WO2019029387A1

WO2019029387A1 - Aerial vehicle and arm assembly and frame thereof

Info

Publication number: WO2019029387A1
Application number: PCT/CN2018/097520
Authority: WO
Inventors: 余春
Original assignee: 深圳市道通智能航空技术有限公司
Priority date: 2017-08-10
Filing date: 2018-07-27
Publication date: 2019-02-14
Also published as: CN207141359U

Abstract

An aircraft and an arm assembly (10) and frame thereof, the arm assembly (10) comprising: an elastic locking member (100), a fixing seat (200) and an arm (300); the arm (300) is rotatably connected to the fixing seat (200) such that the arm (300) may rotate relative to the fixing seat (200) between a folding position and an unfolding position; the elastic locking member (100) is connected to the fixing seat (200), being used for locking the arm (300) when the arm (300) is in the folding position or unfolding position. By means of the foregoing manner, stable folding and rapid unfolding of the arm may be achieved, thus reducing the volume of an unused unmanned aerial vehicle.

Description

Aircraft and its arm components and racks

Technical field

Embodiments of the present invention relate to the field of aircraft, and more particularly to an arm assembly of an aircraft, a frame, and an aircraft using the arm assembly or frame.

Background technique

With the development of science and technology, unmanned aerial vehicle technology is becoming more and more mature, and unmanned aerial vehicles are often used to perform tasks such as aerial photography, monitoring, and exploration. An unmanned aerial vehicle generally includes a fuselage and a plurality of arms extending outward from the fuselage for supporting the power assembly at a predetermined position around the fuselage to drive the unmanned aerial vehicle to fly.

When the UAV is not in use, the outwardly extending arm increases the volume of the UAV, which is not conducive to the storage and carrying of the UAV. In view of this, it is necessary to provide an arm assembly for an aircraft to solve the above problems.

Summary of the invention

The technical problem to be solved by the embodiments of the present invention is to provide an arm assembly, a frame, and an aircraft using the arm assembly or the frame, which can realize stable folding and rapid deployment of the arm, and reduce the UAV in Volume in non-use state.

In order to solve the above technical problem, a technical solution adopted by the present invention is to provide an arm assembly of an aircraft, including:

a fixing base connected to the fuselage of the aircraft for locking the arm when the arm is in the folded position or the deployed position;

a resilient locking member mounted to the mount;

An arm that is rotatably coupled to the mount such that the arm is rotatable relative to the mount between a folded position and a deployed position.

In an embodiment of the invention, the arm includes a pivotal connection with the fixed seat

An end portion, the proximal end portion is provided with a first groove and a second groove;

The elastic locking member includes a pressing block that engages with the first groove or the second groove and a resilient member for pressing the pressing piece into the first groove or the second groove;

The pressing block is engaged with the first groove when the arm is in the folded position; the pressing block is engaged with the second concave when the arm is in the deployed position a slot; the resilient member is compressed when the arm is between the folded position and the deployed position.

In an embodiment of the invention, the first groove or the second groove is a circular arc groove, and the pressure block is a circular arc shaped pressure piece.

In an embodiment of the invention, the fixing base includes an upper wall, a lower wall opposite to the upper wall, and a side wall connecting the upper wall and the lower wall, the upper wall and the lower side The wall and the side wall enclose a receiving cavity, and the proximal end of the arm is disposed in the receiving cavity.

In an embodiment of the invention, the proximal end portion is provided with a mounting hole;

The arm assembly further includes a rotating connector that is disposed through the mounting hole and connected to the fixing base.

In an embodiment of the invention, the rotary joint includes a rotating shaft having an internally threaded hole and a screw threadedly coupled to the internally threaded hole, the rotating shaft passing through the mounting hole.

In an embodiment of the invention, the rotating connecting member is a rotating shaft, and two ends of the rotating shaft are respectively connected to the upper wall and the lower wall of the fixing base.

In an embodiment of the invention, the elastic locking member is mounted to the side wall.

In an embodiment of the invention, when the arm is in the folded position, the arm is parallel to a sidewall of the fixing seat;

When the arm is in the deployed position, the arm is at a predetermined angle with a sidewall of the fixing seat.

