Descending speed reducer for aerial photography unmanned aerial vehicle

Abstract

The utility model discloses an aerial photography unmanned aerial vehicle descending speed reducer in the technical field of unmanned aerial vehicles, which comprises an unmanned aerial vehicle body, wings are fixedly connected to the front and rear sides of the left and right side walls of the unmanned aerial vehicle body, the tops of the wings are provided with accommodating grooves, and the outer side walls of the wings on the left and right sides are fixedly connected with flying impellers. The device comprises an unmanned aerial vehicle body, descending speed reduction mechanisms are arranged on the left side and the right side of the unmanned aerial vehicle body, mounting plates are fixedly connected to the left side wall and the right side wall of the unmanned aerial vehicle body, landing buffer mechanisms are arranged below the mounting plates on the left side and the right side, and each descending speed reduction mechanism comprises a first telescopic rod, a connecting plate, a bottom plate, a second telescopic rod and a baffle. The structure design is reasonable, when the unmanned aerial vehicle lands, the descending speed of the unmanned aerial vehicle can be effectively reduced, the descending speed of the unmanned aerial vehicle is prevented from being too high, and impact force generated when the unmanned aerial vehicle lands can be effectively buffered and counteracted.

Description

TECHNICAL FIELD

[0001] The utility model relates to an unmanned plane technical field, concretely is a kind of aerial photography unmanned plane descent speed reducer. BACKGROUND

[0002] Aerial photography unmanned plane is also called aerial photography unmanned pilot aircraft, and is a set of aerodynamics, material mechanics, automatic control technology, software technology as an integrated high-tech product using radio remote control equipment and self-provided program control device to manipulate unmanned aircraft, and aerial photography unmanned plane has the advantages of high definition, large scale, small area and high current situation.

[0003] The existing aerial photography unmanned plane cannot effectively control the falling speed of the unmanned plane during landing, which may cause the unmanned plane to be damaged due to the excessive falling speed and impact with the ground, and the existing aerial photography unmanned plane lacks effective buffer mechanism during landing, which cannot effectively buffer the impact force during landing of the unmanned plane, so the unmanned plane is easily damaged. Therefore, we propose a kind of aerial photography unmanned plane descent speed reducer. UTILITY MODEL CONTENT

[0004] The utility model aims at providing a kind of aerial photography unmanned plane descent speed reducer to solve the problem that the existing aerial photography unmanned plane cannot effectively control the falling speed of the unmanned plane during landing in the above background technology, which may cause the unmanned plane to be damaged due to the excessive falling speed and impact with the ground, and the existing aerial photography unmanned plane lacks effective buffer mechanism during landing, which cannot effectively buffer the impact force during landing of the unmanned plane, so the unmanned plane is easily damaged.

[0005] To achieve the above purpose, the utility model provides the following technical scheme: a kind of aerial photography unmanned plane descent speed reducer, including unmanned plane body, the left and right side walls of the unmanned plane body are fixedly connected with aileron on front and back two sides, the top of the aileron is provided with receiving slot, the outer side wall of the aileron on left and right sides is fixedly connected with flight impeller, the left and right sides of the unmanned plane body are provided with descent speed reducer mechanism, the left and right side walls of the unmanned plane body are fixedly connected with mounting plate, and the lower portion of the mounting plate on left and right sides is provided with landing buffer mechanism.

[0006] As a further description of the above technical scheme:

[0007] Descent speed reducer mechanism includes first telescopic link, connecting plate, bottom plate, second telescopic link, baffle.

[0008] As a further description of the above technical scheme:

[0009] The first telescopic link is fixedly connected to the front and back side walls of the aileron, the end of the first telescopic link on left and right sides is fixedly connected with connecting plate, and the outer side wall of the connecting plate on left and right sides is fixedly connected with bottom plate.

[0010] As a further description of the above technical solutions:

[0011] The second telescopic rod is fixedly connected to the top of the bottom plate, and a baffle is fixedly connected between the top ends of the second telescopic rods on the front and back sides, and the baffle is located between the inner side walls of the storage groove.

[0012] As a further description of the above technical solutions:

[0013] The landing buffering mechanism comprises a mounting cylinder, a sealing rubber ring, damping oil, a pressing rod, a liquid permeation plate, a liquid permeation hole, a damping spring and a landing support.

[0014] As a further description of the above technical solutions:

[0015] The mounting cylinder is fixedly connected to the bottom of the mounting plate on the left and right sides, and the mounting cylinders are arranged in sequence from front to back, the bottom end of the mounting cylinder is bonded with the sealing rubber ring, and the inner cavity of the mounting cylinder is filled with the damping oil.

