CN114379800A - Unmanned aerial vehicle flight buffer stop - Google Patents
Unmanned aerial vehicle flight buffer stop Download PDFInfo
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- CN114379800A CN114379800A CN202111661598.5A CN202111661598A CN114379800A CN 114379800 A CN114379800 A CN 114379800A CN 202111661598 A CN202111661598 A CN 202111661598A CN 114379800 A CN114379800 A CN 114379800A
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- unmanned aerial
- aerial vehicle
- buffer stop
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- vehicle flight
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- 238000012545 processing Methods 0.000 claims description 21
- 238000003780 insertion Methods 0.000 claims description 5
- 230000037431 insertion Effects 0.000 claims description 5
- 244000309464 bull Species 0.000 claims description 4
- 238000013461 design Methods 0.000 abstract description 3
- 230000000694 effects Effects 0.000 abstract description 3
- 239000000758 substrate Substances 0.000 description 3
- 238000000034 method Methods 0.000 description 2
- 235000008331 Pinus X rigitaeda Nutrition 0.000 description 1
- 235000011613 Pinus brutia Nutrition 0.000 description 1
- 241000018646 Pinus brutia Species 0.000 description 1
- 230000004888 barrier function Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000011010 flushing procedure Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000005389 magnetism Effects 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
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- 238000007493 shaping process Methods 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT 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
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
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Abstract
The application discloses unmanned aerial vehicle flight buffer stop includes: the inserted rods are assembled on two sides of the unmanned aerial vehicle main body, and hoses are arranged on the surfaces of the inserted rods; the ring body is distributed at one end of the inserted rod, the inserted rod is connected with the top end of the ring body through a rotating rod, a plurality of air bag pipes are uniformly assembled between the inner wall of the ring body and the inserted rod, and the two groups of ring bodies are connected in a magnetic attraction manner; the unmanned aerial vehicle has the technical key points that the inserted link and the ring body are combined, and the air pump is utilized to inflate each air bag pipe, so that the two ring bodies are mutually attached to form two conical structures, the unmanned aerial vehicle can be comprehensively protected under the condition that the normal flight of the unmanned aerial vehicle is not influenced, and a better anti-collision effect can be achieved; at the gasbag pipe below design support frame that corresponds, use the air pump to aerify the back to each gasbag pipe, can aerify the support frame simultaneously, the support frame after the complete expansion can make whole unmanned aerial vehicle main part safety and stability descend to appointed plane on.
Description
Technical Field
The invention belongs to the field of unmanned aerial vehicles, and particularly relates to a flight anti-collision device for an unmanned aerial vehicle.
Background
At present, an unmanned plane is called an unmanned plane for short, and is an unmanned plane operated by utilizing a radio remote control device and a self-contained program control device; the airplane is not provided with a cockpit, but is provided with an automatic pilot, a program control device and other equipment; tracking, positioning, remote control, remote measurement and digital transmission are carried out on the personnel at the ground, the naval vessel or the mother aircraft remote control station through equipment such as a radar; the airplane can take off like a common airplane or launch to lift off by using a boosting rocket under the radio remote control, and can also be thrown into the air by a mother airplane to fly; during recovery, the aircraft can automatically land in the same way as the common aircraft landing process, and can also be recovered by a parachute or a barrier net through remote control; can be repeatedly used for many times; the system is widely used for aerial reconnaissance, monitoring, communication, anti-submergence, electronic interference and the like;
the existing unmanned aerial vehicle has a wide application field, the traditional unmanned aerial vehicle adopts more spiral blades on the body, and the body can be assembled with a camera and other structures, so that the subsequent operation is convenient;
however, the existing unmanned aerial vehicle usually adopts a collar designed on the outer side of the spiral blade of the unmanned aerial vehicle to protect the spiral blade on improving the anti-collision performance of the unmanned aerial vehicle, but the protection performance is lower, and the unmanned aerial vehicle can easily contact with the spiral blade when encountering large birds, so that the normal operation of the unmanned aerial vehicle is influenced.
