CN113460318B - Autonomous landing system of offshore unmanned aerial vehicle - Google Patents
Autonomous landing system of offshore unmanned aerial vehicle Download PDFInfo
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- CN113460318B CN113460318B CN202110911877.6A CN202110911877A CN113460318B CN 113460318 B CN113460318 B CN 113460318B CN 202110911877 A CN202110911877 A CN 202110911877A CN 113460318 B CN113460318 B CN 113460318B
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- 238000009434 installation Methods 0.000 claims description 30
- 229910000831 Steel Inorganic materials 0.000 claims description 12
- 239000010959 steel Substances 0.000 claims description 12
- 238000013016 damping Methods 0.000 claims description 11
- 239000007787 solid Substances 0.000 claims description 4
- 230000003139 buffering effect Effects 0.000 abstract description 4
- 238000000034 method Methods 0.000 abstract description 4
- 230000008878 coupling Effects 0.000 description 4
- 238000010168 coupling process Methods 0.000 description 4
- 238000005859 coupling reaction Methods 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000001125 extrusion Methods 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/12—Ground or aircraft-carrier-deck installations for anchoring aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U80/00—Transport or storage specially adapted for UAVs
- B64U80/70—Transport or storage specially adapted for UAVs in containers
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
- F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
- F16F15/04—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means
- F16F15/06—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means with metal springs
- F16F15/067—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means with metal springs using only wound springs
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Transportation (AREA)
- Physics & Mathematics (AREA)
- Acoustics & Sound (AREA)
- Emergency Lowering Means (AREA)
- Forklifts And Lifting Vehicles (AREA)
Abstract
The invention discloses an autonomous landing system of an offshore unmanned aerial vehicle, which comprises a containing box, a limiting table, a first clamping groove, a first mounting groove, a first sliding groove, a fixing component, a vibration reduction component, rollers, a rotating shaft, a first spring, a base, a second mounting groove, a second sliding groove, a second spring, a clamping block, a landing table, a third sliding groove, a first mounting cavity, a second mounting cavity, a fourth sliding groove, a third mounting cavity, a third mounting groove, a fifth sliding groove, a lifting handle, a through groove, a supporting rod, a first sliding block, a second sliding block, a third spring, a fourth spring and a telescopic rod, wherein compared with the existing landing platform of the offshore unmanned aerial vehicle, the autonomous landing system is designed with a vibration reduction function, and achieves the purpose of buffering in the landing process; the unmanned aerial vehicle is designed with a fixing function, and can be fixedly protected after falling, so that the unmanned aerial vehicle is prevented from being damaged; the invention has the accommodating function, can be used for accommodating the unmanned aerial vehicle and the landing platform together into the accommodating box, and is convenient to carry and use.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to an autonomous landing system of an offshore unmanned aerial vehicle.
Background
Along with the development of science and technology, unmanned aerial vehicles gradually appear in the field of people, unmanned aerial vehicles are often used in the fields of monitoring, reconnaissance, transportation and the like, when unmanned aerial vehicles are recovered at sea, unmanned aerial vehicle landing platforms are usually required to be used, but the existing offshore unmanned aerial vehicle landing platforms lack damping devices, and damping and buffering cannot be carried out on the landing process; the existing landing platform of the marine unmanned aerial vehicle lacks a fixing function, and the unmanned aerial vehicle cannot be protected after falling; most of existing landing platforms of the offshore unmanned aerial vehicle are fixed, and are inconvenient to carry.
Disclosure of Invention
The invention aims to provide an autonomous landing system of an offshore unmanned aerial vehicle, so as to solve the problems in the background technology.
