclosure;

FIG. 8 illustrates a protective strip conforming to a fuselage sleeve according to an embodiment of the present disclosure;

FIG. 9 illustrates an example method for replacing a holster of an aircraft in accordance with an embodiment of the present disclosure.

Detailed Description

The technical scheme of the disclosure is clearly and completely described in the following with reference to the accompanying drawings. It is to be understood that the described embodiments are only a few, and not all, of the disclosed embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments disclosed herein without making any creative effort, shall fall within the protection scope of the present disclosure.

In the description of the present disclosure, 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 describing and simplifying the present disclosure, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present disclosure. 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 disclosure, it is to be noted that the terms "mounted," "connected," and "connected" are to be construed broadly unless otherwise explicitly 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 meaning of the above terms in the present disclosure can be understood in specific instances by those of ordinary skill in the art.

In addition, technical features involved in different embodiments of the present disclosure 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 present disclosure. As shown in fig. 1, an aircraft 100 (e.g., an ornithopter) according to embodiments of the present disclosure may include: a nose 110 disposed at a front end of the aircraft for pointing in a flight direction of the aircraft; a fuselage 120 connected to the nose 110 for mounting wings and a tail; a holster 130 for covering the handpiece 110 and/or the fuselage 120. The holster 130 may include a holster cover and/or a body cover. The head cover is provided with a first opening, and the head cover can be sleeved on the head 110 through the first opening, so that the head cover covers the head 110. The fuselage sleeve is provided with a second opening through which the fuselage sleeve can be sleeved on the fuselage 120, so that the fuselage sleeve covers the fuselage 120. In one embodiment, the holster 130 may include only a holster cover. In another embodiment, the holster 130 may include only a body holster. In yet another embodiment, the holster 130 may include both a holster cover and a body cover. With respect to the fuselage cover and fuselage cover, details will be described later in connection with fig. 2-5.

Furthermore, in one embodiment of the present disclosure, the nose 110 and fuselage 120 of the aircraft 100 shown in fig. 1 may be integrally formed, which may enhance the structural stability of the aircraft. In one embodiment, at least one of the wing, tail, nose sleeve and fuselage sleeve of the aircraft is removable, which facilitates replacement of these components. Of course, in other embodiments, the handpiece 110 and the body 120 may be detachable.

The aircraft described above in connection with fig. 1 has a holster 130, which makes the aircraft more beautiful in appearance, more versatile in shape, less prone to damage, and increases the buffering time when the aircraft is impacted, thus increasing the safety factor when the aircraft collides.

Fig. 2 further illustrates an example of a holster of an aircraft according to an embodiment of the present disclosure. As shown in fig. 2, a holster (e.g., holster 130 shown in fig. 1) may include a holster cover 132 and a body holster 134. In one embodiment, the holster 130 (nose cup 132 and/or fuselage cup 134) is fixedly wrapped around the nose 110 and/or fuselage 120 such that the holster 130 does not move about during flight of the aircraft. In one embodiment, the nose piece sleeve 132 may be sized and shaped to fit over the nose 110 such that the nose piece sleeve 132 is fixedly wrapped around the nose 110, and/or the body sleeve 134 may be sized and shaped to fit over the body 120 such that the body sleeve 132 is fixedly wrapped around the body 120. In yet another embodiment, the holster 130 is secured by a securing structure to wrap around the airframe (i.e., the nose 110 and/or the fuselage 120) of the aircraft, such as by at least one of snapping, gluing, pressing, snapping, and screwing. Of course, the holster 130 may be fixedly wrapped around the handpiece 110 and/or the fuselage 120 in other manners. In this embodiment, the shape and size of the handpiece sheath 132 can be adapted to the handpiece 110, or can be larger than the handpiece 110, as long as there is a fixing structure to fix the handpiece sheath 132 and the handpiece 110 to each other. The body housing 134 may be sized to fit the body 120 or larger than the body 120, as long as there is a fixed structure as the head housing 132 is secured to the head 110. In one embodiment, the first opening 132_2 in the handpiece sheath 132 can be distal from the front end of the handpiece 110, e.g., toward the body 120, as shown in fig. 2. The above embodiments may be used in any combination.