Disclosure of Invention
Technical problem to be solved
Aiming at the defects of the prior art, the invention provides an unmanned aerial vehicle flight anti-collision device, which solves the problems in the prior art.
(II) technical scheme
In order to achieve the purpose, the invention is realized by the following technical scheme:
an unmanned aerial vehicle flight buffer stop, includes:
the inserted rods are assembled on two sides of the unmanned aerial vehicle main body, and hoses are arranged on the surfaces of the inserted rods;
the ring body is distributed at one end of the inserted rod, the inserted rod is connected with the top end of the ring body through a rotating rod, a plurality of air bag pipes are uniformly assembled between the inner wall of the ring body and the inserted rod, and the two groups of ring bodies are connected in a magnetic attraction manner;
the control assembly, it sets up in the unmanned aerial vehicle main part, and control assembly contains air pump, baroceptor and central processing unit, and the central processing unit of this department adopts the controller of PLC226 model, the unmanned aerial vehicle main part top is installed to the air pump, the baroceptor is used for detecting the atmospheric pressure in the hose to pass through the wire with central processing unit and be connected, the hose is used for connecting air pump and each gasbag pipe.
Further, the inserted bar is cylindrical, and the one end of inserted bar and the outer surface of unmanned aerial vehicle main part are connected in a spiral manner.
By adopting the technical scheme: when the inserted bar is demolishd to needs, can at first separate connecting pipe and the hose that corresponds, then take off the spiral pine of inserted bar and unmanned aerial vehicle main part for whole inserted bar and circle body and unmanned aerial vehicle main part separation can accomplish the dismantlement work.
Furthermore, the outer surface of the inserted bar is provided with a placing groove, and the hose is embedded in the corresponding placing groove.
By adopting the technical scheme: the hose of this department is gone into to the corresponding standing groove of card when the installation, prevents that the hose from direct and external contact, to a certain extent, multiplicable this hose's life.
Further, one side that unmanned aerial vehicle main part surface is close to the inserted bar is provided with the connecting pipe, and the one end of this connecting pipe is connected with the gas outlet of air pump, the other end and the hose spiral connection that corresponds.
By adopting the technical scheme: when the assembly connecting pipe, with the spiral connection of one end of connecting pipe and hose, can realize that the gas circuit is unobstructed, the gas flow direction when aerifing is for:
the air pump is opened work, then enters into the connecting pipe through playing the gas port, then enters into each gasbag intraductally through the hose for gasbag pipe is after extending completely, aerifys the support frame, closes the pneumatic valve after the support frame shaping completely can.
Furthermore, the circle center of a circle formed by the inner wall of the ring body is always overlapped with the corresponding inserted rod, one end of the rotating rod is connected with the ring body through a rotating shaft, and the other end of the rotating rod is connected with the corresponding inserted rod through a rotating shaft.
By adopting the technical scheme: when receiving the circle body, make the bull stick deflect, guarantee that the circle body keeps flushing with the unmanned aerial vehicle main part, can carry out the work of demolising the inserted bar.
Furthermore, a plurality of positioning pieces are welded on the side face of any one group of the ring body, the positioning pieces are cylindrical magnetic blocks, and slots are formed in the positions, corresponding to the positioning pieces, on the surface of the other group of the ring body.
By adopting the technical scheme: after each air bag pipe is completely extended, the air bag pipe can drive the two ring bodies to be close to each other, then the ring body with a plurality of positioning pieces is enabled to be tightly attached to the other ring body, and the magnetic attraction acting force of the magnetic blocks and the slots is utilized to ensure the stability of the two ring bodies after being connected.
Furthermore, each under the inflation state gasbag pipe is cylindricly, is located a set of gasbag pipe surface under the bull stick still is provided with the support frame, and this support frame is used for supporting whole buffer stop.