In order to achieve the above purpose, the present invention provides the following technical solutions: the utility model provides an autonomous landing system of marine unmanned aerial vehicle, includes containing case, spacing platform, first draw-in groove, first mounting groove, first spout, fixed subassembly, damping subassembly, gyro wheel, pivot, first spring, base, second mounting groove, second spout, second spring, fixture block, landing platform, third spout, first mounting chamber, second mounting chamber, fourth spout, third mounting chamber, second mounting groove, fifth spout and handle, the base has been cup jointed on one side inner wall of containing case, and the second mounting groove has been seted up to the distribution on one side outer wall of base, cup jointed the fixture block on one side inner wall of second mounting groove, fixedly connected with second spring on one side outer wall of fixture block, and the one end fixed connection of second spring is on one side inner wall of second mounting groove, and on one side inner wall of containing case the distribution has seted up first draw-in groove, has cup jointed the gyro wheel on one side inner wall of first mounting groove, rotates on one side inner wall of gyro wheel and is connected with the first side inner wall of first side of first mounting groove, and the pivot on one side of first side of symmetry has been seted up on one side inner wall of second mounting groove, and the pivot is connected to one side of first spring.
Preferably, the damping subassembly is installed on the top of base, damping subassembly includes the bracing piece, first slider, the second slider, the third spring, the fourth spring, guide ring and telescopic link, fixedly connected with telescopic link on the top outer wall of base, the top of base is provided with the descending platform, and telescopic link fixed connection is on the bottom outer wall of descending platform, the bracing piece is installed to the bottom symmetry of descending platform, the first slider of one end fixedly connected with of bracing piece, the third spout has been seted up on the bottom outer wall of descending platform, and first slider sliding connection is on one side inner wall of third spout, fixedly connected with third spring on one side outer wall of first slider, and one end fixedly connected with of third spring is on one side inner wall of third spout, the other end fixedly connected with second slider of bracing piece, the second spout has been seted up on the top outer wall of base, and second slider sliding connection is on one side inner wall of second spout, fixedly connected with fourth spring on one side outer wall of second slider, and one end fixedly connected with of fourth spring is on one side inner wall of second spout.
Preferably, the internally mounted of the landing stage has a fixed component, the fixed component includes first lead screw, the steel cable, the second lead screw, the fifth spring, the third slider, first solid fixed ring, the fourth slider, the second solid fixed ring, the fifth slider, the stopper, the connecting rod, the sixth spring, button and coupling, the inside of the landing stage has seted up first installation cavity, rotationally connect with the second lead screw on one side inner wall of first installation cavity, cup joint the fifth spring on one side outer wall of second lead screw, and the one end fixed connection of fifth spring is on one side inner wall of first installation cavity, the other end fixed connection is on one side outer wall of second lead screw, the one end fixed connection of second lead screw has the coupling, fixedly connected with first lead screw on one side outer wall of coupling, and first lead screw rotates and connects on one side inner wall of first installation cavity, set up the second installation cavity on one side inner wall of first installation cavity, and the steel cable cup joints the one side inner wall of second installation cavity on one side inner wall of first lead screw, and the fourth end fixed connection has the third slider on one side inner wall of fourth lead screw, the bottom end fixed connection of fourth slider is on one side inner wall of fourth slider fixed connection has, the top of fourth slider is fixed connection of fourth slider is on one side inner wall of fourth side inner wall fixed connection, the top end fixed connection of fourth slider is on the fourth side inner wall of fourth slider is fixed connection of fourth slider is on one side inner wall of fourth side inner wall fixed connection of fourth slider, the top end fixed connection is connected with the fourth slider is connected with the fourth end top end of the fourth slider, the button is sleeved on the inner wall of one side of the third mounting groove, and the button is fixedly connected to the outer wall of the top end of the connecting rod.
Preferably, the top of base is provided with spacing platform, and spacing platform fixed connection is on the inner wall of one side of acceping the case.
Preferably, the bottom of the landing platform is provided with a guide ring, and the telescopic rod is fixedly connected to the inner wall of one side of the guide ring.