With respect to connection of the nose cup to the aircraft, as shown in fig. 5, in one embodiment, the nose cup 132 may be removably connected to at least one of the nose 110, the fuselage 120, and the fuselage cup 134 via a snap 510 (e.g., velcro, snap, etc.). For example, in the case where the body cover 134 encloses both the body 120 and the head 110, a male buckle may be provided on the body cover 132, a female buckle may be provided on the body cover 134, or vice versa, so that the body cover 134 is detachably connected to the head cover 132. This arrangement facilitates the attachment of the head cover 132 to the head 110, facilitating both the manufacture of the aircraft and the use by the user.

In other embodiments, the first opening on the handpiece sheath 132 may be located elsewhere on the upper or lower portion of the handpiece sheath 132, etc. For example, when the aircraft nose 110 is detachable from the fuselage 120, the first opening of the nose cover 132 may be located at the upper or lower portion of the nose cover 132, and the entire aircraft nose 110 may be housed in the nose cover 132 through the first opening at the upper or lower portion of the nose cover 132. In this case, in one embodiment, a zipper may be provided on the first opening. After the handpiece 110 is sleeved in the handpiece cover 132, the first opening is sealed by a zipper.

Regarding the shape of the headgear cover 132, as shown in fig. 2, it may be in the shape of a bird's head, such as an eagle, a pigeon, a wild goose, a parrot, etc. Of course, other shapes are possible, such as various cartoon characters and the like. In one embodiment, the handpiece sheath 132 may be cloth. The fabric nose cover 132 can buffer the impact force when the aircraft is impacted, and reduce the weight of the nose cover. Of course, other materials may be used to form the head cover 132 (e.g., plastic, rubber, etc., which may also provide cushioning and weight reduction), but the disclosure is not limited thereto. In a further embodiment, the handpiece sheath 130 may be filled with a filler, which is a material having a cushioning effect, such as cotton, foam, or polyester fiber. The filler with the buffering effect is filled in the aircraft hood 132, so that the buffering acting force can be further increased when the aircraft collides, and the safety factor of the aircraft in collision is improved.

Likewise, the fuselage sleeve 134 may be sized and shaped to fit the fuselage 120 such that the fuselage sleeve 134 does not move freely while the aircraft is in flight. In one embodiment, the fuselage sleeve 134 may be made of a resilient wear-resistant material, such as a polyester material or a polyester blend material. The body cover 134 made of elastic wear-resistant material not only can make the body cover 134 not easy to damage, but also facilitates the sleeving of the body cover 134 on the body 120, and makes the body cover 134 and the body 120 tightly fit after the body cover 134 is sleeved on the body 120.

Referring again to fig. 2, the second opening 134_2 on the fuselage sleeve 134 may be on the underside of the fuselage sleeve (i.e., the underside of the fuselage 120 of the aircraft). This arrangement may make the aircraft overall more aesthetically pleasing. It should be understood that the second opening 134_2 is provided at the lower side of the body cover 134 by way of example only, and not limitation of the present disclosure. Those skilled in the art may arrange the second opening at a suitable position on the fuselage sleeve 134 according to the characteristics and design requirements of the aircraft, so that the fuselage sleeve 134 may be sleeved on the fuselage 120. For example, the second opening may be provided at the foremost, upper, left, or right side of the body cover, or the like.

Regarding the second opening 134_2, as shown in fig. 3, in one embodiment, an opening and closing structure 134_2_2 may be disposed on the second opening 134_2, and the second opening 134_2 may be opened or closed by the opening and closing structure 134_2_ 2. For example, the opening and closing structure may be at least one of a zipper, a male button, and a female button strip. Closing the second opening after the fuselage cover 134 is fitted over the fuselage 120 may make the fuselage cover more securely wrapped around the fuselage 120 and make the overall aircraft more aesthetically pleasing. Of course, in other embodiments, the opening and closing structure 134_2_2 may not be provided.

In one embodiment, the second opening 134_2 may correspond to a battery mounting location of the aircraft, through which second opening 134_2 the battery of the aircraft may be replaced. The arrangement facilitates the replacement of the battery of the aircraft, and further improves the user experience. Furthermore, in the case where the second opening 134_2 does not correspond to the battery mounting position of the aircraft, a dedicated opening for performing battery replacement of the aircraft may be provided at the battery mounting position of the aircraft. For example, a second opening for fitting onto the fuselage 120 may be provided at the foremost (upper, left, right, etc.) of the fuselage sleeve, and an opening for performing battery replacement of the aircraft may be provided at a position corresponding to the battery installation position of the aircraft. Also, an opening and closing structure may be provided on the opening.

