CN117902082B - Unmanned aerial vehicle is used in survey and drawing with descending shock-absorbing function - Google Patents
Unmanned aerial vehicle is used in survey and drawing with descending shock-absorbing function Download PDFInfo
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- CN117902082B CN117902082B CN202410309248.XA CN202410309248A CN117902082B CN 117902082 B CN117902082 B CN 117902082B CN 202410309248 A CN202410309248 A CN 202410309248A CN 117902082 B CN117902082 B CN 117902082B
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- 238000013507 mapping Methods 0.000 claims abstract description 15
- 238000013016 damping Methods 0.000 claims abstract description 10
- 238000001125 extrusion Methods 0.000 claims description 41
- 230000008878 coupling Effects 0.000 claims description 18
- 238000010168 coupling process Methods 0.000 claims description 18
- 238000005859 coupling reaction Methods 0.000 claims description 18
- 238000005192 partition Methods 0.000 claims description 14
- 230000005611 electricity Effects 0.000 claims description 7
- 238000004080 punching Methods 0.000 claims description 5
- 238000010030 laminating Methods 0.000 claims description 3
- 235000017166 Bambusa arundinacea Nutrition 0.000 claims 1
- 235000017491 Bambusa tulda Nutrition 0.000 claims 1
- 241001330002 Bambuseae Species 0.000 claims 1
- 235000015334 Phyllostachys viridis Nutrition 0.000 claims 1
- 239000011425 bamboo Substances 0.000 claims 1
- 239000004575 stone Substances 0.000 description 9
- 230000003139 buffering effect Effects 0.000 description 5
- 238000000926 separation method Methods 0.000 description 4
- 238000012876 topography Methods 0.000 description 4
- 238000003491 array Methods 0.000 description 2
- 238000004891 communication Methods 0.000 description 2
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- 238000007906 compression Methods 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000006978 adaptation Effects 0.000 description 1
- 230000001174 ascending effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
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Abstract
The invention relates to the technical field of unmanned aerial vehicle surveying and mapping, in particular to an unmanned aerial vehicle with a landing damping function for surveying and mapping. The novel rotary wing comprises a main body, wherein a wing frame is arranged on the main body, a rotor wing is fixedly connected to the wing frame, a surveying instrument is fixedly connected to the lower side face of the main body, a fixed shaft is fixedly connected to the lower side face of the main body, sliding cylinders are connected to the fixed shaft in a sliding mode, a pressure sensor is arranged at the bottom of each sliding cylinder, a supporting shaft is connected to the spline of each sliding cylinder, and a locking assembly is arranged on the main body. According to the invention, the eight support shafts are adapted to the gradient of the ground, so that the eight sliding cylinders form a horizontal landing platform, the unmanned aerial vehicle is ensured to land horizontally, and the unmanned aerial vehicle is prevented from being directly and vertically landed on the slope, so that the bottom of the unmanned aerial vehicle cannot be simultaneously contacted with the ground, and the unmanned aerial vehicle is enabled to roll along the ground by inertia, so that the unmanned aerial vehicle is damaged.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicle surveying and mapping, in particular to an unmanned aerial vehicle with a landing damping function for surveying and mapping.
Background
Survey and drawing unmanned aerial vehicle utilizes unmanned aerial vehicle's convenience to regard global navigation satellite positioning system as technical core, through selecting the existing characteristic point in ground and boundary line, rethread measuring means obtains the figure and the positional information of reflection ground current situation, realize going on to the survey and drawing of topography, and unmanned aerial vehicle takes photo by plane mostly in complicated topography, like mountain area and forest zone, when surveying and drawing in complicated mountain area topography, the relief of mountain area topography is high and mostly is the hillside, when unmanned aerial vehicle accomplishes the survey and lands, unmanned aerial vehicle descends the position mostly and has slope or rugged ground, lead to one side of unmanned aerial vehicle to contact with ground at first, cause unmanned aerial vehicle to receive the holding power distribution inequality when descending, lead to unmanned aerial vehicle to very easily roll along the ground after the landing, cause unmanned aerial vehicle to damage.
Disclosure of Invention
In order to overcome the defects in the background art, the invention provides an unmanned aerial vehicle with a landing damping function for surveying and mapping.
