CN114162305A - Unmanned aerial vehicle for monitoring - Google Patents
Unmanned aerial vehicle for monitoring Download PDFInfo
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- CN114162305A CN114162305A CN202111553305.1A CN202111553305A CN114162305A CN 114162305 A CN114162305 A CN 114162305A CN 202111553305 A CN202111553305 A CN 202111553305A CN 114162305 A CN114162305 A CN 114162305A
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- undercarriage
- unmanned aerial
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- 238000012544 monitoring process Methods 0.000 title claims abstract description 22
- 238000005452 bending Methods 0.000 claims description 2
- 241000463219 Epitheca Species 0.000 claims 2
- 230000006835 compression Effects 0.000 claims 1
- 238000007906 compression Methods 0.000 claims 1
- 239000004576 sand Substances 0.000 abstract description 33
- 230000005484 gravity Effects 0.000 abstract description 3
- 238000005516 engineering process Methods 0.000 description 6
- 239000002689 soil Substances 0.000 description 3
- 238000006424 Flood reaction Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000035515 penetration Effects 0.000 description 2
- 238000013459 approach Methods 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000003780 insertion Methods 0.000 description 1
- 230000037431 insertion Effects 0.000 description 1
- 238000004377 microelectronic Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- 238000012549 training Methods 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/061—Frames
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/068—Fuselage sections
- B64C1/069—Joining arrangements therefor
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/58—Arrangements or adaptations of shock-absorbers or springs
- B64C25/62—Spring shock-absorbers; Springs
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C2025/325—Alighting gear characterised by elements which contact the ground or similar surface specially adapted for helicopters
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Remote Sensing (AREA)
- Catching Or Destruction (AREA)
Abstract
The invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to an unmanned aerial vehicle for monitoring. The unmanned aerial vehicle for monitoring comprises an undercarriage, a casing arranged at the top of the undercarriage, a monitoring camera arranged at the bottom of the casing and a rotor wing arranged on the casing, wherein the casing is divided into an upper casing and a lower casing, the top of the inner side of the upper casing is connected with the lower casing through a push-up spring, the push-up spring is in a compressed state, and the bottom edge of the upper casing is fixedly connected with a deep-in plate; according to the sand-free deep-in plate, the pushing piece is pushed by the gravity of sand, the pushing piece drives the pushing plate to move, the pushing plate pushes the transverse plate to move upwards, the transverse plate pulls the horizontal rod out of the through hole through the connecting rope, or the connecting rope is driven by the inertia force of the transverse plate to pull the horizontal rod out of the through hole, so that the deep-in plate is unlocked, at the moment, the restoring force of the lifting spring pushes the upper shell to rise, the distance between the upper shell and the lower shell is increased, the probability that the whole body is completely submerged into the sand is reduced, and the convenience of subsequent searching is improved.
Description
Technical Field
The invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to an unmanned aerial vehicle for monitoring.
Background
The early unmanned aerial vehicle is more used as a target drone and a scout aircraft for test training and scout monitoring, and along with the continuous development and application of a microelectronic technology, a micromechanical sensing technology, a global satellite navigation technology, an autonomous control technology and a digital communication technology, the unmanned aerial vehicle gradually develops into a novel aerial force and can play an important role in the field of boring tasks, the field of severe environment tasks and the field of dangerous tasks. In order to improve the monitoring effect on the airport, the unmanned aerial vehicle is also widely applied to the upper air of the airport for monitoring.
When current unmanned aerial vehicle carries out the control of desert plant, when personnel search desert area operation such as, when it breaks down and drops in the sand soil, because the sand is comparatively dispersed, unmanned aerial vehicle floods the sand soil completely easily, even current unmanned aerial vehicle has GPS locate function, when reaching the region at place, the unmanned aerial vehicle who floods in the sand soil searches also can become unusual difficulty, influences the efficiency of retrieving.
Therefore, it is necessary to invent a monitoring drone to solve the above problems.
Disclosure of Invention
Aiming at the problems, the invention provides an unmanned aerial vehicle for monitoring, which aims to solve the problems in the background technology.
