CN113135297A - Unmanned aerial vehicle anti-falling device - Google Patents
Unmanned aerial vehicle anti-falling device Download PDFInfo
- Publication number
- CN113135297A CN113135297A CN202110533685.6A CN202110533685A CN113135297A CN 113135297 A CN113135297 A CN 113135297A CN 202110533685 A CN202110533685 A CN 202110533685A CN 113135297 A CN113135297 A CN 113135297A
- Authority
- CN
- China
- Prior art keywords
- hollow shell
- plate
- aerial vehicle
- unmanned aerial
- telescopic rod
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 230000003139 buffering effect Effects 0.000 claims abstract description 35
- 230000000712 assembly Effects 0.000 claims abstract description 24
- 238000000429 assembly Methods 0.000 claims abstract description 24
- 210000001015 abdomen Anatomy 0.000 claims abstract description 8
- 239000004744 fabric Substances 0.000 claims description 19
- 230000009471 action Effects 0.000 claims description 9
- 230000005484 gravity Effects 0.000 claims description 8
- 238000009434 installation Methods 0.000 claims description 7
- 238000005452 bending Methods 0.000 claims description 3
- 230000002265 prevention Effects 0.000 abstract description 5
- 238000007493 shaping process Methods 0.000 description 23
- 230000000694 effects Effects 0.000 description 12
- 238000000465 moulding Methods 0.000 description 8
- 230000008859 change Effects 0.000 description 4
- 238000004880 explosion Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 2
- 239000011435 rock Substances 0.000 description 2
- 230000035939 shock Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
- B64D45/04—Landing aids; Safety measures to prevent collision with earth's surface
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
- B64D45/04—Landing aids; Safety measures to prevent collision with earth's surface
- B64D45/06—Landing aids; Safety measures to prevent collision with earth's surface mechanical
Abstract
The invention discloses an anti-falling device of an unmanned aerial vehicle, which comprises a hollow shell, an air bag component and a plurality of buffering wing components, wherein the air bag component is arranged in the hollow shell; the outer surface of the top wall of the hollow shell is fixedly connected with the abdomen of the unmanned aerial vehicle, and the bottom wall of the hollow shell is of an open structure; the safety air bag assembly is fixedly connected inside the hollow shell, an air bag in the safety air bag assembly can be extruded out from an opening of the bottom wall of the hollow shell after being inflated and expanded, and a primary buffer structure is formed; the buffer wing assemblies are at least four groups and are evenly distributed along the circumferential direction of the inner surface of the side wall of the hollow shell, the side wall of the hollow shell is provided with an opening for the buffer wing assemblies to penetrate through, and the plurality of buffer wing assemblies surround the hollow shell to form a side turning prevention structure. The invention can slow down the impact force of falling of the unmanned aerial vehicle and prevent the unmanned aerial vehicle from turning over on the slope to cause more serious loss.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicle design, in particular to an anti-falling device of an unmanned aerial vehicle.
Background
The application range of the existing unmanned aerial vehicle is wider and wider, but sometimes, no one has a fault, and the phenomenon of accidental crash occurs, so that economic loss is caused; when the accident of unmanned aerial vehicle crashes on the more slope of rock, unmanned aerial vehicle takes place easily to turn on one's side, aggravates unmanned aerial vehicle's damage degree for economic loss increases.
Disclosure of Invention
The invention provides a falling prevention device for an unmanned aerial vehicle, which can slow down the falling impact force of the unmanned aerial vehicle when the unmanned aerial vehicle accidentally falls on a slope with more rocks, and prevent the unmanned aerial vehicle from turning over on the slope to cause more serious loss.
The invention is realized by the following technical scheme:
an unmanned aerial vehicle anti-falling device comprises a hollow shell, an air bag component and a plurality of buffering wing components; the outer surface of the top wall of the hollow shell is fixedly connected with the abdomen of the unmanned aerial vehicle, and the bottom wall of the hollow shell is of an open structure; the safety air bag assembly is fixedly connected inside the hollow shell, an air bag in the safety air bag assembly can be extruded out from an opening of the bottom wall of the hollow shell after being inflated and expanded, and a primary buffer structure is formed; the buffer wing assemblies are at least four groups and are uniformly distributed along the circumferential direction of the inner surface of the side wall of the hollow shell, and the side wall of the hollow shell is provided with an opening through which the buffer wing assemblies pass; the buffer wing assembly comprises a folding rod, a wind cloth and a first telescopic rod fixedly connected in the hollow shell, the first telescopic rod can extend to penetrate through an opening in the side wall of the hollow shell, one end of the folding rod is fixed on the telescopic end of the first telescopic rod, the other end of the folding rod is far away from the first telescopic rod and is fixedly connected to the inner surface of the side wall of the hollow shell, one side edge of the wind cloth is fixedly connected to the folding rod, and the other side edge of the wind cloth is fixedly connected to a fixing section of the first telescopic rod; the first telescopic rod can drive the folding rod to be stored in the hollow shell, or drive the folding rod to extend out of the hollow shell, so that the folding rod, the wind cloth and the first telescopic rod together form a buffer wing, and a plurality of buffer wing assemblies surround the hollow shell to form a rollover prevention structure; when unmanned aerial vehicle normally flies, anti-falling device can not start, and first telescopic link, folding rod and wind cloth all are located inside hollow shell this moment, and when the emergence flight accident, anti-falling device starts, and gasbag among the air bag begins to inflate, forms one-level buffer structure, and the extension of first telescopic link drives folding rod and wind cloth and passes the opening on the hollow shell lateral wall, forms the buffering wing, and a plurality of buffering wings combined action place unmanned aerial vehicle and take place to turn on one's side on slope.
