CN220349940U - Unmanned aerial vehicle parachute ejection device and unmanned aerial vehicle - Google Patents
Unmanned aerial vehicle parachute ejection device and unmanned aerial vehicle Download PDFInfo
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- CN220349940U CN220349940U CN202322113605.9U CN202322113605U CN220349940U CN 220349940 U CN220349940 U CN 220349940U CN 202322113605 U CN202322113605 U CN 202322113605U CN 220349940 U CN220349940 U CN 220349940U
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Abstract
The utility model discloses an unmanned aerial vehicle parachute ejection device and an unmanned aerial vehicle, relates to the technical field of unmanned aerial vehicles, and solves the technical problem that a parachute rope of a parachute is easy to wind a wing of the unmanned aerial vehicle, so that the unmanned aerial vehicle cannot safely land. The device comprises a mounting frame and an anti-winding ring, wherein the mounting frame and the anti-winding ring are arranged on the unmanned aerial vehicle; an ejection cylinder is arranged in the mounting frame, a parachute is arranged in the ejection cylinder, and the parachute is fixedly connected with the ejection cylinder through a parachute rope; the anti-winding ring is fixedly connected to the mounting frame and is used for preventing the parachute ropes of the parachute from winding the wings of the unmanned aerial vehicle. The utility model can prevent the parachute ropes from winding the wings of the unmanned aerial vehicle and ensure the safe landing of the unmanned aerial vehicle.
Description
Technical Field
The utility model relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle parachute ejection device and an unmanned aerial vehicle.
Background
Unmanned aircraft, for short, "unmanned aircraft," is unmanned aircraft that is maneuvered using a radio remote control device and a self-contained programming device, or is operated autonomously, either entirely or intermittently, by an on-board computer. Unmanned aerial vehicles are widely used for airborne reconnaissance, surveillance, communication, anti-dive, electronic interference, and the like. When the unmanned aerial vehicle executes the flight task outside, the loss of the connection of the frying machine is common. Serious consequences are often experienced when the battery is about to run out or when extreme weather is encountered causing an abnormally rapid descent of the aircraft to crash. Therefore, when the unmanned aerial vehicle fails in performing a mission, a parachute is required to ensure that the unmanned aerial vehicle can safely land to the ground from the air. However, in the state of unbalanced attitude of the unmanned aerial vehicle, the parachute line of the parachute is easily wound around the wing of the unmanned aerial vehicle, resulting in an inability of the unmanned aerial vehicle to land safely.
In carrying out the present utility model, the applicant has found that at least the following problems exist in the prior art:
under unmanned aerial vehicle gesture unbalance state, the parachute line of parachute twines unmanned aerial vehicle's wing easily, leads to unmanned aerial vehicle to drop safely.
Disclosure of Invention
The utility model aims to provide an unmanned aerial vehicle parachute ejection device and an unmanned aerial vehicle, and aims to solve the technical problem that in the prior art, under the unbalanced state of the posture of the unmanned aerial vehicle, parachute ropes of a parachute are easy to wind wings of the unmanned aerial vehicle, so that the unmanned aerial vehicle cannot safely land. The preferred technical solutions of the technical solutions provided by the present utility model can produce a plurality of technical effects described below.
In order to achieve the above purpose, the present utility model provides the following technical solutions:
the utility model provides an unmanned aerial vehicle parachute ejection device, which comprises a mounting frame (2) and an anti-winding ring (3) which are arranged on an unmanned aerial vehicle (1); an ejection cylinder (4) is arranged in the mounting frame (2), a parachute (5) is arranged in the ejection cylinder (4), and the parachute (5) is fixedly connected with the ejection cylinder (4) through a parachute rope (51); the anti-winding ring (3) is fixedly connected to the mounting frame (2) and is used for preventing the parachute ropes (51) of the parachute (5) from winding the wings (11) of the unmanned aerial vehicle (1).
