Survey device for territorial space planning and use method thereof

Abstract

The invention relates to the technical field of measuring instruments, and discloses a surveying device for land space planning and a using method thereof.The surveying device comprises a fuselage, four fixed rails are fixedly connected to the side wall of the fuselage, and propellers are fixedly connected to the ends, away from the fuselage, of the four fixed rails; at the moment, due to inclination of a machine body, the gradienter generates an electric signal to force an electric telescopic rod I and an electric telescopic rod II to contract or extend, and through control of the electric telescopic rod I and the electric telescopic rod II, a mounting plate and a sliding long plate are driven to move; the long sliding plate drives the sliding blocks on the two sides and the balancing weight to move towards the tilted end, the weight of the tilted end is increased, when the unmanned aerial vehicle suffers from crosswind, the different positions of the balancing weight in the fixed rail are adjusted through the long sliding plate, the gravity center position of the unmanned aerial vehicle is changed, and it is guaranteed that the unmanned aerial vehicle cannot be damaged when facing crossflow and strong wind flow; and the machine body can be automatically adjusted quickly.

Description

Technical Field

[0001] The present invention relates to the technical field of measuring instruments and equipment, and specifically to a surveying device for national land space planning and a method of using the same. Background Art

[0002] The survey work in national land space planning involves a variety of devices and technologies, mainly including the following: Total station: used to measure angles and distances, and conduct precise ground measurements and positioning. GPS receiver: provides high-precision geographic location data through the global positioning system to help conduct large-scale measurements. Laser scanner: used to obtain high-precision three-dimensional spatial data, often used for detailed surveys of buildings and terrain. UAV (unmanned aerial vehicle): obtains large-scale terrain and land data through aerial photography, supports high-resolution image and data collection, and other professional equipment.

[0003] Among them, when the UAV carries the survey equipment and flies into the air to collect information, it may encounter factors such as strong winds and crosswinds, causing the fuselage to tilt or move sideways uncontrollably, and the drone itself is prone to imbalance, causing the drone to lose balance and ultimately cause damage to the instrument. To address the above problems, the following solutions are proposed. Summary of the invention

[0004] In order to solve the above technical problems, the present invention provides a surveying device for land space planning, comprising a fuselage, four fixed rails are fixedly connected to the side wall of the fuselage, a propeller is fixedly connected to one end of the four fixed rails away from the fuselage, a level is fixedly connected to the top of the fuselage, a fixed frame is fixedly connected to the inner wall of the fuselage, a surveying instrument is slidably connected to the inner wall of the fixed frame, a mounting groove is opened on the side wall of the fixed frame, a contraction component is fixedly connected to the inner wall of the mounting groove, a wind receiving component is fixedly connected to the bottom of the fixed rail, and a limit frame is fixedly connected to the bottom of the fixed rail;

[0005] The adjustment mechanism includes an electric telescopic rod 1 fixedly connected to the inner wall of the fuselage, the other end of the electric telescopic rod 1 is fixedly connected to the mounting plate, the side of the mounting plate away from the electric telescopic rod 1 is fixedly connected to the electric telescopic rod 2, and the top of the mounting plate is fixedly connected to the sliding long plate;

[0006] The counterweight mechanism includes sliding blocks fixedly connected to both ends of the sliding long board. The outer wall of the sliding block is slidably connected to the inner wall of the fixed track. The top of the sliding block is fixedly connected with a counterweight block. When the UAV is hit by a crosswind after it is launched, the fuselage will tilt. At this time, the level will generate an electrical signal to the electric telescopic rod 1 and the electric telescopic rod 2 due to the tilt of the fuselage, forcing the electric telescopic rod 1 and the electric telescopic rod 2 to shrink or extend, showing as follows Figure 3 The status shown in Figure 3When the position of the electric telescopic rod one is tilted upward due to the horizontal placement, the electric telescopic rod one will contract, and the electric telescopic rod two at the other end will generate an extension force. Through the control of the above electric telescopic rod one and the electric telescopic rod two, the mounting plate and the sliding long plate are driven to move, and the sliding long plate drives the sliding blocks and the counterweight blocks on both sides to move toward the tilted end, increasing the weight of the tilted end, and the counterweight block and the sliding block move toward the tilted end, and the weight of the other end decreases. Through the application of the above components, when the UAV is subjected to crosswind, the sliding long plate can be used to adjust the different positions of the counterweight block in the fixed track to change the center of gravity of the UAV, ensuring that the UAV can quickly complete the self-adjustment of the fuselage when facing crossflow and strong wind flow, thereby ensuring the smooth operation of the UAV.

[0007] Preferably, the wind-receiving component includes a limit frame fixedly connected to the bottom of the fixed track, a rotating column rotatably connected to the inner wall of the through hole of the limit frame, an inclined plate fixedly connected to the outer wall of the rotating column, a vortex spring fixedly connected to the side wall of the inclined plate, one end of the vortex spring away from the inclined plate is fixedly connected to the side wall of the limit frame, and a linkage component is fixedly connected to the bottom of the inclined plate.

