CN210681172U

CN210681172U - Avionics cabin and unmanned aerial vehicle

Info

Publication number: CN210681172U
Application number: CN201920972028.XU
Authority: CN
Inventors: 金猛; 巴航; 刘城斌; 杨祥磊; 滕强
Original assignee: Beijing Jingdong Qianshi Technology Co Ltd
Current assignee: Beijing Jingdong Qianshi Technology Co Ltd
Priority date: 2019-06-25
Filing date: 2019-06-25
Publication date: 2020-06-05
Anticipated expiration: 2029-06-25

Abstract

The utility model provides an avionics cabin (112) for install avionics system. The avionics bay (112) comprises: a cabin door (10) and an avionics cabin body (20). The avionics cabin body comprises a cabin body opening (22) and a cabin body connecting structure (21); wherein the cabin opening (22) is located at an upper portion of the avionics cabin (20), the cabin connection structure (21) is configured to be connected with a fuselage body (111) of the unmanned aerial vehicle (1). Wherein the cabin door (10) is detachably connected to the upper part of the avionics cabin body (20) and is matched with the cabin body opening (22). The utility model also provides an unmanned aerial vehicle (1) including avionics cabin (112).

Description

Avionics cabin and unmanned aerial vehicle

Technical Field

The utility model relates to a storage commodity circulation field, more specifically relates to an avionics cabin and an unmanned aerial vehicle.

Background

The current logistics unmanned aerial vehicle mainly has two structural forms. One is that the upper and lower layers of central plates of the fuselage clamp the horn, the cargo hold locates between the undercarriages under the fuselage; the other is that the fuselage and the arms are in an integral shell type, and the cargo hold is also positioned between the landing gears below the fuselage. The position of avionics system requires to be close to unmanned aerial vehicle's center as far as possible, and is close to the rotation plane of rotor as far as possible, so the mounted position of avionics part is installed between two-layer fuselage center plate mostly, or in the shell of the whole shell of fuselage, because of limited and battery of shell inner space also is in the shell, throw away in the whole shell and need design about center plate and install avionics equipment. The vibration reduction and the dustproof and waterproof effects are considered, the main mode is that an independent vibration reduction structure is installed on a flight control unit or an IMU, and a cover is additionally arranged on a machine body plate to achieve the dustproof and waterproof effects.

In the process of implementing the present invention, the inventor finds that the prior art has at least the following defects: on the one hand, the dustproof and waterproof effect is poor. The avionics system is installed between two-layer fuselage center plate, covers through the epitheca and plays the guard action, and the leakproofness is poor, can not be fine play dustproof and waterproof's effect. And on the other hand, the installation and the inspection of the avionics system are inconvenient. The two-layer fuselage center plate is a key part for bearing force and keeping rigidity of the whole machine, and the strength of the whole machine is seriously influenced by opening the upper plate of the two-layer fuselage center plate, so that the installation, wiring and maintenance in a narrow space are not convenient enough.

SUMMERY OF THE UTILITY MODEL

In view of this, the utility model provides a be used for the whole avionics cabin that independently installs together of avionics system and including the unmanned aerial vehicle of this avionics cabin, can realize the modularization of avionics system when unmanned aerial vehicle design and installation with this mode and handle.

In one aspect of the disclosure, an avionics bay is provided for installing an avionics system. The avionics cabin comprises a cabin door and an avionics cabin body. The avionic cabin body comprises a cabin body opening and a cabin body connecting structure; wherein, cabin body opening is located the upper portion of avionics cabin body, cabin body connection structure is configured to be connected with unmanned aerial vehicle's fuselage main part. The cabin door is detachably connected to the upper part of the cabin body of the avionic cabin and is matched with the opening of the cabin body.

According to an embodiment of the present disclosure, the edge of the door and the edge of the opening of the cabin comprise cooperating sealing structures.

According to an embodiment of the disclosure, the cabin connection structure comprises a shock absorbing device.

According to an embodiment of the disclosure, the avionics compartment body comprises at least one through hole configured for passing through at least one cable plug of the avionics system. According to an embodiment of the disclosure, the at least one through hole is arranged on a non-windward side of the avionics cabin body.

In another aspect of the present disclosure, a drone is provided. Unmanned aerial vehicle includes fuselage main part and avionics cabin, the avionics cabin connect in the fuselage main part. The avionics cabin comprises a cabin door and an avionics cabin body. The avionic cabin body comprises a cabin body opening and a cabin body connecting structure; wherein, cabin body opening is located the upper portion of avionics cabin body, cabin body connection structure is configured to be connected with unmanned aerial vehicle's fuselage main part. The cabin door is detachably connected to the upper part of the cabin body of the avionic cabin and is matched with the opening of the cabin body.