The technical scheme of the invention is as follows: the utility model provides an unmanned aerial vehicle is used in survey and drawing with descending shock-absorbing function, includes the main part, be provided with control terminal in the main part, the outside of main part is provided with annular array's wing frame, annular array the wing frame is kept away from the one end of main part all the rigid coupling has the rotor of being connected with the control terminal electricity, the downside rigid coupling of main part has the surveying instrument of being connected with the control terminal electricity, the downside rigid coupling of main part has annular array's fixed axle, annular array the equal sliding connection of fixed axle has a sliding cylinder, fixed axle and adjacent be provided with first elastic element between the sliding cylinder, the bottom of sliding cylinder is provided with the pressure sensor who is connected with the control terminal electricity, sliding cylinder spline connection has the back shaft, the back shaft is adjacent with pressure sensor contact cooperation, sliding cylinder and adjacent be provided with second elastic element between the back shaft, second elastic element's coefficient of elasticity is less than first elastic element's elastic element, the main part is provided with and is used for locking annular array the locking subassembly of back shaft.
Further, the support shaft is inclined outwardly along a central axis adjacent the sliding cylinder.
Further, the locking assembly comprises an electric push rod electrically connected with the control terminal, the electric push rod is fixedly connected with the main body, a trigger ring is fixedly connected with the telescopic end of the electric push rod, the trigger ring is provided with a notch positioned at the position of the mapping instrument, the trigger ring is fixedly connected with a pushing shaft of an annular array, the pushing shaft of the annular array is all in sliding connection with the adjacent sliding cylinder, the pushing shaft of the annular array is positioned in the adjacent sliding cylinder, the sliding cylinders of the annular array are all in sliding connection with extrusion strips distributed in a mirror image mode, the extrusion strips distributed in the mirror image mode are all in locking fit with the adjacent supporting shaft, the pushing shafts of the annular array are all fixedly connected with extrusion blocks positioned in the adjacent linear arrays in the sliding cylinders, and the extrusion blocks of the linear arrays and the extrusion strips distributed in the mirror image mode are in the same sliding cylinders in extrusion fit.
Further stated, the extrusion block is provided with inclined surfaces distributed in mirror image, and the extrusion strip is provided with inclined surfaces matched with the extrusion block.
Further, one end, far away from the adjacent sliding cylinder, of the supporting shaft of the annular array is slidably connected with a mirror-distributed dislocation block, a third elastic element is arranged between the dislocation block and the adjacent supporting shaft, the dislocation block is conical, and one end, with a large diameter, of the dislocation block is close to the adjacent supporting shaft.
Further, the annular array is fixedly connected with a buffer cylinder, the buffer cylinder is in sliding connection with the adjacent fixed shaft, a recoil cylinder is fixedly connected to the lower side face of the surveying instrument, a reverse punching hole is formed in the bottom of the recoil cylinder, and flexible pipes are fixedly connected and communicated between the bottom of the buffer cylinder and the recoil cylinder of the annular array.
Further, the bottom rigid coupling of fixed axle has and is located adjacently the sliding shaft in the buffer tube, annular array the sliding shaft all is provided with the spout, annular array the bottom is all rotated in the buffer tube and is connected with the swivel, the swivel with be adjacent the laminating of the inner wall of buffer tube, the last side rigid coupling of swivel has annular array's partition block, the inner wall rigid coupling of swivel has the fixture block, the fixture block with be adjacent on the sliding shaft the spout sliding fit.
Further, the separation block is isosceles triangle-like, and the separation block is attached to the inner wall of the buffer tube adjacent to the buffer tube, and the bottom edge of the separation block is attached to the upper plane of the swivel.
Further, a servo motor electrically connected with the control terminal is fixedly connected to the upper side face of the main body, the wing frames of the annular array are hinged to the main body, cables are fixedly connected between the wing frames of the annular array and output shafts of the servo motor, and fourth elastic elements distributed in a mirror image mode are arranged between the wing frames of the annular array and the main body.
Further, the outer side of the main body is fixedly connected with annular array buffer air bags, the annular array buffer air bags are electrically connected with the control terminal, and the annular array buffer air bags and the annular array wing frames are distributed alternately.
