Unmanned aerial vehicle for topographic surveying and mapping

Abstract

The invention relates to an unmanned aerial vehicle for topographic surveying and mapping, and relates to the field of unmanned aerial vehicles, the unmanned aerial vehicle comprises a flight main body, a flight mechanism, a stabilizing mechanism and a shooting mechanism, the flight mechanism is arranged on the flight main body and used for flight, the stabilizing mechanism is arranged on the flight main body, and the shooting mechanism is arranged on the stabilizing mechanism. The stabilizing mechanism drives the shooting mechanism to rotate. The method has the effect that the terrain surveying and mapping quality of the unmanned aerial vehicle is better.

Description

Technical Field

[0001] The present application relates to the field of unmanned aerial vehicles, and in particular to an unmanned aerial vehicle for terrain surveying and mapping. Background Art

[0002] Topographic surveying refers to the work of mapping topographic maps, that is, measuring the projection position and elevation of the objects and terrain on the earth's surface on the horizontal plane, reducing them at a certain ratio, and drawing them into topographic maps with symbols and annotations. The mapping of topographic maps basically adopts aerial photogrammetry methods, and uses aerial photographs to mainly map indoors. With the continuous development of science and technology, advanced digital aerial photogrammetry technology has been widely used in the mapping and geographic information industry, and my country's topographic surveying and mapping industry has also made great progress in the field of drones.

[0003] According to Chinese patent authorization number CN 111792032 A, a multi-angle detection mechanism, a buffer soft landing mechanism, a protective mechanism, a mounting frame and a carrying platform are disclosed; the top edge of the UAV body is provided with four rotating arms distributed in a matrix, and the top of each rotating arm is provided with a propeller, and the protective mechanism includes a driving assembly and four propeller protection assemblies arranged on the top of the carrying platform, and each propeller protection assembly includes a protective cover, a buffer assembly, a mounting seat and a connecting plate.

[0004] With regard to the above-mentioned related technologies, when a drone conducts terrain mapping, it needs to continuously fly forward, backward or sideways. At this time, the multi-angle detection mechanism pitches or tilts along with the drone body, which may easily cause the image taken by the multi-angle detection mechanism to shake, and may easily cause deviations in the mapped terrain. Summary of the invention

[0005] In order to improve the quality of terrain mapping by drones, the present application provides a drone for terrain mapping.

[0006] The present application provides a UAV for terrain surveying and mapping that adopts the following technical solution: A drone for terrain surveying and mapping comprises a flying body, a flying mechanism, a stabilizing mechanism and a shooting mechanism. The flying mechanism is arranged on the flying body and used for flying, the stabilizing mechanism is arranged on the flying body, and the shooting mechanism is arranged on the stabilizing mechanism. When the flying body pitches or tilts, the stabilizing mechanism drives the shooting mechanism to rotate.

[0007] By adopting the above technical solution, when the flying body needs to fly, the flying mechanism drives the flying body to fly; when the flying mechanism drives the flying body to fly forward, backward or sideways, the stabilizing mechanism drives the shooting mechanism to rotate relatively around the flying body, thereby resisting the pitch or tilt of the flying body, so that the shooting position of the shooting mechanism always remains unchanged, thereby improving the quality of terrain mapping by the UAV and improving the situation that the UAV needs to continuously fly forward, backward or sideways when conducting terrain mapping. At this time, the shooting mechanism pitches or tilts together with the UAV body, which can easily cause the picture taken by the shooting mechanism to shake, and easily cause the surveyed terrain to deviate.

[0008] Optionally, the stabilization mechanism also includes a stabilization cover, two stabilization rods and a stabilization ring. The stabilization cover is rotatably arranged on the flying body, and the two stabilization rods are coaxially fixed on the stabilization cover. The axes of the two stabilization rods are perpendicular to the rotation axis of the stabilization cover. The stabilization ring has two stabilization holes that are arranged through the stabilization ring. When the stabilization ring is rotatably arranged on the stabilization cover, the two stabilization rods are respectively passed through and rotatably connected to the two stabilization holes, and the shooting mechanism is arranged on the stabilization ring.