[0008] Preferably, the wind receiving component also includes an inclined plate fixedly connected to the top of the inclined plate, the outer wall of the sliding long plate is slidably connected to the inner wall of the through hole of the fuselage, the end of the electric telescopic rod second away from the mounting plate is fixedly connected to the inner wall of the fuselage, the bottom of the sliding block is fixedly connected to the roller frame, and the side wall of the sliding block is fixedly connected to the rolling column, the top of the inclined plate is provided with a sliding groove, the outer wall of the roller frame is slidably connected to the inner wall of the sliding groove by utilizing the characteristics of the sliding block moving inside the fixed track, wherein an inclined plate and a roller frame are arranged inside the equipment, wherein the inclined plate is pushed by the vortex spring to drive the top of the inclined plate to contact the bottom of the fixed track, and there is a gap between the inclined plate and the fixed track, and the rolling column rotates in the gap, when the sliding block is pushed outward by the sliding long plate to move outward, the rolling column will synchronously move outward along the inclined surface of the inclined plate, and under the influence of the inclined surface of the inclined plate, when the rolling column moves outward, it will push the inclined plate and the inclined plate to rotate downward, presenting a Figure 5 In the state shown, the wind flow of the external environment acts on the drone in the G route. When the inclined tilting plate contacts the wind flow, a downward pressure will be applied to the tilting plate at the tilted end of the drone. Through the application of the above components, the influence of strong wind flow can be avoided to cause the drone to tilt at a large angle, thereby achieving balance adjustment of the equipment.

[0009] Preferably, the linkage assembly includes a rotating frame 1 fixedly connected to the bottom of the inclined plate, a piston rod is rotatably connected to the inner wall of the rotating frame 1, and an end of the piston rod away from the rotating frame 1 is fixedly connected to the piston plate 1.

[0010] Preferably, the linkage assembly also includes a rotating frame 2 fixedly connected to the side wall of the fixed frame, an air pressure box 1 is rotatably connected to the outer wall of the rotating frame 2, the inner wall of the air pressure box 1 is slidably connected to the outer wall of the piston plate 1, a transmission pipe is connected through one side wall of the air pressure box, and a plurality of push grooves are opened on the side wall of the surveying instrument.

[0011] Preferably, the contraction component includes an air pressure box 2 fixedly connected to the inner wall of the installation groove, a piston plate 2 is slidably connected to the inner wall of the air pressure box 2, an L-shaped tube is connected to the top of the piston plate 2, and an air pressure telescopic rod is connected to the end of the L-shaped tube away from the piston plate 2. When the drone is tilted, one end is tilted and the other end is in a lowered state, and the contraction component and the surveying instrument are designed to be in a separated state, wherein the tilting plate at the tilted end of the drone will rotate downward due to the push of the rolling column, while the tilting plate at the other end will not change, wherein the air pressure telescopic rod at the tilted end will contact the surface of the push block due to expansion, and drive the surveying instrument to move upward. During this process, the remaining tilting plates do not tilt, and the corresponding air pressure telescopic rods cannot expand. When the surveying instrument moves upward, the remaining air pressure telescopic rods will not contact the inner wall of the push groove. Through the application of the above-mentioned components, while protecting the surveying instrument, the contraction components and linkage components in other directions will not be deformed due to the contraction of the surveying instrument, causing the remaining tilting plates to move downward and affecting the balance of the equipment.

[0012] Preferably, the contraction component also includes a fixed plate fixedly connected to the top of the L-shaped tube, the bottom of the fixed plate is fixedly connected to a pulling spring, the end of the pulling spring away from the fixed plate is fixedly connected to the side wall of the air pressure box two, and a pushing block is fixedly connected to the inner wall of the pushing groove. Utilizing the characteristic of the above-mentioned inclined plate rotating downward, a linkage component and a contraction component are arranged inside the equipment. When the inclined plate rotates downward, the inclined plate pushes the piston plate one to move along the inner wall of the air pressure box one through the rotating frame one and the piston rod, and the internal gas of the air pressure box one is pressurized and enters the interior of the air pressure box two through the transmission pipe. At this time, the internal gas of the air pressure box two enters the interior of the L-shaped tube. As the bottom of the piston plate two and the internal gas of the L-shaped tube are connected The piston plate 2 will move upward along the inner wall of the air pressure box 2. In this process, the spring will be pulled to apply a downward pulling force, forcing the gas inside the L-shaped tube to change to high pressure. The high-pressure gas will push the air pressure telescopic rod to expand outward, so that the L-shaped tube moves upward while the air pressure telescopic rod expands to both ends, so that the outer wall of the air pressure telescopic rod is in contact with the bottom of the pushing block, and the upward thrust of the L-shaped tube will drive the surveying instrument to move upward along the inner wall of the fixed frame through the pushing block. Through the application of the above components, when the UAV is subjected to crosswind, the surveying instrument can be recovered to prevent the surveying instrument from contacting with sand and dust in the strong wind, causing dust to adhere to the surveying instrument and affecting the measurement accuracy.

