CN211810219U

CN211810219U - Aircraft

Info

Publication number: CN211810219U
Application number: CN201922149492.1U
Authority: CN
Inventors: 杨祥磊
Original assignee: Beijing Jingdong Qianshi Technology Co Ltd
Current assignee: Beijing Jingdong Qianshi Technology Co Ltd
Priority date: 2019-12-04
Filing date: 2019-12-04
Publication date: 2020-10-30
Anticipated expiration: 2029-12-04

Abstract

An embodiment of the utility model provides an aircraft relates to the aerospace field. The aircraft comprises: a cabin component; one end of the wing component is connected with the cabin component, and the other end of the wing component is provided with a first supporting part; a rotor component connected with the nacelle component. Such that the first support portion may act as a landing gear to support the entire aircraft when the wing members are in the folded condition; and can realize vertical takeoff and landing through the rotor part, after the aircraft enters cruise state, the wing part expandes, provides lift for the aircraft to energy saving, and then can prolong the journey of aircraft.

Description

Aircraft

Technical Field

The utility model relates to an aerospace field especially relates to an aircraft.

Background

At present, many rotor unmanned aerial vehicle can take off and land perpendicularly, has reduced the requirement to the airport, and has simple structure and the easy characteristics of control, obtains extensive application in fields such as photography, plant protection, aerial survey, patrol and examine, commodity circulation, but its journey and duration are shorter, can not realize remote mission flight, have restricted its further development and application.

SUMMERY OF THE UTILITY MODEL

In view of this, the embodiment of the utility model provides an aircraft can solve current many rotor crafts short range, the short problem of continuation of the journey.

To achieve the above object, according to one aspect of the present invention, an aircraft is provided.

The utility model discloses an aircraft includes:

a cabin component;

one end of the wing component is connected with the cabin component, and the other end of the wing component is provided with a first supporting part;

a rotor component connected with the nacelle component.

Optionally, the cabin component comprises:

the cabin body, wing part and rotor part all with this body coupling of cabin body.

Optionally, the cabin component further comprises:

a second support portion through which the wing component and/or the rotor component is connected to the nacelle body.

Optionally, the wing component comprises:

one end of the wing body is connected with the cabin component, and the first supporting part is arranged at the other end of the wing body;

the folding assembly, folding assembly's one end with this body coupling of wing, folding assembly's the other end with cabin body part connects, folding assembly is used for making the wing body is in fold condition or expansion state.

Optionally, the folding assembly comprises:

one end of the first driving structure is connected with the cabin component, and the other end of the first driving structure is connected with the wing body.

Optionally, the folding assembly further comprises:

the other end of the first driving structure is hinged with one end of the rocker arm;

the other end of the rocker arm is hinged with one end of the connecting rod, and the other end of the connecting rod is hinged with the wing component.

Optionally, the folding assembly further comprises:

and the first driving structure is connected with the cabin component through the base.

Optionally, one end of the wing body is provided with a first connecting portion, and the cabin component is provided with a second connecting portion adapted to the first connecting portion.

Optionally, the rotor component comprises:

a rotor body;

the second drive structure, the second drive structure with cabin body part connects, the rotor body with the second drive structure is connected.

Optionally, the rotor component further comprises:

and the second driving structure is connected with the cabin component through the frame.

According to the technical scheme of the utility model, an embodiment in the above-mentioned utility model has following advantage or beneficial effect:

the aircraft provided by the embodiment of the utility model is provided with a rotor wing part and a foldable wing part, and the wing part is provided with a first supporting part which can be used as an undercarriage to support the whole aircraft when the wing part is in a folded state; and can realize vertical takeoff and landing through the rotor part, after the aircraft enters cruise state, the wing part expandes, provides lift for the aircraft to energy saving, and then can prolong the journey of aircraft.

Further effects of the above-mentioned non-conventional alternatives will be described below in connection with the embodiments.

Drawings

The accompanying drawings are included to provide a better understanding of the present invention and are not intended to constitute an undue limitation on the invention. Wherein:

fig. 1 is one of the structural schematics of an aircraft according to an embodiment of the invention;

fig. 2 is a second schematic structural view of an aircraft according to an embodiment of the invention;

fig. 3 is a third schematic structural view of an aircraft according to an embodiment of the invention;

figure 4 is a fourth schematic structural view of an aircraft according to an embodiment of the invention;

fig. 5 is a fifth schematic structural view of an aircraft according to an embodiment of the invention;

fig. 6 is a schematic structural view of a folding assembly according to an embodiment of the present invention;

fig. 7 is a schematic structural diagram of a wing body according to an embodiment of the present invention.