Preferably, a third sliding block is connected to the outer wall of one side of the first screw rod in a threaded manner, a first fixing ring is fixedly connected to the outer wall of the top end of the third sliding block, a fifth sliding groove is formed in the outer wall of the top end of the landing platform, the first fixing ring is connected to the inner wall of one side of the fifth sliding groove in a sliding manner, a fourth sliding block is connected to the outer wall of one side of the second screw rod in a threaded manner, a second fixing ring is fixedly connected to the outer wall of the top end of the fourth sliding block, and the second fixing ring is connected to the inner wall of one side of the fifth sliding groove in a sliding manner.
Preferably, handles are symmetrically arranged on two sides of the landing platform and fixedly connected to the outer wall of the top end of the base.
Compared with the prior art, the invention has the beneficial effects that: compared with the existing landing platform of the marine unmanned aerial vehicle, the landing platform is designed with a vibration reduction function, so that the purpose of buffering in the landing process is achieved; the unmanned aerial vehicle is designed with a fixing function, and can be fixedly protected after falling, so that the unmanned aerial vehicle is prevented from being damaged; the invention has the accommodating function, can be used for accommodating the unmanned aerial vehicle and the landing platform together into the accommodating box, and is convenient to carry and use.
Drawings
FIG. 1 is a schematic overall perspective view of the present invention;
FIG. 2 is a schematic view of a three-dimensional cutaway front view of the accommodating box of the invention;
FIG. 3 is a schematic perspective view of a base of the present invention;
FIG. 4 is a schematic view of a front cut-away view of a vibration damping assembly of the present invention;
FIG. 5 is a schematic top view of the landing stage of the present invention;
FIG. 6 is a schematic view of a front view of a base of the present invention in partial cutaway;
FIG. 7 is a schematic view of a partially cut-away front view of the landing stage of the present invention;
FIG. 8 is an enlarged view of the structure of area A of FIG. 1;
FIG. 9 is an enlarged view of the structure of region B of FIG. 1;
FIG. 10 is an enlarged view of the structure of region C of FIG. 1;
FIG. 11 is an enlarged view of the structure of the region D in FIG. 2;
FIG. 12 is an enlarged view of the structure of the area E in FIG. 4;
FIG. 13 is an enlarged view of the structure of area F in FIG. 5;
fig. 14 is an enlarged view of the structure of the G region in fig. 5;
in the figure: 1. a storage box; 11. a limiting table; 12. a first clamping groove; 13. a first mounting groove; 131. a first chute; 2. a fixing assembly; 21. a first screw rod; 211. a steel rope; 22. a second screw rod; 221. a fifth spring; 23. a third slider; 231. a first fixing ring; 24. a fourth slider; 241. a second fixing ring; 25. a fifth slider; 26. a limiting block; 27. a connecting rod; 271. a sixth spring; 28. a button; 29. a coupling; 3. a vibration damping assembly; 31. a support rod; 32. a first slider; 33. a second slider; 34. a third spring; 35. a fourth spring; 36. a guide ring; 37. a telescopic rod; 4. a roller; 41. a rotating shaft; 42. a first spring; 5. a base; 51. a second mounting groove; 52. a second chute; 53. a second spring; 54. a clamping block; 6. a landing stage; 61. a third chute; 62. a first mounting cavity; 63. a second mounting cavity; 64. a fourth chute; 65. a third mounting cavity; 66. a third mounting groove; 67. a fifth chute; 7. a handle.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
Referring to fig. 1-14, an embodiment of the present invention is provided: the autonomous landing system of the marine unmanned aerial vehicle comprises a containing box 1, a limiting table 11, a first clamping groove 12, a first mounting groove 13, a first sliding groove 131, a fixing component 2, a damping component 3, a roller 4, a rotating shaft 41, a first spring 42, a base 5, a second mounting groove 51, a second sliding groove 52, a second spring 53, a clamping block 54, a landing table 6, a third sliding groove 61, a first mounting cavity 62, a second mounting cavity 63, a fourth sliding groove 64, a third mounting cavity 65, a third mounting groove 66, a fifth sliding groove 67 and a lifting handle 7, wherein the base 5 is sleeved on one side inner wall of the containing box 1, the second mounting groove 51 is distributed on one side outer wall of the base 5, a clamping block 54 is sleeved on one side