CN212074397U

CN212074397U - Rotary wing retraction mechanism and unmanned aerial vehicle

Info

Publication number: CN212074397U
Application number: CN202020519077.0U
Authority: CN
Inventors: 张恒睿; 许旭; 胡志龙
Original assignee: China Science & Technology Co ltd
Current assignee: China Science & Technology Co ltd
Priority date: 2020-04-10
Filing date: 2020-04-10
Publication date: 2020-12-04
Anticipated expiration: 2030-04-10

Abstract

The utility model discloses a rotary retraction jack of a wing and an unmanned aerial vehicle, wherein the rotary retraction jack of the wing comprises a lifting rotating device, and a main wing and a horizontal tail wing both rotate and retract by taking the lifting rotating device as a center; the lifting and rotating device comprises a double-sliding-groove lifting mechanism and a rotating mechanism which drive wings at two sides to rotate and retract; the double-sliding-groove lifting mechanism comprises a first rotating column connected with one side wing, at least two oblique guide grooves are formed in the side face of the first rotating column, and horizontal cylindrical pins capable of sliding relative to the oblique guide grooves are inserted in the oblique guide grooves, so that the rotating motion of the first rotating column is converted into rotating lifting motion to drive the one side wing to rotate and lift; the rotating mechanism comprises a second rotating column connected with the wing on the other side, and the rotating motion of the second rotating column drives the wing on the other side to rotate. The wing rotating mechanism realizes linkage of the main wing, the horizontal tail wing and the vertical tail wing, and can automatically release and unfold the wings under the action of the spring connecting rod mechanism.

Description

Rotary wing retraction mechanism and unmanned aerial vehicle

Technical Field

The utility model relates to an unmanned air vehicle technique field, more specifically say, relate to a rotatory jack of wing and have this rotatory jack's unmanned aerial vehicle.

Background

The conventional fixed wing unmanned aerial vehicle has a long wingspan and is inconvenient to store and transport, generally, wings are detached to be placed or packaged for transport, time and labor are wasted, a large space is occupied, and the wings are connected to a machine body when taking off is needed; on the other hand, when the unmanned aerial vehicle is launched, a professional flyer is needed to operate, otherwise, the flying track is difficult to guarantee.

SUMMERY OF THE UTILITY MODEL

1. Technical problem to be solved by the utility model

The utility model aims to overcome the not enough of the inconvenient storage of current unmanned aerial vehicle wing and transportation among the prior art, provide a rotatory jack mechanism of wing, adopt the technical scheme of the utility model, can realize whole folding and automatic span that expandes. It is still another object of the present invention to provide an aircraft having the above-mentioned rotary wing retraction mechanism.

2. Technical scheme

In order to achieve the above purpose, the utility model provides a technical scheme does: the rotary retraction mechanism of the wing comprises a lifting and rotating device, and the main wing and the horizontal tail wing respectively rotate and retract by taking the lifting and rotating device as a center;

the lifting and rotating device comprises a double-sliding-groove lifting mechanism and a rotating mechanism which drive wings at two sides to rotate and retract;

the double-sliding-groove lifting mechanism comprises a first rotating column connected with one side wing, at least two oblique guide grooves are formed in the side face of the first rotating column, and horizontal cylindrical pins capable of sliding relative to the oblique guide grooves are inserted in the oblique guide grooves, so that the rotating motion of the first rotating column is converted into rotating lifting motion to drive the one side wing to rotate and lift;

the rotating mechanism comprises a second rotating column connected with the wing on the other side, and the rotating motion of the second rotating column drives the wing on the other side to rotate.

As a further improvement of the present invention, the second rotary column includes a second inner sleeve and a second outer sleeve that are mutually sleeved, and the first rotary column is sleeved inside the second inner sleeve.

As a further improvement, the utility model also comprises a spring link mechanism, and the two ends of the spring link mechanism are respectively connected with the lifting and rotating device of the main wing and the horizontal tail wing through a linkage mechanism.