Detailed Description

Exemplary embodiments of the invention are described below with reference to the accompanying drawings, in which various details of embodiments of the invention are included to assist understanding, and which are to be considered exemplary only. Accordingly, those of ordinary skill in the art will recognize that various changes and modifications of the embodiments described herein can be made without departing from the scope and spirit of the invention. Also, descriptions of well-known functions and constructions are omitted in the following description for clarity and conciseness.

Generally, compared with a multi-rotor wing, a fixed wing aircraft has wings with a large lift-drag ratio, and the forward flying speed of the aircraft can provide lift force, so that energy is saved, and the fixed wing aircraft has the characteristics of long flight time and long flying distance, but has higher requirements on a landing and landing site due to the fact that the fixed wing aircraft cannot vertically take off and land, and therefore the application of the fixed wing aircraft is limited. In summary, the following problems exist with current multi-rotor aircraft:

1) the multi-rotor aircraft has short range and cannot realize long-distance mission flight;

2) the multi-rotor aircraft has no wings, and the forward flying speed cannot provide lift force for the aircraft;

3) fixed wing aircraft have wings, and the speed of flight is ahead of the flight can provide lift, but can not VTOL.

Based on above analysis, the embodiment of the utility model provides an aircraft is provided, this aircraft both includes wing part 2 and rotor part 3, promotes the lifting force of aircraft and realizes the purpose of VTOL to energy saving prolongs the aircraft journey. It should be explained that the aircraft is an apparatus for flying in the atmosphere or in the space outside the atmosphere (space), and the aircraft may be an airplane or an unmanned plane, etc.

Fig. 1 to 5 are schematic structural views of an aircraft according to an embodiment of the invention, with reference to fig. 1 to 5, the aircraft comprising: a cabin component 1, a foldable wing component 2 and a rotor component 3; wherein the wing part 2 is used for providing lift for the aircraft through the forward flying speed, and the rotor part 3 is used for realizing the vertical take-off and landing of the aircraft. One end of the wing component 2 is connected with the cabin component 1, the other end of the wing component 2 is provided with a first supporting part 21, and the rotor component 3 is connected with the cabin component 1.

In an embodiment of the invention, the wing part 2 comprises: a folded state and an unfolded state. In which fig. 1 to 3 show a schematic view of the wing part 2 in a folded state, as shown in fig. 1 to 3, the first support part 21 may be used as a landing gear to support the entire aircraft when the wing part 2 is in the folded state. Fig. 4 to 5 show the wing element 2 in a deployed state, which, as shown in fig. 4 and 5, can provide lift for an aircraft when the wing element 2 is in the deployed state. It will be appreciated that the wing elements 2 may be adjusted to the deployed state when the aircraft is taking off and entering cruise conditions, such that the wing elements 2 provide lift to the aircraft. When the aircraft lands, can with wing part 2 adjusts to fold condition, this moment first supporting part 21 can be as the undercarriage, first supporting part 21 can be for shaft-like structure for when the aircraft lands to the ground first supporting part 21 has sufficient supporting area, guarantees the stable parking after the aircraft lands.

It is emphasized that the wing parts 2 need to be in a dead centre position in either the deployed or folded position to ensure that the aircraft is stable in either the deployed or folded position.

The aircraft provided by the embodiment of the utility model is provided with a rotor wing part 3 and a foldable wing part 2, the wing part 2 is provided with a first supporting part 21, and when the wing part 2 is in a folded state, the first supporting part 21 can be used as an undercarriage to support the whole aircraft; and can realize vertical takeoff and landing through rotor part 3, after the aircraft entered cruise the state, wing part 2 expandes, provides lift for the aircraft to energy saving, and then can prolong the aircraft journey.

The embodiment of the present invention provides a position of the cabin component 1 can be determined according to different requirements, for example: the cabin components 1 can be arranged on top of the aircraft to provide installation space for other avionic structures. The wing part 2 and the rotor part 3 can be mounted in a plurality of positions on the nacelle part 1, and it is necessary to ensure that the wing part 2 and the rotor part 3 do not interfere with each other. For example: the wing parts 2 can be arranged on both sides of the nacelle part 1, or the wing parts 2 can also be arranged above the nacelle part 1. Likewise, the rotor parts 3 can be arranged on both sides of the cabin part 1 or the rotor parts 3 can be arranged below the cabin part 1.

In some embodiments, the cabin component 1 comprises: the cabin body 11, the wing part 2 with the rotor part 3 all with the cabin body 11 is connected. It will be appreciated that the wing components 2 and the rotor components 3 may be directly connected to the nacelle body 11.

In other embodiments, referring to fig. 1, 2 and 4, the wing component 2 and/or the rotor component 3 may be indirectly connected to the nacelle body 11. The cabin component 1 further comprises: the second support portion 12, through which the wing component 2 and/or the rotor component 3 are connected to the cabin body 11, may be a plate-shaped structure 12, but is not limited thereto.