Preferably, the anti-winding ring (3) comprises a first outer ring (31), a first inner ring (32) and a plurality of first connection plates (33); the first outer ring (31) is fixedly connected to the outer side of the first inner ring (32) through the first connecting plate (33).
Preferably, the anti-winding ring (3) further comprises a second outer ring (34), a second inner ring (35) and a plurality of second connection plates (36); the second outer ring (34) is fixedly connected to the outer side of the second inner ring (34) through a plurality of second connecting plates (36); the second outer ring (34) is provided with a groove (341), and the first inner ring (31) is fixedly connected in the groove (341); the second inner ring (35) is fixedly connected to the top of the mounting frame (2).
Preferably, the mounting frame (2) comprises a fixed plate (21), a bracket (22), a first supporting plate (23), a second supporting plate (24) and a plurality of supporting columns (25); the fixed plate (21) is fixedly connected to the top of the unmanned aerial vehicle (1); the first supporting plate (23) is fixedly connected right above the fixed plate (21) through the bracket (22); the second supporting plate (24) is fixedly connected right above the first supporting plate (23) through a plurality of supporting columns (25).
Preferably, the ejection cylinder (4) is fixedly connected between the first support plate (23) and the second support plate (24); the supporting columns (25) encircle the ejection cylinder (4); the middle of the second supporting plate (24) is provided with a circular opening, and the circular opening is used for enabling the ejection cylinder (4) to eject the parachute (5).
Preferably, the fixing plates (21) are symmetrically distributed; the fixing plate (21) is provided with slotted holes (211) which are distributed at equal intervals, and the slotted holes (211) are fixedly connected with the bracket (22).
Preferably, a reinforcing plate is arranged between the fixing plates, and is used for reinforcing the connection stability between the fixing plates.
Preferably, the device further comprises a display (6) and a battery (7); the display (6) is electrically connected with the battery (7); the display (6) is fixedly connected to one side of the mounting frame (2); the battery (7) is fixedly connected inside the mounting frame (2).
Preferably, the display (6) is provided with a GPS signal module (61) for transmitting GPS signals.
An unmanned aerial vehicle comprising the unmanned aerial vehicle parachute ejection device.
By implementing one of the technical schemes, the utility model has the following advantages or beneficial effects:
according to the utility model, the anti-winding ring is arranged at the top of the unmanned aerial vehicle, the grid-shaped parachute rope and the wings of the unmanned aerial vehicle are arranged, and the parachute rope can fall on the anti-winding ring preferentially during landing, so that the parachute rope is prevented from winding the wings of the unmanned aerial vehicle.
Drawings
For a clearer description of the technical solutions of embodiments of the present utility model, the drawings that are needed in the description of the embodiments will be briefly described below, it being obvious that the drawings in the following description are only some embodiments of the present utility model, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art, in which:
fig. 1 is a schematic structural view of an unmanned aerial vehicle parachute ejection device according to an embodiment of the present utility model;
fig. 2 is a schematic view of a first view angle structure of an unmanned aerial vehicle parachute ejection device according to an embodiment of the present utility model;
fig. 3 is a schematic view of a second view angle structure of an unmanned aerial vehicle parachute ejection device according to an embodiment of the present utility model
In the figure: 1. unmanned plane; 11. a wing; 2. a mounting frame; 21. a fixing plate; 211. a slot hole; 22. a bracket; 23. a first support plate; 24. a second support plate; 25. a support column; 26. a reinforcing plate; 3. an anti-winding ring; 31. a first outer ring; 32. a first inner ring; 33. a first connection plate; 34. a second outer ring; 341. a groove; 35. a second inner ring; 36. a second connecting plate; 4. an ejection cylinder; 5. a parachute; 51. an umbrella rope; 6. a display; 61. a GPS signal module; 7. and a battery.