Furthermore, the anti-falling device also comprises a plurality of air bag limiting assemblies, wherein the air bag limiting assemblies are uniformly distributed along the circumferential direction of the inner surface of the side wall of the hollow shell, each air bag limiting assembly comprises a plastic plate and a limiting piece, each plastic plate is of an arc-shaped structure, and one end of each plastic plate is rotatably connected with the inner surface of the side wall of the hollow shell; the limiting piece comprises a stress part and a supporting part; one side edge of the stress part is rotatably connected with the lower edge of the opening in the side wall of the hollow shell, and the lower edge of the opening in the side wall of the hollow shell can rotate by a first rotating shaft; the supporting part is of a bending structure and is far away from the upper edge of an opening on the side wall of the hollow shell, one end of the supporting part is fixedly connected to the stress part, the connection point is close to the first rotating shaft, the other end of the supporting part is abutted against the side wall of the hollow shell, the supporting part and the side wall of the hollow shell form a mounting cavity, and the plastic plate is arranged in the mounting cavity; when the first telescopic link is extended, the stress part can be driven to rotate, so that a gap appears between the supporting part and the side wall of the hollow shell, the plastic plates can penetrate under the action of gravity to rotate downwards in the gap, so that the plastic plates are separated from the supporting part to limit the shape of the air bag together, and the buffering effect of the air bag is increased.
Furthermore, the air bag limiting assembly further comprises a secondary buffer plate and a second telescopic rod, one end of the plastic plate, which is rotatably connected with the side wall of the hollow shell, is a rotating end, and the other end of the plastic plate is a free end; the secondary buffer plate is of an arc-shaped structure, one end of the secondary buffer plate is rotatably connected with the free end of the plastic plate to form a second rotating shaft, and the secondary buffer plate can rotate around the second rotating shaft to be attached to the plastic plate; the second telescopic rod is fixedly connected to the rotating end of the plastic plate, a groove is formed in the rotating end, a protrusion matched with the groove is arranged at the other end of the secondary buffer plate, the second telescopic rod can extend to penetrate through the protrusion and the groove to fixedly connect the secondary buffer plate and the plastic plate, an impact sensor used for detecting whether the airbag explodes is installed on one side face, away from the plastic plate, of the secondary buffer plate, and the impact sensor is connected with an electric control part of the second telescopic rod; play cushioning effect when being full of gas gasbag and slope contact, but if bumping sharp-pointed article, the gasbag can explode, and after the gasbag explosion, the signal is received to the automatically controlled part of second telescopic link, and the second telescopic link shortens, the second grade buffer board winds the second rotation axis rotates down, forms second grade buffer structure, and the second grade buffer board has increased the high distance on unmanned aerial vehicle and slope, and the second grade buffer board contacts with the slope at first, plays cushioning effect.
Further, second grade buffer board one end with the rotation of the free end of moulding the shaped plate is connected and is dismantled connection structure, because the direct buffer action that plays with the slope contact of second grade buffer board, compares in other structures of anti-falling device, and the damage of second grade buffer board can be more serious, consequently is connected second grade buffer board one end and the rotation of the free end of moulding the shaped plate and sets up to dismantling connection structure, when the damage of second grade buffer board is serious, need not change whole device, only need with the change of second grade buffer board can.
Further, the arc structure of the plastic plate comprises a straight plate section and an arc plate section, the arc structure of the secondary buffer plate also comprises a straight plate section and an arc plate section, and the radian of the arc plate section of the plastic plate is the same as that of the arc plate section of the secondary buffer plate.
Further, the stress part is of a plate-shaped structure, and the central point of the stress part is located in the extension direction of the first telescopic rod; the supporting part is a U-shaped plate, one wing plate end part of the U-shaped plate is fixedly connected to the stress part, the other wing plate end part of the U-shaped plate is abutted against the side wall of the hollow shell, and the U-shaped plate and the side wall of the hollow shell form a mounting cavity together; the supporting part of U template structure possess enough big space and place the plastic plate, and when first telescopic link extended, just directly pushed the atress portion forward, because the atress portion rotates with hollow shell and is connected, consequently, the atress portion can rotate under the effect of first telescopic link to make the clearance appear between supporting part and the hollow shell lateral wall, supply the plastic plate to rotate to pass.
Further, the hollow shell is of a cuboid structure, the top wall of the hollow shell is of a square structure, and an installation frame for installing the first telescopic rod is arranged inside the hollow shell; the buffering wing assembly has four groups, first telescopic link all with correspond mounting bracket fixed connection.
Furthermore, the ratio of the extended length of the first telescopic rod to the side length of the top wall of the hollow shell is 3-4: 1, the extended length of the first telescopic rod is much longer than the side length of the top wall of the hollow shell, the longer the extended length of the first telescopic rod is, the better the anti-rollover effect on the unmanned aerial vehicle is, and after comprehensive tests, when the ratio of the extended length of the first telescopic rod to the side length of the top wall of the hollow shell is 4-5: 1, the anti-rollover capacity and the cost can be parallel.