Specifically, the support frame comprises a first bag and a second bag, wherein,
the first air bag is used for communicating the second air bag with a group of air bag pipes right below the rotating rod; the section of the second bag in the inflated state is in a semicircular ring shape.
By adopting the technical scheme: firstly, the second bag is unfolded, then the first bag is completely unfolded, and at the moment, the lower surface of the first bag is flush with the lower surfaces of the two groups of ring bodies in a mutually-jointed state, so that the whole device is ensured to be kept stable and stable after being landed on a plane
Furthermore, the central processing unit is arranged on a substrate, and the substrate is positioned in the unmanned aerial vehicle body and can be fixed through screws.
Further, an air valve is arranged on an air outlet of the air pump, and the air valve and the air pressure sensor are both connected with the central processing unit through wires; in particular, the method comprises the following steps of,
the baroceptor of this department is used for detecting the atmospheric pressure in connecting pipe and the hose under the full of the gas state, and baroceptor conveys the atmospheric pressure data that detect in real time to central processing unit, if central processing unit detects atmospheric pressure and takes place the continuation and reduce, then sends the instruction for whole unmanned aerial vehicle main part for the unmanned aerial vehicle main part carries out the automatic landing, and reminds the staff to overhaul the processing.
In summary, the invention includes at least one of the following beneficial effects:
firstly, the inserted link and the ring body are combined, and the air pump is utilized to inflate each air bag pipe, so that the two ring bodies are tightly attached to each other to form two conical structures, the comprehensive protection of the unmanned aerial vehicle main body can be completed under the condition that the normal flight of the unmanned aerial vehicle is not influenced, and a better anti-collision effect can be achieved;
secondly, at the gasbag pipe below design support frame that corresponds, use the air pump to aerify the back to each gasbag pipe, can aerify the support frame simultaneously, the support frame after the complete expansion can make whole unmanned aerial vehicle main part safety and stability descend to appointed plane on, under the uninflated state, can expand whole circle body completely, avoids dismantling the operation of screw, and the convenience is maintained and is changed the processing to the unmanned aerial vehicle main part.
Drawings
Fig. 1 is a schematic view of the insertion rod and control assembly of the present invention in an assembled state with the main body of the drone;
FIG. 2 is an elevational view of the overall construction of the present invention;
FIG. 3 is a side view of the overall structure of the present invention;
FIG. 4 is an enlarged view of the partial structure A of FIG. 1 of the present invention;
FIG. 5 is a schematic view of the support frame of the present invention;
fig. 6 is a schematic diagram of a control assembly of the present invention.
Reference numerals: 1. an unmanned aerial vehicle main body; 2. inserting a rod; 3. an air pump; 4. a loop body; 5. a rotating rod; 6. a balloon tube; 7. a support frame; 71. a first pocket; 72. a second pocket; 8. a positioning member; 9. a central processing unit; 10. a hose; 11. an air valve; 12. an air pressure sensor; 13. a connecting pipe; 14. and (6) placing the groove.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention. In addition, for the convenience of description, the terms "upper", "lower", "left" and "right" are used to refer to the same direction as the upper, lower, left, right, etc. of the drawings, and the terms "first", "second", etc. are used for descriptive distinction and have no special meaning.
Example 1:
this embodiment provides whole buffer stop and unmanned aerial vehicle main part concrete structure, as shown in fig. 1-6, an unmanned aerial vehicle flight buffer stop includes: the unmanned aerial vehicle comprises an inserting rod 2, a connecting rod and a connecting rod, wherein the inserting rod 2 is assembled on two sides of a main body 1 of the unmanned aerial vehicle, and a hose 10 is arranged on the surface of the inserting rod 2; circle body 4, its distribution is in the one end of inserted bar 2, and is connected through setting up bull stick 5 between the top of inserted bar 2 and circle body 4 to a plurality of gasbag pipes 6 of even formula assembly between 4 inner walls of circle body and inserted bar 2, the formula is connected is inhaled to magnetism between two sets of circle bodies 4.