[0009] By adopting the above technical solution, when the flying body pitches up and down, the gravity of the shooting mechanism drives the stabilizing cover to rotate relatively around the flying body, thereby resisting the pitching of the flying body, so that the shooting position of the shooting mechanism remains unchanged; when the flying body rolls, the gravity of the shooting mechanism drives the stabilizing cover to rotate relatively around the flying body, thereby resisting the roll of the flying body, so that the shooting position of the shooting mechanism remains unchanged, making the shooting position of the shooting mechanism more stable, thereby improving the quality of terrain mapping of the UAV.

[0010] Optionally, the stabilization mechanism also includes a locking assembly, which includes a locking ratchet, two locking pawls, two locking torsion springs, a locking motor and a locking block, wherein the locking ratchet is coaxially fixed on the rotating shaft of the stabilization cover, the two locking pawls are rotatably set on the flight body, one end of the two locking torsion springs is fixedly connected to the flight body, and the other ends of the two locking torsion springs are respectively fixedly connected to the two locking pawls, the locking motor is fixedly set on the flight body, and the locking block is fixedly set on the output shaft of the locking motor, and when the two locking pawls are engaged with the locking ratchet, the two locking pawls abut against the locking block.

[0011] By adopting the above technical solution, when the stabilizing cover needs to resist the pitch of the flying body, the locking motor is driven, and the output shaft of the locking motor drives the locking block to rotate, so that the locking block is disengaged from the abutment with the two locking ratchets, so that the two locking torsion springs respectively drive the two locking ratchets to rotate in the direction away from each other, so that the two locking ratchets are disengaged from the engagement with the locking ratchet, so that when the flying body pitches, the stabilizing cover rotates relative to the flying body; when the stabilizing cover does not need to resist the pitch of the flying body, one end of the two locking ratchets abuts against the locking block, and the other ends of the two locking ratchets engage with the locking ratchet, so that the stabilizing cover is fixed to the flying body, so that when the flying body pitches, the stabilizing cover pitches with the flying body, so that the stabilizing mechanism can more easily meet the different shooting requirements of the drone, making it more usable.

[0012] Optionally, the stabilizing mechanism also includes a locking assembly, which includes two locking blocks, two locking springs, a locking motor and an unlocking block. The two locking blocks are slidably fitted in the stabilizing ring, one end of the two locking springs is fixedly connected to the stabilizing ring, and the other ends of the two locking springs are respectively fixedly connected to the two locking blocks. The locking motor is fixedly arranged on the stabilizing ring, and the unlocking block is coaxially fixedly arranged on the output shaft of the locking motor. When the stabilizing ring is fixedly arranged on the stabilizing cover, the two locking blocks are respectively tightly fixed to the two sides of one of the stabilizing rods.

[0013] By adopting the above technical solution, when the stabilizing ring needs to resist the roll of the flying body, the locking motor is driven, and the output shaft of the locking motor drives the unlocking block to rotate. The rotation of the unlocking block drives the two locking blocks to slide in the direction of moving away from each other until the two locking blocks are disengaged from the stabilizing bar and are tightly fixed. Therefore, when the flying body rolls, the stabilizing ring rotates relative to the flying body. When the stabilizing ring does not need to resist the roll of the flying body, the two locking springs respectively push the two locking blocks to slide in the direction of approaching each other until the two locking blocks are tightly fixed to the two sides of one of the stabilizing bars, thereby fixing the stabilizing ring and the stabilizing cover. Therefore, when the flying body rolls, the stabilizing ring rolls with the flying body, thereby making it easier for the stabilizing mechanism to meet different shooting requirements of the drone, making it more usable.

[0014] Optionally, the shooting mechanism includes a rotating motor and a shooting module, the rotating motor is fixedly disposed on a stabilizing ring, one end of the shooting module is rotatably connected to the stabilizing ring, and the other end of the shooting module is fixedly connected to an output shaft of the rotating motor.

[0015] By adopting the above technical solution, when the shooting angle of the shooting module needs to be rotated, the rotating motor is driven, and the output shaft of the rotating motor drives the shooting to rotate relative to the stabilizing ring, thereby completing the adjustment of the shooting angle, thereby making the shooting angle of the drone more diversified and making it more usable.

[0016] Optionally, the shooting mechanism further includes a balancing block, which is rotatably connected to the stabilizing ring, and when the shooting module rotates, the balancing block rotates in the opposite direction.

[0017] By adopting the above technical solution and setting the balancing block, when the shooting module rotates relative to the stabilizing ring, the center of gravity of the shooting mechanism always remains stable and is not prone to deviation, so that the position of the shooting mechanism driven by the stabilizing mechanism always remains stable, making it more usable.