For example: referring to fig. 1, 4 and 5, the wing components 2 are located on two sides of the cabin body 11, the rotor components 3 are located below the cabin body 11, the rotor components 3 are connected to the cabin component 1 through the second support portion 12, and the wing components 2 are directly connected to the cabin body 11. In this case, the second support portion 12 is located between the cabin body 11 and the rotor component 3, the second support portion 12 may be used as a mounting seat for the folding assembly 23, and the second support portion 12 may also be used to support the wing body 22, so that the wing body 22 is used as a landing gear when in the folded state; when the wing body 22 is in the unfolded state, the wing body 22 can have a long span, so that sufficient lift force can be provided. Referring to fig. 2, the wing component 2 is located above the cabin body 11, the rotor component 3 is located on two sides of the cabin body 11, the wing component 2 is connected to the cabin body 11 through the second supporting portion 12, and the rotor component 3 is directly connected to the cabin body 11. When the wing body 22 is in a bending state, after the wing body 22 is unfolded, the height of the wing body 22 is increased, so that the second supporting portion 12 can be omitted, as shown in fig. 3, the wing parts 2 are located on two sides of the cabin body 11, the rotor parts 3 are located below the cabin body part 1, the wing parts 2 and the rotor parts 3 are directly connected with the cabin body 11, and the height of the cabin body 11 is reduced by the mode, so that the gravity center of the aircraft is reduced.

With continued reference to fig. 1-6, the wing component 2 includes: wing body 22 and folding assembly 23; wherein, the folding assembly 23 is used for driving the wing body 22 to fold or unfold. One end of the wing body 22 is connected with the cabin component 1, and the first supporting part 21 is arranged at the end part of the other end of the wing body 22; one end of the folding assembly 23 is connected to the wing body 22, the other end of the folding assembly 23 is connected to the cabin component, and the folding assembly 23 is used to enable the wing body 22 to be in a folded state or an unfolded state.

In the embodiment of the present invention, the folding assembly 23 may be disposed on the second supporting portion 12 of the wing component 2, and it can be understood that one end of the folding assembly 23 is connected to the second supporting portion 12, and the other end of the folding assembly 23 is connected to the wing body 22. Further, the folding assembly 23 is connected to the wing body 22 through a hinge shaft. The wing body 22 can be made to be in an unfolded or folded state by the driving of the folding assembly 23.

Referring to fig. 6, further, the folding assembly 23 may include: a first driving structure 231, one end of the first driving structure 231 is connected to the cabin component, and the other end of the first driving structure 231 is connected to the wing body 22. Wherein the first driving structure 231 is used for driving the wing body 22 to fold or unfold. The first driving structure 231 may be a hydraulic cylinder, a steering engine, a servo motor, a stepping motor, or the like, but is not limited thereto. Because the steering engine has advantages such as low price and compact structure, the steering engine can be preferably adopted to first drive structure 231.

It should be noted that the first driving structure 231 may directly or indirectly drive the wing body 22 to fold or unfold. When the first driving structure 231 drives the wing body 22 to fold or unfold in a direct manner, the first driving structure 231 is directly connected with the wing body 22. When the first driving structure 231 drives the wing body 22 to fold or unfold in an indirect manner, the first driving structure 231 may be indirectly connected with the wing body 22 through a link structure, a lead screw structure, a gear structure, or the like.

When the first driving structure 231 indirectly drives the wing body 22 to fold or unfold in a link structure, the folding assembly 23 further includes, in addition to the first driving structure 231: a rocker arm 232 and a connecting rod 233, wherein the other end of the first driving structure 231 is hinged with one end of the rocker arm 232; the other end of the rocker arm 232 is hinged to one end of the connecting rod 233, and the other end of the connecting rod 233 is hinged to the wing member 2.

In the embodiment of the present invention, the first driving structure 231, the wing body 22, the rocker arm 232, and the connecting rod 233 form a four-bar structure. The first driving structure 231, the wing body 22, the rocker 232 and the link 233 can realize the unfolding or folding of the wing body 22, and the wing body 22 can be positioned at the dead point position in the unfolding state and the folding state by properly designing the sizes of the components.

In order to facilitate the fastening of the first drive structure 231 to the cabin component 1, the folding assembly 23 further comprises: a base 234, and the first driving structure 231 is connected to the cabin component 1 through the base 234. For example: the first driving structure 231 is fixedly connected to the cabin component 1 by a bolt or a rivet structure.

In order to facilitate assembling the wing body 22 and the capsule component 1 together, a first connecting portion 221 is disposed at one end of the wing body 22, and a second connecting portion adapted to the first connecting portion 221 is disposed on the capsule component 1. Further, the second connection portion is provided on the capsule body of the capsule component 1. The first connecting portion 221 may be a plurality of protrusions or grooves, and correspondingly, the second connecting portion may be a groove or a protrusion. For example: referring to fig. 7, the first connection portion 221 may be a plurality of square protrusions arranged in an array, and correspondingly, the second connection portion may be a plurality of square grooves arranged in an array.