As a further improvement, the spring link mechanism includes a spindle connecting rod, the both ends of the spindle connecting rod and the link gear rigid connection of both sides are provided with movable spring housing on the spindle connecting rod of main wing one side, are equipped with fixed spring housing on the spindle connecting rod of horizontal fin one side, be provided with the spring between movable spring housing and the fixed spring housing.

As a further improvement of the present invention, the linkage mechanism comprises an auxiliary rotating rod and a linear slider, one end of the auxiliary rotating rod is slidably connected with the first rotating column, the other end of the auxiliary rotating rod is connected with the linear slider, and the rotating motion of the first rotating column is output as the linear motion of the linear slider through the auxiliary rotating rod; the linear motion of the linear slider is output as the rotary motion of the first rotary column through the auxiliary rotary rod.

As a further improvement of the utility model, the main shaft connecting rod is rigidly connected with the linear sliding blocks on the two sides.

As a further improvement of the present invention, the linkage mechanism further includes a linear slide rail for sliding the linear slide block.

As a further improvement, the linkage mechanism on one side of the horizontal tail is provided with a rotary connecting rod mechanism which enables the vertical tail to rotate and retract.

As a further improvement, the rotary linkage mechanism includes linkage rods symmetrically distributed on both sides of the linkage mechanism, the linkage rods are connected with the linear sliders through rotating shafts, and the linkage rods are provided with fixing portions for fixing vertical tail fins.

As a further improvement of the present invention, an aircraft comprises the rotary folding and unfolding mechanism of the wing as described above.

3. Advantageous effects

Adopt the technical scheme provided by the utility model, compare with prior art, have following beneficial effect:

1. the utility model discloses a rotatory jack of wing realizes folding of host computer wing and horizontal tail wing through lifting and drop rotating device and receive and releases, and the both sides wing is folding when receiving and releasing in opposite directions, must appear interfering phenomenon, and this just requires in folding while, and the both sides wing should be in different heights, has guaranteed through two chute mechanisms and rotary mechanism that the both sides wing can not appear controlling the interference phenomenon when folding receiving and releasing.

2. The utility model discloses a rotatory jack of wing, host computer wing and vertical tail wing and horizontal tail wing need not dismantle, and wing and fuselage integral connection link can automatic release expansion wing under spring link mechanism's effect.

3. The utility model discloses a rotary folding and unfolding mechanism of a wing, which realizes the non-disassembly, integral folding and unfolding of the wing span, the linkage of a main wing, a horizontal tail wing and a vertical tail wing, the folding can be completed instantly without technology, and the minimum packaging and transportation space is provided; when the unmanned aerial vehicle is used for launching on site, a professional flyer is not needed, and the main wing, the horizontal tail wing and the vertical tail wing are automatically unfolded at the same time for remote flight control.

Drawings

Fig. 1 is a schematic structural diagram of an aircraft according to the present invention;

fig. 2 is a schematic structural diagram of an aircraft according to the present invention;

FIG. 3 is a schematic structural view of the lifting and rotating device;

FIG. 4 is a schematic view of the wing in an open (unfolded) configuration;

FIG. 5 is a schematic view of the wing during folding;

FIG. 6 is a schematic view of the folded wing;

the reference numerals in the schematic drawings illustrate:

1. a main wing; 2. a horizontal rear wing; 3. a vertical tail; 4. a lifting and rotating device; 5. a spring link mechanism; 6. a rotating link mechanism; 7. a linkage mechanism; 41. a first spin column; 411. an oblique guide groove; 412. a horizontal cylindrical pin; 42. a second spin column; 421. a second inner sleeve; 422. a second outer sleeve; 51. a spindle connecting rod; 511. fixing the spring sleeve; 512. a movable spring housing; 513. a spring; 61. a first linkage rod; 62. a second linkage rod; 63. a fixed part; 71. an auxiliary rotating rod; 72. a linear slider; 73. a linear slide rail.

Detailed Description

For a further understanding of the present invention, reference will now be made in detail to the present invention, examples of which are illustrated in the accompanying drawings.

In the description of the present invention, it is to be understood that the terms "center", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "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 description and simplicity of description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be construed as limiting the present invention.