The beneficial effects of the invention are as follows: 1. the slope on eight back shafts adaptation ground makes eight slide cylinders build a horizontally and falls the platform, ensures that unmanned aerial vehicle is the horizontal landing, avoids unmanned aerial vehicle direct vertical landing in the slope, leads to unmanned aerial vehicle bottom unable simultaneously with ground contact, causes unmanned aerial vehicle to receive inertia along the ground roll, causes unmanned aerial vehicle to damage.
2. Two dislocation blocks distributed through the mirror image extrude the stone, make dislocation block and stone dislocation, avoid the back shaft to be located on the stone, lead to the unable steady support in ground to fall behind unmanned aerial vehicle, cause unmanned aerial vehicle to appear empting.
3. The gas in eight buffer cylinders through the annular array carries out preliminary buffering to the unmanned aerial vehicle, then makes gas along the recoil hole of below discharge downwards, and gas along the recoil hole discharge downwards apply ascending thrust to the unmanned aerial vehicle and further cushion the unmanned aerial vehicle.
4. The partition blocks of the annular array are rotated to periodically increase and reduce the gas flow in the flexible pipe to form damping force, so that the falling speed of the unmanned aerial vehicle is reduced, the falling speed of the unmanned aerial vehicle is prevented from being too high, the falling acting force of the unmanned aerial vehicle cannot be effectively counteracted by gas in the buffer cylinder, the unmanned aerial vehicle is caused to be in hard contact with eight sliding cylinders of the annular array, and the internal parts of the unmanned aerial vehicle are damaged.
5. Through the top with four wing frames upset to the main part of annular array, fold unmanned aerial vehicle, reduce unmanned aerial vehicle's space coverage, then through annular array's four buffer air bags buffering and the impact force on ground, avoid unmanned aerial vehicle directly to drop to ground, lead to unmanned aerial vehicle to receive the impact force to appear damaging.
Drawings
FIG. 1 is a schematic perspective view of the present invention;
FIG. 2 is a schematic perspective view of a stationary shaft and a sliding cylinder according to the present invention;
FIG. 3 is a schematic cross-sectional view of a slide cartridge according to the present invention;
FIG. 4 is a schematic perspective view of the extrusion strip and extrusion block of the present invention;
FIG. 5 is a schematic perspective view of a dislocation block according to the present invention;
FIG. 6 is a schematic perspective view of a surge drum and recoil drum of the present invention;
FIG. 7 is a schematic cross-sectional view of a perspective structure of a damper cylinder according to the present invention;
FIG. 8 is a schematic perspective view of a swivel and a partition block of the present invention;
FIG. 9 is a schematic perspective view of a servo motor and cable of the present invention;
fig. 10 is a schematic perspective view of a cushion airbag according to the present invention.
In the above figures: 101: body, 102: wing frame, 103: rotor, 104: surveying instrument, 105: fixed shaft, 106: slide cylinder, 107: first elastic element, 108: pressure sensor, 109: support shaft, 110: second elastic element, 201: electric putter, 202: trigger ring, 203: pushing shaft, 204: extrusion strip, 205: extrusion block, 301: bit block, 302: third elastic element, 401: buffer tube, 402: recoil tube, 403: reverse punching, 404: flexible tube, 405: sliding shaft, 406: chute, 407: swivel, 408: separation block, 409: fixture block, 501: servo motor, 502: cable, 503: fourth elastic element, 504: and a buffer air bag.
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 apparent that the described embodiment is only one of the preferred embodiments of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that may be conceived by those skilled in the art without making any inventive effort within the scope of the present invention should be covered.