[0013] A method for using a surveying device for national land space planning includes the following steps:

[0014] S1: Before use, install the device on the drone. When the drone is launched and encounters crosswind, the fuselage will tilt. At this time, the level will generate an electrical signal to the electric telescopic rod 1 and the electric telescopic rod 2 due to the tilt of the fuselage, forcing the electric telescopic rod 1 and the electric telescopic rod 2 to contract or extend;

[0015] S2: Figure 3 When the electric telescopic rod 1 is tilted upward due to the horizontal placement, the electric telescopic rod 1 will be contracted, and the electric telescopic rod 2 at the other end will generate an extension force. Through the control of the above electric telescopic rod 1 and the electric telescopic rod 2, the mounting plate and the sliding long plate are driven to move;

[0016] S3: The sliding long board drives the sliding blocks and the counterweight blocks on both sides to move toward the tilted end, increasing the weight of the tilted end, while the counterweight block and the sliding block move toward the tilted end, and the weight at the other end decreases.

[0017] The present invention has the following beneficial effects:

[0018] (1) The present invention utilizes the fact that when a drone is blown by external crosswind, the drone will tilt to a certain extent. A sliding block and an adjustment mechanism are arranged inside the device. When the drone is blown by crosswind after it is launched, the fuselage will tilt. At this time, the level will generate an electrical signal to the electric telescopic rod 1 and the electric telescopic rod 2 due to the tilt of the fuselage, forcing the electric telescopic rod 1 and the electric telescopic rod 2 to contract or extend, showing as follows Figure 3 The status shown in Figure 3 When the position of the electric telescopic rod one is tilted upward due to the horizontal placement, the electric telescopic rod one will contract, and the electric telescopic rod two at the other end will generate an extension force. Through the control of the above electric telescopic rod one and the electric telescopic rod two, the mounting plate and the sliding long plate are driven to move, and the sliding long plate drives the sliding blocks and the counterweight blocks on both sides to move toward the tilted end, increasing the weight of the tilted end, and the counterweight block and the sliding block move toward the tilted end, and the weight of the other end decreases. Through the application of the above components, when the UAV is subjected to crosswind, the sliding long plate can be used to adjust the different positions of the counterweight block in the fixed track to change the center of gravity of the UAV, ensuring that the UAV can quickly complete the self-adjustment of the fuselage when facing crossflow and strong wind flow, thereby ensuring the smooth operation of the UAV.

[0019] (2) The present invention utilizes the characteristic that the sliding block moves inside the fixed track, and an inclined plate and a roller frame are arranged inside the device, wherein the inclined plate is pushed by the spiral spring to drive the top of the inclined plate to contact the bottom of the fixed track, and there is a gap between the inclined plate and the fixed track, and the rolling column rotates in the gap. When the sliding block is pushed outward by the sliding long plate, the rolling column will move outward synchronously along the inclined surface of the inclined plate. Affected by the inclined surface of the inclined plate, when the rolling column moves outward, it will push the inclined plate and the inclined plate to rotate downward, presenting a Figure 5 In the state shown, the wind flow of the external environment acts on the drone in the G route. When the inclined tilting plate contacts the wind flow, a downward pressure will be applied to the tilting plate at the tilted end of the drone. Through the application of the above components, the influence of strong wind flow can be avoided to cause the drone to tilt at a large angle, thereby achieving balance adjustment of the equipment.

[0020] (3) The present invention utilizes the characteristic that the above-mentioned inclined plate rotates downward, and a linkage component and a contraction component are arranged inside the device. When the inclined plate rotates downward, the inclined plate pushes the piston plate one to move along the inner wall of the air pressure box one through the rotating frame one and the piston rod. The gas inside the air pressure box one is pressurized and enters the inside of the air pressure box two through the transmission pipe. At this time, the gas inside the air pressure box two enters the inside of the L-shaped tube. As the gas at the bottom of the piston plate two and the inside of the L-shaped tube increase, the piston plate two will move upward along the inner wall of the air pressure box two. In this process, the pulling spring applies a downward pulling force, forcing the gas inside the L-shaped tube to change to high pressure. The high-pressure gas will push the pneumatic telescopic rod to expand outward, so that the L-shaped tube moves upward while the pneumatic telescopic rod expands to both ends, so that the outer wall of the pneumatic telescopic rod is in contact with the bottom of the pushing block, and the upward thrust of the L-shaped tube will drive the surveying instrument to move upward along the inner wall of the fixed frame through the pushing block. Through the application of the above-mentioned components, when the UAV is subjected to crosswind, the surveying instrument is recovered to prevent the surveying instrument from contacting with sand, gravel and dust in the strong wind, causing the surveying instrument to be attached with dust, affecting the measurement accuracy.