inner wall of the second mounting groove 51, a second spring 53 is fixedly connected to one side inner wall of the second mounting groove 51, a first clamping groove 12 is distributed on one side inner wall of the containing box 1, a first clamping block 54 is connected to one side inner wall of the first clamping groove 12, a roller 13 is distributed on one side inner wall of the first side inner wall 1 is sleeved on one side inner wall of the first side inner wall of the containing groove 13, a roller 13 is connected to one side inner wall of the first side of the roller 41 is fixedly connected to one side of the roller 13, and one side of the roller 13 is fixedly connected to one side inner wall of the roller 13 is sleeved on one side of the first side inner wall 13; the top end of the base 5 is provided with a vibration reduction assembly 3, the vibration reduction assembly 3 comprises a supporting rod 31, a first sliding block 32, a second sliding block 33, a third spring 34, a fourth spring 35, a guide ring 36 and a telescopic rod 37, the outer wall of the top end of the base 5 is fixedly connected with the telescopic rod 37, the top end of the base 5 is provided with a landing table 6, the telescopic rod 37 is fixedly connected to the outer wall of the bottom end of the landing table 6, the bottom end of the landing table 6 is symmetrically provided with the supporting rod 31, one end of the supporting rod 31 is fixedly connected with the first sliding block 32, the outer wall of the bottom end of the landing table 6 is provided with a third sliding groove 61, the first sliding block 32 is in sliding connection with one side inner wall of the third sliding groove 61, one side outer wall of the first sliding block 32 is fixedly connected with the third spring 34, one end of the third spring 34 is fixedly connected with one side inner wall of the third sliding groove 61, the other end of the supporting rod 31 is fixedly connected with the second sliding block 33, the outer wall of the top end of the base 5 is provided with a second sliding groove 52, the second sliding block 33 is in sliding connection with one side inner wall of the second sliding groove 52, one side of the second sliding groove 35 is fixedly connected with the fourth spring 35, and one side of the fourth spring 35 is fixedly connected with one side inner wall 52; the fixed component 2 is arranged in the landing table 6, the fixed component 2 comprises a first screw rod 21, a steel rope 211, a second screw rod 22, a fifth spring 221, a third sliding block 23, a first fixed ring 231, a fourth sliding block 24, a second fixed ring 241, a fifth sliding block 25, a limiting block 26, a connecting rod 27, a sixth spring 271, a button 28 and a coupler 29, a first installation cavity 62 is arranged in the landing table 6, a second screw rod 22 is rotationally connected on one side inner wall of the first installation cavity 62, a fifth spring 221 is sleeved on one side outer wall of the second screw rod 22, one end of the fifth spring 221 is fixedly connected on one side inner wall of the first installation cavity 62, the other end of the fifth spring 221 is fixedly connected on one side outer wall of the second screw rod 22, one end of the second screw rod 22 is fixedly connected with the coupler 29, a first screw rod 21 is fixedly connected on one side outer wall of the coupler 29, the first screw rod 21 is rotationally connected on one side inner wall of the first installation cavity 62, a steel rope 211 is sleeved on one side outer wall of the first screw rod 21, one end of the steel rope 211 is fixedly connected to one side outer wall of the first screw rod 21, a second installation cavity 63 is formed on one side inner wall of the first installation cavity 62, the steel rope 211 is sleeved on one side inner wall of the second installation cavity 63, a fourth sliding groove 64 is formed on one side outer wall of the landing table 6, a fifth sliding block 25 is slidingly connected on one side inner wall of the fourth sliding groove 64, the other end of the steel rope 211 is fixedly connected to one side outer wall of the fifth sliding block 25, a third installation cavity 65 is formed on the bottom end inner wall of the fourth sliding groove 64, a connecting rod 27 is installed in the third installation cavity 65, sixth springs 271 are symmetrically fixed on the bottom end outer wall of the connecting rod 27, one end of each sixth spring 271 is fixedly connected to the bottom end inner wall of the third installation cavity 65, one end of each connecting rod 27 is fixedly connected with a limiting block 26, the limiting block 26 is connected to the bottom