Example 1: 1-3, including main part 101, be provided with control terminal in the main part 101, control terminal and remote control terminal signal connection, the outside of main part 101 is provided with four wing frames 102 of annular array, the rotor 103 that is all rigid coupling with control terminal is kept away from to four wing frames 102 of annular array, the lower part rigid coupling of main part 101 front side has the surveying instrument 104 that is connected with control terminal electricity, the surveying instrument 104 is used for shooting geographic elements and catching ground characteristic point, the bottom rigid coupling of main part 101 has eight fixed axles 105 of annular array, the shooting head of surveying instrument 104 is located between two adjacent fixed axles 105, avoid fixed axle 105 to shelter from the survey viewing angle of surveying instrument 104, all sliding connection has slide cylinders 106 in annular array, all be provided with first elastic element 107 between eight fixed axles 105 of annular array and the adjacent slide cylinders 106, first elastic element 107 is the spring, and initial state is compressed state, make eight slide cylinders 106 of annular array be located adjacent fixed axle 105's bottom during the aircraft flight, eight slide cylinders 106 are located adjacent fixed axle 108, annular array's bottom 108 are located adjacent to annular array's axial support 109, all be provided with annular array's axial support 109 and are located adjacent annular array's axial support 109, the mutual annular array 109 is located along the axial support 109 is adjacent to annular array's axial support 109, the mutual support 109 is connected with annular array's axial support 109, the mutual support is located between annular array's the adjacent axial support 109, the axial support 109 is more than adjacent axial support 109 is connected with annular array's axial support, the annular array ' is connected with annular array's 109, the second elastic element 110 is the spring, initial state is compressed state, ensure that eight back shafts 109 of annular array are located the bottom of adjacent slide tube 106, avoid unmanned aerial vehicle to receive inertia during the flight along the upper and lower slip of adjacent slide tube 106, the elasticity coefficient of second elastic element 110 is less than the elasticity coefficient of first elastic element 107, ensure that second elastic element 110 compresses at first, main part 101 is provided with the locking subassembly that is used for locking eight back shafts 109 of annular array, when making unmanned aerial vehicle whereabouts, adapt to the slope on ground through eight back shafts 109 of annular array, make eight slide tube 106 of annular array construct a horizontal landing platform, ensure that unmanned aerial vehicle falls to be horizontal landing, avoid unmanned aerial vehicle direct perpendicular to slope, lead to unmanned aerial vehicle bottom unable contact with the ground simultaneously, cause unmanned aerial vehicle to receive inertia along the ground to roll, cause unmanned aerial vehicle damage.
As shown in fig. 3 and fig. 4, the locking assembly comprises an electric push rod 201 electrically connected with the control terminal, the electric push rod 201 is fixedly connected to the rear side of the main body 101, a trigger ring 202 is fixedly connected to the telescopic end of the electric push rod 201, the trigger ring 202 is provided with a notch, the notch is located at the position of the mapping instrument 104, the lower side surface of the trigger ring 202 is fixedly connected with eight push shafts 203 of the annular array, the electric push rod 201 synchronously drives the eight push shafts 203 of the annular array to move upwards through the trigger ring 202, the eight push shafts 203 of the annular array are all in sliding connection with the adjacent sliding cylinders 106, the eight push shafts 203 of the annular array are located in the adjacent sliding cylinders 106, two extrusion strips 204 distributed in a mirror image are all in sliding connection, the two extrusion strips 204 distributed in a mirror image are all in locking fit with the adjacent supporting shafts 109, the five extrusion blocks 205 of the annular array are fixedly connected to the five extrusion blocks 205 located in the adjacent sliding cylinders 106, the five extrusion blocks 205 of the upper linear array are synchronously moved upwards, the extrusion blocks 205 of the annular array are provided with two extrusion blocks 205 distributed in a vertical direction, and the two extrusion blocks 204 are distributed in a mirror image form in the same direction, and the two extrusion blocks are distributed in the same plane, and the two extrusion blocks are distributed in the adjacent extrusion blocks are distributed in a mirror image form, and are matched with the two extrusion blocks and are distributed in the adjacent extrusion blocks, and two extrusion blocks 204 are distributed in a sliding blocks, and are closely, and two extrusion blocks are distributed in a sliding blocks, and are distributed in a compression cylinder and are in a and has a compression cylinder.
As shown in fig. 5, two dislocating blocks 301 distributed in a mirror image are slidably connected to the lower end of the support shaft 109 of the annular array, the dislocating blocks 301 are conical, one end with a large diameter of the dislocating blocks 301 is close to the adjacent support shaft 109, a third elastic element 302 is arranged between the two dislocating blocks 301 distributed in a mirror image and the adjacent support shaft 109, the third elastic element 302 is a tension spring and is used for driving the adjacent dislocating blocks 301 to reset, stones are extruded by the two dislocating blocks 301 distributed in a mirror image, the dislocating blocks 301 and the stones are dislocated, the support shaft 109 is prevented from being located on the stones, the unmanned aerial vehicle which falls down cannot be stably supported on the ground, and the unmanned aerial vehicle is caused to topple.