[0021] (4) The present invention utilizes the fact that when the drone is tilted, one end is tilted up and the other end is lowered, and designs the retracting component and the surveying instrument to be in a separated state, wherein the tilting plate at the tilted end of the drone will rotate downward due to the push of the rolling column, while the tilting plate at the other end will not change. The pneumatic telescopic rod at the tilted end will contact the outer surface of the push block due to expansion, and drive the surveying instrument to move upward. During this process, the remaining tilting plates do not tilt, and the corresponding pneumatic telescopic rods cannot expand either. When the surveying instrument moves upward, the remaining pneumatic telescopic rods will not contact the inner wall of the push groove. Through the application of the above-mentioned components, while protecting the surveying instrument, the contraction of the surveying instrument will not cause the deformation of the retracting components and linkage components in other directions, causing the remaining tilting plates to move downward and affecting the balance of the equipment. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the accompanying drawings required for describing the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other accompanying drawings can be obtained based on these accompanying drawings without paying creative work.

[0023] Figure 1It is a schematic diagram of the bottom of the overall structure of the present invention;

[0024] Figure 2 It is a schematic diagram of the internal components of the overall structure of the present invention;

[0025] Figure 3 It is a cross-sectional schematic diagram of the adjustment mechanism of the present invention;

[0026] Figure 4 For the present invention Figure 3 A is an enlarged schematic diagram;

[0027] Figure 5 For the present invention Figure 3 A magnified schematic diagram of B;

[0028] Figure 6 It is a schematic diagram of the working state of the present invention;

[0029] Figure 7 It is a cross-sectional schematic diagram of the linkage assembly of the present invention;

[0030] Figure 8 For the present invention Figure 7 A magnified schematic diagram of middle C;

[0031] Fig. 9 It is a schematic diagram of the working process of the present invention.

[0032] In the accompanying drawings, the components represented by the reference numerals are listed as follows:

[0033] In the figure: 1, fuselage; 11, fixed track; 12, propeller; 13, level; 14, fixed frame; 15, surveying instrument; 2, adjustment mechanism; 21, electric telescopic rod 1; 22, mounting plate; 23, electric telescopic rod 2; 24, sliding long board; 3, counterweight mechanism; 31, sliding block; 32, counterweight block; 4, wind receiving component; 41, limit frame; 42, rotating column; 43, tilting plate; 44, vortex spring; 45, roller frame ; 46. Rolling column; 47. Sliding groove; 48. Inclined plate; 5. Linkage assembly; 51. Rotating frame 1; 52. Piston rod; 53. Piston plate 1; 54. Air pressure box 1; 55. Rotating frame 2; 56. Transmission pipe; 57. Pushing groove; 58. Mounting groove; 6. Contraction assembly; 61. Air pressure box 2; 62. Piston plate 2; 63. L-shaped tube; 64. Air pressure telescopic rod; 65. Fixed plate; 66. Pull spring; 67. Push block. DETAILED DESCRIPTION

[0034] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0035] For example, see Figure 1 - Figure 5 The present invention is a surveying device for land space planning, comprising a fuselage 1, four fixed rails 11 are fixedly connected to the side wall of the fuselage 1, a propeller 12 is fixedly connected to the end of the four fixed rails 11 away from the fuselage 1, a level 13 is fixedly connected to the top of the fuselage 1, a fixed frame 14 is fixedly connected to the inner wall of the fuselage 1, a surveying instrument 15 is slidably connected to the inner wall of the fixed frame 14, a mounting groove 58 is opened on the side wall of the fixed frame 14, a contraction component 6 is fixedly connected to the inner wall of the mounting groove 58, a wind receiving component 4 is fixedly connected to the bottom of the fixed rail 11, and a limiting frame 41 is fixedly connected to the bottom of the fixed rail 11;

[0036] The adjusting mechanism 2 includes an electric telescopic rod 1 21 fixedly connected to the inner wall of the fuselage 1, the other end of the electric telescopic rod 1 21 is fixedly connected to the mounting plate 22, the side of the mounting plate 22 away from the electric telescopic rod 1 21 is fixedly connected to the electric telescopic rod 2 23, and the top of the mounting plate 22 is fixedly connected to the sliding long plate 24;

