WO2017202222A1

WO2017202222A1 - Aerial vehicle and foldable landing gear thereof

Info

Publication number: WO2017202222A1
Application number: PCT/CN2017/084326
Authority: WO
Inventors: 胡华智; 靳洪胜
Original assignee: 亿航智能设备（广州）有限公司
Priority date: 2016-05-25
Filing date: 2017-05-15
Publication date: 2017-11-30
Also published as: CN205916326U

Abstract

An aerial vehicle and a foldable landing gear thereof, comprising: a first support frame provided with a first gear; a second support frame arranged below the first support frame and pivotally connected to the first support frame, the second support frame being provided with a second gear meshed with the first gear, and the first gear rotating to drive the second gear into rotation, thus allowing the first support frame to move relative to the second support frame.

Description

Aircraft and its folding stand

Technical field

The present application relates to an aircraft and a folding tripod for use on an aircraft, and more particularly to a folding tripod that can be automatically folded in the air when the aircraft is flying in the air.

Background technique

With the acceleration of the civilianization process of drone technology, multi-rotor aircraft, that is, drones, have begun to be used in various industries, especially in the field of image aerial photography. Image aerial photography requires the aircraft to install a retractable landing gear, so that some parts of the aircraft itself are taken into the picture during image capture.

At present, the folding structure is integrated on the motor, resulting in a large motor load, and no self-locking function, uneven force, resulting in unstable tripod and easy to damage when landing.

Therefore, it is necessary to design a new aircraft and its folding stand to overcome the above problems.

technical problem

Problem solution

Technical solution

The purpose of the present application is to provide a folding stand that is self-locking, capable of withstanding high impact forces and is very stable, enables stable landing when the aircraft is lowered, and automatically locks itself.

The purpose of the present application is as follows: a folding stand comprising: a first support frame is provided with a first gear; a second support frame is pivotally connected to the first support frame under the first support frame The second support frame is provided with a second gear that meshes with the first gear, and the first gear rotates to drive the second gear to rotate, so that the first support frame and the second support frame are opposite to the second support frame mobile.

Further, the first support frame extends downwardly to a fixed leg, a motor is fixed to the fixed leg, the rear side of the motor is provided with the first gear, and the second support frame is provided with a folding arm, One end of the folding arm is provided with the second gear, the other end of the folding arm is rotatably mounted to the second supporting frame, and the motor rotates to rotate the first gear to drive the second gear to rotate, so that The folding arm moves to move the first support frame and the second support frame relative to each other.

Further, the folding arm includes a first arm and a second arm, and the first arm rotates at one end Mounted on the front side of the first support frame, the other end of the first arm is rotatably mounted on the front side of the second support frame, and the second arm is provided at one end of the second arm Engaging with the first gear, the other end of the second arm is rotatably mounted on a rear side of the second support frame. .

Further, a lower end of the first support frame extends a limiting arm on a side of the folding arm to prevent the folding arm from excessively moving.

Further, an end of the limiting arm is provided with an arcuate limiting slot for limiting the folding arm.

Further, a first support arm is obliquely extended from a left end of the first support frame, a second support arm extends vertically upward from a right end of the first support frame, and a third support arm connects the first support arm and the third support arm a second support arm, the first support arm being lower than the second support arm such that the third support arm is gradually inclined upward from left to right.

The purpose of the present application is also to be achieved as follows: an aircraft includes: a flying body, the front end of the flying body is a nose, and the rear end is a tail; the folding stand is fixed to the bottom surface of the flying main 1 The third support arm is fixed to the bottom surface of the flying body.

Further, a first arm extends to the left side of the flying body, a second arm extends to the right side of the flying body, and the first arm is provided with a fixing portion connected to the flying body, and the fixing portion is front a first cantilever is bent forwardly from the side, and a second cantilever is bent backward from the rear side of the fixing portion, and a connecting portion connects the first cantilever and the second cantilever, so that the first cantilever, A through hole is defined between the second cantilever and the connecting portion.