Detailed Description
For a better understanding of the objects, technical solutions and advantages of the present utility model, reference should be made to the various exemplary embodiments described hereinafter with reference to the accompanying drawings, which form a part hereof, and in which are described various exemplary embodiments which may be employed in practicing the present utility model. The same reference numbers in different drawings identify the same or similar elements unless expressly stated otherwise. The implementations described in the following exemplary examples are not representative of all implementations consistent with the present disclosure. It is to be understood that they are merely examples of processes, methods, apparatuses, etc. that are consistent with certain aspects of the present disclosure as detailed in the appended claims, other embodiments may be utilized, or structural and functional modifications may be made to the embodiments set forth herein without departing from the scope and spirit of the present disclosure.
In the description of the present utility model, it should be understood that the terms "center," "longitudinal," "transverse," and the like are used in an orientation or positional relationship based on that shown in the drawings, and are merely for convenience in describing the present utility model and to simplify the description, rather than to indicate or imply that the elements referred to must have a particular orientation, be constructed and operate in a particular orientation. The terms "first," "second," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. The term "plurality" means two or more. The terms "connected," "coupled" and "connected" are to be construed broadly and may be, for example, fixedly connected, detachably connected, integrally connected, mechanically connected, electrically connected, communicatively connected, directly connected, indirectly connected via intermediaries, or may be in communication with each other between two elements or in an interaction relationship between the two elements. The term "and/or" includes any and all combinations of one or more of the associated listed items. The specific meaning of the above terms in the present utility model can be understood by those of ordinary skill in the art according to the specific circumstances.
In order to illustrate the technical solutions of the present utility model, the following description is made by specific embodiments, only the portions related to the embodiments of the present utility model are shown.
Embodiment one:
as shown in fig. 1, the utility model provides an unmanned aerial vehicle parachute ejection device, which comprises a mounting frame 2 and an anti-winding ring 3, wherein the mounting frame 2 and the anti-winding ring 3 are arranged on an unmanned aerial vehicle 1; an ejection cylinder 4 is arranged in the mounting frame 2, a parachute 5 is arranged in the ejection cylinder 4, and the parachute 5 is fixedly connected with the ejection cylinder 4 through a parachute rope 51; the anti-winding ring 3 is fixedly connected to the mounting frame 2 for preventing the parachute ropes 51 of the parachute 5 from winding the wing 11 of the unmanned aerial vehicle 1. According to the embodiment, the anti-winding ring is arranged at the top of the unmanned aerial vehicle, the grid-shaped parachute ropes and the wings of the unmanned aerial vehicle, and the parachute ropes can fall on the anti-winding ring preferentially during landing, so that the parachute ropes are prevented from winding the wings of the unmanned aerial vehicle.
As an alternative embodiment, the anti-winding ring 3 comprises a first outer ring 31, a first inner ring 32 and a plurality of first connection plates 33; the first outer ring 31 is fixedly connected to the outer side of the first inner ring 32 through a first connecting plate 33; the first connection plate 33 is welded between the first outer ring 31 and the first inner ring 32 in a ring shape. The anti-winding ring 3 further comprises a second outer ring 34, a second inner ring 35 and a plurality of second connection plates 36; the second outer ring 34 is fixedly connected to the outer side of the second inner ring 35 through a plurality of second connecting plates 36; the second outer ring 34 is provided with a groove 341, and the first inner ring 32 is fixedly connected in the groove 341; the groove 341 is internally provided with threads which can be connected with the first inner ring 32 in a threaded manner; the second inner ring 35 is fixedly connected to the top of the mounting frame 2, and the second support plate 24 of the mounting frame of the second inner ring 35 is fixedly connected. If the unmanned aerial vehicle is unbalanced in the falling process, the parachute ropes can fall on the first outer ring 31 and the first connecting plate 33 and cannot wind the wings of the unmanned aerial vehicle, so that the safe falling of the unmanned aerial vehicle is ensured.