When need utilize unmanned aerial vehicle to survey and draw, the staff places this device in ground, then opens annular array's four rotors 103 and surveying instrument 104 through control terminal, and annular array's four rotors 103 rotate and drive main part 101 and rise off gradually to drive it and survey and draw the appearance 104 in the air, after the survey and draw, the staff controls annular array's four rotors 103 and slows down rotation speed, makes unmanned aerial vehicle downstream descend.
When the landing position of the unmanned aerial vehicle is a slope or uneven ground, the unmanned aerial vehicle drops to drive eight support shafts 109 of the annular array below the unmanned aerial vehicle to synchronously drop, the ground is assumed to be a slope, the support shafts 109 positioned at the high position of the slope of the eight support shafts 109 of the annular array are firstly contacted with the ground, then the unmanned aerial vehicle continues to move downwards, the support shafts 109 contacted with the ground are upwards slid along the adjacent sliding cylinders 106 under the action of the ground, the support shafts 109 are separated from the pressure sensors 108, meanwhile, the second elastic element 110 is compressed, the rest support shafts 109 are gradually contacted with the ground until the eight support shafts 109 of the annular array are contacted with the ground and continue to enable the unmanned aerial vehicle to move downwards, the eight support shafts 109 of the annular array are upwards slid along the adjacent sliding cylinders 106, namely the eight support shafts 109 of the annular array are separated from the adjacent pressure sensors 108, and at the moment, the eight pressure sensors 108 of the annular array detect that the pressure is lost, and then signals are sent to the control terminal.
After receiving the signal, the control terminal starts the electric push rod 201, the telescopic end of the electric push rod 201 drives the trigger ring 202 to move upwards, the trigger ring 202 moves upwards to drive the eight pushing shafts 203 of the annular array to move upwards synchronously, the pushing shafts 203 move upwards to drive the five extrusion blocks 205 of the upper linear array to move upwards synchronously, the five extrusion blocks 205 of the linear array move upwards to extrude two extrusion strips 204 distributed in adjacent mirror images, the two extrusion strips 204 distributed in mirror images slide outwards along the adjacent sliding cylinders 106 by extrusion force to tightly support the adjacent supporting shafts 109, and the eight sliding cylinders 106 of the annular array are locked and fixed with the adjacent supporting shafts 109.
After eight slide drums 106 of the annular array are locked and fixed with the adjacent support shafts 109, the unmanned aerial vehicle continues to move downwards and drives eight fixed shafts 105 of the annular array to move downwards synchronously, at the moment, the eight slide drums 106 of the annular array are locked with the adjacent support shafts 109, the eight fixed shafts 105 of the annular array move downwards to slide downwards along the adjacent slide drums 106, meanwhile, eight first elastic elements 107 of the annular array compress and slow down the falling speed of the unmanned aerial vehicle until the unmanned aerial vehicle falls safely, the eight support shafts 109 of the annular array adapt to the gradient of the ground and lock with the adjacent slide drums 106, so that the eight slide drums 106 of the annular array construct a horizontal falling platform to ensure the falling safety of the unmanned aerial vehicle, the unmanned aerial vehicle is prevented from falling perpendicularly to a slope, the bottom of the unmanned aerial vehicle cannot be contacted with the ground at the same time, the unmanned aerial vehicle is caused to roll due to inertia, and damage is caused to the unmanned aerial vehicle.
When eight back shaft 109 downward movement, back shaft 109 drives two dislocation pieces 301 synchronous downward movement on it, appear Dan Zishi with ground contact position when two dislocation pieces 301, the stone extrudees two dislocation pieces 301 this moment, make two dislocation pieces 301 slide along adjacent back shaft 109, simultaneously two adjacent third elastic element 302 are stretched, make two dislocation pieces 301 that mirror image distributes misplace with the stone on ground, avoid back shaft 109 to be located on the stone, lead to the unable steady support in ground to descend the unmanned aerial vehicle behind, cause unmanned aerial vehicle to appear empting.