[0018] Optionally, the shooting mechanism also includes a linkage assembly, which includes a main linkage gear and a secondary linkage gear. The main linkage gear is coaxially fixed to the output shaft of the rotating motor, and the secondary linkage gear is fixedly connected to the balance block. The main linkage gear and the secondary linkage gear are meshed.

[0019] By adopting the above technical solution, when the rotating motor rotates, the output shaft of the rotating motor drives the main linkage gear to rotate, the rotation of the main linkage gear drives the secondary linkage gear to rotate, and the rotation of the secondary linkage gear drives the balance block to rotate relative to the stable ring, thereby completing the driving of the balance block and the shooting module in opposite directions, making the driving of the balance block simpler and more convenient, and making it easier to use.

[0020] Optionally, it also includes a landing mechanism, which includes a landing seat, a plurality of landing rods and a landing assembly, the landing seat is fixedly set on the flight body, and each of the landing rods is rotatably set on the landing seat, and the landing assembly includes a plurality of shock absorbers, one end of each of the shock absorbers is fixedly connected to the landing seat, and the other end of each of the shock absorbers is fixedly connected to each landing rod.

[0021] By adopting the above technical solution, when the UAV lands, the flying body drives the landing seat to land, and the landing seat drives the landing rods to land until all the landing rods are in contact with the ground. Each landing rod rotates toward the direction close to the UAV, thereby compressing each shock absorber respectively. Then each shock absorber drives each landing rod to reset respectively, thereby reducing the impact force when the UAV lands, making it more usable.

[0022] Optionally, each of the landing rods includes a first landing part and a second landing part, and each of the first landing parts is slidingly matched with each of the second landing parts. The landing assembly also includes a plurality of landing springs, and one end of each of the landing springs is fixedly connected to each of the first landing parts, and the other end of each of the landing springs is fixedly connected to each of the second landing parts.

[0023] By adopting the above technical solution, when the drone lands, each second landing part slides towards the direction close to each first landing part, thereby compressing each landing spring respectively, and then each landing spring drives each second landing part to reset, thereby further reducing the impact force when the drone lands, making it more usable.

[0024] Optionally, the landing mechanism also includes a fixing assembly, which includes a plurality of fixing blocks and a plurality of fixing springs, each of the fixing blocks is slidably fitted on the flying body, one end of each of the fixing springs is fixedly connected to the flying body, and the other end of each of the fixing springs is respectively fixedly connected to each of the fixing blocks, and the landing seat is provided with a plurality of fixing grooves, and when the landing seat is fixedly connected to the flying body, each of the fixing blocks is respectively penetrated and snap-fitted into each of the fixing grooves.

[0025] By adopting the above technical solution, when the landing seat needs to be fixed on the flight body, each fixing block slides towards the direction close to each fixing groove until each fixing block is respectively penetrated and snap-fitted with each fixing groove, thereby fixing the landing seat to the flight body; when the landing seat needs to be released from the fixed connection with the flight body, the landing seat is moved away from the flight body, thereby pushing each fixing block to slide towards the direction away from each fixing groove until each fixing block is released from the snap-fitting with each fixing groove, thereby releasing the landing seat from the fixation with the flight body, thereby making the disassembly of the landing seat simpler and more convenient, and improving the usability.

[0026] In summary, the present application includes at least one of the following beneficial technical effects: When the flying body needs to fly, the flying mechanism drives the flying body to fly. When the flying mechanism drives the flying body to fly forward, backward or sideways, the stabilizing mechanism drives the shooting mechanism to rotate relatively around the flying body, thereby resisting the pitch or tilt of the flying body, so that the shooting position of the shooting mechanism remains unchanged, thereby improving the quality of terrain mapping by the UAV and improving the situation that the UAV needs to continuously fly forward, backward or sideways for terrain mapping. At this time, the multi-angle detection mechanism pitches or tilts together with the UAV body, which may easily cause the picture taken by the multi-angle detection mechanism to shake, and may easily cause the surveyed terrain to deviate.