According to an embodiment of the present disclosure, the fuselage body includes an avionics bay mounting plate, and the bay body connection structure includes a shock absorbing device. The avionics cabin body is connected to the avionics cabin mounting plate through the damping device.

According to an embodiment of the disclosure, the avionics pod body comprises at least one through hole, which is arranged on a non-windward side of the avionics pod body.

According to an embodiment of the present disclosure, the avionics bay is connected to a bottom of the fuselage body. Wherein the avionics bay further comprises fasteners, and wherein the bay door is detachably connected to the avionics bay body by the fasteners. The body includes a detachment space of the fastener.

Drawings

The above and other objects, features and advantages of the present disclosure will become more apparent from the following description of embodiments of the present disclosure with reference to the accompanying drawings, in which:

fig. 1A schematically illustrates a perspective structural view of a drone according to an embodiment of the present disclosure;

fig. 1B schematically illustrates a top view of the drone in fig. 1A;

FIG. 2 schematically illustrates a block diagram of an avionics pod in accordance with an embodiment of the present disclosure;

FIG. 3 schematically shows a block diagram of the avionics bay body of the avionics bay of FIG. 2; and

FIG. 4 schematically illustrates a connection of the avionics pod to the fuselage body of FIG. 2;

Detailed Description

Hereinafter, embodiments of the present disclosure will be described with reference to the accompanying drawings. It should be understood that the description is illustrative only and is not intended to limit the scope of the present disclosure. In the following detailed description, for purposes of explanation, numerous specific details are set forth in order to provide a thorough understanding of the embodiments of the disclosure. It may be evident, however, that one or more embodiments may be practiced without these specific details. Moreover, in the following description, descriptions of well-known structures and techniques are omitted so as to not unnecessarily obscure the concepts of the present disclosure.

The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the disclosure. The terms "comprises," "comprising," and the like, as used herein, specify the presence of stated features, steps, operations, and/or components, but do not preclude the presence or addition of one or more other features, steps, operations, or components.

All terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art unless otherwise defined. It is noted that the terms used herein should be interpreted as having a meaning that is consistent with the context of this specification and should not be interpreted in an idealized or overly formal sense.

Where a convention analogous to "at least one of A, B and C, etc." is used, in general such a construction is intended in the sense one having skill in the art would understand the convention (e.g., "a system having at least one of A, B and C" would include but not be limited to systems that have a alone, B alone, C alone, a and B together, a and C together, B and C together, and/or A, B, C together, etc.). Where a convention analogous to "A, B or at least one of C, etc." is used, in general such a construction is intended in the sense one having skill in the art would understand the convention (e.g., "a system having at least one of A, B or C" would include but not be limited to systems that have a alone, B alone, C alone, a and B together, a and C together, B and C together, and/or A, B, C together, etc.).

In the context of the present disclosure, when an element is referred to as being "on" or "connected to" another element, it can be directly on or connected to the other element or other elements may be present therebetween. In addition, if a component is "on" another component in one orientation, that component may be "under" the other component when the orientation is reversed. When an element is referred to as being "between" two other elements, it can be directly between the two other elements or intervening elements may also be present.

The embodiment of the disclosure provides an avionics bay and an unmanned aerial vehicle comprising the avionics bay. The avionics bay is used for installing an avionics system. This avionics bay includes: a cabin door and an avionics cabin body. The avionics cabin body comprises a cabin body opening and a cabin body connecting structure; wherein, cabin body opening is located the upper portion of avionics cabin body, and cabin body connection structure is configured to be connected with unmanned aerial vehicle's fuselage main part. The cabin door is detachably connected to the upper part of the cabin body of the avionic cabin and is matched with the opening of the cabin body.

According to the embodiment of the disclosure, the avionics cabin can be an independent closed cabin body, and the avionics system can be centrally arranged in the avionics cabin and then the avionics cabin is installed on the unmanned aerial vehicle. In this way, make the avionics system in the unmanned aerial vehicle can form modular structure, simplify the design and the installation to the avionics system of unmanned aerial vehicle.

Fig. 1A schematically shows a perspective structural view of a drone 1 according to an embodiment of the present disclosure; fig. 1B schematically shows a top view of the drone 1 in fig. 1A. It should be noted that the drone 1 shown in fig. 1A and 1B is only one example of a drone structure of an avionics bay to which the embodiments of the present disclosure can be applied, so as to help those skilled in the art understand the technical content of the present disclosure, but it does not mean that the embodiments of the present disclosure cannot be applied to drones of other structural forms.

As shown in fig. 1A, the drone 1 is a multi-rotor drone. The drone 1 includes a drone body 110, a plurality of propellers 120, and a control system or the like. The control system can comprise a power battery, an avionic system and the like. Avionics systems may include flight controls, IMUs, communication modules, and radio modules, among others.