Example 2: on the basis of the embodiment 1, as shown in fig. 6-8, the lower sides of eight sliding drums 106 of the annular array are fixedly connected with buffer drums 401, the buffer drums 401 are in sliding connection with adjacent fixed shafts 105, the lower sides of the mapping instrument 104 are fixedly connected with recoil drums 402, the bottoms of the recoil drums 402 are provided with reverse punching holes 403, the lower parts of the recoil drums 402 are in reverse conical shapes and are used for converging air flow to form stronger gas impact force, the bottoms of the eight buffer drums 401 of the annular array are fixedly connected with the recoil drums 402 and are communicated with flexible pipes 404, the flexible pipes 404 leave enough margin for adapting to the position change of the recoil drums 402 and the eight buffer drums 401, the gas in the eight buffer drums 401 of the annular array is used for carrying out preliminary buffering on the unmanned aerial vehicle, then the gas is downwards discharged along the recoil holes 403 below, the gas downwards discharges along the recoil holes 403 to apply upward thrust to the unmanned aerial vehicle to further buffer the unmanned aerial vehicle, the bottoms of the eight fixed shafts 105 of the annular array are fixedly connected with sliding shafts 405 positioned in the adjacent buffer cylinders 401, the fixed shafts 105 drive the adjacent sliding shafts 405 to move downwards, sliding grooves 406 are formed in the side walls of the eight sliding shafts 405 of the annular array, rubber pads used for being jointed with the sliding grooves 406 are arranged on the lower sides of the eight buffer cylinders 401 of the annular array, gas in the buffer cylinders 401 enters the recoil cylinders 402 along the adjacent flexible pipes 404, rotating rings 407 are rotationally connected to the bottoms of the eight buffer cylinders 401 of the annular array, the rotating rings 407 are jointed with the inner walls of the adjacent buffer cylinders 401, partition blocks 408 of the annular array are fixedly connected to the upper planes of the rotating rings 407, the partition blocks 408 are isosceles-like triangles, the partition blocks 408 are jointed with the inner walls of the adjacent buffer cylinders 401, the bottom edges of the partition blocks 408 are jointed with the upper planes of the rotating rings 407, clamping blocks 409 are fixedly connected to the inner walls of the rotating rings 407 of the annular array, the fixture blocks 409 are in sliding fit with the sliding grooves 406 on the adjacent sliding shafts 405, the sliding shafts 405 move downwards to drive the upper sliding grooves 406 to push the adjacent fixture blocks 409, the swivel 407 drives the partition blocks 408 of the annular array on the swivel to rotate synchronously, the gas flow in the flexible pipe 404 is periodically increased and reduced to form damping force through the rotation of the partition blocks 408 of the annular array, the falling speed of the unmanned aerial vehicle is reduced, the falling speed of the unmanned aerial vehicle is prevented from being too high, the falling speed of the unmanned aerial vehicle cannot be effectively reduced due to the gas in the buffer cylinder 401, hard acting force is generated between the unmanned aerial vehicle and the ground, and the internal parts of the unmanned aerial vehicle are damaged.
When the unmanned aerial vehicle drives eight fixed axles 105 to slide downwards, eight fixed axles 105 slide downwards along adjacent buffer barrels 401 synchronously, the gas inside the buffer barrels is pushed, then the gas in the buffer barrels 401 enters the recoil barrels 402 along adjacent flexible pipes 404, the gas entering the recoil barrels 402 is discharged downwards through the reverse punching holes 403 below, the gas is discharged downwards along the recoil holes 403 to apply upward thrust to the unmanned aerial vehicle to further buffer the unmanned aerial vehicle, the gas in the eight buffer barrels 401 is extruded to perform preliminary buffering to the unmanned aerial vehicle, and then the gas is discharged downwards along the recoil holes 403 to form reverse thrust to the unmanned aerial vehicle to further buffer the falling speed of the unmanned aerial vehicle.
In the process that the fixed shaft 105 slides downwards, the fixed shaft 105 drives the sliding shaft 405 to slide downwards, the sliding shaft 405 drives the upper sliding groove 406 to move downwards, the sliding groove 406 moves downwards to push the clamping block 409 to drive the swivel 407 to rotate, the swivel 407 drives the partition block 408 on the swivel to synchronously rotate, and the gas in the buffer cylinder 401 cannot effectively counteract the falling acting force of the unmanned aerial vehicle, so that the unmanned aerial vehicle is in hard contact with the eight sliding cylinders 106 of the annular array, and the internal parts of the unmanned aerial vehicle are damaged.