[0016] As a further description of the above technical solutions:

[0017] The pressing rod is inserted into the bottom end of the mounting cylinder, the outer side wall of the pressing rod is in contact with the sealing rubber ring, the top end of the pressing rod penetrates through the mounting cylinder and extends to the inner cavity of the mounting cylinder, the top end of the pressing rod is fixedly connected with the liquid permeation plate, a liquid permeation hole is formed around the top of the liquid permeation plate, and the liquid permeation holes are uniformly distributed.

[0018] As a further description of the above technical solutions:

[0019] The damping spring is embedded in the inner cavity of the mounting cylinder, and the damping spring is located above the liquid permeation plate.

[0020] As a further description of the above technical solutions:

[0021] The landing support is fixedly connected between the bottom ends of the pressing rods arranged in sequence from front to back on the left and right sides.

[0022] Compared with the prior art, the utility model has the advantages that:

[0023] 1. The aerial unmanned plane descending speed reducing device, when the unmanned plane is descending, the second telescopic rod is started to extend, the baffle installed on the second telescopic rod is moved out of the storage groove, then the first telescopic rod is started to extend, the connecting plate connected with the first telescopic rod is moved, the second telescopic rod on the bottom plate is moved, so that the baffle installed on the second telescopic rod is moved to the upper side of the flight impeller, the air vent of the flight impeller is blocked, the resistance when the unmanned plane body is descending is increased, the descending speed of the unmanned plane body is slowed down, so that the descending speed of the unmanned plane can be effectively slowed down when the unmanned plane is landing, and the descending speed of the unmanned plane is prevented from being too fast.

[0024] 2. The aerial unmanned plane descending speed reducing device, after the unmanned plane lands, the landing support is contacted with the ground to generate an impact force, the compression rod connected with the landing support absorbs the impact force, the compression rod is moved into the mounting cylinder, the liquid permeation plate installed on the compression rod extrudes the damping oil liquid and the shock absorbing spring in the mounting cylinder, the damping oil liquid flows to the other side of the liquid permeation plate through the liquid permeation hole on the liquid permeation plate to generate a damping force, meanwhile, the shock absorbing spring is deformed to cooperate with the liquid permeation plate extruding the damping oil liquid to buffer the impact force when the unmanned plane lands, so that the impact force when the unmanned plane lands can be effectively buffered and offset. BRIEF DESCRIPTION OF DRAWINGS

[0025] Fig. 1 It is a front view of the aerial unmanned plane descending speed reducing device provided by the utility model;

[0026] Fig. 2 It is a front view of the descending speed reducing mechanism of the aerial unmanned plane descending speed reducing device provided by the utility model;

[0027] Fig. 3 It is a sectional view of the landing buffering mechanism of the aerial unmanned plane descending speed reducing device provided by the utility model;

[0028] In the drawing: 100, unmanned plane body; 110, wing; 111, storage groove; 120, flight impeller; 130, first telescopic rod; 140, connecting plate; 141, bottom plate; 150, second telescopic rod; 160, baffle; 200, mounting plate; 210, mounting cylinder; 211, sealing rubber ring; 212, damping oil liquid; 220, compression rod; 221, liquid permeation plate; 222, liquid permeation hole; 230, shock absorbing spring; 240, landing support. DETAILED DESCRIPTION

[0029] With reference to the drawings of the embodiments of the present application, the technical solutions in the embodiments of the present application will be clearly and completely described, obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments of the present application, all other embodiments obtained by those skilled in the art without creative labor are within the scope of protection of the present application.

[0030] In the description of the present application, it should be understood that the orientation or positional relationship indicated by the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present application and simplifying the description, and does 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 cannot be understood as a limitation on the present application. In addition, the features defined as "first" and "second" can explicitly or implicitly include one or more of the features. In the description of the present application, unless otherwise specified, the meaning of "a plurality of" is two or more.