Furthermore, after the first telescopic rod is extended, an included angle formed between the first telescopic rod and the folding rod ranges from 10 degrees to 12 degrees.
The invention has the following advantages and beneficial effects:
on one hand, the impact force of falling of the unmanned aerial vehicle is relieved by arranging the safety airbag assembly, so that the unmanned aerial vehicle is prevented from directly colliding with a slope, and on the other hand, the buffering wing assemblies are distributed around the unmanned aerial vehicle, so that the unmanned aerial vehicle is prevented from turning on the slope and causing more serious loss; still set up the shaping board, inject the shape after the gasbag, increase the shock-absorbing capacity of gasbag, utilize locating part and first telescopic link cooperation, put suitable position under with the shaping board before starting the gasbag to still set up the second grade buffer board, under the condition that the gasbag damaged, still can accomplish buffer function, protection unmanned aerial vehicle.
Drawings
The accompanying drawings, which are included to provide a further understanding of the embodiments of the invention and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the invention and together with the description serve to explain the principles of the invention. In the drawings:
fig. 1 is a schematic view of the overall structure of the present invention.
FIG. 2 is a schematic view of the bumper wing assembly of the present invention in a deployed state.
FIG. 3 is a top view of the bumper wing assembly of the present invention when stowed.
Figure 4 is a top view of the bumper wing assembly of the present invention as deployed.
Fig. 5 is a matching structure view of the plastic plate of the inner side wall of the hollow shell and the limiting member of the invention.
FIG. 6 is a view showing the structure of the hollow shell of the present invention in which the plastic plate is fitted to the secondary buffer plate.
Fig. 7 is a detail view of the invention at point a.
Fig. 8 is a detail view of the invention at point B.
Reference numbers and corresponding part names in the drawings:
the device comprises a hollow shell, 21, a first telescopic rod, 22, a folding rod, 3, a plastic plate, 4, a limiting piece, 41, a stress part, 42, a supporting part, 5, a secondary buffer plate, 6, a second telescopic rod and 7, and an impact sensor.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail below with reference to examples and accompanying drawings, and the exemplary embodiments and descriptions thereof are only used for explaining the present invention and are not meant to limit the present invention.
Examples
An unmanned aerial vehicle anti-falling device is shown in figures 1 to 8 and comprises a hollow shell 1, an air bag assembly and a plurality of buffering wing assemblies; the outer surface of the top wall of the hollow shell 1 is fixedly connected with the abdomen of the unmanned aerial vehicle, and the bottom wall of the hollow shell 1 is of an open structure; the safety airbag assembly is fixedly connected inside the hollow shell 1, the safety airbag assembly adopts the existing products on the market, when a control part of the safety airbag assembly receives a signal capable of being started, an airbag in the safety airbag assembly starts to inflate, the airbag can be extruded out from an opening of the bottom wall of the hollow shell 1 after inflation and expansion, and a primary buffer structure is formed, when the unmanned aerial vehicle accidentally falls on a slope, the airbag filled with air at the abdomen of the unmanned aerial vehicle is firstly contacted with the slope, the impact after the unmanned aerial vehicle descends is buffered, and the primary buffer structure is formed; in order to prevent the side turning phenomenon of the unmanned aerial vehicle on a slope while buffering, at least four groups of buffering wing assemblies are arranged and are uniformly distributed along the circumferential direction of the inner surface of the side wall of the hollow shell 1, and the side wall of the hollow shell 1 is provided with an opening for the buffering wing assemblies to penetrate through; the buffering wing assembly comprises a folding rod 22, a wind cloth (not shown) and a first telescopic rod 21 fixedly connected in the hollow shell 1, the first telescopic rod 21 can extend to penetrate through an opening in the side wall of the hollow shell 1, one end of the folding rod 22 is fixed on the telescopic end of the first telescopic rod 21, the other end of the folding rod 22 is far away from the first telescopic rod 21 and is fixedly connected to the inner surface of the side wall of the hollow shell 1, one side edge of the wind cloth is fixedly connected to the folding rod 22, and the other side edge of the wind cloth is fixedly connected to a fixing section of the first telescopic rod 21; the first telescopic link 21 can drive the folding rod 22 to be stored in the hollow shell 1, or the folding rod 22 is driven to extend out of the hollow shell 1, so that the folding rod 22, the wind cloth and the first telescopic link 21 jointly form a buffer wing, and a plurality of buffer wing assemblies form a rollover prevention structure around the hollow shell 1.
In the above technical solution, after receiving a start signal, the electric control part of the first telescopic rod 21 starts to extend out of the hollow housing 1, it should be noted that the first telescopic rod 21 is started before the airbag module is started, when the first telescopic rod 21 extends, the folding rod 22 is driven to extend out of the hollow housing 1 together, the wind cloth is connected between the folding rod 22 and the first telescopic rod 21, after the extension of the buffering wing is completed, the folding rod 22 is connected with the first telescopic rod 21, the wind cloth is not sealed, the wind cloth is connected in a cavity formed by the folding rod 22 and the first telescopic rod 21, due to the characteristics of the first telescopic rod 21, the wind cloth is connected with only the fixed section of the first telescopic rod 21, so that the wind cloth cannot be sealed, therefore, the buffering wing structure can only provide a part of buffering effect, and the most important effect of the buffering wing is also used for preventing the unmanned aerial vehicle from rolling over, the length of buffering wing is far longer than the length or the width of unmanned aerial vehicle body, and when unmanned aerial vehicle on the slope, when will take place to turn on one's side under the effect of gravity, the structure of turning on one's side of preventing that a plurality of buffering wing subassemblies formed has increased unmanned aerial vehicle's the area of turning on one's side, leads to unmanned aerial vehicle to turn on one's side the difficulty, can't turn on one's side even to protect unmanned aerial vehicle.