It should be understood that although the handpiece housing 132 and the body housing 134 are described separately in the above description in connection with fig. 2 and 3, this is by way of example only and not by way of limitation of the present disclosure. In the present disclosure, the handpiece sheath and the body sheath may be a single body, and are sleeved outside the handpiece and the body through the second opening 134_ 2.

In addition to including the second opening 134_2, a fuselage sleeve (e.g., fuselage sleeve 134 shown in fig. 2) may also include a third opening 134_4, a fourth opening 134_6, and an aperture 134_8 as shown in fig. 4. The example of the fuselage cover 134 shown in FIG. 4 may be used, for example, where the fuselage cover 134 is not rigged to a wing and/or tail. Referring to fig. 4, in one embodiment, the third openings 134_4 may be disposed at both sides of the fuselage sleeve 134, i.e., at positions corresponding to both wings of the aircraft after the fuselage sleeve 134 is sleeved on the fuselage 120. Through the third opening 134_4, the wing can be mounted to the fuselage 120. In this case, in one embodiment, the third opening 134_4 may be sized such that the wing just fits onto the fuselage 120, thereby facilitating the installation of the wing and making the overall aircraft more aesthetically pleasing. In another embodiment, the third opening 134_4 may be disposed at one side of the fuselage sleeve 134, for example, a longer opening penetrating the back of the fuselage 120 is disposed at the upper side of the fuselage sleeve 134 (which is sleeved outside the fuselage 120 and corresponds to the upper side of the fuselage 120), such as an opening penetrating the back of the fuselage 120 in a direction perpendicular to the extension direction of the fuselage 120, through which the wings of the aircraft are mounted to the fuselage 120. In this case, a covering sleeve may be provided outside the opening so as to cover the opening, making the aircraft more aesthetically pleasing overall. Providing an opening on one or both sides of the fuselage sleeve 134 such that both wings of the aircraft are mounted to the fuselage 120 of the aircraft through the opening may facilitate separate manufacture of the fuselage and wings, as well as facilitate user exchange of the fuselage or wings of the aircraft.

With continued reference to FIG. 4, a fourth opening 134_6 may be provided in the fuselage sleeve 134 at a location corresponding to the empennage, which may be mounted to the fuselage 120 via the fourth opening 134_ 6. Similar to the third opening 134_4, the fourth opening 134_6 is provided at a position of the body cover 134 corresponding to the rear wing such that the rear wing of the aircraft is mounted to the body 120 of the aircraft through the fourth opening 134_6, which can facilitate separate manufacturing of the body and the rear wing, and replacement of the body or the rear wing of the aircraft by a user.

In addition, as shown in fig. 4, at least one opening (for example, 3 openings 134_8 shown in fig. 4) may be further disposed on the upper side of the fuselage sleeve 134, that is, after the fuselage sleeve 134 is sleeved on the fuselage 120, at least one opening 134_8 is disposed at a position corresponding to the upper side of the fuselage 120, and at least one connector on the upper side of the fuselage 120 for connecting with a wing of an aircraft may pass through the opening 134_8 to connect with the wing of the aircraft, for example, hinge-connect, and the like. At least one opening is provided on the upper side of the fuselage sleeve 134, so that at least one connection on the upper side of the fuselage 120 for connection to the wing surface of an aircraft passes through the opening 134_8 and is connected to the wing surface of the aircraft. Such an arrangement helps the fuselage sleeve 134 more stably envelop the fuselage 120 of the aircraft so that the fuselage sleeve is less likely to move about during flight of the aircraft. Furthermore, the wing surface of the aircraft can be further stabilized by means of the connecting element.

Fig. 6 illustrates a mount and a shield for an aircraft according to an embodiment of the disclosure. As shown in fig. 6, in the aircraft according to the present disclosure, a fixing element 610 may be disposed at a wing installation position of the fuselage 120, for example, a wing interface, such as the wing interface 600 shown in fig. 6, is disposed on the fuselage, and the fixing element 610 is disposed corresponding to the wing interface 600. In one example, the securing member 610 is made of plastic, i.e., a plastic piece. In other implementations, the fixture 610 may be made of other materials, such as metals, alloys, and the like. The mount 610 includes an opening 612 that is shaped to fit the wing interface 600 on the fuselage such that the wing of the aircraft can be mounted to the fuselage via the opening 612 and the wing interface 600.