[0027] When the flying body pitches up and down, the gravity of the shooting mechanism drives the stabilizing cover to rotate relatively around the flying body, thereby resisting the pitching of the flying body, so that the shooting position of the shooting mechanism remains unchanged. When the flying body rolls, the gravity of the shooting mechanism drives the stabilizing cover to rotate relatively around the flying body, thereby resisting the roll of the flying body, so that the shooting position of the shooting mechanism remains unchanged. This makes the shooting position of the shooting mechanism more stable, thereby improving the quality of terrain mapping by the UAV.

[0028] When the stabilizing cover needs to resist the pitching of the flying body, the locking motor is driven, and the output shaft of the locking motor drives the locking block to rotate, so that the locking block is disengaged from the abutment with the two locking ratchets, so that the two locking torsion springs respectively drive the two locking ratchets to rotate away from each other, so that the two locking ratchets are disengaged from the engagement with the locking ratchet, so that when the flying body pitches, the stabilizing cover rotates relative to the flying body; when the stabilizing cover does not need to resist the pitching of the flying body, one end of the two locking ratchets abuts against the locking block, and the other ends of the two locking ratchets engage with the locking ratchet, so that the stabilizing cover is fixed to the flying body, so that when the flying body pitches, the stabilizing cover pitches with the flying body, so that the stabilizing mechanism can more easily meet the different shooting requirements of the drone, making it more usable. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1 It is a schematic diagram of the overall structure of an embodiment of the present application.

[0030] Figure 2 It is a schematic diagram of the structure of the stabilizing mechanism of an embodiment of the present application.

[0031] Figure 3 It is a schematic diagram of the structure of the stabilizing cover according to an embodiment of the present application.

[0032] Figure 4 It is a schematic diagram of the structure of the locking assembly of an embodiment of the present application.

[0033] Figure 5 It is a schematic diagram of the locking assembly structure of an embodiment of the present application.

[0034] Figure 6 yes Figure 2 A magnified view of part A.

[0035] Description of reference numerals: 1. flight body; 2. flight mechanism; 21. flight bracket; 22. flight motor; 23. flight blade; 3. stabilizing mechanism; 31. stabilizing cover; 32. stabilizing rod; 33. stabilizing ring; 34. locking assembly; 341. locking ratchet; 342. locking pawl; 343. locking torsion spring; 344. locking motor; 345. locking block; 35. locking assembly; 351. locking block; 352. locking spring; 353. locking motor; 35 4. Unlocking block; 4. Shooting mechanism; 41. Shooting seat; 42. Rotating motor; 43. Shooting module; 44. Linkage assembly; 441. Main linkage gear; 442. Secondary linkage gear; 45. Balance block; 5. Landing mechanism; 51. Landing seat; 52. Fixing assembly; 521. Fixing block; 522. Fixing spring; 53. Landing rod; 531. First landing part; 532. Second landing part; 54. Landing assembly; 541. Shock absorber; 542. Landing spring. DETAILED DESCRIPTION

[0036] The following is combined with Figure 1-5 This application is described in further detail.

[0037] The present application embodiment discloses a drone for terrain surveying and mapping. Figure 1 and Figure 2 A terrain surveying and mapping UAV includes a flying body 1, a flying mechanism 2, a stabilizing mechanism 3, a shooting mechanism 4 and a landing mechanism 5. The flying body 1 is square, the flying mechanism 2 is arranged on the flying body 1, the stabilizing mechanism 3 is arranged on the flying body 1, the shooting mechanism 4 is arranged on the stabilizing mechanism 3, and the landing mechanism 5 is arranged on the flying body 1.

[0038] Reference Figure 1 The flight mechanism 2 includes multiple flight brackets 21, multiple flight motors 22 and multiple flight blades 23. Each flight bracket 21 is rotatably set on the flight body 1. Each flight motor 22 is respectively fixedly set on one end of each flight bracket 21 away from the flight body 1. Each flight blade 23 is respectively coaxially fixedly set on the output shaft of each flight motor 22.

[0039] Reference Figure 2 The stabilization mechanism 3 also includes a stabilization cover 31, two stabilization rods 32 and a stabilization ring 33. A stabilization groove is opened in the middle position of the flight body 1. In the embodiment of the present application, the stabilization cover 31 is a large hemispherical transparent cover body. The stabilization cover 31 is rotatably set in the stabilization groove. The two stabilization rods 32 are coaxially fixed on the stabilization cover 31. The two stabilization rods 32 are respectively located on both sides of the stabilization cover 31. The axes of the two stabilization rods 32 are perpendicular to the rotation axis of the stabilization cover 31. The stabilization ring 33 is annular. The stabilization ring 33 has two stabilization holes that are penetrated. When the stabilization ring 33 is rotatably set on the stabilization cover 31, the two stabilization rods 32 are respectively penetrated and rotatably connected to the two stabilization holes.