In this embodiment, the folding rod 22 is of a simple folding structure, the folding rod 22 can easily move along with the extension of the first telescopic rod 21, and if necessary, some limiting structures may be further disposed on the folding rod 22, so that the folding rod 22 can be smoothly retracted into the hollow housing 1.
When needs use unmanned aerial vehicle in the more place in slope, choose the unmanned aerial vehicle anti-falling device that this embodiment provided for use, with 1 direct mount of hollow casing at unmanned aerial vehicle's belly, adopt screw installation or other connected mode, if unmanned aerial vehicle meets accident at the flight in-process, lead to the unable normal clear of flight, first telescopic link 21 is at first started, then the air bag subassembly starts, the buffering wing subassembly after the expansion makes unmanned aerial vehicle can unload some impact force at the in-process that falls, when unmanned aerial vehicle falls on the slope, the gasbag that is full of gas is handled remaining impact force.
Furthermore, the anti-falling device also comprises a plurality of air bag limiting assemblies for limiting the air bags, and the positions of the limited air bags, which are touched with the slope, are positions of inflated feet, so that the buffering function can be better implemented; the air bag limiting assemblies are uniformly distributed along the circumferential direction of the inner surface of the side wall of the hollow shell 1 and comprise plastic plates 3 and limiting pieces 4, the plastic plates 3 are of arc-shaped structures, and one ends of the plastic plates are rotatably connected with the inner surface of the side wall of the hollow shell 1; the limiting member 4 comprises a force receiving portion 41 and a supporting portion 42; one side of the stress part 41 is rotatably connected with the lower edge of the opening on the side wall of the hollow shell 1, and the lower edge of the opening on the side wall of the hollow shell 1 can rotate by taking the first rotating shaft as a first rotating shaft; the supporting part 42 is of a bending structure and is far away from the upper edge of an opening on the side wall of the hollow shell 1, one end of the supporting part 42 is fixedly connected to the stress part 41, the connection point is close to the first rotating shaft, the other end of the supporting part 42 is abutted against the side wall of the hollow shell 1, the supporting part 42 and the side wall of the hollow shell 1 form an installation cavity, and the shaping plate 3 is arranged in the installation cavity; when the first telescopic rod 21 is extended, the force-bearing portion 41 can be driven to rotate, so that a gap is formed between the supporting portion 42 and the side wall of the hollow shell 1, and the shaping plate 3 can rotate downwards through the gap under the action of gravity, so that the shaping plates 3 separated from the supporting portion 42 limit the shape of the airbag together.
In the technical proposal, when the whole anti-falling device is not started, the shaping plate 3 is transversely placed and is attached to the inner surface of the side wall of the hollow shell 1, one end of the shaping plate is a rotating end, the other end of the shaping plate is placed in a rotating cavity, when the first telescopic rod 21 in the buffering wing assembly is started, the force bearing part 41 rotates under the thrust of the first telescopic rod 21, so that the support portion 42 also starts to rotate, there is a gap in the installation cavity formed by the support portion 42 and the hollow housing 1, when the lower part of the shaping plate 3 is not supported by the supporting part 42, the shaping plate 3 can rotate under the action of gravity, pass through the gap and reach a preset designated position, the rotation and falling of the shaping plate 3 are a quick process, during the design, the starting time point of the airbag module is later than the starting time point of the first telescopic rod 21, and in the time difference, all the shaping plates 3 reach the proper positions; because the anti-falling device that this embodiment provided is unexpected start in the twinkling of an eye appears in unmanned aerial vehicle flight, unmanned aerial vehicle still is in belly down position state this moment, and under this condition, moulding board 3 can be transferred smoothly under the effect of gravity.
In this embodiment, the overall structure size of the limiting member 4 is determined according to the sizes of the hollow housing 1 and the plastic plate 3, the limiting member 4 is driven by the first telescopic rod 21 to complete the rotation and the action of the lower plastic plate 3, when the anti-falling device is not started, the plastic plate 3 can be stably fixed by the limiting member 4, and when the anti-falling device is started, the gap between the supporting portion 42 of the limiting member 4 and the sidewall of the hollow housing 1 can allow the plastic plate 3 to rotate and fall.