In the description of the present invention, a plurality of means are one or more, a plurality of means are two or more, and the terms greater than, less than, exceeding, etc. are understood as not including the number, and the terms greater than, less than, within, etc. are understood as including the number. If the first and second are described for the purpose of distinguishing technical features, they are not to be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated or implicitly indicating the precedence of the technical features indicated.

In the description of the present invention, unless there is an explicit limitation, the words such as setting, installation, connection, etc. should be understood in a broad sense, and those skilled in the art can reasonably determine the specific meanings of the above words in combination with the specific contents of the technical solution.

Referring to fig. 1-3, the rotary retraction mechanism of the wing includes two lifting/lowering rotary devices 4, and the main wing 1 and the horizontal tail wing 2 are respectively rotatably retracted and retracted around the respective lifting/lowering rotary devices 4; the lifting and rotating device 4 comprises a double-sliding-groove lifting mechanism and a rotating mechanism which drive wings at two sides to rotate and retract; the double-sliding-groove lifting mechanism comprises a first rotating column 41 connected with one side wing, at least two oblique guide grooves 411 are arranged on the side surface of the first rotating column, and horizontal cylindrical pins 412 capable of sliding relative to the oblique guide grooves 411 are inserted into the oblique guide grooves 411, so that the rotating motion of the first rotating column 41 is converted into rotating lifting motion for driving the one side wing to rotate and lift; the rotating mechanism comprises a second rotating column 42 connected with the wing on the other side, and the rotating motion of the second rotating column 42 drives the wing on the other side to rotate.

Taking the main wing 1 as an example, when the wings on the two sides are folded and folded in opposite directions, an interference phenomenon is inevitably generated, which requires that the wings on the two sides should be at different heights while being folded. The main wing 1 is installed at the upper end of the lifting and rotating device 4, when the main wing 1 is folded and unfolded, the first rotating column 41 and the second rotating column 42 rotate to drive the wings at the left side and the right side of the main wing 1 to rotate in opposite directions, the wing edge connected with the first rotating column 41 rotates and ascends and descends, and the wing connected with the second rotating column 42 only rotates, so that the interference phenomenon of the wings at the two sides is avoided, the folding and unfolding operation of the main wing 1 is completed, and the processes are opposite when the wings are unfolded.

The folding process of collecting and releasing the horizontal tail wing 2 is the same as that of the main wing, and is not repeated here, and the difference is only that: since the main wing 1 is installed at the upper end of the body and the horizontal rear wing 2 is installed at the lower end of the body, the orientations of the elevation rotation means 4 on the main wing 1 and the horizontal rear wing 2 are different by 180 °.

The utility model discloses a lifting and rotating device 4 realizes folding receiving and releasing of main wing 1 and horizontal tail wing 2, has guaranteed through double-chute mechanism and rotary mechanism that the interference phenomenon can not appear when folding receiving and releasing of both sides wing.

In a preferred embodiment, the second rotating column 42 includes a second inner sleeve 421 and a second outer sleeve 422, which are sleeved with each other, and the first rotating column 41 is sleeved inside the second inner sleeve 421. The first rotating column 41, the second inner sleeve 421 and the second outer sleeve 422 are all hollow structures, the first rotating column 41 independently drives one wing to rotate and lift, and the second rotating column 42 independently drives the other wing to rotate.

Referring to fig. 4-6, in a preferred embodiment, the wing rotary retraction mechanism further includes a spring linkage 5, and both ends of the spring linkage 5 are respectively connected to the lifting rotary device 4 of the main wing 1 and the horizontal rear wing 2 through a linkage 7.

In a preferred embodiment, the spring linkage mechanism 5 includes a spindle link 51, two ends of the spindle link 51 are rigidly connected to the linkages 7 on two sides, a movable spring housing 512 is disposed on the spindle link 51 near the main wing 1, a fixed spring housing 511 is disposed on the spindle link 51 near the horizontal tail wing 2, and a spring 513 is disposed between the movable spring housing 512 and the fixed spring housing 511. The movable spring housing 512 is movable on the spindle link 51, and the fixed spring housing 511 is fixed on the spindle link 51. Two ends of the spring link mechanism 5 are respectively and rigidly connected with the linkage mechanism 7, and a bridge is provided for linkage folding of the main wing 1 and the horizontal tail wing 2.