end inner wall of the fourth chute 64 in a clamping manner, a third mounting groove 66 is formed in the top end outer wall of the landing platform 6, a button 28 is sleeved on one side inner wall of the third mounting groove 66, and the button 28 is fixedly connected to the top end outer wall of the connecting rod 27; the top end of the base 5 is provided with a limiting table 11, the limiting table 11 is fixedly connected to the inner wall of one side of the accommodating box 1, and the limiting table 11 is used for limiting the base 5; the bottom end of the landing table 6 is provided with a guide ring 36, a telescopic rod 37 is fixedly connected to the inner wall of one side of the guide ring 36, and the guide ring 36 is used for guiding the landing table 6 to lift; the outer wall of one side of the first screw rod 21 is in threaded connection with a third sliding block 23, the outer wall of the top end of the third sliding block 23 is fixedly connected with a first fixed ring 231, the outer wall of the top end of the landing platform 6 is provided with a fifth sliding groove 67, the first fixed ring 231 is in sliding connection with the inner wall of one side of the fifth sliding groove 67, the outer wall of one side of the second screw rod 22 is in threaded connection with a fourth sliding block 24, the outer wall of the top end of the fourth sliding block 24 is fixedly connected with a second fixed ring 241, the second fixed ring 241 is in sliding connection with the inner wall of one side of the fifth sliding groove 67, and the third sliding block 23, the first fixed ring 231, the fourth sliding block 24 and the second fixed ring 241 are used for fixing the unmanned aerial vehicle; the two sides of the landing platform 6 are symmetrically provided with handles 7, the handles 7 are fixedly connected to the outer wall of the top end of the base 5, and the handles 7 are used for pulling and rotating the base 5.
Working principle: when the unmanned aerial vehicle is used for landing, the fifth sliding block 25 is firstly slid along the fourth sliding groove 64 until the fifth sliding block 25 is blocked by the limiting block 26, the fifth sliding block 25 drives the first screw rod 21 to rotate through the steel rope 211, the first screw rod 21 drives the second screw rod 22 through the coupler 29, at the moment, the fifth spring 221 in the first installation cavity 62 is compressed, the third sliding block 23 slides on the first screw rod 21, the fourth sliding block 24 slides on the second screw rod 22, the first fixing ring 231 and the second fixing ring 241 in the fifth sliding groove 67 are mutually far away, the unmanned aerial vehicle falls on the landing table 6, the landing table 6 is downwards displaced, the two mutually hinged supporting rods 31 rotate to drive the first sliding block 32 to extrude the fourth spring 35 in the third sliding groove 61, the second sliding block 33 extrudes the third spring 34 in the second sliding groove 52, and vibration reduction and buffering of the vibration reduction assembly 3 on the unmanned aerial vehicle landing process are completed, the unmanned aerial vehicle is fixed by using the fixing component 2, the button 28 is pressed down along the third mounting groove 66, the button 28 drives the limiting block 26 through the connecting rod 27, the sixth spring 271 is compressed at the moment, the fifth sliding block 25 loses limit, the second screw 22 rotates under the reset action of the fifth spring 221, the first fixing ring 231 and the second fixing ring 241 move oppositely until the unmanned aerial vehicle is clamped, the landing table 6 and the unmanned aerial vehicle are retracted into the accommodating box 1, the lifting handle 7 is grasped, the base 5 is rotated, the base 5 drives the clamping block 54 through the second mounting groove 51, the clamping block 54 is separated from the first clamping groove 12 through the extrusion of the accommodating box 1, the second spring 53 is compressed at the moment, the lifting handle 7 is released, the base 5 moves downwards under the action of gravity, the roller 4 is touched and extruded, the roller 4 rotates around the rotating shaft 41 and extrudes the rotating shaft 41, the rotating shaft 41 slides along the first sliding groove 131 in the first mounting groove 13, the first spring 42 is compressed at the moment, the limiting table 11 is used for limiting the base 5, the guide ring 36 and the telescopic rod 37 are used for guiding the lifting of the landing platform 6, the second mounting cavity 63 is used for mounting the steel rope 211, and the third mounting cavity 65 is used for mounting the connecting rod 27.