The present invention also provides a frame for an aircraft for solving the technical problems thereof, the frame including a body and a boom assembly as described above connected to the body.

In an embodiment of the invention, two sets of the arm assemblies are disposed on the same side of the fuselage, and the two sets of arms on the same side of the fuselage are in a folded state when the rack is in a folded state. The arms of the assembly are different in height from the bottom of the fuselage.

The present invention also provides an aircraft for solving the technical problems thereof, the aircraft comprising a frame as described above and a flight control module mounted inside the frame.

The utility model has the beneficial effects that the arm assembly of the aircraft of the embodiment of the invention comprises an elastic locking member, a fixing base and an arm, wherein the arm is rotatably connected with the fixing seat, and the elastic locking member is connected with the fixing seat. It is used to lock the arm when the arm is in the folded position or the unfolded position, which can realize the stable folding and rapid deployment of the arm, and reduce the volume of the UAV in the non-use state.

DRAWINGS

The one or more embodiments are exemplified by the accompanying drawings in the accompanying drawings, and FIG. The figures in the drawings do not constitute a scale limitation unless otherwise stated.

1 is a structural exploded view of an arm assembly of an aircraft according to an embodiment of the present invention;

Figure 2 is a schematic view of the arm of the arm assembly shown in Figure 1 in a folded position;

Figure 3 is a schematic view of the arm of the arm assembly shown in Figure 1 in a deployed position;

4 is a schematic view of the aircraft of the embodiment of the present invention in an unfolded state;

Figure 5 is a schematic view of the aircraft of the embodiment of the present invention when the frame of the aircraft is in a folded state;

Figure 6 is another schematic view of the aircraft of the embodiment of the present invention when the frame of the aircraft is in a folded state;

Fig. 7 is still another schematic view of the aircraft of the embodiment of the present invention when the frame of the aircraft is in a folded state.

Specific embodiment

In order to facilitate the understanding of the present invention, the present invention will be described in more detail below with reference to the accompanying drawings and specific embodiments. It is to be noted that when an element is described as being "fixed" to another element, it can be directly on the other element or one or more of the elements in the middle. When an element is referred to as "connected" to another element, it can be a <RTI ID=0.0> </ RTI> </ RTI> <RTIgt; The terms "vertical," "horizontal," "left," "right," and the like, as used in this specification, are for the purpose of illustration.

Unless otherwise defined, all technical and scientific terms used in the specification are the same meaning The terms used in the description of the present invention are for the purpose of describing the specific embodiments and are not intended to limit the invention. The term "and/or" used in this specification includes any and all combinations of one or more of the associated listed items.

Referring to FIG. 1 , FIG. 1 is an exploded view of an arm assembly of an aircraft according to an embodiment of the present invention. As shown in FIG. 1 , the arm assembly 10 includes an elastic locking member 100 , a fixing base 200 , and an arm 300 . . The arm 300 is rotatably coupled to the fixed base 200 such that the arm 300 is rotatable relative to the fixed seat 200 between the folded position and the deployed position. The elastic locking member 100 is mounted to the fixed base 200 for being placed at the arm 300. The arm 300 is locked in the folded or deployed position.

The arm 300 includes a proximal end 310 that is rotationally coupled to the mount 200 and a distal end 320 that is remote from the proximal end 310. The end of the distal end portion 320 is provided with a power assembly (not shown) for driving the aircraft to move, such as driving the aircraft to take off, land, hover, change direction, speed, orientation, and the like.

The mount 200 includes an upper wall 210, a lower wall 220 disposed opposite the upper wall 210, and a side wall 230 connecting the upper wall 210 and the lower wall 220. The upper wall 210, the lower wall 220, and the side wall 230 are disposed to form a receiving cavity 240. The proximal end portion 310 of the arm 300 and the fixing base 200 is rotatably disposed in the accommodating cavity 240.