In a preferred embodiment, the linkage mechanism 7 includes an auxiliary rotating rod 71 and a linear slider 72, one end of the auxiliary rotating rod 71 is connected with the first rotating column 41 in a sliding manner, and the other end is connected with the linear slider 72, and the rotating motion of the first rotating column 41 can be output as the linear motion of the linear slider 72 through the auxiliary rotating rod 71; the linear motion of the linear slider 72 can be output as the rotational motion of the first rotating cylinder 41 through the auxiliary rotating lever 71.

In a preferred embodiment, the spindle link 51 is rigidly connected to the linear slides 72 on both sides,

when the main wing 1 rotates to be folded, the linkage mechanism 7 on one side of the main wing 1 drives the linkage mechanism 7 on one side of the horizontal tail wing 2 through the main shaft connecting rod 51, and the linkage mechanism 7 on one side of the horizontal tail wing 2 drives the horizontal tail wing 2 to rotate to be folded.

The folding and folding linkage process of the main wing 1 and the horizontal tail wing 2 comprises the following steps: the first and second rotary columns of the main wing 1 rotate to drive the wings on both sides of the main wing 1 to rotate, at this time, the auxiliary rotary rod 71 outputs the rotary motion of the first rotary column 41 as the linear motion of the linear slider 72, the motion is transmitted to the linear motion of the linear slider 72 at the horizontal tail wing 2 through the spring link mechanism 5, and then the auxiliary rotary rod 71 outputs the linear motion as the rotary retraction motion of the horizontal tail wing 2 again. Set up link gear's aim at: the main wing 1 can rotate to retract and the horizontal tail wing 2 can rotate to retract and retract, so that the main wing 1 and the horizontal tail wing 2 can be folded or unfolded simultaneously.

In practical application, referring to fig. 4, taking the linkage mechanism 7 on one side of the main wing 1 as an example, a linear sliding slot perpendicular to the first rotary column 41 is convexly formed at the lower end of the first rotary column 41, the auxiliary rotary rod 71 is inserted into the linear sliding slot, the auxiliary rotary rod 71 is parallel to the first rotary column 41, the upper end of the auxiliary rotary rod 71 is connected to the linear slider 72, the auxiliary rotary rod 71 is driven to rotate while the first rotary column 41 rotates, the auxiliary rotary rod 71 slides in the linear sliding slot, and the linear slider 72 is driven to slide back and forth, which substantially outputs the rotary motion of the first rotary column 41 as the linear motion of the linear slider 72.

The linkage mechanism 7 on one side of the horizontal tail wing 2 is the same as the main wing 1, and is not described herein again, but the difference lies in: since the orientations of the lifting and rotating devices 4 on the main wing 1 and the horizontal rear wing 2 differ by 180 °, the corresponding linkage 7 also differs in orientation by 180 °.

In a preferred embodiment, the linkage mechanism 7 further comprises a linear slide 73 that slides the linear slide 72.

In a preferred embodiment, a rotating link mechanism 6 for rotatably retracting the vertical tail 3 is arranged on the linkage mechanism 4 at one side of the horizontal tail 2, so that the vertical tail 3 can be retracted and retracted together in a linkage and folding manner.

In a preferred embodiment, the rotating link mechanism 6 comprises linkage rods symmetrically distributed on two sides of the linkage mechanism 7, the linkage rods are connected with the linear sliding blocks 72 through rotating shafts, and the linkage rods are provided with fixing parts 63 for fixing the vertical wings 3.

In practical application, the linkage rod comprises a first linkage rod 61 and a second linkage rod 62 which are connected through a rotating shaft and can be linked, the free end of the first linkage rod 61 is connected to the linear sliding block 72 through the rotating shaft, and the free end of the second linkage rod 62 is provided with a fixing part 63 for fixing the vertical tail fin 3. When the linear sliding block 72 on one side of the horizontal tail wing 2 slides, the linkage rod is driven to be linked, and then the vertical tail wing 3 is driven to be folded and unfolded.