[0037] The counterweight mechanism 3 includes a sliding block 31 fixedly connected to both ends of the sliding long plate 24. The outer wall of the sliding block 31 is slidably connected to the inner wall of the fixed track 11. The top of the sliding block 31 is fixedly connected to a counterweight block 32. When the UAV is launched and encounters a crosswind, the fuselage will tilt. At this time, the level 13 will generate an electrical signal to the electric telescopic rod 1 21 and the electric telescopic rod 2 23 due to the tilt of the fuselage 1, forcing the electric telescopic rod 1 21 and the electric telescopic rod 2 23 to shrink or extend, showing as shown in the figure. Figure 3 The status shown in Figure 3When the position of the electric telescopic rod 21 is tilted upward due to the horizontal placement, the electric telescopic rod 21 will contract, and the electric telescopic rod 23 at the other end will generate an extension force. Through the control of the above electric telescopic rod 21 and the electric telescopic rod 23, the mounting plate 22 and the sliding long plate 24 are driven to move, and the sliding long plate 24 drives the sliding blocks 31 and the counterweight blocks 32 on both sides to move toward the tilted end, increasing the weight of the tilted end, and the counterweight blocks 32 and the sliding blocks 31 move toward the tilted end, and the weight at the other end decreases. Through the application of the above components, when the UAV is subjected to crosswind, the sliding long plate 24 is used to adjust the counterweight blocks 32 to different positions in the fixed track 11, thereby changing the center of gravity of the UAV, ensuring that the UAV can quickly complete the self-adjustment of the fuselage when facing crossflow and strong wind flow, thereby ensuring the smooth operation of the UAV.

[0038] For example 2, please refer to Figure 6 - Fig. 9 The present invention is a surveying device for land space planning. On the basis of embodiment one, the wind receiving component 4 includes a limit frame 41 fixedly connected to the bottom of the fixed track 11, and a rotating column 42 is rotatably connected to the inner wall of the through hole of the limit frame 41, and an inclined plate 43 is fixedly connected to the outer wall of the rotating column 42. A vortex spring 44 is fixedly connected to the side wall of the inclined plate 43, and one end of the vortex spring 44 away from the inclined plate 43 is fixedly connected to the side wall of the limit frame 41, and a linkage component 5 is fixedly connected to the bottom of the inclined plate 43.

[0039] The wind receiving component 4 also includes an inclined panel 48 fixedly connected to the top of the inclined plate 43, the outer wall of the sliding long plate 24 is slidably connected to the inner wall of the through hole of the fuselage 1, the end of the electric telescopic rod 23 away from the mounting plate 22 is fixedly connected to the inner wall of the fuselage 1, the bottom of the sliding block 31 is fixedly connected to a roller frame 45, the side wall of the sliding block 31 is fixedly connected to a rolling column 46, the top of the inclined plate 43 is provided with a sliding groove 47, the outer wall of the roller frame 45 is slidably connected to the inner wall of the sliding groove 47, and the sliding block 31 is moved inside the fixed track 11. The inclined plate 43 and the roller frame 45 are provided at the bottom of the inclined plate 48, wherein the inclined plate 43 is pushed by the spiral spring 44 to drive the top of the inclined plate 48 to contact the bottom of the fixed track 11, and there is a gap between the inclined plate 48 and the fixed track 11, and the rolling column 46 rotates in the gap. When the sliding block 31 is pushed outward by the sliding long plate 24, the rolling column 46 will move outward synchronously along the inclined surface of the inclined plate 48. Affected by the inclined surface of the inclined plate 48, when the rolling column 46 moves outward, it will push the inclined plate 48 and the inclined plate 43 to rotate downward, presenting a Figure 5In the state shown, the wind flow of the external environment acts on the drone along the G route. When the inclined inclined plate 43 contacts the wind flow, a downward pressure is applied to the inclined plate 43 at the tilted end of the drone. By applying the above components, the influence of strong wind flow is avoided, which causes the drone to tilt at a large angle, thereby achieving balance adjustment of the equipment.

[0040] The linkage assembly 5 includes a rotating frame 51 fixedly connected to the bottom of the inclined plate 43, a piston rod 52 is rotatably connected to the inner wall of the rotating frame 51, and one end of the piston rod 52 away from the rotating frame 51 is fixedly connected to a piston plate 53.

[0041] The linkage assembly 5 also includes a rotating frame 55 fixedly connected to the side wall of the fixed frame 14, and an air pressure box 54 is rotatably connected to the outer wall of the rotating frame 55. The inner wall of the air pressure box 54 is slidably connected to the outer wall of the piston plate 53. A transmission pipe 56 is connected through the side wall of the air pressure box 54, and a plurality of push grooves 57 are opened on the side wall of the surveying instrument 15.

[0042] The contraction assembly 6 includes an air pressure box 61 fixedly connected to the inner wall of the mounting groove 58, a piston plate 62 is slidably connected to the inner wall of the air pressure box 61, an L-shaped tube 63 is connected to the top of the piston plate 62, and an end of the L-shaped tube 63 away from the piston plate 62 is connected to a pneumatic telescopic rod 64. When the drone is tilted, one end is tilted up and the other end is in a lowered state, and the contraction assembly 6 and the surveying instrument 15 are designed to be in a separated state, wherein the tilting plate 43 at the tilted end of the drone will rotate downward due to the push of the rolling column 46, while the tilting plate 43 at the other end will not change. The pneumatic telescopic rod 64 at the tilted end will contact the surface of the pushing block 67 due to expansion, and drive the surveying instrument 15 to move upward. During this process, the remaining inclined plates 43 do not tilt, and the corresponding pneumatic telescopic rods 64 cannot expand. When the surveying instrument 15 moves upward, the remaining pneumatic telescopic rods 64 will not contact the inner wall of the pushing groove 57. Through the application of the above-mentioned components, while protecting the surveying instrument 15, the contraction of the surveying instrument 15 will not cause deformation of the contraction components 6 and the linkage components 5 in other directions, causing the remaining inclined plates 43 to move downward, affecting the balance of the equipment.