In order to achieve the purpose, the invention provides the following technical scheme: an unmanned aerial vehicle for monitoring comprises an undercarriage, a casing arranged at the top of the undercarriage, a monitoring camera arranged at the bottom of the casing and a rotor wing arranged on the casing, wherein the casing is divided into an upper casing and a lower casing, the top of the inner side of the upper casing is connected with the lower casing through a push-up spring, the push-up spring is in a compressed state, the bottom edge of the upper casing is fixedly connected with a deep-in plate, one surface of the deep-in plate, which is close to the center of the casing, is provided with a through hole, the top edge of the lower casing is provided with a deep-in hole, and the through hole is positioned in the deep-in hole; a horizontal rod is inserted in the through hole, one end of the horizontal rod is fixedly connected with an insertion spring, and the end of the horizontal rod is fixedly connected with a connecting rope;
the undercarriage is U-shaped, comprises a horizontal section and vertical sections arranged at two ends of the horizontal section, a protruding cover is integrally formed at the top of the horizontal section of the undercarriage, horizontal holes are formed in the middle of the two vertical sections of the undercarriage, the undercarriage and the protruding cover at the bottom of the horizontal hole are arranged and communicated with each other in a hollow mode, a vertical plate is arranged at the bottom of the inner side of the protruding cover, limiting springs are fixedly connected to the front side and the rear side of the vertical plate, one end, far away from the vertical plate, of each limiting spring is fixedly connected with a push plate, the top ends of the push plates are oblique planes, transverse plates are supported on the oblique planes of the two push plates together, the centers of the bottoms of the transverse plates are connected with connecting ropes, one face, far away from the limiting springs, of each push plate is fixedly connected with a push part, and the end parts of each push part are located at the bottom of the undercarriage.
Preferably, the edge of the bottom of the upper shell is hinged with a hinged plate, the end part of the hinged plate is close to the outer surface of the upper shell, the hinged end of the hinged plate is close to the inner wall and is provided with a torsion spring, the end part of the free end of the hinged plate is inserted with an extension plate, and the extension plate is connected with the hinged plate through a push-out spring.
Preferably, the edge of the top of the hinged plate is integrally formed with an extension edge, the bottom of the extension edge is a plane, and the plane of the bottom of the extension edge is provided with a plurality of concave holes.
Preferably, the thickness of the extension plate gradually increases towards the direction away from the push-out spring, and the end part of the extension plate is horizontally provided with a storage channel.
Preferably, the top of the transverse plate is fixedly connected with a limiting pipe, the top of the limiting pipe is inserted with a limiting rod matched with the limiting pipe, and the top end of the limiting rod is fixedly connected to the top of the inner side of the raised cover.
Preferably, the outer surface of the limiting rod is fixedly connected with a rubber sleeve, and the outer diameter of the rubber sleeve is equal to the inner diameter of the limiting pipe.
Preferably, two the slurcam side all runs through and is provided with bar magnet, and the polarity of the adjacent one end of two bar magnets is different, and bar magnet top and bottom are all fixed in the slurcam through the stretch cord.
Preferably, the two connecting ropes at the top of the lower shell are respectively connected with the bottoms of the transverse plates in the two landing gears, and the connecting ropes penetrate through the landing gears and then enter the side walls of the lower shell.
Preferably, the bottom of one end of the horizontal rod, which is positioned in the deep hole, is embedded with a ball, and the end is a chamfer plane, and the height of the chamfer plane is gradually reduced towards the rear side.