An unmanned aerial vehicle, its rotatory jack that includes foretell wing.

The present invention and its embodiments have been described above schematically, and the description is not limited thereto, and what is shown in the drawings is only one of the embodiments of the present invention, and the actual structure is not limited thereto. Therefore, if the person skilled in the art receives the teaching of the present invention, without departing from the inventive spirit of the present invention, the person skilled in the art should also design the similar structural modes and embodiments without creativity to the technical solution, and all shall fall within the protection scope of the present invention.

Claims

1. The rotary retraction mechanism of the wing is characterized in that: the main wing (1) and the horizontal tail wing (2) rotate and retract by taking the lifting and rotating device (4) as a center respectively;

the lifting and rotating device (4) comprises a double-sliding-groove lifting mechanism and a rotating mechanism which drive wings on two sides to rotate and retract;

the double-sliding-groove lifting mechanism comprises a first rotating column (41) connected with one side wing, at least two inclined guide grooves (411) are formed in the side face of the first rotating column, and horizontal cylindrical pins (412) capable of sliding relative to the inclined guide grooves are inserted into the inclined guide grooves (411), so that the rotating motion of the first rotating column (41) is converted into rotating lifting motion, and the rotating lifting motion is used for driving one side wing to rotate and lift;

the rotating mechanism comprises a second rotating column (42) connected with the wing on the other side, and the rotating motion of the second rotating column (42) drives the wing on the other side to rotate.

2. A rotary wing retraction mechanism according to claim 1, wherein: the second rotating column (42) comprises a second inner sleeve (421) and a second outer sleeve (422) which are sleeved with each other, and the first rotating column (41) is sleeved inside the second inner sleeve (421).

3. A rotary wing retraction mechanism according to claim 1, wherein: and the lifting and rotating device also comprises a spring connecting rod mechanism (5), and two ends of the spring connecting rod mechanism are respectively connected with the lifting and rotating device (4) of the main wing (1) and the horizontal tail wing (2) through a linkage mechanism (7).

4. A rotary wing retraction mechanism according to claim 3, wherein: spring link mechanism (5) include main shaft connecting rod (51), the link gear (7) rigid connection of both ends and both sides of main shaft connecting rod (51), be provided with movable spring housing (512) on main shaft connecting rod (51) of main wing (1) one side, be equipped with fixed spring housing (511) on main shaft connecting rod (51) of horizontal tail wing (2) one side, be provided with spring (513) between movable spring housing (512) and fixed spring housing (511).

5. The rotary wing retractor mechanism of claim 4, wherein: the linkage mechanism (7) comprises an auxiliary rotating rod (71) and a linear sliding block (72), one end of the auxiliary rotating rod (71) is connected with the first rotating column (41) in a sliding mode, the other end of the auxiliary rotating rod is connected with the linear sliding block (72), and the rotating motion of the first rotating column (41) is output to be the linear motion of the linear sliding block (72) through the auxiliary rotating rod (71); the linear motion of the linear slider (72) is output as a rotational motion of the first rotary column (41) through the auxiliary rotary rod (71).

6. The rotary wing retractor mechanism of claim 5, wherein: the main shaft connecting rod (51) is rigidly connected with the linear sliding blocks (72) on the two sides.

7. The rotary wing retractor mechanism of claim 5, wherein: the linkage mechanism (7) further comprises a linear slide rail (73) which enables the linear slide block (72) to slide.

8. A rotary wing retraction mechanism according to claim 1, wherein: a rotating link mechanism (6) which enables the vertical tail (3) to rotate and retract is arranged on the linkage mechanism (7) at one side of the horizontal tail (2).

9. A rotary wing retraction mechanism according to claim 8, wherein: the rotating connecting rod mechanism (6) comprises linkage rods symmetrically distributed on two sides of the linkage mechanism (7), the linkage rods are connected with the linear sliding blocks (72) through rotating shafts, and fixing portions (63) used for fixing the vertical tail wings (3) are arranged on the linkage rods.

10. An unmanned aerial vehicle, its characterized in that: rotary pitch and yaw mechanism comprising a wing according to claims 1-9.