In some examples, the insertion rod 2 is of a cylindrical structure, and one end of the insertion rod 2 is in spiral connection with the outer surface of the unmanned aerial vehicle main body 1; the outer surface of the inserted bar 2 is provided with a placing groove 14, and the hose 10 is embedded in the corresponding placing groove 14; a connecting pipe 13 is arranged on one side of the outer surface of the unmanned aerial vehicle main body 1, which is close to the inserted link 2, one end of the connecting pipe 13 is connected with an air outlet of the air pump 3, and the other end of the connecting pipe 13 is spirally connected with a corresponding hose 10; the circle center of a circle formed by the inner wall of the ring body 4 is always coincided with the corresponding inserted rod 2, one end of the rotating rod 5 is connected with the ring body 4 through a rotating shaft, and the other end of the rotating rod is connected with the corresponding inserted rod 2 through a rotating shaft.
Specifically, a plurality of positioning pieces 8 are welded on the side surface of any one group of ring bodies 4, the positioning pieces 8 are cylindrical magnetic blocks, and slots are formed in the positions, corresponding to the positioning pieces 8, on the surface of the other group of ring bodies 4.
By adopting the technical scheme:
combine inserted bar 2 and circle body 4, utilize air pump 3 to aerify each gasbag pipe 6 for two circle bodies 4 are hugged closely each other, form the state that two coniform structures refer to figure 2, under the condition that does not influence unmanned aerial vehicle normal flight, can accomplish the comprehensive protection to unmanned aerial vehicle main part 1, better crashproof effect that can play.
Example 2:
the present embodiment shows a specific structure of the whole airbag tube, as shown in fig. 2 and 5, each airbag tube 6 in an inflated state is cylindrical, and a support frame 7 is further provided on the surface of one set of airbag tubes 6 located right below the rotating rod 5, and the support frame 7 is used for supporting the whole anti-collision device.
The support frame 7 comprises a first pocket 71 and a second pocket 72, wherein,
the first bag 71 is used for communicating the second bag 72 with a group of air bag tubes 6 right below the rotating rod 5; the section of the second pocket 72 in the inflated state is semicircular.
In some examples, the central processor 9 is provided to a substrate, which is located within the drone body 1.
By adopting the technical scheme:
at 6 below design support frames 7 of gasbag pipe that correspond, use air pump 3 to aerify back to each gasbag pipe 6, can aerify support frame 7 simultaneously, support frame 7 after the complete expansion can make landing of whole unmanned aerial vehicle main part 1 safety and stability to appointed plane, under the uninflated state, can expand whole circle body 4 completely, avoid dismantling the operation of screw, the convenience is maintained and is changed the processing to unmanned aerial vehicle main part 1.
Example 3:
the concrete connection state of control assembly is given to this embodiment, refer to fig. 6, control assembly, it sets up to in the unmanned aerial vehicle main part 1, and control assembly contains air pump 3, baroceptor 12 and central processing unit 9, and the top of unmanned aerial vehicle main part 1 is installed to air pump 3, and baroceptor 12 is used for detecting the atmospheric pressure in the hose 10 to pass through the wire with central processing unit 9 and be connected, hose 10 is used for connecting air pump 3 and each gasbag pipe 6.
In some examples, an air valve 11 is installed on an air outlet of the air pump 3, and both the air valve 11 and the air pressure sensor 12 are connected to the central processing unit 9 through wires.
By adopting the technical scheme:
The foregoing is a more detailed description of the invention in connection with specific preferred embodiments and it is not intended that the invention be limited to these specific details. For those skilled in the art to which the invention pertains, several simple deductions or substitutions can be made without departing from the spirit of the invention, and all shall be considered as belonging to the protection scope of the invention.