When the unmanned aerial vehicle accidentally falls, the impact force is too large when the air bag touches the slope, if sharp stones, branches and other objects exist on the slope, the air bag can be damaged under multiple impacts, the air bag directly explodes, after the air bag explodes, the part directly contacting the slope becomes the shaping plate 3, and because the distance between the shaping plate 3 and the unmanned aerial vehicle is too close, the unmanned aerial vehicle body is easily damaged under the condition, so that the secondary buffer plate 5 is designed, the air bag limiting assembly further comprises the secondary buffer plate 5 and a second telescopic rod 6, one end of the shaping plate 3, which is rotatably connected with the side wall of the hollow shell 1, is a rotating end, and the other end of the shaping plate is a free end; the secondary buffer plate 5 is of an arc-shaped structure, one end of the secondary buffer plate is rotatably connected with the free end of the shaping plate 3 to form a second rotating shaft, and the secondary buffer plate 5 can rotate around the second rotating shaft to be attached to the shaping plate 3; the second telescopic rod 6 is fixedly connected to the rotating end of the plastic plate 3, a groove is formed in the rotating end, a protrusion matched with the groove is formed in the other end of the secondary buffer plate 5, the second telescopic rod 6 can extend to penetrate through the protrusion and the groove, the secondary buffer plate 5 and the plastic plate 3 are fixedly connected, an impact sensor 7 used for detecting whether an airbag explodes is installed on one side face, away from the plastic plate 3, of the secondary buffer plate 5, and the impact sensor 7 is connected with an electric control portion of the second telescopic rod 6; after the airbag explodes, the second telescopic rod 6 is shortened, and the second-stage buffer plate 5 rotates downwards around the second rotating shaft to form a second-stage buffer structure.
In the technical scheme, the structure of the secondary buffer plate 5 is the same as that of the shaping plate 3 and is an arc-shaped plate, when the secondary buffer plate 5 rotates at a certain angle, the secondary buffer plate 5 can be completely attached to the shaping plate 3 and placed in a placing cavity formed by the supporting part 42 and the hollow shell 1, when the anti-falling device is started, the shaping plate 3 is attached to the secondary buffer plate 5 and rotates together to fall to a proper position, after an airbag explodes in an extreme condition, the impact sensor 7 detects the explosion of the airbag, transmits a signal to the electric control part of the second telescopic rod 6, the second telescopic rod 6 is started to begin to shorten, the connecting structure between the secondary buffer plate 5 and the shaping plate 3 is removed, and the secondary buffer plate 5 falls under the action of gravity until the secondary buffer plate contacts with a slope; the secondary buffer plate 5 increases the distance between the unmanned aerial vehicle and the slope to form a secondary buffer structure to protect the unmanned aerial vehicle in a secondary mode, and in the embodiment, the secondary buffer plate 5 is made of a high-elasticity material with a buffer function, such as a rubber composite material; the sensor for detecting whether the airbag explodes selects the impact sensor 7, the sensor directly selects the existing products on the market, and the size of the impact sensor 7 and the size relation between the secondary buffer plates 5 need to be noticed during selection.
Because second grade buffer board 5 carries out direct contact with the slope, the impact force of receiving is very big, basically every time use will be worn and torn, and degree of wear is also comparatively serious, consequently is connected 5 one end of second grade buffer board and the rotation of moulding board 3's free end and sets up to dismantling connection structure, when second grade buffer board 5 damages seriously, need not change whole device, only need with second grade buffer board 5 change can.
The arc-shaped structure of the plastic plate 3 comprises a straight plate section and an arc-shaped plate section, the arc-shaped structure of the secondary buffer plate 5 also comprises a straight plate section and an arc-shaped plate section, and the radian of the arc-shaped plate section of the plastic plate 3 is the same as that of the arc-shaped plate section of the secondary buffer plate 5; in this embodiment, 3 straight board sections of moulding board are rotated with 1 lateral wall of hollow shell and are connected, the arc board section rotates with second grade buffer board 5 to be connected, after the gasbag explosion, because the structural constraint of 3 bodies of moulding board, make the focus of moulding board 3, the focus of second grade buffer board 5 is all partial to the arc board section of the two structurally, after second telescopic link 6 shortens, moulding board 3 and 5 contact connection relations of second grade buffer board, second grade buffer board 5 then can rotate under the effect of gravity and weigh down, form second grade buffer structure.
The force-bearing part 41 is of a plate-shaped structure, and the central point of the force-bearing part 41 is positioned in the extending direction of the first telescopic rod 21; the supporting part 42 is a U-shaped plate, one wing plate end part of the U-shaped plate is fixedly connected to the stress part 41, the other wing plate end part is abutted against the side wall of the hollow shell 1, and the U-shaped plate and the side wall of the hollow shell 1 form a mounting cavity together; the supporting part 42 of U-shaped plate structure possesses enough big space to place plastic plate 3, and when first telescopic link 21 extended, just directly pushed stress part 41 forward, because stress part 41 rotates with hollow shell 1 and is connected, consequently, stress part 41 can rotate under the effect of first telescopic link 21 to make the clearance appear between supporting part 42 and the hollow shell 1 lateral wall, supply plastic plate 3 to rotate and pass.
The hollow shell 1 is of a cuboid structure, the top wall of the hollow shell 1 is of a square structure, and an installation frame for installing a first telescopic rod 21 is arranged inside the hollow shell 1; the buffer wing assemblies are provided with four groups, and the first telescopic rods 21 are fixedly connected with the corresponding mounting frames; the first telescopic rod 21 is directly fixed on the mounting frame and forms a stable connection relation with the hollow shell 1; the four groups of the buffering wing assemblies form a buffering wing plane, the four groups of the buffering wing assemblies are of a central symmetry structure, and a central symmetry point is a projection point of a central point of the unmanned aerial vehicle on the buffering wing plane.
In order to ensure the overall stability of the anti-rollover structure and ensure the better anti-rollover effect, the length of the first telescopic rod 21 after being extended, namely the length of the buffer wings, is set to be very long, but the rollover effect and the actual manufacturing cost are comprehensively considered, the ratio of the length of the first telescopic rod 21 after being extended to the length of the top wall of the hollow shell 1 is set to be 4-5: 1, and the anti-rollover effect and the manufacturing cost can be balanced within the proportion range.