[0040] Reference Figure 3 The stabilizing mechanism 3 also includes a locking assembly 34, which includes a locking ratchet 341, two locking pawls 342, two locking torsion springs 343, a locking motor 344 and a locking block 345. The flight body 1 is provided with a locking groove, the locking ratchet 341 is coaxially fixedly arranged on the rotating shaft of the stabilizing cover 31 and is located in the locking groove, the two locking pawls 342 are both rotatably arranged in the locking groove body, the two locking torsion springs 343 are both located in the locking groove, one end of the two locking torsion springs 343 is fixedly connected to the flight body 1, and the other ends of the two locking torsion springs 343 are respectively fixedly connected to the two locking pawls 342, the locking motor 344 is fixedly arranged on the locking groove body, and the locking block 345 is fixedly arranged on the output shaft of the locking motor 344. When the two locking pawls 342 are engaged with the locking ratchet 341, the two locking pawls 342 are both in contact with the locking block 345.

[0041] When the stabilizing cover 31 needs to resist the pitching of the flight body 1, the locking motor 344 is driven, and the output shaft of the locking motor 344 drives the locking block 345 to rotate, so that the locking block 345 is disengaged from the two locking pawls 342, so that the two locking torsion springs 343 respectively drive the two locking pawls 342 to rotate away from each other near one end of the locking ratchet 341, so that the two locking pawls 342 are disengaged from the locking ratchet 341, so that when the flight body 1 pitches up and down, the stabilizing cover 31 rotates relative to the flight body 1, and when the stabilizing cover 31 does not need to To resist the pitching of the flight body 1, the locking motor 344 is driven, and the output shaft of the locking motor 344 drives the locking block 345 to rotate, so that the two locking pawls 342 close to the locking block 345 are both in contact with the locking block 345, so that the two locking pawls 342 close to the locking ratchet 341 are rotated toward each other until the other ends of the two locking pawls 342 are engaged with the locking ratchet 341, so that the stabilizing cover 31 is fixed to the flight body 1, so that when the flight body 1 pitches up and down, the stabilizing cover 31 pitches up and down with the flight body 1.

[0042] Reference Figure 4 The stabilizing mechanism 3 also includes a locking assembly 35, which includes two locking blocks 351, two locking springs 352, a locking motor 353 and an unlocking block 354. The stabilizing ring 33 is provided with two locking grooves, the two locking blocks 351 are respectively penetrated and slidably matched in the two locking grooves, the two locking springs 352 are respectively located in the two locking grooves, one end of the two locking springs 352 is respectively fixedly connected to the two locking groove bodies, and the other ends of the two locking springs 352 are respectively fixedly connected to the two locking blocks 351, the locking motor 353 is fixedly arranged on the stabilizing ring 33, and the unlocking block 354 is coaxially fixedly arranged on the output shaft of the locking motor 353. When the stabilizing ring 33 is fixedly arranged on the stabilizing cover 31, the two locking blocks 351 are respectively tightly fixed to the two sides of one of the stabilizing bars 32.

[0043] When the stabilizing ring 33 needs to resist the roll of the flight body 1, the locking motor 353 is driven, and the output shaft of the locking motor 353 drives the unlocking block 354 to rotate. The rotation of the unlocking block 354 drives the two locking blocks 351 to slide in the directions away from each other until the two locking blocks 351 are disengaged from the stabilizing bar 32 and are tightly fixed. Therefore, when the flight body 1 rolls, the stabilizing ring 33 rotates relative to the flight body 1. When the stabilizing ring 33 does not need to resist the roll of the flight body 1, the two locking springs 352 respectively push the two locking blocks 351 to slide in the directions close to each other until the two locking blocks 351 are respectively tightly fixed to the two sides of one of the stabilizing bars 32, thereby fixing the stabilizing ring 33 to the stabilizing cover 31. Therefore, when the flight body 1 rolls, the stabilizing ring 33 rolls with the flight body 1.