The invention has the technical effects and advantages that:
1. according to the sand-free deep-in plate, the pushing piece is pushed by the gravity of sand, the pushing piece drives the pushing plate to move, the pushing plate pushes the transverse plate to move upwards, the transverse plate pulls the horizontal rod out of the through hole through the connecting rope, or the connecting rope is driven by the inertia force borne by the transverse plate to pull the horizontal rod out of the through hole, so that the deep-in plate is unlocked, the restoring force of the lifting spring can push the upper shell to ascend, the distance between the upper shell and the lower shell is increased, the probability that the whole body is completely submerged into the sand is reduced, and the convenience of subsequent searching is improved;
2. according to the invention, the thickness of the extension plate is gradually increased towards the direction far away from the push-out spring, sand can be stirred towards the interior of the upper shell, so that the quantity of the sand at the bottom of the upper shell is increased, the resistance when the upper shell sinks is improved, meanwhile, the weight of the extension plate can be reduced due to the arrangement of the storage channel, the speed in flight is improved, and after the storage channel is contacted with the sand, the sand can enter the storage channel, so that the weight of the storage channel is increased, and the sinking depth of the storage channel is reduced;
3. according to the invention, when the pushing plate is pushed by the entering sand through the other pushing part to move, the pushing plate drives the bar-shaped magnets to move so as to be close to the other pushing plate which is not moved, the bar-shaped magnets on the pushing plate are attracted, so that the two pushing plates are driven to be close to each other, the transverse plate smoothly rises and cannot be influenced by the rubber sleeve, and the bar-shaped magnets are connected through the elastic rope, so that when the flying vehicle accelerates or decelerates, the two bar-shaped magnets move simultaneously and are always kept at a distance which cannot be attracted.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and those skilled in the art can also obtain other drawings according to the drawings without creative efforts.
FIG. 1 is a side view of the present invention;
FIG. 2 is a cross-sectional view of portion A of FIG. 1 in accordance with the present invention;
FIG. 3 is a side sectional view of the landing gear of the present invention;
FIG. 4 is a bottom view of the upper shell of the present invention;
FIG. 5 is an enlarged view of portion B of FIG. 4 according to the present invention;
FIG. 6 is a cross-sectional view of a hinge plate in longitudinal section in accordance with the present invention;
fig. 7 is a front view of the push plate of the present invention.
In the figure: the landing gear comprises a landing gear 1, a machine shell 2, an upper shell 201, a lower shell 202, a monitoring camera 3, a rotor 4, a deep-in plate 5, a through hole 6, a horizontal rod 7, a plugging spring 8, a connecting rope 9, a convex cover 10, a horizontal hole 11, a vertical plate 12, a limiting spring 13, a pushing plate 14, a transverse plate 15, a pushing piece 16, a hinge plate 17, an extension plate 18, a pushing spring 19, an extension edge 20, a limiting pipe 21, a rubber sleeve 22, a bar-shaped magnet 23, an elastic rope 24, a ball 25, a pushing spring 26 and a storage channel 27.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, 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 some, but not all, embodiments of the present invention. All other embodiments obtained by a person of ordinary skill in the art based on the embodiments of the present invention without any creative effort belong to the protection scope of the present invention;
in the description of the present invention, it is to be understood that the terms "length", "width", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on the orientations or positional relationships illustrated in the drawings, and are used merely for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed in a particular orientation, and be operated, and thus, are not to be construed as limiting the present invention. Further, in the description of the present invention, "a plurality" means two or more unless specifically defined otherwise.
The invention provides an unmanned aerial vehicle for monitoring as shown in figures 1-7, which comprises an undercarriage 1, a casing 2 arranged at the top of the undercarriage, a monitoring camera 3 arranged at the bottom of the casing 2 and a rotor 4 arranged on the casing 2, wherein the casing 2 is divided into an upper casing 201 and a lower casing 202, the top of the inner side of the upper casing 201 is connected with the lower casing 202 through a push-up spring 26, the push-up spring 26 is in a compressed state, the bottom edges of the upper casing 201 are fixedly connected with deep-going plates 5, one surface of each deep-going plate 5, which is close to the center of the casing 2, is provided with a through hole 6, the top edge of the lower casing 202 is provided with a deep-going hole, and the through hole 6 is positioned inside the deep-going hole; a horizontal rod 7 is inserted in the through hole 6, one end of the horizontal rod 7 is fixedly connected with an inserting spring 8, and the end is fixedly connected with a connecting rope 9;
the undercarriage comprises two undercarriage 1 which are respectively positioned at two sides of the bottom of a casing 2, the undercarriage 1 is U-shaped, the undercarriage 1 comprises a horizontal section and vertical sections arranged at two ends of the horizontal section, a convex cover 10 is integrally formed at the top of the horizontal section of the undercarriage 1, a horizontal hole 11 is formed in the middle of each of the two vertical sections of the undercarriage 1, the undercarriage 1 and the convex cover 10 at the bottom of the horizontal hole 11 are hollow and communicated with each other, a vertical plate 12 is arranged at the bottom of the inner side of the convex cover 10, a limiting spring 13 is fixedly connected to the front side and the rear side of the vertical plate 12, one end of the limiting spring 13 far away from the vertical plate 12 is fixedly connected with a push plate 14, the top end of the push plate 14 is a chamfer, a transverse plate 15 is supported on the chamfer of the two push plates 14 together, the center of the bottom of the transverse plate 15 is connected with a connecting rope 9, the two connecting ropes 9 at the top of a lower shell 202 are respectively connected with the bottoms of the transverse plates 15 in the two undercarriage 1, the connecting rope 9 penetrates through the landing gear 1 and then enters the side wall of the lower shell 202, a pushing piece 16 is fixedly connected to one surface, away from the limiting spring 13, of the pushing plate 14, and the end part of the pushing piece 16 is located at the bending position of the bottom of the landing gear 1; the top of the transverse plate 15 is fixedly connected with a limiting pipe 21, the top of the limiting pipe 21 is inserted with a limiting rod matched with the limiting pipe, and the top end of the limiting rod is fixedly connected with the top of the inner side of the convex cover 10.