Claims (10)
1. The utility model provides an unmanned aerial vehicle flight buffer stop, its characterized in that includes:
the unmanned aerial vehicle comprises insertion rods (2) which are assembled on two sides of a main body (1) of the unmanned aerial vehicle, and hoses (10) are arranged on the surfaces of the insertion rods (2);
the ring body (4) is distributed at one end of the inserted rod (2), the inserted rod (2) is connected with the top end of the ring body (4) through a rotating rod (5), a plurality of air bag pipes (6) are uniformly assembled between the inner wall of the ring body (4) and the inserted rod (2), and the two groups of ring bodies (4) are connected in a magnetic attraction manner;
control assembly, it sets up in unmanned aerial vehicle main part (1), and control assembly contains air pump (3), baroceptor (12) and central processing unit (9), unmanned aerial vehicle main part (1) top is installed in air pump (3), baroceptor (12) are used for detecting the atmospheric pressure in hose (10) to be connected through the wire with central processing unit (9), hose (10) are used for connecting air pump (3) and each gasbag pipe (6).
2. An unmanned aerial vehicle flight buffer stop according to claim 1, characterized in that: inserted bar (2) cylindric structure, and spiral connection between the one end of inserted bar (2) and unmanned aerial vehicle main part (1) surface.
3. An unmanned aerial vehicle flight buffer stop according to claim 1, characterized in that: the outer surface of the inserted bar (2) is provided with a placing groove (14), and the hose (10) is embedded in the corresponding placing groove (14).
4. An unmanned aerial vehicle flight buffer stop according to claim 1, characterized in that: one side that unmanned aerial vehicle main part (1) surface is close to inserted bar (2) is provided with connecting pipe (13), and the one end of this connecting pipe (13) is connected with the gas outlet of air pump (3), the other end and hose (10) spiral connection that correspond.
5. An unmanned aerial vehicle flight buffer stop according to claim 1, characterized in that: the circle center of the circle formed by the inner wall of the ring body (4) is always coincided with the corresponding inserted bar (2), one end of the rotating rod (5) is connected with the ring body (4) through a rotating shaft, and the other end of the rotating rod is connected with the corresponding inserted bar (2) through a rotating shaft.
6. An unmanned aerial vehicle flight buffer stop according to claim 1, characterized in that: a plurality of positioning pieces (8) are welded on the side face of any one group of the ring body (4), the positioning pieces (8) are cylindrical magnetic blocks, and slots are formed in the positions, corresponding to the positioning pieces (8), on the surface of the other group of the ring body (4).
7. An unmanned aerial vehicle flight buffer stop according to claim 1, characterized in that: each under the inflation state gasbag pipe (6) are cylindricly, are located a set of gasbag pipe (6) surface under bull stick (5) still is provided with support frame (7), and this support frame (7) are used for supporting whole buffer stop.
8. An unmanned aerial vehicle flight buffer stop according to claim 7, characterized in that: the support frame (7) comprises a first number bag (71) and a second number bag (72), wherein,
the first bag (71) is used for communicating the second bag (72) with a group of air bag pipes (6) right below the rotating rod (5); the section of the second pocket (72) in the inflated state is in a semicircular ring shape.
9. An unmanned aerial vehicle flight buffer stop according to claim 1, characterized in that: central processing unit (9) set up to the base plate on, this base plate is located unmanned aerial vehicle main part (1).
10. An unmanned aerial vehicle flight buffer stop according to claim 1, characterized in that: an air valve (11) is installed on an air outlet of the air pump (3), and the air valve (11) and the air pressure sensor (12) are connected with the central processing unit (9) through wires.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111661598.5A CN114379800A (en) | 2021-12-31 | 2021-12-31 | Unmanned aerial vehicle flight buffer stop |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111661598.5A CN114379800A (en) | 2021-12-31 | 2021-12-31 | Unmanned aerial vehicle flight buffer stop |
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2021
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Application publication date: 20220422 |