According to an embodiment of the present disclosure, the drone fuselage 110 includes a fuselage body 111 and an avionics pod 112, the avionics pod 112 being connected to the fuselage body 111. For example, the avionics bay 112 may be attached to a bottom central location of the fuselage body 111. The various devices in the avionics system may be mounted inside the avionics bay 112 (e.g., affixed inside the avionics bay 112).

The upper part of the avionics bay 112 may be provided with a movable bay door. The doors are closed after the avionics system is installed in the avionics bay body of the avionics bay 112. The pod doors may also be removable or movable to facilitate servicing of the avionics systems inside the avionics pod 112. For example, the avionics bay 112 may include fasteners by which the bay door and the avionics bay body are removably connected. A space for detaching the fastener is reserved in the body main body 111. Thus, when the avionics bay 112 is connected in the fuselage body 111, the bay doors can also be removed by removing the fasteners, and the equipment in the avionics system inside the avionics bay 112 can then be serviced.

The avionics bay 112 may also be provided with a sealing structure, for example, a sealing structure is provided at the closing position of the bay door and the avionics bay body, so as to achieve a rainproof and waterproof effect. The avionics bay 112 may also be reserved with through holes for cable plugs to pass through.

The power battery in the unmanned aerial vehicle 1 can be installed around the fuselage main body 111, far away from the avionics bay 112. Thus, the avionics pod 112 is far from the battery and is not disturbed by the magnetic field of the large current of the battery. The avionics bay 112 can withstand a certain impact in the event of an accidental collision of the drone 1. Moreover, the avionic cabin 112 is far away from the battery, so that the hidden danger of flammability and explosiveness of the battery is avoided, and the avionic equipment in the avionic cabin 112 is protected.

Fig. 2 schematically illustrates a block diagram of an avionics bay 112 in accordance with an embodiment of the present disclosure. Fig. 3 schematically shows a block diagram of the avionics bay body 20 of the avionics bay 112 in fig. 2.

As shown in fig. 2 and 3, the avionics bay 112 includes bay doors 10 and an avionics bay body 20. The avionics cabin body 20 comprises a cabin body opening 22 and a cabin body connection structure 21, wherein the cabin body opening 22 is located at an upper portion of the avionics cabin body 20. The cabin connection structure 21 is configured to be connected with a fuselage main body 111 of the drone 1 (see fig. 4). The hatch 10 is detachably connected to the upper part of the avionics cabin 20 and cooperates with the cabin opening 22.

According to embodiments of the present disclosure, the edge of the door 10 and the edge of the cabin opening 22 may include cooperating sealing structures. For example, the edges of the hatch 10 and the edges of the cabin opening 22 may comprise cooperating groove structures or the like. In this way, the avionics bay 112 is hermetically designed to achieve the waterproof and rainproof performance of the avionics bay 112.

According to an embodiment of the present disclosure, the avionics compartment body 20 comprises at least one through hole 23, the at least one through hole 23 being configured for the passage of at least one cable plug of an avionics system. Specifically, the number, position, and form of the through holes 23 correspond to those of cable plugs of the avionics system arranged in the avionics compartment body 20.

According to an embodiment of the present disclosure, at least one through hole 23 is provided on the non-windward side of the avionics nacelle body 20. The non-windward side of the avionics bay body 20 refers to the non-windward side determined by the direction of the line connecting the head and the tail of the unmanned aerial vehicle 1 when the avionics bay 112 is installed on the unmanned aerial vehicle 1. Like this, when unmanned aerial vehicle 1 flies under the condition of rainy, can avoid the rainwater to the influence of cable socket, reach rainproof effect.

Fig. 4 schematically shows a connection scheme of the avionics bay 112 and the fuselage body 111 in fig. 2.

Referring to fig. 2 and 4, the cabin connection structure 21 of the avionics cabin 112 may comprise a shock absorbing device 211. The damping device 211 may be, for example, a damping ball or the like. For example, four vibration-damping balls may be bolted to a mounting plate in the body 111, and the vibration-damping balls may be disposed above the mounting plate of the body 111, so that vibration damping of the entire avionic bay 112 may be achieved by squeezing the vibration-damping balls.

The avionics bay 112 of the disclosed embodiment is good in three-proofing (waterproof, rainproof and anti-collision) effect. The entire avionics pod 112 may be of an integrated sealed design and the avionics systems installed inside the avionics pod 112 may use waterproof plugs. Thus, the avionics bay 112 and the avionics systems therein can be flushed directly with a faucet or even immersed in water. The avionics bay 112 adopts an integral vibration reduction mode, and vibration prevention protection can be effectively achieved for avionics equipment installed inside the avionics bay 112.

The avionics bay 112 of the disclosed embodiment is convenient to install and facilitates inspection of the avionics system. The installation of the avionics system can be done before the fuselage body 111 of the drone 1 is assembled. During maintenance and inspection, the cabin door 10 can be opened, and the avionics cabin 112 can be integrally detached, so that the operation space is wide, and convenience and rapidness are realized.