Further, a thickness of the connection between the fixing portion and the flying body is greater than a thickness of the connection between the fixing portion and the first cantilever.

Further, a plane where the third support arm is located is in contact with a bottom surface of the fixing portion.

Further, the upper surface of the handpiece is provided with a first plane and a first curved surface extending from the first plane and extending smoothly downward from the first plane, and a second curved surface is smoothed downward from the first arc and backwards The extension is formed, an indicator light is disposed on the first arc surface, and the second arc surface is provided with a heat dissipation hole.

Advantageous effects of the invention

Beneficial effect

The beneficial effects of the present application are:

Compared with the prior art, one end of the second arm of the present application is provided with a second gear and the first gear The other end of the second arm is rotatably mounted on a rear side of the second support frame, and the motor rotates to drive the first gear to drive the second gear to rotate, so that the second arm The movement causes the first support frame and the second support frame to move relative to each other, thereby preventing the folding stand from having no self-locking function, uneven force, resulting in unstable tripod and easy damage during landing. .

Brief description of the drawing

DRAWINGS

Figure 1 is a front elevational view of the aircraft according to an embodiment of the present application;

2 is a top plan view of an aircraft according to an embodiment of the present application;

3 is a side view of the folding stand according to the embodiment of the present application in a closed state;

4 is a side view of the folding stand according to the embodiment of the present application in an open state;

Figure 5 is a perspective view of a folding arm according to an embodiment of the present application;

Fig. 6 is a perspective view of the electric motor according to the embodiment of the present application.

Description of the reference signs:

Flight main body 1, head 10, tail 11, indicator light 2, first plane 101, first curved surface 102, second curved surface 103, heat dissipation hole 104, first arm 12, second arm 13, fixed Portion 121, first cantilever 122, second cantilever 123, connecting portion 124, through hole 125, folding stand 3, first support frame 31, fixed leg 311, motor 4, first gear 41, second support frame 32, Folding arm 33, first arm 331, second arm 332, second gear 333, first support arm 312, second support arm 313, third support arm 314, limit arm 315, lock lever 5, aircraft Tripod 6.

Invention embodiment

Embodiments of the invention

The present application will be further described with reference to the drawings and specific embodiments in order to facilitate a better understanding of the purpose, structure, features and functions of the present application.

Referring to FIG. 1 , FIG. 2 and FIG. 3 , an aircraft comprising a flying body 1 , the flying body 1 is substantially elliptical, and an arm assembly disposed on the flying body 1 , the flying body 1 The front end is the head 10, the rear end is the tail 11, the thickness of the head 10 is smaller than the thickness of the tail 11, and the head 10 is provided with two indicator lights 2. A first plane 101 and a first curved surface 102 are formed on the upper surface of the head 10 from the first plane 101, and a second curved surface 103 is formed from the first curved surface 102. Under And the indicator light 2 is disposed on the first curved surface 102, and the two indicator lights 2 are symmetrically disposed on the left and right sides of the first curved surface 102, and the second arc The surface 103 is provided with a heat dissipation hole 104 for dissipating heat to the flying body 1.

Referring to FIG. 1 , FIG. 2 and FIG. 3 , the arm assembly includes a first arm 12 and a second arm 13 , and the left side of the flying body 1 extends outwardly from the first arm. 12, the second arm 13 extends outwardly from the right side of the flying body 1. The first arm 12 has the same structure as the second arm 13, and the first arm 12 is provided with a fixing portion. The connecting portion 121 is connected to the flying main body 1 , and the front side of the fixing portion 121 is bent forwardly to a first cantilever 122 . The rear side of the fixing portion 121 extends rearward and extends a second cantilever 123 , and a connecting portion 124 is connected. The first cantilever 122 and the second cantilever 123 form a through hole 125 between the first cantilever 122, the second cantilever 123 and the connecting portion 124, and the through hole 125 is provided The operator's hand makes it easier for the operator to hold the first arm 12 and the second arm 13 by the operator. The thickness of the joint of the fixing portion 121 with the flying body 1 is greater than the thickness of the joint of the fixing portion 121 and the first cantilever 122, thereby reinforcing the first arm 12 and the second arm 13 The strength is connected to the flying body 1. An antenna (not labeled) is disposed behind the second cantilever 123 on the left and right sides of the aircraft. The tail 11 is provided with a receiving cavity (not shown) for insertion of the battery component (not numbered).