When it fails during the monitoring task performed in the sand;
when the landing gear 1 firstly contacts sand, after the landing gear 1 is submerged in the sand, the sand enters the hollow part of the landing gear 1 through the horizontal hole 11, the pushing part 16 is pushed by the gravity of the sand, the pushing part 16 drives the pushing plate 14 to move, the pushing plate 14 pushes the transverse plate 15 to move upwards, the transverse plate 15 pulls out the horizontal rod 7 from the through hole 6 through the connecting rope 9, the deep penetration plate 5 is unlocked, and at the moment, the restoring force of the lifting spring 26 can push the upper shell 201 to rise;
when the top of the upper shell 201 contacts sand first, after the upper shell 201 impacts the sand, the transverse plate 15 is subjected to inertia to pull the connecting rope 9 to move, so that the horizontal rod 7 is pulled to move, the deep plate 5 is unlocked, and the lifting spring 26 is restored, so that the lower shell 202 and the landing gear 1 are pushed to ascend;
the distance between the upper shell 201 and the lower shell 202 can be increased by the two modes, the probability that the whole body is completely submerged into sand is reduced, and the convenience of subsequent searching is improved.
Referring to the attached drawings 4, 5 and 6 in the specification, a hinged plate 17 is hinged to the bottom edge of the upper shell 201, the end of the hinged plate 17 is close to the outer surface of the upper shell 201, the hinged end of the hinged plate 17 is close to the inner wall and is provided with a torsion spring, the end of the free end of the hinged plate 17 is plugged with an extension plate 18, and the extension plate 18 is connected with the hinged plate 17 through a push-out spring 19.
When the deep penetration plate 5 is locked in a contact mode and the pushing-up spring 26 is restored, after the upper shell 201 is separated from the lower shell 202, the torsion spring restores to drive the hinged plate 17 to be in a horizontal state, meanwhile, the extension plate 18 in the upper shell is pushed out by the pushing-out spring 19, when the upper shell moves downwards continuously, the resistance of sand firstly enables the hinged plate 17 to be in the horizontal state again, the torsion spring deforms to consume a part of downward impact force, and meanwhile, the contact area of the torsion spring and the sand is increased through the blocking effect of the extension plate 18, so that the resistance when the upper shell 201 moves downwards is increased, the depth of the upper shell submerged sand is reduced, and the convenience of subsequent searching is improved.
Referring to the attached fig. 5 of the specification, an extending edge 20 is integrally formed at the top edge of the hinge plate 17, the bottom of the extending edge 20 is a plane, and a plurality of concave holes are formed on the plane at the bottom of the extending edge 20.
Extend the setting on limit 20, increase the area of contact of sand, there are a plurality of shrinkage pools bottom simultaneously, reduce the smoothness nature of its bottom surface, and when sand blockked it, the resistance is better, reduces the degree of depth of its subsidence.
Referring to the specification and the attached fig. 6, the thickness of the extension plate 18 gradually increases in the direction away from the push-out spring 19, and a storage channel 27 is horizontally formed at the end of the extension plate 18.