It will be evident to those skilled in the art that the invention is not limited to the details of the foregoing illustrative embodiments, and that the present invention may be embodied in other specific forms without departing from the spirit or essential characteristics thereof. The present embodiments are, therefore, to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.
Claims (6)
1. Autonomous landing system of marine unmanned aerial vehicle, including accommodating case (1), spacing platform (11), first draw-in groove (12), first mounting groove (13), first spout (131), fixed subassembly (2), damping subassembly (3), gyro wheel (4), pivot (41), first spring (42), base (5), second mounting groove (51), second spout (52), second spring (53), fixture block (54), landing platform (6), third spout (61), first installation chamber (62), second installation chamber (63), fourth spout (64), third installation chamber (65), third mounting groove (66), fifth spout (67) and handle (7), its characterized in that: the base (5) has been cup jointed on the one side inner wall of containing box (1), second mounting groove (51) has been seted up to the distribution on the one side outer wall of base (5), fixture block (54) has been cup jointed on the one side inner wall of second mounting groove (51), fixedly connected with second spring (53) on the one side outer wall of fixture block (54), and the one end fixed connection of second spring (53) is on the one side inner wall of second mounting groove (51), first draw-in groove (12) has been seted up on the one side inner wall of containing box (1) distribution, and fixture block (54) block joint is connected on the one side inner wall of first draw-in groove (12), first mounting groove (13) has been seted up on the one side inner wall of containing box (1) distribution, gyro wheel (4) have been cup jointed on the one side inner wall of first mounting groove (13), rotationally connected with pivot (41) on the one side inner wall of gyro wheel (4), first spout (131) have been seted up on the one side inner wall of first mounting groove (13) symmetrically, and pivot (41) sliding connection is on one side inner wall of first spout (131), first draw-in groove (42) are connected on one side inner wall of pivot (41), first spring (42) are connected on one side inner wall (2) of first inner wall (2) is fixed in one side of first fixed component (2) including first lead screw (2) is fixed, first one end component is fixed in one side (2) is fixed in one side component (2) The first installation cavity (62) is formed in the landing table (6), the second screw rod (22) is rotationally connected to one side inner wall of the first installation cavity (62), the fifth spring (221) is sleeved on one side outer wall of the second screw rod (22), one end of the fifth spring (221) is fixedly connected to one side inner wall of the first installation cavity (62), the other end of the fifth spring (221) is fixedly connected to one side outer wall of the second screw rod (22), one end of the second screw rod (22) is fixedly connected with the coupler (29), the first screw rod (21) is fixedly connected to one side outer wall of the coupler (29), the first screw rod (21) is rotationally connected to one side inner wall of the first installation cavity (62), the second screw rod (22) is rotationally connected to one side outer wall of the first screw rod (21), one side outer wall of the first screw rod (21) is fixedly connected to one side outer wall of the first installation cavity (62), one end of the second screw rod (211) is fixedly connected to one side outer wall of the first screw rod (211), and steel cable (211) cup joints on one side inner wall of second installation cavity (63), fourth spout (64) have been seted up on one side outer wall of descending platform (6), sliding connection has fifth slider (25) on one side inner wall of fourth spout (64), and the other end fixed connection of steel cable (211) is on one side outer wall of fifth slider (25), third installation cavity (65) have been seted up on the bottom inner wall of fourth spout (64), internally mounted in third installation cavity (65) has connecting rod (27), symmetry is fixed with sixth spring (271) on the bottom outer wall of connecting rod (27), and on the bottom inner wall of third installation cavity (65) one end fixedly connected with stopper (26) of connecting rod (27), and stopper (26) block connection is on the bottom inner wall of fourth spout (64), third mounting groove (66) have been seted up on the top outer wall of descending platform (6), button (28) have been cup jointed on the one side inner wall of third mounting groove (66), and button (28) are fixed connection on the outer wall of connecting rod (27).