The proximal end portion 310 of the arm 300 is provided with a mounting hole 311 through which the mounting hole 311 passes. The arm assembly 10 further includes a rotary connector that is disposed through the mounting hole 311. The rotary connector is fixed to the upper wall 210 and/or the lower wall 220 of the mount 200 to rotatably mount the arm 300 to the mount 200. In the present embodiment, the rotary joint includes a rotating shaft 410 provided with an internally threaded hole and a screw 420 threadedly coupled to the internally threaded hole. The rotating shaft 410 is threadedly connected to the screw 420 after passing through the mounting hole 311. In other embodiments, the rotary joint may also include only the rotating shaft, and the two ends of the rotating shaft are respectively connected to the upper wall 210 and the lower wall 220 of the fixed base 200.

Referring to FIGS. 2 and 3 , the proximal end portion 310 is provided with a first recess 312 and a second recess 313 . In an embodiment of the invention, the elastic locking member 100 is mounted to the side wall 230 of the fixing base 200. The elastic locking member 100 includes a baffle 130 connected to the side wall 230 of the fixing base 200, a pressing block 110 engaged with the first groove 312 or the second groove 313, and a pressing block 110 for pressing the pressing block 110 into the first A recess 312 or a resilient element 120 in the second recess 313. The elastic member 120 has one end connected to the pressing block 110 and the other end connected to the baffle 130. When the arm 300 is between the folded position and the deployed position, the resilient member 120 is compressed. In other embodiments, the other end of the elastic member 120 can also be directly fixed to the fixing base 200. For example, the elastic member 120 is a compression spring, and a cylindrical pin can be disposed on the fixing seat, and the other end of the compression spring is sleeved on the cylinder. On the pin; for example, the elastic member 120 is a reset elastic piece, and the reset elastic piece can be fixed on the fixing base 200 by adhesive or welding.

As shown in FIG. 2, when the arm 300 is in the folded position, the clamp 110 is engaged with the first recess 312 to securely hold the arm 300 in the folded position. As shown in FIG. 3, when the arm 300 is in the deployed position, the clamp 110 is engaged with the second recess 313 to securely hold the arm 300 in the deployed position. Wherein, when the arm 300 is in the folded position, the arm 300 is parallel to the side wall 230 of the fixing base 200; when the arm 300 is in the deployed position, the arm 300 is at a predetermined angle with the side wall 230 of the fixing base 200, Such as 0°, 30°, 45° or 60°. As such, when the aircraft does not need to fly, the arm 300 is held in the folded position to facilitate storage, carrying or transportation of the aircraft.

When the arm 300 is rotated relative to the fixed seat 200 from one of the folded position and the deployed position to another position, the elastic potential energy stored by the elastic member 120 due to the compression can clamp the pressing block 110 to the concave corresponding to the position. In the slot. For example, when the arm 300 is in the folded position, the pressing block 110 is engaged with the first groove 312 of the arm 300, and the arm 300 is rotated from the folded position to the deployed position after being subjected to an external force in a certain direction, the elastic member. The 120 is compressed, and when the arm 300 is rotated to the deployed position, the elastic force of the elastic member 120 enables the clamp 110 to snap into the second recess 313 of the arm 300.

In order to facilitate the rotation of the arm 300 relative to the fixed base 200, the bottom of the first groove 312 or the second groove 313 of the arm 300 is a circular arc groove, correspondingly, with the first groove 312 or the second groove 313 The head of the combined compact 110 is also arcuate.

It should be understood by those skilled in the art that the number of the first groove 312 or the second groove 313 may be one or more. When the number of the first groove 312 or the second groove 313 is plural, the corresponding pressure block The number of the 110 and the elastic members 120 connected to the compact 110 is also plural.

Different from the prior art, the arm assembly of the aircraft of the embodiment includes the elastic locking member 100, the fixing base 200 and the arm 300. The arm 300 is rotatably connected with the fixing base 200, and the elastic locking member 100 and the fixing seat are fixed. The 200 fixed connection is used to lock the arm 300 when the arm 300 is in the folded position or the deployed position, which can achieve stable folding and rapid deployment of the arm, and reduce the volume of the UAV in the non-use state.

The embodiment of the invention further provides a frame of an aircraft, comprising a fuselage 20 and the arm assembly 10 as described above, wherein the fixed base 200 of the arm assembly 10 can be part of the fuselage 20 or independent of the machine The body 20 is fixedly connected to the body 20.