[0044] Reference Figure 2The shooting mechanism 4 includes a shooting seat 41, a rotating motor 42 and a shooting module 43. The shooting seat 41 is fixedly arranged at the middle position of the stabilizing ring 33, the rotating motor 42 is fixedly arranged at one side of the shooting seat 41, and the shooting module 43 is arranged at one side of the shooting seat 41. One end of the shooting module 43 is rotatably connected to the stabilizing ring 33, and the other end of the shooting module 43 is fixedly connected to the output shaft of the rotating motor 42.

[0045] Reference Figure 2 The shooting mechanism 4 also includes a linkage assembly 44, which includes a main linkage gear 441 and a secondary linkage gear 442. The main linkage gear 441 is coaxially fixed to the output shaft of the rotating motor 42, and the secondary linkage gear 442 is rotatably connected to the shooting seat 41. The main linkage gear 441 and the secondary linkage gear 442 are meshed.

[0046] Reference Figure 2 The shooting mechanism 4 also includes a balancing block 45, which is rectangular and rotatably connected to the middle position of the shooting seat 41, and one end of the balancing block 45 is fixedly connected to the secondary linkage gear 442, so that when the shooting module 43 rotates, the balancing block 45 rotates in the opposite direction.

[0047] Reference Figure 1 and Figure 5 The landing mechanism 5 includes a landing seat 51 and a fixing assembly 52. ​​The landing seat 51 is rectangular. A landing slot is provided in the middle of the landing seat 51. The flight body 1 is inserted into the landing slot. The fixing assembly 52 includes a plurality of fixing blocks 521 and a plurality of fixing springs 522. The flight body 1 is provided with a plurality of sliding slots. Each fixing block 521 is respectively inserted into and slidably matched with each sliding slot. Each fixing spring 522 is respectively located in each sliding slot. One end of each fixing spring 522 is respectively fixedly connected to the sliding slot body, and the other end of each fixing spring 522 is respectively fixedly connected to each fixing block 521. The landing seat 51 is provided with a plurality of fixing slots. Each fixing slot is respectively connected to each sliding slot. When the landing seat 51 is fixedly connected to the flight body 1, each fixing block 521 is respectively inserted into and snap-fitted with each fixing slot.

[0048] Reference Figure 1The landing mechanism 5 also includes a plurality of landing rods 53 and a landing assembly 54. Each landing rod 53 is evenly distributed around the axis of the landing seat 51. Each landing rod 53 includes a first landing portion 531 and a second landing portion 532. Each first landing portion 531 is respectively slidably matched with each second landing portion 532. Each first landing portion 531 is rotatably connected to the landing trough. The landing assembly 54 includes a plurality of shock absorbers 541 and a plurality of landing springs 542. One end of each shock absorber 541 is fixedly connected to the landing seat 51, and the other end of each shock absorber 541 is respectively fixedly connected to each landing rod 53. Each second landing portion 532 is respectively penetrated by each landing spring 542. One end of each landing spring 542 is respectively fixedly connected to each first landing portion 531, and the other end of each landing spring 542 is respectively fixedly connected to each second landing portion 532.