The thickness of the extension plate 18 gradually increases towards the direction away from the push-out spring 19, sand can be shifted towards the inside of the upper shell 201, so that the amount of sand at the bottom of the upper shell 201 is increased, the resistance when the upper shell 201 sinks is improved, meanwhile, the weight of the extension plate 18 can be reduced due to the arrangement of the storage channel 27, the flying speed is improved, and after the storage channel 27 is contacted with the sand, the sand can enter the storage channel 27, the weight of the storage channel is increased, and the sinking depth of the storage channel is reduced.
Referring to the attached figure 3 of the specification, the outer surface of the limiting rod is fixedly connected with a rubber sleeve 22, and the outer diameter of the rubber sleeve 22 is equal to the inner diameter of the limiting pipe 21.
Rubber sleeve 22 cup joints behind the gag lever post outside, when accelerating or slowing down at the flight in-process, only one impeller 16 promotes undercarriage 1 when receiving inertia this moment, because the setting of rubber sleeve 22 can make diaphragm 15 be in the tilt state, can't be in rebound to guarantee normal flight, prevent to cause the interference to the flight.
Referring to the attached figure 7 of the specification, bar magnets 23 penetrate through the side faces of the two push plates 14, the adjacent ends of the two bar magnets 23 have different polarities, and the tops and the bottoms of the bar magnets 23 are fixed in the push plates 14 through elastic ropes 24.
When the landing gear 1 falls into sand in an inclined mode, the hollow part of the horizontal section at the bottom of the landing gear 1 is in an inclined state, so that the sand entering the pushing part 16 cannot enable the pushing part 16 to move along the inclined hollow part, therefore, when the other pushing part 16 is pushed by the entering sand, the pushing plate 14 adjacent to the other pushing part 16 moves to drive the bar magnet 23 to move, and therefore when the other pushing part 14 is close to the pushing plate 14 which is not moved, the bar magnet 23 on the pushing plate 14 is attracted to drive the two pushing plates 14 to mutually approach to enable the transverse plate 15 to smoothly rise and not be influenced by the rubber sleeve 22;
meanwhile, as the bar magnets 23 are connected through the elastic ropes 24, when the aircraft accelerates or decelerates in the flight process, the two bar magnets 23 move simultaneously and always keep the interval between the bar magnets which cannot be attracted.
Referring to the description of the attached fig. 2, the horizontal rod 7 has a ball 25 embedded in the bottom of the end inside the deep hole, and the end is a chamfered surface, and the height of the chamfered surface gradually decreases toward the rear side.
Due to the restoring force of the pushing spring 26, the friction force between the horizontal rod 7 and the deep plate 5 is large, and due to the arrangement of the balls 25, the horizontal rod 7 can be pulled to move by small force, so that the smoothness in working is ensured.
Although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.
Claims (9)
1. The utility model provides an unmanned aerial vehicle is used in control, includes undercarriage (1), installs casing (2) at undercarriage (1) top, installs surveillance camera machine (3) in casing (2) bottom and installs rotor (4) on casing (2), its characterized in that: the casing (2) is divided into an upper casing (201) and a lower casing (202), the top of the inner side of the upper casing (201) is connected with the lower casing (202) through a push-up spring (26), the push-up spring (26) is in a compression state, a deep-entering plate (5) is fixedly connected to the edge of the bottom of the upper casing (201), a through hole (6) is formed in one surface, close to the center of the casing (2), of the deep-entering plate (5), a deep-entering hole is formed in the edge of the top of the lower casing (202), and the through hole (6) is located inside the deep-entering hole; a horizontal rod (7) is inserted in the through hole (6), one end of the horizontal rod (7) is fixedly connected with an inserting spring (8), and the end is fixedly connected with a connecting rope (9);
the undercarriage (1) is two in number and is respectively positioned on two sides of the bottom of the shell (2), the undercarriage (1) is U-shaped, the undercarriage (1) comprises a horizontal section and vertical sections arranged at two ends of the horizontal section, a protruding cover (10) is integrally formed at the top of the horizontal section of the undercarriage (1), horizontal holes (11) are formed in the middle of the two vertical sections of the undercarriage (1), the undercarriage (1) and the protruding cover (10) at the bottom of the horizontal holes (11) are arranged in a hollow mode and are communicated with each other, a vertical plate (12) is arranged at the bottom of the inner side of the protruding cover (10), limiting springs (13) are fixedly connected to the front side and the rear side of each vertical plate (12), one ends, far away from the vertical plates (12), of the limiting springs (13) are fixedly connected with push plates (14), the top ends of the push plates (14) are oblique planes, the oblique planes of the two push rods (14) are abutted against and held with transverse plates (15) together, and the centers of the bottoms of the transverse plates (15) are connected with connecting ropes (9), one surface of the push rod (14) far away from the limiting spring (13) is fixedly connected with a pushing piece (16), and the end part of the pushing piece (16) is positioned at the bending part of the bottom of the landing gear (1).