Optionally, said rotor member 3 comprises: a rotor body 31 and a second drive structure 32; wherein the second drive structure 32 is connected to the cabin component 1, and the rotor body 31 is connected to the second drive structure 32. The second driving structure 32 is used for driving the rotor body 31 to rotate, and the second driving structure 32 may be a motor.

In order to facilitate mounting of the rotor component 3 to the nacelle component 1, the rotor component 3 further comprises: a frame 33, by means of which frame 33 the second drive structure 32 is connected to the cabin part 1. Wherein the rotor part 3 can be connected to the cabin part 1 via the frame 33 and interference between the rotor part 3 and the cabin part 1 or the wing part 2 can also be avoided.

In some embodiments, the frame 33 may have an H-shaped configuration. The number of the rotor body 31 and the second driving structure 32 may be at least one. There are various ways of connecting the rotor body 31 and the second drive structure 32. For example: referring to fig. 1 to 5, when there are 4 rotor units 3, 4 rotor units 3 may be disposed at four corners of the airframe 33, that is, the rotor units 3 may be disposed in a 4-axis multi-rotor or coaxial multi-rotor layout. When there are 8 rotor parts 3, the rotor parts 3 can be arranged in an 8-axis feathered multi-rotor arrangement. Preferably, the wing parts 2 can be arranged in a 4-axis multi-rotor configuration. The second drive structure 32 may be oriented downward as shown in fig. 1-5, so that the rotor body 31 and the wing part 2 are separated from each other, thereby avoiding interference and facilitating folding or unfolding of the wing part 2. The layout mode can realize the vertical take-off and landing and attitude control of the aircraft by controlling the rotating speed of the second driving structure 32.

In the embodiment of the present invention, the first driving structure 231 may drive the wing body 22 to fold or unfold in an indirect or direct manner, and when the wing body 22 is in the folded state, the first supporting portion 21 at the other end of the wing body 22 may be used as an undercarriage to support the whole aircraft; the wing body 22 may provide lift to the aircraft when the wing body 22 is in the deployed state.

The above detailed description does not limit the scope of the present invention. Those skilled in the art will appreciate that various modifications, combinations, sub-combinations, and substitutions can occur, depending on design requirements and other factors. Any modification, equivalent replacement, and improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. An aircraft, characterized in that it comprises:

a cabin component (1);

the foldable wing component (2), one end of the wing component (2) is connected with the cabin component (1), and the other end of the wing component (2) is provided with a first supporting part (21);

a rotor component (3), the rotor component (3) being connected to the cabin component (1).

2. The aircraft of claim 1, characterized in that the cabin component (1) comprises:

cabin body (11), wing part (2) and rotor part (3) all with cabin body (11) are connected.

3. The aircraft of claim 2, characterized in that the cabin component (1) further comprises:

a second support part (12), by means of which the wing part (2) and/or the rotor part (3) is connected to the cabin body (11).

4. The aircraft of claim 1, characterized in that the wing element (2) comprises:

the aircraft wing comprises a wing body (22), one end of the wing body (22) is connected with the cabin component (1), and the first supporting part (21) is arranged at the other end of the wing body (22);

the wing comprises a folding assembly (23), one end of the folding assembly (23) is connected with the wing body (22), the other end of the folding assembly (23) is connected with the cabin component, and the folding assembly (23) is used for enabling the wing body (22) to be in a folded state or an unfolded state.

5. The aircraft according to claim 4, characterized in that said folding assembly (23) comprises:

a first drive structure (231), one end of the first drive structure (231) being connected to the nacelle component, the other end of the first drive structure (231) being connected to the wing body (22).

6. The aircraft of claim 5, characterized in that the folding assembly (23) further comprises:

the other end of the first driving structure (231) is hinged with one end of the rocker arm (232);

the other end of the rocker arm (232) is hinged to one end of the connecting rod (233), and the other end of the connecting rod (233) is hinged to the wing component (2).

7. The aircraft of claim 5, characterized in that the folding assembly (23) further comprises:

a base (234), the first drive arrangement (231) being connected to the cabin component (1) via the base (234).

8. The aircraft of claim 4, characterized in that one end of the wing body (22) is provided with a first connection (221), and the nacelle component (1) is provided with a second connection adapted to the first connection (221).

9. The aircraft of claim 1, characterized in that said rotor member (3) comprises:

a rotor body (31);

a second drive structure (32), the second drive structure (32) being connected to the cabin component (1), the rotor body (31) being connected to the second drive structure (32).

10. The aircraft of claim 9, characterized in that said rotor member (3) further comprises:

a frame (33), the second drive structure (32) being connected to the cabin part (1) via the frame (33).