As an alternative embodiment, the mounting frame 2 includes a fixing plate 21, a bracket 22, a first support plate 23, a second support plate 24, and a plurality of support columns 25; the fixed plate 21 is fixedly connected to the top of the unmanned aerial vehicle 1 and is connected with the unmanned aerial vehicle through bolts; the bracket 22 is welded on the fixed plate 23, and the first supporting plate 23 is fixedly connected right above the fixed plate through the bracket 22 and is also welded with the bracket 22; the second support plate 24 is fixedly connected right above the first support plate 23 through a plurality of support columns 25; a plurality of support posts 25 are threadedly coupled to the first support plate 23, and are threadedly coupled to the second support plate 24 thereabove. The second inner ring 35 is fixedly connected above the second support plate 24. Due to the arrangement of the fixing plate 21, the support 22, the first support plate 23, the plurality of support columns 25 and the second support plate 24, the catapulting cylinder 4 and the unmanned aerial vehicle 1 are arranged from bottom to top in sequence, and therefore, when the catapulting cylinder 4 catapults out of the parachute 5, the parachute ropes are not easy to wind the unmanned aerial vehicle wings 11.
The ejection cylinder 4 is fixedly connected between the first support plate 23 and the second support plate 24; a plurality of support columns 25 encircle the ejection cylinder 4; the second support plate 24 has a circular opening in the middle for enabling the ejection cylinder 4 to eject the parachute bullets 5. The two fixing plates 21 are symmetrically distributed, so that the device is conveniently and firmly fixed on the unmanned aerial vehicle 1; the fixed plate 21 is provided with slotted holes 211 which are distributed at equal intervals, and the slotted holes 211 are fixedly connected with the bracket 22; the slot 211 and the bracket 22 may be connected by rivets or bolts. A reinforcing plate 26 is provided between the fixing plates 21 for reinforcing the connection stability between the fixing plates 21.
As an alternative embodiment, the device further comprises a display 6 and a battery 7; the display 6 is electrically connected with the battery 7; the display 6 is fixedly connected to one side of the mounting frame 2 and is connected with the bracket 22 through bolts; the battery 7 is fixedly connected inside the mounting frame 2, and particularly is connected in the middle of the bracket 22 through bolts. The display 6 is provided with a GPS signal module 61 for transmitting GPS signals. The battery 7 is a storage battery, and when the unmanned aerial vehicle 1 system is damaged and unavailable, the storage battery can independently supply power to the display 6, so that the display 6 sends signals through the GPS signal module 61, and the position of the unmanned aerial vehicle 1 can be quickly found out according to the signals.
The embodiment is a specific example only and does not suggest one such implementation of the utility model.
Embodiment two:
the second embodiment is different from the first embodiment in that: an unmanned aerial vehicle comprising an unmanned aerial vehicle parachute ejection device of any of the embodiments. The unmanned aerial vehicle is provided with the parachute ejection device, so that when the unmanned aerial vehicle fails, the ejection cylinder can rapidly eject the parachute, and the unmanned aerial vehicle cannot crash; the device is provided with the anti-winding device, so that the parachute ropes can be prevented from winding the unmanned aerial vehicle wings, and the safe landing of the unmanned aerial vehicle is ensured.
The foregoing is only illustrative of the preferred embodiments of the utility model, and it will be appreciated by those skilled in the art that various changes in the features and embodiments may be made and equivalents may be substituted without departing from the spirit and scope of the utility model. In addition, many modifications may be made to adapt a particular situation or material to the teachings of the utility model without departing from the essential scope thereof. Therefore, it is intended that the utility model not be limited to the particular embodiment disclosed, but that the utility model will include all embodiments falling within the scope of the appended claims.