In one embodiment, the outer edge of the fixing member 610 forms a receiving space with the fuselage 120 for receiving at least a portion of an edge of an opening of the fuselage sleeve 134 corresponding to the wing interface 600 (i.e., the third opening 134_4 described above). For example, in the case that the third opening is provided at one side of the fuselage sleeve 134, the outer edge of the fixing member 610 may cover a part of the edge of the third opening 134_4, that is, the edge of the third opening 134_4 around the wing socket 600 is inserted into the receiving space (e.g., the receiving space is a slit) between the fixing member 610 and the fuselage 120. In the case where the third openings are provided at both sides of the body housing 134, the outer edge of the fixing member 610 may cover the entirety of the edge of the third opening 134_4, i.e., the entirety of the edge of the third opening 134_4 is tucked into the receiving space between the fixing member 610 and the body 120. The provision of the fasteners 610 at the wing interface 600 of the fuselage 120 may strengthen the structure of the fuselage 120, making the fuselage 120 stronger at that location. In addition, at least a part of the edge of the third opening 134_4 of the fuselage cover 134 corresponding to the wing interface 600 is received by the receiving space between the outer edge of the fixing member 610 and the fuselage, so that the function of positioning and beautifying the opening edge of the fuselage cover 134 can be achieved.

With respect to the placement of the fasteners 610, in one embodiment, the fasteners 610 may be affixed to the fuselage 120 at the wing interface 600 by glue (e.g., high strength glue). In a further embodiment, as shown in fig. 6, the fixing member 610 includes a hollow protrusion 614, and an adhesive (e.g., glue) can be filled in the hollow protrusion 614, and then the fixing member 610 can be adhered to the body 120 through the adhesive (e.g., glue) in the hollow protrusion 614, which facilitates the adhesion of the fixing member 610 and the control of the gap between the fixing member 610 and the body 120. In another embodiment, the fasteners 610 may be secured to the periphery of the wing interface 600 through openings 612, such as by snap-fitting or other snap-fitting. For example, in one embodiment, the fixing member 610 may include at least one first snap member 616, such as a snap, disposed at the opening 612 as shown in fig. 7, and the at least one snap member 616 may be used to snap into the wing interface 600, thereby fixing the fixing member 610 to the fuselage. In yet another embodiment, the fixing member 610 may be attached to the wing interface 600 of the fuselage 120 by glue, and the first snap-in unit 616 may be disposed on the fixing member 610, so as to further enhance the connection between the fixing member 610 and the fuselage 120 and prevent the fixing member 610 from falling off. In still another embodiment, the fixing member 610 may be integrally formed with the body 120, which may greatly prevent the fixing member 610 from falling off.

Referring again to fig. 6, in one embodiment, at least one hole 630 may be provided at the front side of the body 120, and although fig. 6 shows only one hole 630, the present disclosure does not limit the number of the holes 630. In one embodiment of the present disclosure, the at least one hole 630 may serve as a vent (heat dissipation channel). In the flight process, wind enters from the hole 630 and flows out from the wing interface 600 and/or the air outlet arranged on the fuselage 120, so that heat dissipation of electronic devices inside the aircraft is facilitated, and wind resistance is reduced. Accordingly, the fuselage sleeve 134 may include at least one fuselage sleeve aperture 622 at a location corresponding to the aperture 630.

In further embodiments, the aircraft 100 may also include a protection shield 620. The shielding member 620 may include at least one plug 624 that is shape-fitted to the at least one hole 630. In one embodiment, the guard 620 may be disposed on the fuselage 120, i.e., integrally formed with the fuselage 120. In this case, when the body cover 134 is fitted to the body 120, the body cover hole 622 may be fitted around the plug 624, whereby the protection member 620 is fixed outside the body cover 130. In another embodiment, the guard 620 may be independent of the fuselage 120. In this case, the protective element 620 can be inserted into the hole 630 through the plug 624 through the body sleeve hole 622 on the body sleeve 134, whereby the protective element 620 is fixed outside the body sleeve 130. The guard 620 may act to secure the body cover 134 against sliding of the body cover 134 on the body 120. Preferably, the plug 624 is a hollow through hole structure, the shape of the through hole structure is matched with the hole 630, specifically, the outer wall of the through hole structure is matched with the shape of the hole 630, so that the plug 624 can pass through the insertion hole 630 of the body sleeve hole 622 without shielding the hole 630, and the body sleeve 134 can be fixed while the heat dissipation of the hole 630 is prevented from being influenced by the shielding of the hole 630 due to sliding of the body sleeve 134. Further, the outer edge of the plug 624 may secure the edge of the body pocket 622, for example, may form a receiving space between the protection member 620 (e.g., the plug 624) and the body 120 to secure the edge of the body pocket 622, similar to the securing member 610, which may further prevent the body pocket 134 from sliding on the body 120 and serve as a beautification to shield the gap (i.e., the edge of the hole 630 and the edge of the body pocket 622). In a further embodiment, at least one plug 624 includes a second snap 628 for snapping into a corresponding aperture (i.e., at least one aperture 630). For example, in a case where at least one hole 630 includes 3 holes and the protection member 620 includes 3 plug elements 624 corresponding thereto, in one embodiment, the second clamping member 628 may be provided on only one plug element of the 3 plug elements 624, and the second clamping member 628 may be clamped with the corresponding hole 630. In another embodiment, a second clamping member 628 may be provided on each of the 3 plug members 624, and the second clamping member 628 may be clamped with the corresponding hole 630. The second clamping member 628 is disposed on the plug 624 to strengthen the fixing between the protection component 620 and the body 120, so as to prevent the protection component 620 from falling off.