Example 3: on the basis of embodiment 2, as shown in fig. 9 and 10, a servo motor 501 electrically connected with a control terminal is fixedly connected on the upper plane of the main body 101, four wing frames 102 of the main body 101 and the annular array are hinged, cables 502 are fixedly connected between the four wing frames 102 of the annular array and the output shaft of the servo motor 501, the output shaft of the servo motor 501 rotates and winds the four cables 502 of the annular array, the four cables 502 of the annular array pull the adjacent wing frames 102 to turn upwards to fold the unmanned aerial vehicle, the space coverage rate of the unmanned aerial vehicle is reduced, two fourth elastic elements 503 distributed in a mirror image manner are arranged between the four wing frames 102 of the annular array and the main body 101, the fourth elastic elements 503 are torsion springs for driving the adjacent wing frames 102 to reset, four buffer air bags 504 of the annular array are fixedly connected on the outer side of the main body 101 (the principle of the air bags on the automobile is the same, but be inertial block receives inertial communication circuit to open the air bag on the car, this is the switch direct communication circuit and opens the air bag), four buffer air bags 504 of annular array all are connected with the control terminal electricity, four buffer air bags 504 of annular array and four wing frame 102 of annular array distribute in turn, four buffer air bags 504 of annular array are the arc after the inflation, and laminate each other to be annular, and buffer air bag 504 middle part thickness is less than both sides, avoid two buffer air bags 504's junction impact force to appear separating, cause the damage to inside wing frame 102, laminate the parcel with unmanned aerial vehicle to inside through four buffer air bags 504 of annular array, buffer the impact force with ground through four buffer air bags 504 of annular array, avoid unmanned aerial vehicle direct drop to ground, lead to unmanned aerial vehicle to receive the impact force to appear damaging.
When unmanned aerial vehicle survey and drawing work in winter, the low temperature makes unmanned aerial vehicle's internal battery's electric quantity reduce, perhaps make unmanned aerial vehicle electric quantity insufficient during survey and drawing, be difficult to support unmanned aerial vehicle safety drop, before the electric quantity is exhausted, servo motor 501 is opened to the staff, servo motor 501's output shaft rotates four hawsers 502 of rolling, four hawsers 502 pulling adjacent wing frame 102 is upwards overturned along main part 101, simultaneously fourth elastic element 503 takes place to twist reverse, so until four wings 102 upset to main part 101's top with annular array, fold unmanned aerial vehicle, reduce unmanned aerial vehicle's space coverage, then open four buffer air bags 504, four buffer air bags 504 rapid expansion and laminating each other are the annular with unmanned aerial vehicle parcel to inside, then unmanned aerial vehicle falls by the sky downwards, until falling to ground, annular array's four buffer air bags 504 buffering and the impact force on ground this moment, avoid unmanned aerial vehicle directly to drop to ground, lead to unmanned aerial vehicle receives the impact force to appear damaging.
The foregoing has shown and described the basic principles, principal features and advantages of the invention. It will be understood by those skilled in the art that the present invention is not limited to the foregoing embodiments, which have been described in the foregoing description as preferred embodiments of the invention, but rather that various changes and modifications may be made therein without departing from the spirit and scope of the invention as defined by the appended claims and their equivalents.