Referring to FIG. 1 to FIG. 6 , a folding stand 3 is fixed to the bottom surface of the fixing portion 121 . The folding stand 3 includes: a first support frame 31, the first support frame 31 extends downwardly to a fixed leg 311, the fixing leg 311 is used for fixing a motor 4, and the rear side of the motor 4 is provided with a a first gear 41; a second support frame 32 is pivotally connected to the first support frame 31 under the first support frame 31; the second support frame 32 includes a folding arm 33, and the folding arm 33 includes a first arm 331 and a second arm 332. The first arm 331 is rotatably mounted on a front side of the first support frame 31, and the other end of the first arm 331 is rotatably mounted. On the front side of the second support frame 32; one end of the second arm 332 is provided with a second gear 333 meshing with the first gear 41, and the other end of the second arm 332 is rotatably mounted on the a rear side of the second support frame 32, the motor 4 rotates to drive the first gear 41 to drive the second gear 333 to rotate, so that the second arm 332 moves to make the first support frame 31 and The second support frame 32 is movable relative to the second support frame 32. A first support arm 312 extends obliquely from the left end of the first support frame 31, and a second support arm 313 and a third support arm 314 extend perpendicularly from the right end of the first support frame 31. Connecting the first support arm 312 and the second support arm 313, the first support arm 312 is lower than the second support arm 313, so that the third support arm 314 is gradually inclined upward from left to right. The plane in which the third support arm 314 is located is in contact with the bottom surface of the fixing portion 121. A limiting arm 315 is disposed on a side of the folding arm 33 to prevent the folding arm 33 from moving excessively. The limiting arm 315 is provided with an arc-shaped limiting slot at the end of the limiting arm 315 (not labeled) ) for limiting the movement of the second arm 332 excessively.

Please refer to FIG. 1 to FIG. 6 at the same time, further including a locking rod 5 rotatably mounted on the lower end of the second supporting frame 32 for locking an aircraft stand 6 and the second supporting frame 32.

Please refer to FIG. 1 to FIG. 6 simultaneously. In S1, the folding stand 33 is in a stowed state. When the folding stand 33 needs to be opened, the operator's manipulation command carries a set opening speed and an opening angle. After the control board is processed, a control signal is sent to a steering gear body, thereby driving the motor 4 to rotate at a specific (not shown) speed; and the first gear 41 drives the first gear 41 by the motor 4 The two gears 333 are rotated such that the second arm 332 moves downward, so that the second support frame 32 moves downward relative to the first support frame 31 when the first arm 331 is resisted. When the end of the inner wall of the arcuate limit notch is held, the folding stand 33 is opened to open the aircraft foot; S2, after the folding stand 33 reaches the set opening angle, the lock is rotated The buckle 5 causes the lock lever 5 to lock the aircraft stand 6 and the second support frame 32; S3, the folding stand 33 is in an open state, when the folding stand 33 needs to be manipulated to be stowed The operator's control command carries a set stowage speed through a control After the arithmetic processing, a control signal is sent to a steering gear body (not shown), thereby driving the motor 4 to rotate in a reverse direction at a specific speed; and the first gear 41 drives the first gear 41 by the motor 4 The two gears 333 are rotated in the direction such that the second arm 332 is moved upward, so that the second support frame 32 is moved upward relative to the first support frame 31 so as to be in a stowed state.