After the first telescopic rod 21 is extended, the first telescopic rod 21, the folding rod 22 and the edge of the hollow shell 1 form a triangular structure, and the vertex angle of the triangle, namely the included angle formed by the extended first telescopic rod 21 and the folding rod 22, is 10 degrees to 12 degrees.
The whole operation steps of the whole anti-falling device are as follows: when the unmanned aerial vehicle needs to fly in a place with a large slope, the anti-falling device is selected for use, the device is fixedly mounted on the belly of the unmanned aerial vehicle to be protected, attention needs to be paid during mounting, the central position of the whole anti-falling device is preferably on the same straight line with the central position of the unmanned aerial vehicle, and the situation that the flying of the unmanned aerial vehicle is greatly influenced due to the addition of the anti-falling device is avoided; when the unmanned aerial vehicle flies and falls, the control part of the first telescopic rod 21 and the control part of the airbag module receive signals, but the first telescopic rod 21 is started first, the airbag module is started later, in the time difference, the plastic plate 3 reaches a preset position under the matching of the first telescopic rod 21 and the limiting part 4, then the airbag starts to inflate, the shape of the airbag is limited under the action of the plastic plate 3, and the buffering effect of the airbag is enhanced; when the unmanned aerial vehicle falls, the buffering wings can dissolve part of impact force, the rest impact force is buffered by the air bags, when the unmanned aerial vehicle falls onto a slope, the unmanned aerial vehicle can be protected from side turning by the side turning prevention structure formed by the buffering wing assemblies, damage is reduced, and if the air bags are punctured by sharp objects on the slope, the secondary buffering plate 5 attached to the shaping plate 3 starts to rotate to form a secondary buffering structure so as to protect the unmanned aerial vehicle; carry out the buffering shock attenuation by the gasbag to unmanned aerial vehicle under the general condition, but if meet extreme condition, for example the gasbag damages, then can also cushion the shock attenuation by the second grade buffer board, further protect unmanned aerial vehicle.
The above-mentioned embodiments are intended to illustrate the objects, technical solutions and advantages of the present invention in further detail, and it should be understood that the above-mentioned embodiments are merely exemplary embodiments of the present invention, and are not intended to limit the scope of the present invention, and any modifications, equivalent substitutions, improvements and the like made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (9)
1. An unmanned aerial vehicle anti-falling device is characterized by comprising a hollow shell (1), an air bag component and a plurality of buffering wing components;
the outer surface of the top wall of the hollow shell (1) is fixedly connected with the abdomen of the unmanned aerial vehicle, and the bottom wall of the hollow shell (1) is of an open structure;
the safety airbag module is fixedly connected inside the hollow shell (1), and an airbag in the safety airbag module can be extruded out from an opening of the bottom wall of the hollow shell (1) after being inflated and expanded to form a primary buffer structure;
the buffer wing assemblies are at least four groups and are uniformly distributed along the circumferential direction of the inner surface of the side wall of the hollow shell (1), and the side wall of the hollow shell (1) is provided with an opening through which the buffer wing assemblies pass;
the buffer wing assembly comprises a folding rod (22), a piece of wind cloth and a first telescopic rod (21) fixedly connected in the hollow shell (1), the first telescopic rod (21) can extend to penetrate through an opening in the side wall of the hollow shell (1), one end of the folding rod (22) is fixed to the telescopic end of the first telescopic rod (21), the other end of the folding rod is far away from the first telescopic rod (21) and is fixedly connected to the inner surface of the side wall of the hollow shell (1), one side edge of the wind cloth is fixedly connected to the folding rod (22), and the other side edge of the wind cloth is fixedly connected to a fixing section of the first telescopic rod (21);
first telescopic link (21) can drive folding rod (22) accomodate to in hollow casing (1), perhaps drive folding rod (22) stretch out hollow casing (1), make folding rod (22) with wind cloth and first telescopic link (21) form the buffering wing jointly, and a plurality of buffering wing subassemblies surround hollow casing (1) forms prevents the structure of turning on one's side.
2. The anti-falling device for the unmanned aerial vehicle is characterized by further comprising a plurality of air bag limiting assemblies, wherein the air bag limiting assemblies are uniformly distributed along the circumferential direction of the inner surface of the side wall of the hollow shell (1), each air bag limiting assembly comprises a plastic plate (3) and a limiting piece (4), each plastic plate (3) is of an arc-shaped structure, and one end of each plastic plate is rotatably connected with the inner surface of the side wall of the hollow shell (1);
the limiting piece (4) comprises a force bearing part (41) and a supporting part (42); one side of the stress part (41) is rotatably connected with the lower edge of the opening on the side wall of the hollow shell (1), and the lower edge of the opening on the side wall of the hollow shell (1) can rotate by taking the first rotating shaft as the lower edge; the supporting part (42) is of a bending structure and is far away from the upper edge of an opening on the side wall of the hollow shell (1), one end of the supporting part (42) is fixedly connected to the stress part (41), the connection point is close to the first rotating shaft, the other end of the supporting part is abutted to the side wall of the hollow shell (1), the supporting part (42) and the side wall of the hollow shell (1) form a mounting cavity, and the plastic plate (3) is arranged in the mounting cavity;
when first telescopic link (21) is elongated, can drive atress portion (41) rotates, makes supporting part (42) with appear the clearance between hollow shell (1) lateral wall, shape board (3) can pass under the action of gravity the clearance rotates downwards, thereby makes a plurality ofly break away from supporting part (42) shape board (3) restrict jointly the shape of gasbag.