[0043] The contraction assembly 6 also includes a fixed plate 65 fixedly connected to the top of the L-shaped tube 63, a pulling spring 66 fixedly connected to the bottom of the fixed plate 65, an end of the pulling spring 66 away from the fixed plate 65 is fixedly connected to the side wall of the air pressure box 61, and a pushing block 67 is fixedly connected to the inner wall of the pushing groove 57. Utilizing the characteristic that the above-mentioned inclined plate 43 rotates downward, a linkage assembly 5 and a contraction assembly 6 are arranged inside the equipment. When the inclined plate 43 rotates downward, the inclined plate 43 pushes the piston plate 53 to move along the inner wall of the air pressure box 54 through the rotating frame 51 and the piston rod 52, and the gas inside the air pressure box 54 is pressurized and enters the inside of the air pressure box 61 through the transmission pipe 56. At this time, the gas inside the air pressure box 61 enters the inside of the L-shaped tube 63. As the bottom of the piston plate 62 and the L-shaped tube As the internal gas of 63 increases, the piston plate 62 will move upward along the inner wall of the air pressure box 61. In this process, the pulling spring 66 applies a downward pulling force, forcing the internal gas of the L-shaped tube 63 to change to high pressure. The high-pressure gas will push the pneumatic telescopic rod 64 to expand outward, so that the L-shaped tube 63 moves upward while the pneumatic telescopic rod 64 expands to both ends, so that the outer wall of the pneumatic telescopic rod 64 contacts the bottom of the pushing block 67, and the upward thrust of the L-shaped tube 63 will drive the surveying instrument 15 to move upward along the inner wall of the fixed frame 14 through the pushing block 67. Through the application of the above-mentioned components, when the UAV is subjected to crosswind, the surveying instrument 15 can be recovered to prevent the surveying instrument 15 from contacting with sand, gravel and dust in the strong wind, causing the surveying instrument 15 to be attached with dust, affecting the measurement accuracy.

[0044] The method for using the survey device includes the following steps:

[0045] S1: Before use, the device is installed on the drone. When the drone is launched and encounters crosswind, the fuselage will tilt. At this time, the level 13 will generate an electrical signal to the electric telescopic rod 1 21 and the electric telescopic rod 2 23 due to the tilt of the fuselage 1, forcing the electric telescopic rod 1 21 and the electric telescopic rod 2 23 to contract or extend;

[0046] S2: Figure 3 When the electric telescopic rod 1 21 is tilted upward due to the horizontal placement, the electric telescopic rod 1 21 will be contracted, and the electric telescopic rod 2 23 at the other end will generate an extension force. Through the control of the electric telescopic rod 1 21 and the electric telescopic rod 2 23, the mounting plate 22 and the sliding long plate 24 are driven to move;

[0047] S3: The sliding long board 24 drives the sliding blocks 31 and the counterweight blocks 32 on both sides to move toward one end of the tilting, increasing the weight of the tilting end, while the counterweight blocks 32 and the sliding blocks 31 move toward the tilting end, and the weight of the other end decreases.

[0048] A specific application of this embodiment is: before use, the device is installed on a drone. When the drone is launched and encounters a crosswind, the fuselage will tilt. At this time, the level 13 will generate an electrical signal to the electric telescopic rod 1 21 and the electric telescopic rod 2 23 due to the tilt of the fuselage 1, forcing the electric telescopic rod 1 21 and the electric telescopic rod 2 23 to shrink or extend, showing as follows Figure 3 The status shown in Figure 3 When the position of the electric telescopic rod 21 is tilted upward due to the horizontal placement, the electric telescopic rod 21 will contract, and the electric telescopic rod 23 at the other end will generate an extension force. Through the control of the above electric telescopic rod 21 and the electric telescopic rod 23, the mounting plate 22 and the sliding long plate 24 are driven to move, and the sliding long plate 24 drives the sliding blocks 31 and the counterweight blocks 32 on both sides to move toward the tilted end, increasing the weight of the tilted end, and the counterweight blocks 32 and the sliding blocks 31 move toward the tilted end, and the weight at the other end decreases. Through the application of the above components, when the UAV is subjected to crosswind, the sliding long plate 24 is used to adjust the counterweight blocks 32 to different positions in the fixed track 11, thereby changing the center of gravity of the UAV, ensuring that the UAV can quickly complete the self-adjustment of the fuselage when facing crossflow and strong wind flow, thereby ensuring the smooth operation of the UAV.