The specific shape and structure of the airframe 20 are not limited in this embodiment, and those skilled in the art can set according to specific requirements. Similarly, the number of the arm assemblies 10 can also be set according to specific requirements, such as two, three, four, six, etc., two or more sets of arm assemblies 10 along the center of the fuselage 20 Symmetrically disposed on the body 20. For convenience of description, the following embodiment is described by taking a rack including four sets of arm assemblies 10 as an example.

Please refer to FIG. 4. FIG. 4 is a schematic view of the aircraft frame in an unfolded state, and FIGS. 5-7 are schematic views of the aircraft frame in a folded state. Preferably, the same side of the fuselage 20 is oppositely provided with two sets of arm assemblies 10, and when the rack is in a folded state, the arms 300 of the two sets of arm assemblies 10 are different in height from the bottom of the body 20. When the frame is folded, the frame has the smallest lateral dimension and a more compact structure, as shown in Figure 5.

Embodiments of the present invention also provide an unmanned aerial vehicle including a rack as described above and a flight control module mounted inside the rack.

It is to be noted that the preferred embodiments of the present invention are described in the specification of the present invention, and the present invention may be embodied in many different forms and not limited to the embodiments described herein. These examples are not intended to be limiting as to the scope of the present invention, which is intended to provide a more thorough understanding of the present disclosure. Further, the above various technical features are further combined with each other to form various embodiments not enumerated above, and are considered as the scope of the description of the present invention; further, those skilled in the art can improve or change according to the above description. All such improvements and modifications are intended to be included within the scope of the appended claims.

Claims

An arm assembly for an aircraft, comprising:

a fixing base connected to the fuselage of the aircraft for locking the arm when the arm is in the folded position or the deployed position;

a resilient locking member mounted to the mount;

An arm that is rotatably coupled to the mount such that the arm is rotatable relative to the mount between a folded position and a deployed position.
The arm assembly of claim 1 wherein:

The arm includes a proximal end rotatably coupled to the mount, the proximal end being provided with a first recess and a second recess;

The elastic locking member includes a pressing block that engages with the first groove or the second groove and a resilient member for pressing the pressing piece into the first groove or the second groove;

The pressing block is engaged with the first groove when the arm is in the folded position; the pressing block is engaged with the second concave when the arm is in the deployed position a slot; the resilient member is compressed when the arm is between the folded position and the deployed position.
The arm assembly of claim 2, wherein

The first groove or the second groove is a circular arc groove, and the pressure block is a circular arc-shaped pressure piece.
The arm assembly according to any one of claims 1 to 3, characterized in that

The fixing base includes an upper wall, a lower wall opposite to the upper wall, and a side wall connecting the upper wall and the lower wall, and the upper wall, the lower wall and the side wall are circumferentially formed The accommodating cavity is disposed in the accommodating cavity.
The arm assembly of claim 5, wherein

The proximal end portion is provided with a mounting hole;

The arm assembly further includes a rotating connector that is disposed through the mounting hole and connected to the fixing base.
The arm assembly according to claim 5, wherein the rotary joint comprises a rotating shaft having an internally threaded bore and a screw threadedly coupled to the internally threaded bore, the rotary shaft passing through the mounting bore.
The arm assembly according to claim 5, wherein the rotating connecting member is a rotating shaft, and both ends of the rotating shaft are respectively connected to upper and lower walls of the fixing base.
The arm assembly according to any one of claims 4 to 7, wherein the elastic locking member is mounted to the side wall.
A boom assembly according to any one of claims 4-8, wherein

The arm is parallel to a side wall of the fixing seat when the arm is in the folded position;

When the arm is in the deployed position, the arm is at a predetermined angle with a sidewall of the fixing seat.
A frame for an aircraft, characterized in that the frame comprises a fuselage and the arm assembly of any one of claims 1-9 connected to the fuselage.
A frame for an aircraft according to claim 10, wherein

The same side of the fuselage is provided with two sets of the arm assemblies, and when the rack is in a folded state, the arms of the two sets of arm assemblies on the same side of the fuselage are compared to the The height of the bottom of the fuselage is not the same.
An aircraft characterized in that the aircraft comprises a frame as claimed in claim 10 or 11 and a flight control module mounted inside the frame.