[0031] In the description of the present application, it should be noted that, unless otherwise specified and limited, the terms "mounting", "connection", "connection" should be understood broadly, for example, it can be fixedly connected, or it can be detachably connected, or integrally connected, it can be mechanically connected, or it can be electrically connected, it can be directly connected, or it can be indirectly connected through an intermediate medium, it can be the communication between two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0032] The present application provides a kind of aerial photography unmanned plane descending speed reducer, when unmanned plane is landed, the descending speed of unmanned plane can be effectively slowed down, prevent unmanned plane descending speed too fast, the impact force generated when unmanned plane lands can be effectively buffered and offset, please refer to Figs. 1-3 Including unmanned plane body 100 and mounting plate 200;

[0033] Please refer to Figs. 1-2The left and right side walls of the unmanned aerial vehicle body 100 are fixedly connected with wings 110 on the front and back sides, the top of the wing 110 is provided with a receiving groove 111, the outer side walls of the left and right wings 110 are fixedly connected with flight impellers 120, the left and right sides of the unmanned aerial vehicle body 100 are provided with a descending speed reduction mechanism, the descending speed reduction mechanism comprises a first telescopic rod 130, the first telescopic rod 130 is used for adjusting the transverse position of a baffle 160, a connecting plate 140, a bottom plate 141, the bottom plate 141 is used for mounting a second telescopic rod 150, the second telescopic rod 150 is used for adjusting the height of the baffle 160, the baffle 160 is used for the air vent of the flight impeller 120, the first telescopic rod 130 is fixedly connected on the front and back side walls of the wing 110, the ends of the left and right first telescopic rods 130 are fixedly connected with the connecting plates 140, the outer side walls of the left and right connecting plates 140 are fixedly connected with the bottom plates 141, the second telescopic rod 150 is fixedly connected on the top of the bottom plate 141, the top ends of the front and back second telescopic rods 150 are fixedly connected with the baffle 160, the baffle 160 is located between the inner side walls of the receiving groove 111, when the unmanned aerial vehicle descends, the second telescopic rod 150 is started to extend, the baffle 160 mounted on the second telescopic rod 150 is moved out of the receiving groove 111, then the first telescopic rod 130 is started to extend, the connecting plate 140 connected with the first telescopic rod 130 is moved, the second telescopic rod 150 on the bottom plate 141 is moved, so that the baffle 160 mounted on the second telescopic rod 150 is moved above the flight impeller 120, the air vent of the flight impeller 120 is blocked, the resistance of the unmanned aerial vehicle body 100 during descending is increased, and the descending speed of the unmanned aerial vehicle body 100 is slowed down;

[0034] In summary, when the unmanned aerial vehicle lands, the descending speed of the unmanned aerial vehicle can be effectively slowed down, and the descending speed of the unmanned aerial vehicle is prevented from being too fast;

[0035] Please refer again to Figs. 1-3The left and right side walls of the unmanned aerial vehicle body 100 are fixedly connected with mounting plates 200, and the lower part of the left and right mounting plates 200 is provided with a landing buffer mechanism. The landing buffer mechanism comprises mounting cylinders 210, sealing rubber rings 211, damping oil 212, pressure rods 220, liquid permeation plates 221, liquid permeation holes 222, shock absorbing springs 230 and landing supports 240. The sealing rubber rings 211 are used to seal the connection between the pressure rods 220 and the mounting cylinders 210. The liquid permeation plates 221 are used to extrude the damping oil 212. The liquid permeation holes 222 are arranged on the top of the liquid permeation plates 221. The shock absorbing springs 230 are embedded in the inner cavities of the mounting cylinders 210. The landing supports 240 are fixedly connected between the bottom ends of the pressure rods 220 arranged from front to back on the left and right sides. After the unmanned aerial vehicle lands, the landing supports 240 are in contact with the ground and generate an impact force. The pressure rods 220 connected with the landing supports 240 absorb the impact force, move into the mounting cylinders 210, extrude the damping oil 212 and the shock absorbing springs 230 in the mounting cylinders 210, and make the damping oil 212 flow to the other side of the liquid permeation plates 221 through the liquid permeation holes 222 on the liquid permeation plates 221 to generate a damping force. At the same time, the shock absorbing springs 230 are deformed to extrude the liquid permeation plates 221 extruding the damping oil 212, thereby buffering the impact force when the unmanned aerial vehicle lands.

[0036] In summary, the impact force generated when the unmanned aerial vehicle lands can be effectively buffered and offset.