2. The autonomous landing system of an offshore unmanned aerial vehicle of claim 1, wherein: the top of base (5) is installed damping subassembly (3), damping subassembly (3) include bracing piece (31), first slider (32), second slider (33), third spring (34), fourth spring (35), guide ring (36) and telescopic link (37), fixedly connected with telescopic link (37) on the top outer wall of base (5), the top of base (5) is provided with descending platform (6), and telescopic link (37) fixedly connected with on the bottom outer wall of descending platform (6), bracing piece (31) are installed to the bottom symmetry of descending platform (6), the one end fixedly connected with first slider (32) of bracing piece (31), third spout (61) have been seted up on the bottom outer wall of descending platform (6), and first slider (32) sliding connection is on the one side inner wall of third spout (61), and fixedly connected with third spring (34) on the one side outer wall of first slider (32), and the other end fixedly connected with second slider (33) of bracing piece (31) on one side inner wall of third spout (61), the other end fixedly connected with second slider (52) on the outer wall (52) of second spout (33) have been seted up on the outer wall of second slider (52), a fourth spring (35) is fixedly connected to the outer wall of one side of the second sliding block (33), and one end of the fourth spring (35) is fixedly connected to the inner wall of one side of the second sliding groove (52).
3. The autonomous landing system of an offshore unmanned aerial vehicle of claim 1, wherein: the top end of the base (5) is provided with a limiting table (11), and the limiting table (11) is fixedly connected to the inner wall of one side of the accommodating box (1).
4. The autonomous landing system of an offshore unmanned aerial vehicle of claim 1, wherein: the bottom of the landing platform (6) is provided with a guide ring (36), and a telescopic rod (37) is fixedly connected to the inner wall of one side of the guide ring (36).
5. The autonomous landing system of an offshore unmanned aerial vehicle of claim 1, wherein: the utility model discloses a fixed ring of first lead screw, including first lead screw (21), second lead screw (22), first lead screw (24), second lead screw (24), first solid fixed ring (241) of fixedly connected with on the top outer wall of third lead screw (23), fifth spout (67) have been seted up on the top outer wall of landing platform (6), and first solid fixed ring (231) sliding connection is on the inner wall of one side of fifth spout (67), threaded connection has fourth slider (24) on the outer wall of one side of second lead screw (22), fixed ring (241) of fixedly connected with on the top outer wall of fourth slider (24), and fixed ring (241) sliding connection of second is on the inner wall of one side of fifth spout (67).
6. The autonomous landing system of an offshore unmanned aerial vehicle of claim 1, wherein: handles (7) are symmetrically arranged on two sides of the landing platform (6), and the handles (7) are fixedly connected to the outer wall of the top end of the base (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110911877.6A CN113460318B (en) | 2021-08-09 | 2021-08-09 | Autonomous landing system of offshore unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
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| US10914551B2 (en) * | 2017-12-15 | 2021-02-09 | Raytheon Company | Vehicle device separation system with telescoping piston springs |
| CN110001988A (en) * | 2019-04-03 | 2019-07-12 | 南京利剑无人机科技有限公司 | A kind of vehicle-mounted multi-rotor unmanned aerial vehicle landing platform |
| CN210162270U (en) * | 2019-04-25 | 2020-03-20 | 边疆 | Unmanned aerial vehicle's descending platform |
| CN210439750U (en) * | 2019-07-31 | 2020-05-01 | 成都翼比特自动化设备有限公司 | Unmanned aerial vehicle hangar system for transformer substation autonomous patrol |
| CN213800161U (en) * | 2020-12-01 | 2021-07-27 | 中国人民武装警察部队警官学院 | Unmanned aerial vehicle base with shock-absorbing function |
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