[0049] The implementation principle of a topographic surveying drone in the embodiment of the present application is as follows: when the drone needs to fly, the flight mechanism 2 drives the flight body 1 to fly; when the flight mechanism 2 drives the flight body 1 to fly forward, backward or sideways, the stabilizing mechanism 3 drives the shooting mechanism 4 to rotate relatively around the flight body 1, thereby resisting the pitch or tilt of the flight body 1, that is, when the stabilizing cover 31 needs to resist the pitch of the flight body 1, the locking motor 344 is driven, and the output shaft of the locking motor 344 drives the locking block 345 to rotate, thereby disengaging the locking block 345 from the two locking pawls 342, thereby causing the two locking torsion springs 343 to respectively drive the two locking pawls 342 to rotate in a direction away from each other near one end of the locking ratchet 341, thereby causing The two locking pawls 342 are disengaged from the locking ratchet 341, so that when the flight body 1 pitches up and down, the stabilizing cover 31 rotates relative to the flight body 1; when the stabilizing cover 31 does not need to resist the pitching of the flight body 1, the locking motor 344 is driven, and the output shaft of the locking motor 344 drives the locking block 345 to rotate, so that the ends of the two locking pawls 342 close to the locking block 345 are both in contact with the locking block 345, so that the ends of the two locking pawls 342 close to the locking ratchet 341 are rotated toward each other until the other ends of the two locking pawls 342 are meshed with the locking ratchet 341, so that the stabilizing cover 31 is fixed to the flight body 1, so that when the flight body 1 pitches up and down, the stabilizing cover 31 pitches up and down with the flight body 1. When the stabilizing ring 33 needs to resist the roll of the flight body 1, the locking motor 353 is driven, and the output shaft of the locking motor 353 drives the unlocking block 354 to rotate. The rotation of the unlocking block 354 drives the two locking blocks 351 to slide in the directions away from each other until the two locking blocks 351 are disengaged from the stabilizing bar 32 and are tightly fixed. Therefore, when the flight body 1 rolls, the stabilizing ring 33 rotates relative to the flight body 1. When the stabilizing ring 33 does not need to resist the roll of the flight body 1, the two locking springs 352 respectively push the two locking blocks 351 to slide in the directions close to each other until the two locking blocks 351 are respectively tightly fixed to the two sides of one of the stabilizing bars 32, thereby fixing the stabilizing ring 33 to the stabilizing cover 31. Therefore, when the flight body 1 rolls, the stabilizing ring 33 rolls with the flight body 1. Thus, the shooting position of the shooting mechanism 4 remains unchanged, so that the quality of the terrain surveyed by the drone is better, and the problem that the drone needs to continuously fly forward, backward or sideways when conducting terrain surveying is improved, and the multi-angle detection mechanism follows the drone body to pitch or tilt and swing, which easily causes the picture taken by the multi-angle detection mechanism to shake, and easily causes the terrain surveyed to deviate; When the UAV needs to land, the flight body 1 drives the landing seat 51 to land, and the landing seat 51 drives the landing rods 53 to land until each landing rod 53 is in contact with the ground. Each landing rod 53 rotates toward the direction close to the UAV, thereby compressing each shock absorber 541 respectively, and then each shock absorber 541 drives each landing rod 53 to reset respectively, thereby reducing the impact force of the UAV when landing, and each second landing part 532 slides toward the direction close to each first landing part 531 respectively, thereby compressing each landing spring 542 respectively, and then each landing spring 542 drives each second landing part 532 to reset respectively, thereby further reducing the impact force of the UAV when landing.

[0050] The above are all preferred embodiments of the present application, and the protection scope of the present application is not limited thereto. Therefore, any equivalent changes made according to the structure, shape, and principle of the present application should be included in the protection scope of the present application.

Claims

1. A UAV for terrain surveying and mapping, characterized in that: The invention comprises a flying body (1), a flying mechanism (2), a stabilizing mechanism (3) and a photographing mechanism (4); the flying mechanism (2) is arranged on the flying body (1) and is used for flying; the stabilizing mechanism (3) is arranged on the flying body (1); the photographing mechanism (4) is arranged on the stabilizing mechanism (3); when the flying body (1) oscillates in pitch or tilt, the stabilizing mechanism (3) drives the photographing mechanism (4) to rotate.

2. The unmanned aerial vehicle for terrain surveying and mapping according to claim 1, characterized in that: The stabilizing mechanism (3) further comprises a stabilizing cover (31), two stabilizing rods (32) and a stabilizing ring (33); the stabilizing cover (31) is rotatably mounted on the flight body (1); the two stabilizing rods (32) are coaxially fixedly mounted on the stabilizing cover (31); the axes of the two stabilizing rods (32) are perpendicular to the rotation axis of the stabilizing cover (31); the stabilizing ring (33) is provided with two stabilizing holes which are arranged through the stabilizing ring (33); when the stabilizing ring (33) is rotatably mounted on the stabilizing cover (31), the two stabilizing rods (32) are respectively arranged through the two stabilizing holes and are rotatably connected to the two stabilizing holes; and the shooting mechanism (4) is arranged on the stabilizing ring (33).

3. The unmanned aerial vehicle for terrain surveying and mapping according to claim 2, characterized in that: The stabilizing mechanism (3) further comprises a locking assembly (34), wherein the locking assembly (34) comprises a locking ratchet (341), two locking pawls (342), two locking torsion springs (343), a locking motor (344) and a locking block (345), wherein the locking ratchet (341) is coaxially fixedly arranged on a rotating shaft of the stabilizing cover (31), the two locking pawls (342) are both rotatably arranged on the flying body (1), and the two locking torsion springs (343) are arranged on the flying body (1). ) one end is fixedly connected to the flight body (1), the other ends of the two locking torsion springs (343) are respectively fixedly connected to the two locking pawls (342), the locking motor (344) is fixedly arranged on the flight body (1), the locking block (345) is fixedly arranged on the output shaft of the locking motor (344), and when the two locking pawls (342) are engaged with the locking ratchet (341), the two locking pawls (342) are in contact with the locking block (345).