2. A drone for surveillance according to claim 1, characterised in that: articulated hinge plate (17) are articulated at epitheca (201) bottom edge, and articulated hinge plate (17) tip is close to epitheca (201) surface, and the hinged end of articulated hinge plate (17) is close to the inner wall and installs the torsional spring, and the free end tip of articulated hinge plate (17) is pegged graft and is had extension board (18), and extension board (18) are connected with articulated hinge plate (17) through propelling out spring (19).
3. A drone for surveillance according to claim 2, characterised in that: the edge of the top of the hinged plate (17) is integrally formed with an extending edge (20), the bottom of the extending edge (20) is a plane, and a plurality of concave holes are formed in the plane of the bottom of the extending edge.
4. A drone for surveillance according to claim 3, characterised in that: the thickness of the extension plate (18) is gradually increased towards the direction away from the push-out spring (19), and a storage channel (27) is horizontally formed in the end part of the extension plate (18).
5. A unmanned aerial vehicle for monitoring according to claim 4, wherein: the top of the transverse plate (15) is fixedly connected with a limiting pipe (21), the top of the limiting pipe (21) is spliced with a limiting rod matched with the limiting pipe, and the top end of the limiting rod is fixedly connected to the top of the inner side of the raised cover (10).
6. A unmanned aerial vehicle for monitoring according to claim 5, wherein: the outer surface of the limiting rod is fixedly connected with a rubber sleeve (22), and the outer diameter of the rubber sleeve (22) is equal to the inner diameter of the limiting pipe (21).
7. A unmanned aerial vehicle for monitoring according to claim 6, wherein: two pushing plates (14) side all run through and are provided with bar magnet (23), and the polarity of the adjacent one end of two bar magnet (23) is different, and bar magnet (23) top and bottom are all fixed in pushing plates (14) through stretch cord (24).
8. The unmanned aerial vehicle for monitoring of claim 7, wherein: two connecting ropes (9) at the top of the lower shell (202) are respectively connected with the bottoms of the transverse plates (15) in the two undercarriage (1), and the connecting ropes (9) penetrate through the undercarriage (1) and then enter the side walls of the lower shell (202).
9. The unmanned aerial vehicle for monitoring of claim 8, wherein: the bottom of one end of the horizontal rod (7) positioned in the deep hole is embedded with a ball (25), the end is a chamfer plane, and the height of the chamfer plane is gradually reduced towards the rear side.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111553305.1A CN114162305A (en) | 2021-12-17 | 2021-12-17 | Unmanned aerial vehicle for monitoring |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111553305.1A CN114162305A (en) | 2021-12-17 | 2021-12-17 | Unmanned aerial vehicle for monitoring |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114162305A true CN114162305A (en) | 2022-03-11 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111553305.1A Withdrawn CN114162305A (en) | 2021-12-17 | 2021-12-17 | Unmanned aerial vehicle for monitoring |
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| CN (1) | CN114162305A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116873252A (en) * | 2023-09-06 | 2023-10-13 | 山西昊天视界航空科技有限公司 | Unmanned aerial vehicle convenient to receive and release undercarriage |
-
2021
- 2021-12-17 CN CN202111553305.1A patent/CN114162305A/en not_active Withdrawn
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116873252A (en) * | 2023-09-06 | 2023-10-13 | 山西昊天视界航空科技有限公司 | Unmanned aerial vehicle convenient to receive and release undercarriage |
| CN116873252B (en) * | 2023-09-06 | 2023-12-01 | 山西昊天视界航空科技有限公司 | Unmanned aerial vehicle convenient to receive and release undercarriage |
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