It should be understood that although at least one aperture 630 is provided in the fuselage 120 in the above description, this is merely an example and not a limitation of the present disclosure. For example, at least one aperture 630 may also be provided on the handpiece 110.

Referring to fig. 6 and 8, the protection member 620 may further include a protection bar 626, the protection bar 626 may be attached to the front side of the fuselage sleeve 134, and the attachment position of the protection bar 626 to the front side of the fuselage sleeve 134 is selected to be aligned with a contact surface with the ground or other carrying objects after the aircraft normally lands, that is, the protection bar 626 is fixed at the position of the contact surface. In one embodiment, the size and shape of the guard bar 626 may be adapted to the contact area and shape, respectively, of the ground when the aircraft lands (the contact area and shape with a high probability when the aircraft lands, rather than the contact area and shape with the ground each time it lands). Thereby preventing damage to the holster 130 (e.g., fuselage holster 134) from rubbing against the ground and extending the useful life of the holster 130 during aircraft landing.

With respect to the guard 620, in one embodiment, the plug 624, the guard bar 626, and the second snap 628 may be integrally formed, which may prevent the dropping of the respective components and simplify the assembly process. In other embodiments, one or more of the plug 624, the guard bar 626, and the second snap member 628 may be separate components, which facilitates replacement of only one component (e.g., the guard bar) if the component is damaged. In one example, the guard 620 (i.e., one or more of the plug 624, the guard bar 626, and the second snap member 628) is made of plastic, i.e., a plastic piece. In other implementations, the guard 620 may be made of other materials, such as metals, alloys, and the like.

In one embodiment, the securing member 610 and the shielding member 620 are both removable, i.e., both are separable from the aircraft by human force, at least to facilitate replacement after damage to the components.

In the above, the present disclosure provides, in connection with fig. 1 to 8, a holster of an aircraft and an aircraft comprising the holster. The holster according to the present disclosure is used to encase the nose and/or fuselage of the aircraft. The machine cover comprises a machine cover and/or a machine body cover. When the machine cover comprises the machine head cover, the machine head cover is provided with a first opening, the machine head can be sleeved on the machine head through the first opening, and the machine head cover covers the machine head after the machine head is sleeved on the machine head. When the machine cover comprises the machine body cover, the machine body cover is provided with a second opening, the machine body can be sleeved on the machine body through the second opening, and the machine body is covered by the machine body cover after the machine body is sleeved on the machine body. In addition, the shape and size of the head cover can be matched with the head, so that the head cover is tightly attached to the head after being sleeved on the head, and/or the shape and size of the body cover can be matched with the body, so that the body cover is tightly attached to the body after being sleeved on the body. Furthermore, the airframe according to the present disclosure may also include one or more components of the airframe of the aircraft described above in connection with fig. 1-8.

Hereinafter, the present disclosure will describe a method for replacing a holster of an aircraft according to an embodiment of the present disclosure in connection with fig. 9.