[0037] In a specific use, when the unmanned aerial vehicle is descending, the second telescopic rod 150 is extended to move the baffle 160 installed on the second telescopic rod 150 out of the storage slot 111, and then the first telescopic rod 130 is extended to move the connecting plate 140 connected with the first telescopic rod 130, so that the second telescopic rod 150 on the bottom plate 141 moves, thereby moving the baffle 160 installed on the second telescopic rod 150 above the flight impeller 120 to block the air vents of the flight impeller 120, increase the resistance when the unmanned aerial vehicle body 100 is descending, and slow down the descending speed of the unmanned aerial vehicle body 100. After the unmanned aerial vehicle lands, the landing support 240 contacts the ground and generates an impact force, the pressure rod 220 connected with the landing support 240 absorbs the impact force, the pressure rod 220 moves into the mounting cylinder 210, the liquid permeable plate 221 installed on the pressure rod 220 extrudes the damping oil 212 and the shock absorbing spring 230 in the mounting cylinder 210, the damping oil 212 flows to the other side of the liquid permeable plate 221 through the liquid permeable hole 222 on the liquid permeable plate 221, generates a damping force, and at the same time, the shock absorbing spring 230 is extruded and deformed to cooperate with the liquid permeable plate 221 extruding the damping oil 212 to buffer the impact force when the unmanned aerial vehicle lands.

[0038] In the description of the present specification, the description of the terms "one embodiment", "some embodiments", "exemplary embodiment", "example", "specific example", or "some examples" means that the specific features, structures, materials or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present application. In the present specification, the exemplary description of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner.

[0039] Although the embodiments of the present application have been shown and described, those skilled in the art can understand that various changes, modifications, replacements and variations can be made to the embodiments without departing from the principles and purposes of the present application, and the scope of the present application is defined by the claims and their equivalents.

Claims

1. A descent deceleration device for an aerial photography drone, characterized in that: The device includes a drone body (100), with wings (110) fixedly connected to the left and right side walls and the front and rear sides of the drone body (100). The top of the wings (110) has a storage slot (111), and the outer side walls of the wings (110) on the left and right sides are fixedly connected to flight impellers (120). The drone body (100) is provided with descent deceleration mechanisms on the left and right sides. Mounting plates (200) are fixedly connected to the left and right side walls of the unmanned aerial vehicle (100), and landing buffer mechanisms are provided below the mounting plates (200) on both sides.

2. The descent deceleration device for an aerial photography drone according to claim 1, characterized in that: The descent deceleration mechanism includes a first telescopic rod (130), a connecting plate (140), a base plate (141), a second telescopic rod (150), and a baffle (160).

3. The descent deceleration device for an aerial photography drone according to claim 2, characterized in that: The first telescopic rod (130) is fixedly connected to the front and rear side walls of the wing (110), and the ends of the first telescopic rod (130) on the left and right sides are fixedly connected to the connecting plates (140), and the outer side walls of the connecting plates (140) on the left and right sides are fixedly connected to the bottom plate (141).

4. The descent deceleration device for an aerial photography drone according to claim 2, characterized in that: The second telescopic rod (150) is fixedly connected to the top of the base plate (141), and a baffle (160) is fixedly connected between the top ends of the second telescopic rod (150) on the front and rear sides. The baffle (160) is located between the inner walls of the storage groove (111).

5. The descent deceleration device for an aerial photography drone according to claim 1, characterized in that: The landing buffer mechanism includes a mounting cylinder (210), a sealing ring (211), damping oil (212), a pressure rod (220), a seepage plate (221), a seepage hole (222), a shock-absorbing spring (230), and a landing bracket (240).

6. The descent deceleration device for an aerial photography drone according to claim 5, characterized in that: The mounting cylinder (210) is fixedly connected to the bottom of the mounting plates (200) on the left and right sides, and the mounting cylinders (210) are arranged sequentially from front to back. A sealing ring (211) is bonded to the bottom end of the mounting cylinder (210), and the inner cavity of the mounting cylinder (210) is filled with damping oil (212).

7. The descent deceleration device for an aerial photography drone according to claim 5, characterized in that: The pressure rod (220) is inserted into the bottom end of the mounting cylinder (210). The outer side wall of the pressure rod (220) is in contact with the sealing ring (211). The top end of the pressure rod (220) penetrates the mounting cylinder (210) and extends into the inner cavity of the mounting cylinder (210). A seepage plate (221) is fixedly connected to the top end of the pressure rod (220). Seepage holes (222) are opened around the top of the seepage plate (221), and the seepage holes (222) are evenly distributed.

8. The descent deceleration device for an aerial photography drone according to claim 5, characterized in that: The shock-absorbing spring (230) is embedded in the inner cavity of the mounting cylinder (210), and the shock-absorbing spring (230) is located above the seepage plate (221).

9. A descent deceleration device for an aerial photography drone according to claim 5, characterized in that: The landing support (240) is fixedly connected between the bottom ends of the pressure rods (220) arranged sequentially from front to back on both the left and right sides.

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