4. The unmanned aerial vehicle for terrain surveying and mapping according to claim 2, characterized in that: The stabilizing mechanism (3) further comprises a locking assembly (35), wherein the locking assembly (35) comprises two locking blocks (351), two locking springs (352), a locking motor (353) and an unlocking block (354); the two locking blocks (351) are both slidably matched with the stabilizing ring (33); one end of the two locking springs (352) are both fixedly connected to the stabilizing ring (33); the other ends of the two locking springs (352) are respectively fixedly connected to the two locking blocks (351); the locking motor (353) is fixedly arranged on the stabilizing ring (33); the unlocking block (354) is coaxially fixedly arranged on the output shaft of the locking motor (353); when the stabilizing ring (33) is fixedly arranged on the stabilizing cover (31), the two locking blocks (351) are respectively tightly fixed to the two sides of one of the stabilizing rods (32).

5. The unmanned aerial vehicle for terrain surveying and mapping according to claim 2, characterized in that: The shooting mechanism (4) comprises a rotating motor (42) and a shooting module (43); the rotating motor (42) is fixedly arranged on the stabilizing ring (33); one end of the shooting module (43) is rotatably connected to the stabilizing ring (33); and the other end of the shooting module (43) is fixedly connected to the output shaft of the rotating motor (42).

6. The unmanned aerial vehicle for terrain surveying and mapping according to claim 5, characterized in that: The shooting mechanism (4) further comprises a balancing block (45), wherein the balancing block (45) is rotatably connected to the stabilizing ring (33), and when the shooting module (43) rotates, the balancing block (45) rotates in the opposite direction.

7. The unmanned aerial vehicle for terrain surveying and mapping according to claim 6, characterized in that: The shooting mechanism (4) further comprises a linkage assembly (44), wherein the linkage assembly (44) comprises a main linkage gear (441) and a secondary linkage gear (442), wherein the main linkage gear (441) is coaxially fixedly arranged on the output shaft of the rotating motor (42), and the secondary linkage gear (442) is fixedly connected to the balance block (45), and the main linkage gear (441) and the secondary linkage gear (442) are meshed.

8. The unmanned aerial vehicle for terrain surveying and mapping according to claim 2, characterized in that: The invention also comprises a landing mechanism (5), wherein the landing mechanism (5) comprises a landing seat (51), a plurality of landing rods (53) and a landing assembly (54), wherein the landing seat (51) is fixedly arranged on the flight body (1), and each of the landing rods (53) is rotatably arranged on the landing seat (51); and the landing assembly (54) comprises a plurality of shock absorbers (541), one end of each of the shock absorbers (541) is fixedly connected to the landing seat (51), and the other end of each of the shock absorbers (541) is fixedly connected to each of the landing rods (53).

9. The unmanned aerial vehicle for terrain surveying and mapping according to claim 8, characterized in that: Each of the descending rods (53) comprises a first descending portion (531) and a second descending portion (532), and each of the first descending portions (531) is slidably matched with each of the second descending portions (532). The descending assembly (54) further comprises a plurality of descending springs (542), and one end of each of the descending springs (542) is fixedly connected to each of the first descending portions (531), and the other end of each of the descending springs (542) is fixedly connected to each of the second descending portions (532).

10. The unmanned aerial vehicle for terrain surveying and mapping according to claim 8, characterized in that: The landing mechanism (5) further comprises a fixing assembly (52), wherein the fixing assembly (52) comprises a plurality of fixing blocks (521) and a plurality of fixing springs (522), each of the fixing blocks (521) being slidably matched with the flight body (1), one end of each of the fixing springs (522) being fixedly connected with the flight body (1), and the other end of each of the fixing springs (522) being fixedly connected with each of the fixing blocks (521), and the landing seat (51) being provided with a plurality of fixing grooves, and when the landing seat (51) is fixedly connected with the flight body (1), each of the fixing blocks (521) is respectively penetrated and snap-fitted with each of the fixing grooves.

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