3. The unmanned aerial vehicle anti-falling device of claim 2, characterized in that the air bag limiting component further comprises a secondary buffer plate (5) and a second telescopic rod (6), one end of the plastic plate (3) rotatably connected with the side wall of the hollow shell (1) is a rotating end, and the other end is a free end; the secondary buffer plate (5) is of an arc-shaped structure, one end of the secondary buffer plate is rotatably connected with the free end of the plastic plate (3) to form a second rotating shaft, and the secondary buffer plate (5) can rotate around the second rotating shaft to be attached to the plastic plate (3) mutually; the second telescopic rod (6) is fixedly connected to the rotating end of the plastic plate (3), a groove is formed in the rotating end, a protrusion matched with the groove is formed in the other end of the secondary buffer plate (5), the second telescopic rod (6) can extend to penetrate through the protrusion and the groove, the secondary buffer plate (5) is fixedly connected with the plastic plate (3), an impact sensor (7) used for detecting whether the airbag explodes is installed on one side face, far away from the plastic plate (3), of the secondary buffer plate (5), and the impact sensor (7) is connected with an electric control portion of the second telescopic rod (6);
after the airbag explodes, the second telescopic rod (6) is shortened, and the secondary buffer plate (5) rotates downwards around the second rotating shaft to form a secondary buffer structure.
4. An unmanned aerial vehicle fall arrest device according to claim 3, wherein the rotatable connection of one end of the secondary bumper plate (5) to the free end of the shaped plate (3) is a detachable connection.
5. The anti-falling device for unmanned aerial vehicle as claimed in claim 3, wherein the arc structure of the plastic plate (3) comprises a straight plate section and an arc plate section, the arc structure of the secondary buffer plate (5) also comprises a straight plate section and an arc plate section, and the radian of the arc plate section of the plastic plate (3) is the same as that of the arc plate section of the secondary buffer plate (5).
6. The unmanned aerial vehicle anti-falling device of claim 2, wherein the force-bearing part (41) is a plate-shaped structure, and the central point of the force-bearing part (41) is located in the elongation direction of the first telescopic rod (21); the supporting part (42) is a U-shaped plate, one wing plate end part of the U-shaped plate is fixedly connected to the stress part (41), the other wing plate end part of the U-shaped plate is abutted to the side wall of the hollow shell (1), and the U-shaped plate and the side wall of the hollow shell (1) jointly form an installation cavity.
7. The unmanned aerial vehicle anti-falling device according to claim 1, characterized in that the hollow shell (1) is of a rectangular structure, the top wall of the hollow shell (1) is of a square structure, and a mounting rack for mounting the first telescopic rod (21) is arranged inside the hollow shell (1); the buffering wing assemblies are four in number, and the first telescopic rods (21) are fixedly connected with the corresponding mounting frames.
8. The unmanned aerial vehicle anti-falling device of claim 7, wherein the ratio of the extended length of the first telescopic rod (21) to the side length of the top wall of the hollow shell (1) is 4-5: 1.
9. The unmanned aerial vehicle anti-falling device of claim 8, wherein the first telescopic rod (21) extends to form an included angle with the folding rod (22) in a range of 10 degrees to 12 degrees.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110533685.6A CN113135297B (en) | 2021-05-17 | 2021-05-17 | Unmanned aerial vehicle anti-falling device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110533685.6A CN113135297B (en) | 2021-05-17 | 2021-05-17 | Unmanned aerial vehicle anti-falling device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113135297A true CN113135297A (en) | 2021-07-20 |
| CN113135297B CN113135297B (en) | 2022-02-11 |
Family
ID=76817158
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110533685.6A Active CN113135297B (en) | 2021-05-17 | 2021-05-17 | Unmanned aerial vehicle anti-falling device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113135297B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113682463A (en) * | 2021-09-16 | 2021-11-23 | 郑州轻工业大学 | Protection system for improving safety of physical layer of unmanned aerial vehicle |
Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105366065A (en) * | 2015-12-14 | 2016-03-02 | 芜湖万户航空航天科技有限公司 | Anti-falling unmanned aerial vehicle |
| CN106394887A (en) * | 2016-10-24 | 2017-02-15 | 杭州鼎曜信息技术有限公司 | Multi-rotor-wing unmanned aerial vehicle and control method thereof |
| DE102015218456A1 (en) * | 2015-09-25 | 2017-03-30 | Robert Bosch Gmbh | Aircraft with a collision protection device and method for operating an aircraft with a collision protection device |
| CN106927057A (en) * | 2017-03-25 | 2017-07-07 | 林娟娟 | For the airbag apparatus of unmanned plane shatter-resistant |