[0049] Taking advantage of the fact that the sliding block 31 moves inside the fixed track 11, an inclined plate 43 and a roller frame 45 are provided inside the device, wherein the inclined plate 43 is pushed by the spiral spring 44 to drive the top of the inclined plate 48 to contact the bottom of the fixed track 11, and there is a gap between the inclined plate 48 and the fixed track 11, and the rolling column 46 rotates in the gap. When the sliding block 31 is pushed outward by the sliding long plate 24, the rolling column 46 will move outward synchronously along the inclined surface of the inclined plate 48. Affected by the inclined surface of the inclined plate 48, when the rolling column 46 moves outward, it will push the inclined plate 48 and the inclined plate 43 to rotate downward, presenting a Figure 5In the state shown, the wind flow of the external environment acts on the UAV along the G route. When the inclined inclined plate 43 contacts the wind flow, a downward pressure is applied to the inclined plate 43 at the tilted end of the UAV. By applying the above-mentioned components, the influence of strong wind flow and the large-angle tilt of the UAV can be avoided, so as to achieve the balance adjustment of the equipment. By utilizing the downward rotation characteristic of the above-mentioned inclined plate 43, a linkage component 5 and a contraction component 6 are arranged inside the equipment. When the inclined plate 43 rotates downward, the inclined plate 43 pushes the piston plate 1 53 to move along the inner wall of the air pressure box 1 54 through the rotating frame 1 51 and the piston rod 52. The gas inside the air pressure box 1 54 is pressurized and enters the inside of the air pressure box 2 61 through the transmission pipe 56. At this time, the gas inside the air pressure box 2 61 enters the inside of the L-shaped pipe 63. As the piston plate 2 6 2 bottom and the increase of gas inside the L-shaped tube 63, the piston plate 2 62 will move upward along the inner wall of the air pressure box 2 61. In this process, the pulling spring 66 applies a downward pulling force, forcing the gas inside the L-shaped tube 63 to change to high pressure. The high-pressure gas will push the pneumatic telescopic rod 64 to expand outward, so that the L-shaped tube 63 moves upward and the pneumatic telescopic rod 64 expands to both ends, so that the outer wall of the pneumatic telescopic rod 64 contacts the bottom of the pushing block 67, and the upward thrust of the L-shaped tube 63 will drive the surveying instrument 15 to move upward along the inner wall of the fixing frame 14 through the pushing block 67. Through the application of the above components, when the UAV is subjected to crosswind, the surveying instrument 15 is recovered to prevent the surveying instrument 15 from contacting with sand and dust in the strong wind, causing the surveying instrument 15 to be attached with dust, affecting the measurement accuracy.

[0050] When the drone is tilted, one end is tilted up and the other end is in a lowered state. The retracting component 6 and the surveying instrument 15 are designed to be in a separated state, wherein the tilting plate 43 at the tilted end of the drone will rotate downward due to the push of the rolling column 46, while the tilting plate 43 at the other end will not change. The pneumatic telescopic rod 64 at the tilted end will contact the surface of the pushing block 67 due to expansion, and drive the surveying instrument 15 to move upward. During this process, the remaining tilting plates 43 do not tilt, and the corresponding pneumatic telescopic rods 64 cannot expand. When the surveying instrument 15 moves upward, the remaining pneumatic telescopic rods 64 will not contact the inner wall of the pushing groove 57. Through the application of the above-mentioned components, while protecting the surveying instrument 15, the contraction of the surveying instrument 15 will not cause the deformation of the retracting components 6 and the linkage component 5 in the remaining directions, causing the remaining tilting plates 43 to move downward, affecting the balance of the equipment.

[0051] The preferred embodiments of the present invention disclosed above are only used to help illustrate the present invention. The preferred embodiments do not describe all the details in detail, nor do they limit the invention to the specific implementation methods described. Obviously, many modifications and changes can be made according to the content of this specification. This specification selects and specifically describes these embodiments in order to better explain the principles and practical applications of the present invention, so that those skilled in the art can understand and use the present invention well. The present invention is limited only by the claims and their full scope and equivalents.

Claims

1. A surveying device for land space planning, comprising a fuselage (1), wherein four fixed rails (11) are fixedly connected to the side walls of the fuselage (1), a propeller (12) is fixedly connected to one end of the four fixed rails (11) away from the fuselage (1), a level (13) is fixedly connected to the top of the fuselage (1), a fixed frame (14) is fixedly connected to the inner wall of the fuselage (1), a surveying instrument (15) is slidably connected to the inner wall of the fixed frame (14), a mounting groove (58) is provided on the side wall of the fixed frame (14), a contraction component (6) is fixedly connected to the inner wall of the mounting groove (58), a wind receiving component (4) is fixedly connected to the bottom of the fixed rail (11), and a limiting frame (41) is fixedly connected to the bottom of the fixed rail (11), characterized in that: Also includes: An adjustment mechanism (2), the adjustment mechanism (2) comprising an electric telescopic rod (21) fixedly connected to the inner wall of the body (1), the other end of the electric telescopic rod (21) fixedly connected to a mounting plate (22), a side of the mounting plate (22) away from the electric telescopic rod (21) fixedly connected to an electric telescopic rod (23), and a top of the mounting plate (22) fixedly connected to a sliding long plate (24); A counterweight mechanism (3) comprises sliding blocks (31) fixedly connected to both ends of the sliding long plate (24), the outer wall of the sliding block (31) being slidably connected to the inner wall of the fixed track (11), and the top of the sliding block (31) being fixedly connected to a counterweight block (32).