The avionics bay 112 of the disclosed embodiment is convenient to use. The plug of each equipment of avionics system all can be connected with outside cable through-hole 23 to can adopt waterproof aviation plug, can avoid appearing a large amount of cables in avionics cabin 112 with this mode and pile up, the outward appearance is clean and tidy, convenient to use.

The avionics bay 112 of the disclosed embodiment can be arranged in the fuselage main body 111 at a position away from the battery, improving the safety performance of the unmanned aerial vehicle 1. The avionics system can not receive the magnetic field interference of battery heavy current, if the unexpected offend appears in unmanned aerial vehicle 1, the shock attenuation performance of avionics cabin 112 can bear bigger impact, keeps away from the battery moreover and also can avoid the flammable and explosive hidden danger of battery to the inside avionics system of protection cabin electricity cabin 112.

The avionics bay 112 of the disclosed embodiment may not occupy critical spatial locations of the fuselage body 111. The avionics bay 112 may be arranged centrally at the bottom of the fuselage body 111 as in fig. 1. In order to make the change of the center of gravity of the unmanned aerial vehicle 1 as small as possible when the unmanned aerial vehicle is unloaded and fully loaded, the avionic compartment 112 can be connected to the center of the bottom of the main body 111 of the airframe, so that the operation of an avionic system is not influenced, and the unmanned aerial vehicle can not occupy a critical position.

Those skilled in the art will appreciate that various combinations and/or combinations of features recited in the various embodiments and/or claims of the present disclosure can be made, even if such combinations or combinations are not expressly recited in the present disclosure. In particular, various combinations and/or combinations of the features recited in the various embodiments and/or claims of the present disclosure may be made without departing from the spirit or teaching of the present disclosure. All such combinations and/or associations are within the scope of the present disclosure.

The embodiments of the present disclosure have been described above. However, these examples are for illustrative purposes only and are not intended to limit the scope of the present disclosure. Although the embodiments are described separately above, this does not mean that the measures in the embodiments cannot be used in advantageous combination. The scope of the disclosure is defined by the appended claims and equivalents thereof. Various alternatives and modifications can be devised by those skilled in the art without departing from the scope of the present disclosure, and such alternatives and modifications are intended to be within the scope of the present disclosure.

Claims

1. An avionics pod (112) for installing an avionics system, comprising:

a hatch door (10); and

the avionics cabin body (20) comprises a cabin body opening (22) and a cabin body connecting structure (21); wherein the cabin opening (22) is located at an upper portion of the avionics cabin (20), and the cabin connection structure (21) is configured to be connected with a fuselage body (111) of the unmanned aerial vehicle (1);

wherein the cabin door (10) is detachably connected to the upper part of the avionics cabin body (20) and is matched with the cabin body opening (22).

2. The avionics bay (112) of claim 1, characterized in that:

the edge of the hatch (10) and the edge of the cabin opening (22) comprise mutually cooperating sealing structures.

3. The avionics pod (112) of claim 1, characterized in that the pod connection structure (21) comprises a shock absorbing device (211).

4. The avionics bay (112) of claim 1, characterized in that the avionics bay body (20) comprises at least one through hole (23), the at least one through hole (23) being configured for the passage of at least one cable plug of the avionics system.

5. The avionics bay (112) of claim 4, characterized in that the at least one through-hole (23) is provided at a non-windward side of the avionics bay body (20).

6. An unmanned aerial vehicle (1), comprising:

a body main body (111); and

an avionic pod (112) connected to the fuselage body (111);

wherein the avionics bay (112) comprises:

a hatch door (10); and

the avionics cabin body (20) comprises a cabin body opening (22) and a cabin body connecting structure (21); wherein the cabin opening (22) is positioned at the upper part of the avionics cabin body (20), and the cabin body connecting structure (21) is connected with the fuselage main body (111);

7. The drone (1) of claim 6, characterized in that:

the edge of the hatch (10) and the edge of the cabin opening comprise cooperating sealing structures.

8. The drone (1) according to claim 6, wherein the fuselage body (111) comprises an avionics cabin mounting plate and the cabin connection structure (21) comprises a shock-absorbing device (211);

the avionics cabin body (20) is connected to the avionics cabin mounting plate through the damping device (211).

9. The unmanned aerial vehicle (1) of claim 6, wherein the avionics pod (20) comprises at least one through-hole (23), the at least one through-hole (23) being provided at a non-windward side of the avionics pod (20).

10. The drone (1) according to claim 6, characterised in that the avionics bay (112) is connected to the bottom of the fuselage body (111); wherein:

the avionics bay (112) further comprises fasteners, wherein the bay door (10) is detachably connected to the avionics bay body (20) by means of the fasteners;

the body main body (111) includes a detachment space of the fastener.