Claims (6)
1. Unmanned aerial vehicle is used in survey and drawing with descending shock-absorbing function, characterized by: the hydraulic lock comprises a main body (101), a control terminal is arranged in the main body (101), an annular array of wing frames (102) are arranged on the outer side of the main body (101), one ends, far away from the main body (101), of the annular array of wing frames (102) are fixedly connected with rotary wings (103) electrically connected with the control terminal, mapping instruments (104) electrically connected with the control terminal are fixedly connected to the lower side surface of the main body (101), annular array of fixed shafts (105) are fixedly connected to the lower side surface of the main body (101), sliding cylinders (106) are slidably connected to the annular array of fixed shafts (105), first elastic elements (107) are arranged between the fixed shafts (105) and the adjacent sliding cylinders (106), pressure sensors (108) electrically connected with the control terminal are arranged at the bottoms of the sliding cylinders (106), supporting shafts (109) are in spline connection, the supporting shafts (109) are in contact fit with the adjacent pressure sensors (108), second elastic elements (110) are arranged between the sliding cylinders (106) and the adjacent supporting shafts (109), and the second elastic elements (110) are smaller than the elastic elements (110), and the elastic elements (110) are used for locking the annular array (101);
The support shaft (109) is inclined outwards along the central axis of the adjacent sliding cylinder (106);
The locking assembly comprises an electric push rod (201) electrically connected with a control terminal, the electric push rod (201) is fixedly connected with the main body (101), a trigger ring (202) is fixedly connected to the telescopic end of the electric push rod (201), the trigger ring (202) is provided with a notch positioned at the position of the mapping instrument (104), the trigger ring (202) is fixedly connected with an annular array push shaft (203), the annular array push shaft (203) is in sliding connection with the adjacent sliding cylinder (106), the annular array push shaft (203) is positioned in the adjacent sliding cylinder (106), the annular array sliding cylinder (106) is in sliding connection with a mirror-image-distributed extrusion strip (204), the mirror-image-distributed extrusion strips (204) are in locking fit with the adjacent supporting shaft (109), the annular array push shaft (203) is fixedly connected with a linear array extrusion block (205) positioned in the adjacent sliding cylinder (106), and the linear array extrusion blocks (205) and the mirror-image-distributed extrusion strips (204) are in matching;
the extrusion block (205) is provided with inclined surfaces distributed in a mirror image mode, and the extrusion strip (204) is provided with inclined surfaces matched with the extrusion block (205);
The annular array the back shaft (109) keep away from adjacent one end that slides section of thick bamboo (106) all sliding connection has dislocation piece (301) of mirror image distribution, dislocation piece (301) with be provided with between adjacent back shaft (109) third elastic element (302), dislocation piece (301) are conical, just the big one end of dislocation piece (301) diameter is close to adjacent back shaft (109).
2. The unmanned aerial vehicle for surveying and mapping with landing damping function according to claim 1, wherein: the annular array all rigid coupling has a buffer tube (401) in slide tube (106), buffer tube (401) with adjacent fixed axle (105) sliding connection, the downside rigid coupling of surveying instrument (104) has recoil tube (402), the bottom of recoil tube (402) is provided with counter-punching hole (403), annular array buffer tube (401) bottom with all rigid coupling and intercommunication have flexible pipe (404) between recoil tube (402).
3. The unmanned aerial vehicle for surveying and mapping with landing damping function according to claim 2, wherein: the bottom rigid coupling of fixed axle (105) has and is located adjacently sliding shaft (405) in buffer tube (401), annular array sliding shaft (405) all are provided with spout (406), annular array bottom all rotates in buffer tube (401) and is connected with swivel (407), swivel (407) with be adjacent inner wall laminating of buffer tube (401), the upper side rigid coupling of swivel (407) has annular array's partition block (408), the inner wall rigid coupling of swivel (407) has fixture block (409), fixture block (409) with be adjacent on sliding shaft (405) spout (406) sliding fit.
4. A surveying and mapping unmanned aerial vehicle with a landing damping function according to claim 3, characterized in that: the partition block (408) is isosceles triangle-like, the partition block (408) is attached to the inner wall of the buffer cylinder (401) adjacent to the buffer cylinder, and the bottom edge of the partition block (408) is attached to the upper plane of the swivel (407).
5. The unmanned aerial vehicle for surveying and mapping with landing damping function according to claim 1, wherein: the upper side of main part (101) rigid coupling has servo motor (501) with control terminal electricity is connected, annular array wing frame (102) all with main part (101) are articulated, annular array wing frame (102) with all rigid coupling has hawser (502) between the output shaft of servo motor (501), annular array wing frame (102) with all be provided with fourth elastic element (503) of mirror image distribution between main part (101).
6. The unmanned aerial vehicle with landing damping function for surveying and mapping according to claim 5, wherein: the outside rigid coupling of main part (101) has annular array's buffer gasbag (504), annular array buffer gasbag (504) all are connected with control terminal electricity, annular array buffer gasbag (504) with annular array wing frame (102) are distributed in turn.
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| CN117902082A (en) | 2024-04-19 |
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