2. A surveying device for national land space planning according to claim 1, characterized in that: The wind receiving component (4) comprises a limit frame (41) fixedly connected to the bottom of the fixed track (11); a rotating column (42) is rotatably connected to the inner wall of the through hole of the limit frame (41); an inclined plate (43) is fixedly connected to the outer wall of the rotating column (42); a vortex spring (44) is fixedly connected to the side wall of the inclined plate (43); one end of the vortex spring (44) away from the inclined plate (43) is fixedly connected to the side wall of the limit frame (41); and a linkage component (5) is fixedly connected to the bottom of the inclined plate (43).

3. A surveying device for land space planning according to claim 2, characterized in that: The wind receiving component (4) also includes an inclined panel (48) fixedly connected to the top of the inclined plate (43); the outer wall of the sliding long plate (24) is slidably connected to the inner wall of the through hole of the fuselage (1); the end of the second electric telescopic rod (23) away from the mounting plate (22) is fixedly connected to the inner wall of the fuselage (1); the bottom of the sliding block (31) is fixedly connected to a roller frame (45); the side wall of the sliding block (31) is fixedly connected to a rolling column (46); the top of the inclined plate (43) is provided with a sliding groove (47); the outer wall of the roller frame (45) is slidably connected to the inner wall of the sliding groove (47).

4. A surveying device for national land space planning according to claim 3, characterized in that: The linkage assembly (5) comprises a rotating frame (51) fixedly connected to the bottom of the inclined plate (43), a piston rod (52) being rotatably connected to the inner wall of the rotating frame (51), and a piston plate (53) being fixedly connected to one end of the piston rod (52) away from the rotating frame (51).

5. A surveying device for national land space planning according to claim 4, characterized in that: The linkage assembly (5) further comprises a rotating frame 2 (55) fixedly connected to the side wall of the fixed frame (14); an air pressure box 1 (54) is rotatably connected to the outer wall of the rotating frame 2 (55); the inner wall of the air pressure box 1 (54) is slidably connected to the outer wall of the piston plate 1 (53); a transmission pipe (56) is connected through the side wall of the air pressure box 1 (54); and a plurality of push grooves (57) are provided on the side wall of the surveying instrument (15).

6. A surveying device for national land space planning according to claim 5, characterized in that: The contraction assembly (6) comprises an air pressure box (61) fixedly connected to the inner wall of the mounting groove (58), a piston plate (62) being slidably connected to the inner wall of the air pressure box (61), an L-shaped tube (63) being connected through the top of the piston plate (62), and an end of the L-shaped tube (63) away from the piston plate (62) being connected through a pneumatic telescopic rod (64).

7. A surveying device for national land space planning according to claim 6, characterized in that: The contraction assembly (6) also includes a fixing plate (65) fixedly connected to the top of the L-shaped tube (63), a pulling spring (66) fixedly connected to the bottom of the fixing plate (65), an end of the pulling spring (66) away from the fixing plate (65) is fixedly connected to the side wall of the air pressure box (61), and a pushing block (67) is fixedly connected to the inner wall of the pushing groove (57).

8. A method for using a surveying device for national land space planning, using the surveying device for space planning as claimed in claim 7, characterized in that: The following steps are included: S1: Before use, the device is installed on the drone. When the drone is launched and encounters a crosswind, the fuselage will tilt. At this time, the level gauge (13) will generate an electrical signal to the electric telescopic rod 1 (21) and the electric telescopic rod 2 (23) due to the tilt of the fuselage (1), forcing the electric telescopic rod 1 (21) and the electric telescopic rod 2 (23) to contract or extend. S2: When the electric telescopic rod 1 (21) in FIG. 3 is tilted upward due to the horizontal placement, the electric telescopic rod 1 (21) will be contracted, and the electric telescopic rod 2 (23) at the other end will generate an extension force. Through the control of the electric telescopic rod 1 (21) and the electric telescopic rod 2 (23), the mounting plate (22) and the sliding long plate (24) are driven to move; S3: The sliding long plate (24) drives the sliding blocks (31) and the counterweight blocks (32) on both sides to move toward one end of the tilting, thereby increasing the weight of the tilting end, while the counterweight blocks (32) and the sliding blocks (31) move toward the tilting end, and the weight of the other end decreases.

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