FIG. 9 illustrates an example method for replacing a holster of an aircraft in accordance with an embodiment of the present disclosure. Before carrying out a method for changing a fuselage of an aircraft according to an embodiment of the disclosure, a nose and/or a fuselage of the aircraft is covered by a first fuselage, the method for changing the first fuselage covering the nose and/or the fuselage of the aircraft to a second fuselage, the first fuselage comprising a first nose cap and/or a first fuselage sleeve, the second fuselage comprising a second nose cap and/or a second fuselage sleeve. As shown in fig. 9, a method for replacing a holster of an aircraft according to an embodiment of the present disclosure begins at step S910. At step S910, the first head cover sleeved on the head of the aircraft and covering the head is removed at least through the first opening of the first head cover. The method then proceeds to step S920. At step S920, the second head cover is sleeved on the head at least through the first opening of the second head cover, so that the second head cover covers the head. In some cases, for example, where only the headgear cover needs to be replaced, for example, where only the headgear cover is damaged or needs to be replaced with another appearance shape. The method for replacing a nose piece sleeve of an aircraft may terminate after performing step S920. In other cases, for example, where the fuselage cover still needs to be replaced, the method proceeds to step S930. At step S930, the first fuselage sleeve that is fitted to the fuselage of the aircraft and that covers the fuselage is removed at least via the second opening of the first fuselage sleeve. The method then proceeds to step S940. At step S940, the second fuselage sleeve is sleeved to the fuselage at least via the second opening of the second fuselage sleeve such that the second fuselage sleeve encases the fuselage. In one embodiment, for example, where the fuselage sleeve has only one opening (e.g., the second opening described above), replacement of the fuselage sleeve may be performed via only the one opening. In other embodiments, for example, the fuselage sleeve includes a plurality of openings, for example, where the front side of the fuselage sleeve includes an opening for sleeving the fuselage sleeve to the fuselage and also includes a second opening for replacing the battery. The replacement of the body cover may be performed via one or more of the plurality of openings, for example, by opening the second opening for battery replacement (unzipping the second opening as in the above), and then performing the replacement of the body cover through the opening at the front side of the body cover. The replacement of the headgear assembly is also possible, i.e. the replacement of the headgear assembly can be performed via one or more openings in the headgear assembly. In one embodiment, the first fuselage sleeve and the second fuselage sleeve are each shaped and dimensioned to fit the fuselage, the second opening corresponding to a battery mounting location of the aircraft through which a battery exchange of the aircraft is possible.

The replacement of the holster may be performed, for example, by damage to the holster and/or the holster. In this case, the same-looking holster can be replaced. That is, the first head cover and the second head cover have the same appearance, and/or the first body cover and the second body cover have the same appearance. Another example reason may be to change the appearance of the aircraft. In this case, the first body cover can be replaced with a second body cover having a different appearance, i.e., the first and second body covers have different appearances, and/or the first and second body covers have different appearances. For example, the first holster may have the appearance of a hawk, and the second holster may have the appearance of a pigeon. By using the method for replacing the machine sleeve of the aircraft according to the embodiment of the disclosure, the machine sleeve of the aircraft can be replaced at will, and the damaged machine sleeve or the appearance of the machine sleeve can be replaced, so that the service life of the aircraft is prolonged, and the interestingness of use is increased. In addition, it should be understood that the appearance herein includes not only the animal figure of the first and second casings, but also at least one or a combination of at least two of material, shape, color, pattern, etc.

When the aircraft has at least one hole 630 in the front side of the fuselage as shown in fig. 6, the aircraft may further include a first protection element (e.g., the protection element 620 shown in fig. 6) or a second protection element, the first protection element or the second protection element includes at least one plug 624 that is matched in shape with the at least one hole 630, and the at least one plug 624 of the first protection element is inserted into the at least one hole 630. In this case, the method for replacing a holster of an aircraft according to embodiments of the present disclosure may further include: removing the first protective element by removing the at least one plug-in element of the first protective element from the at least one opening before removing the first fuselage sleeve which is fitted to the fuselage of the aircraft and which encloses the fuselage at least via the second opening of the first fuselage sleeve; and installing the second protection part by inserting the at least one plug-in connector of the second protection part into the at least one hole after sheathing the second body cover to the body at least through the second opening of the second body cover so that the second body cover coats the body. In one embodiment, the shielding elements may not be replaced with new ones, for example, in case the first shielding element is not damaged. In this case, the first prevention piece and the second prevention piece are the same prevention piece. In another embodiment, the shield may be replaced with a new shield, for example in the event of damage to the first shield. In this case, the first prevention piece and the second prevention piece are different prevention pieces. In yet another embodiment, for example, the first protection member is configured to match the appearance of the first holster, the second protection member is configured to match the appearance of the second holster, and the first protection member is replaced with the second protection member when the first holster is to be replaced with the second holster. In this case, the first prevention piece and the second prevention piece are different prevention pieces.