This application has the following beneficial effects:

Since the second arm 332 is provided with a second gear 333 at one end and the first gear 41, the other end of the second arm 332 is rotatably mounted on the rear side of the second support frame 32. The rotation of the motor 4 drives the first gear 41 to drive the second gear 333 to rotate, so that the second arm 332 moves to move the first support frame 31 and the second support frame 32 relative to each other. The folding tripod 33 is prevented from having a self-locking function, and the force is uneven, resulting in an unstable tripod and easy to be damaged when landing.

The above-mentioned embodiments are merely illustrative of several embodiments of the present application, and the description thereof is not to be construed as limiting. It should be noted that a number of variations and modifications may be made by those skilled in the art without departing from the spirit and scope of the present application. Therefore, the scope of the invention should be determined by the appended claims.

Claims

A folding stand characterized in that: the folding stand comprises:

a first support frame is provided with a first gear;

a second support frame is pivotally connected to the first support frame under the first support frame, and the second support frame is provided with a second gear to mesh with the first gear, and the first gear rotates to drive the second support frame The second gear rotates such that the first support frame and the second support frame move relative to each other.
The folding stand according to claim 1, wherein the first support frame extends downwardly from a fixed leg, a motor is fixed to the fixed leg, and the first gear is disposed on a rear side of the motor. The second support frame is provided with a folding arm, one end of the folding arm is provided with the second gear, the other end of the folding arm is rotatably mounted to the second support frame, and the motor rotates to make the first gear Rotating to drive the second gear to rotate, such that the folding arm moves to move the first support frame and the second support frame relative to each other.
The folding stand according to claim 2, wherein the folding arm comprises a first arm and a second arm, and the first arm is rotatably mounted to the first support frame at one end. a front side, the other end of the first arm is rotatably mounted on a front side of the second support frame, and one end of the second arm is provided with the second gear meshing with the first gear, The other end of the second arm is rotatably mounted on the rear side of the second support frame.
The folding stand according to claim 2, wherein a lower end of said first support frame extends a retaining arm on a side of said folded arm to prevent said folding arm from moving excessively.
The folding stand according to claim 4, wherein the end of the limiting arm is provided with an arcuate limiting slot for limiting the folding arm.
The folding stand according to claim 1, wherein a first support arm is obliquely extended from a left end of the first support frame, and a second support arm is vertically extended from a right end of the first support frame. a support arm connecting the first support arm and the second support arm, the first support arm being lower than the second support arm such that the third support arm Gradually upward from left to right.
The folding stand of claim 1 further comprising a latching lever rotatably mounted to the lower end of said second support for latching an undercarriage with said second support.
An aircraft characterized by comprising a folding stand according to any one of claims 1 to 7.

The aircraft further includes: a flying body, the front end of the flying body is a nose, and the rear end is a tail;

The folding stand is fixed to the bottom surface of the flying main 1 , and the third supporting arm is fixed to the bottom surface of the flying main body.
The aircraft according to claim 8, wherein a left arm of the flying body extends a first arm, a right arm of the flying body extends a second arm, and the first arm is provided with a fixing portion. The connecting portion is connected to the flying body, and the front side of the fixing portion is bent forwardly to bend a first cantilever. The rear portion of the fixing portion extends rearward and backward to bend a second cantilever, and a connecting portion connects the first cantilever and the The second cantilever is configured to define a through hole between the first cantilever, the second cantilever and the connecting portion.
The aircraft according to claim 9, wherein a thickness of the joint of the fixing portion with the flying body is greater than a thickness of the joint of the fixed portion and the first cantilever.
The aircraft according to claim 9, wherein a plane in which the third support arm is located is in contact with a bottom surface of the fixing portion.
The aircraft according to claim 8, wherein the upper surface of the head is provided with a first plane and a first curved surface is formed from the first plane and extends smoothly from the first plane, and a second curved surface An indicator light is disposed on the first arc surface, and a second heat dissipation hole is disposed on the second arc surface.