| CN207374683U (en) * | 2017-10-20 | 2018-05-18 | 施铠曼航空科技（上海）有限公司 | A kind of anti-crash unmanned plane |
| CN208412109U (en) * | 2018-06-12 | 2019-01-22 | 北京中科遥数信息技术有限公司 | A kind of unmanned plane take-off and landing device |
| CN210113179U (en) * | 2019-03-24 | 2020-02-25 | 林才鸿 | Prevent reconnaissance unmanned aerial vehicle that falls with second grade floating structure |
| CN211336470U (en) * | 2019-12-04 | 2020-08-25 | 黄豪 | Unmanned aerial vehicle's organism cover |
| CN211685656U (en) * | 2019-12-31 | 2020-10-16 | 四川翼空智控科技有限公司 | Emergent extension formula unmanned aerial vehicle |
| CN211766331U (en) * | 2020-03-24 | 2020-10-27 | 辽东学院 | Unmanned aerial vehicle anti-falling device |
| CN212354409U (en) * | 2020-06-28 | 2021-01-15 | 珠海市双捷科技有限公司 | Unmanned aerial vehicle's air bag device |
-
2021
- 2021-05-17 CN CN202110533685.6A patent/CN113135297B/en active Active
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102015218456A1 (en) * | 2015-09-25 | 2017-03-30 | Robert Bosch Gmbh | Aircraft with a collision protection device and method for operating an aircraft with a collision protection device |
| CN105366065A (en) * | 2015-12-14 | 2016-03-02 | 芜湖万户航空航天科技有限公司 | Anti-falling unmanned aerial vehicle |
| CN106394887A (en) * | 2016-10-24 | 2017-02-15 | 杭州鼎曜信息技术有限公司 | Multi-rotor-wing unmanned aerial vehicle and control method thereof |
| CN106927057A (en) * | 2017-03-25 | 2017-07-07 | 林娟娟 | For the airbag apparatus of unmanned plane shatter-resistant |
| CN207374683U (en) * | 2017-10-20 | 2018-05-18 | 施铠曼航空科技（上海）有限公司 | A kind of anti-crash unmanned plane |
| CN208412109U (en) * | 2018-06-12 | 2019-01-22 | 北京中科遥数信息技术有限公司 | A kind of unmanned plane take-off and landing device |
| CN210113179U (en) * | 2019-03-24 | 2020-02-25 | 林才鸿 | Prevent reconnaissance unmanned aerial vehicle that falls with second grade floating structure |
| CN211336470U (en) * | 2019-12-04 | 2020-08-25 | 黄豪 | Unmanned aerial vehicle's organism cover |
| CN211685656U (en) * | 2019-12-31 | 2020-10-16 | 四川翼空智控科技有限公司 | Emergent extension formula unmanned aerial vehicle |
| CN211766331U (en) * | 2020-03-24 | 2020-10-27 | 辽东学院 | Unmanned aerial vehicle anti-falling device |
| CN212354409U (en) * | 2020-06-28 | 2021-01-15 | 珠海市双捷科技有限公司 | Unmanned aerial vehicle's air bag device |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113682463A (en) * | 2021-09-16 | 2021-11-23 | 郑州轻工业大学 | Protection system for improving safety of physical layer of unmanned aerial vehicle |
| CN113682463B (en) * | 2021-09-16 | 2024-03-12 | 郑州轻工业大学 | Protection system for improving physical layer safety of unmanned aerial vehicle |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113135297B (en) | 2022-02-11 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US2974912A (en) | Shock absorber | |
| CN113135297B (en) | Unmanned aerial vehicle anti-falling device | |
| CN109641664B (en) | Small-sized flying object with airbag device | |
| CN115535274A (en) | Unmanned aerial vehicle with safety air bag | |
| US6371410B1 (en) | Emergency landing impact absorbing system for aircraft | |
| WO2019142470A1 (en) | Control method for drone with airbag, and drone with airbag | |
| US20110024569A1 (en) | Attenuated landing system | |
| CN110758747A (en) | Unmanned aerial vehicle with multiple protection devices and control method thereof | |
| KR20170123763A (en) | Airbag Unit and Drone having the same | |
| CN105966637A (en) | Safety recovery device for fixed wing unmanned aerial vehicle | |
| CN113264192A (en) | Unmanned aerial vehicle gasbag device | |
| CN212556783U (en) | Unmanned aerial vehicle with safeguard function | |
| CN211180220U (en) | GNSS receiver and damping device thereof | |
| CN116142513B (en) | Anti-collision unmanned aerial vehicle with shock attenuation buffer function | |
| CN109334946B (en) | Unmanned plane | |
| CN101468634A (en) | Method for protecting passerby by vehicle for collision between passerby and vehicle and safety device | |
| CN101774366A (en) | Driver air-bag | |
| CN113954779B (en) | Correction method based on automatic vehicle rollover correction structure | |
| CN113148159B (en) | Unmanned aerial vehicle takes photo by plane | |
| CN115405661A (en) | Anti-impact liquid crystal display screen | |
| CN111532199B (en) | Car lamp and assembly line thereof | |
| CN219770192U (en) | Unmanned aerial vehicle anticollision structure | |
| CN209870756U (en) | Unmanned aerial vehicle shock attenuation gasbag and unmanned aerial vehicle gasbag damping device | |
| CN112224426A (en) | Falling protection device for unmanned aerial vehicle | |
| CN112810579A (en) | Air-drop war chariot landing rollover prevention device and use method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20231221 Address after: 230000 floor 1, building 2, phase I, e-commerce Park, Jinggang Road, Shushan Economic Development Zone, Hefei City, Anhui Province Patentee after: Dragon totem Technology (Hefei) Co.,Ltd. Address before: Baishi Village, west suburb, Cuiping District, Yibin City, Sichuan Province Patentee before: YIBIN VOCATIONAL AND TECHNICAL College |