In the case where the first guard further includes a first guard bar (e.g., guard bar 626 shown in fig. 6), the second guard may also include a second guard bar, the first guard bar conforming to the front side of the first fuselage sleeve, the first and second guard bars being sized and shaped to fit the contact area and shape of the ground when the aircraft lands. In this case, removing the first protection piece further comprises separating the first protection strip from the first body cover, and mounting the second protection piece further comprises fitting the second protection strip to the front side of the first body cover or the second body cover.

In one embodiment, as shown, for example, in fig. 6, one or both sides of the first and second fuselage sleeves are provided with third openings (e.g., the third openings shown in fig. 4), the wings of the aircraft are mounted to the fuselage through the third openings and wing sockets (e.g., wing socket 600 shown in fig. 6) formed in the fuselage, and a mount (e.g., mount 610 shown in fig. 6) is provided at the wing-insertion interface of the fuselage, with an accommodation space being formed between the outer edge of the mount and the fuselage, for receiving at least a portion of an edge of the third opening, and the anchor includes an opening (e.g., opening 612 shown in FIG. 6) shaped to fit a wing interface (e.g., wing interface 600 shown in FIG. 6) on the fuselage, in this case, the method for replacing a holster of an aircraft according to embodiments of the present disclosure may further include: before the first fuselage sleeve which is fitted to the fuselage of the aircraft and which covers the fuselage is removed at least via the second opening of the first fuselage sleeve, at least part of the edge of the third opening of the first fuselage sleeve is removed from the receiving space; and after the second fuselage sleeve is sleeved on the fuselage at least through the second opening of the second fuselage sleeve, at least a part of the edge of the third opening of the second fuselage sleeve is stuffed into the accommodating space, so that the accommodating space accommodates at least a part of the edge of the third opening of the second fuselage sleeve; alternatively, the fastener (e.g., fastener 610 of fig. 6) is separated from the wing interface (e.g., wing interface 600 of fig. 6) prior to removing the first body sleeve that is nested within and enveloping the fuselage through at least the second opening of the first body sleeve; and after the second fuselage sleeve is fitted to the fuselage at least via the second opening of the second fuselage sleeve, the fixing is arranged at the wing socket such that the accommodation space accommodates at least a part of an edge of the third opening of the second fuselage sleeve.

To this end, the present disclosure has described an aircraft and a holster according to the present disclosure with reference to fig. 1 to 8, and described a method for replacing a holster of an aircraft according to an embodiment of the present disclosure with reference to fig. 9, the aircraft according to an embodiment of the present disclosure has a holster such that the appearance and structure of the aircraft are not easily damaged, and the buffering protection function can be increased when the aircraft is impacted, thereby increasing the safety factor when the aircraft collides, facilitating the replacement of each component of the aircraft, and making the appearance of the aircraft more beautiful and the shape more various. The method for replacing the aircraft holster can replace the holster of the aircraft, can replace the damaged holster or replace the appearance of the holster, prolongs the service life of the aircraft, and increases the use interest.

According to the holster disclosed by the embodiment of the disclosure, the material of the holster and the shapes, colors, patterns and other shapes of the holster can be selected as required, namely, the holster is configured to have at least one or a combination of at least two of the material, the shape, the color and the patterns, so that the holster has different shapes and is sleeved on an aircraft, and the outer surface of the aircraft presents different designs. It can be understood that the color of the holster according to the embodiment of the present disclosure can be set to be a single color, i.e. a pure color, so that the user can design patterns, colors, etc. on the holster by himself or herself.

It should be understood that the aircraft described above in connection with fig. 1-8 is merely an example and not a limitation of the present disclosure. For example, in addition to the first opening, the second opening, the third opening, the fourth opening, and the at least one aperture described above, one skilled in the art may provide more or fewer openings and/or apertures in the holster (nose cup and/or fuselage cup) depending on the characteristics of the aircraft, such as, for example, the detachable components on the aircraft, etc.

It is also to be understood that the above description is only exemplary of some embodiments of the disclosure and is intended to illustrate the principles of the technology employed. 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 does not depart from the spirit of the disclosure. For example, the above features and (but not limited to) the features disclosed in this disclosure having similar functions are replaced with each other 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 disclosure. 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.