Claims (10)
1. The unmanned aerial vehicle parachute ejection device is characterized by comprising a mounting frame (2) and an anti-winding ring (3) which are arranged on an unmanned aerial vehicle (1); an ejection cylinder (4) is arranged in the mounting frame (2), a parachute (5) is arranged in the ejection cylinder (4), and the parachute (5) is fixedly connected with the ejection cylinder (4) through a parachute rope (51); the anti-winding ring (3) is fixedly connected to the mounting frame (2) and is used for preventing the parachute ropes (51) of the parachute (5) from winding the wings (11) of the unmanned aerial vehicle (1).
2. An unmanned aerial vehicle parachute ejection device according to claim 1, wherein the anti-wind ring (3) comprises a first outer ring (31), a first inner ring (32) and a plurality of first connection plates (33); the first outer ring (31) is fixedly connected to the outer side of the first inner ring (32) through the first connecting plate (33).
3. An unmanned aerial vehicle parachute ejection device according to claim 2, wherein the anti-wind ring (3) further comprises a second outer ring (34), a second inner ring (35) and a plurality of second connection plates (36); the second outer ring (34) is fixedly connected to the outer side of the second inner ring (35) through a plurality of second connecting plates (36); the second outer ring (34) is provided with a groove (341), and the first inner ring (32) is fixedly connected in the groove (341); the second inner ring (35) is fixedly connected to the top of the mounting frame (2).
4. The unmanned aerial vehicle parachute ejection device according to claim 1, wherein the mounting frame (2) comprises a fixing plate (21), a bracket (22), a first support plate (23), a second support plate (24) and a plurality of support columns (25); the fixed plate (21) is fixedly connected to the top of the unmanned aerial vehicle (1); the first supporting plate (23) is fixedly connected right above the fixed plate (21) through the bracket (22); the second supporting plate (24) is fixedly connected right above the first supporting plate (23) through a plurality of supporting columns (25).
5. An unmanned aerial vehicle parachute ejection device according to claim 4, wherein the ejection cylinder (4) is fixedly connected between the first support plate (23) and the second support plate (24); the supporting columns (25) encircle the ejection cylinder (4); the middle of the second supporting plate (24) is provided with a circular opening, and the circular opening is used for enabling the ejection cylinder (4) to eject the parachute (5).
6. An unmanned aerial vehicle parachute ejection device according to claim 4, wherein the fixing plates (21) are symmetrically distributed; the fixing plate (21) is provided with slotted holes (211) which are distributed at equal intervals, and the slotted holes (211) are fixedly connected with the bracket (22).
7. An unmanned aerial vehicle parachute ejection device according to claim 4, wherein a reinforcing plate (26) is provided between the fixing plates (21) for reinforcing the connection stability between the fixing plates (21).
8. A parachute ejection device for an unmanned aerial vehicle according to claim 1, further comprising a display (6) and a battery (7); the display (6) is electrically connected with the battery (7); the display (6) is fixedly connected to one side of the mounting frame (2); the battery (7) is fixedly connected inside the mounting frame (2).
9. The unmanned aerial vehicle parachute ejection device according to claim 8, wherein the display (6) is provided with a GPS signal module (61) for transmitting GPS signals.
10. An unmanned aerial vehicle comprising an unmanned aerial vehicle parachute ejection device according to any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322113605.9U CN220349940U (en) | 2023-08-07 | 2023-08-07 | Unmanned aerial vehicle parachute ejection device and unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322113605.9U CN220349940U (en) | 2023-08-07 | 2023-08-07 | Unmanned aerial vehicle parachute ejection device and unmanned aerial vehicle |
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| Publication Number | Publication Date |
|---|---|
| CN220349940U true CN220349940U (en) | 2024-01-16 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202322113605.9U Active CN220349940U (en) | 2023-08-07 | 2023-08-07 | Unmanned aerial vehicle parachute ejection device and unmanned aerial vehicle |
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| Country | Link |
|---|---|
| CN (1) | CN220349940U (en) |
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2023
- 2023-08-07 CN CN202322113605.9U patent/CN220349940U/en active Active
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