Non-contact flowmeter unmanned aerial vehicle launching and recovering device

Abstract

The utility model relates to unmanned aerial vehicle carrying equipment technical field discloses non -contact flow velocity appearance unmanned plane pay -off device, including machine body, support frame and measuring instrument, machine body bottom sets up clamping mechanism, including fixed plate and the fixed ring in square slot, measuring instrument top end fixed block is equipped with slide push and spring no.

Description

Technical Field

[0001] This utility model relates to the field of drone-mounted equipment technology, and in particular to a non-contact flowmeter drone launch and take-off device. Background Technology

[0002] With the rapid development of hydrological monitoring technology, drones are widely used in non-contact measurement of river flow velocity due to their advantages such as high mobility, wide monitoring range and no terrain restrictions. In actual operation, it is usually necessary to mount the non-contact current meter on the belly of the drone or on a special rack so that the drone can hover above the water surface to collect data. However, existing current meter retraction or mounting devices are often designed with simple connection structures, using traditional external clips, simple pins or bolts for rigid fixation. While this connection method can maintain fixation when stationary, UAVs often face complex external environments during flight missions, especially when encountering strong airflow or gusts. The fuselage will generate high-frequency vibrations and turbulence. Under long-term vibration, the traditional simple clip structure is prone to loosening, resulting in a larger connection gap. This will not only cause the current meter's measurement attitude to deviate, seriously affecting the accuracy of the measurement data, but in extreme cases, it may even cause the current meter to accidentally fall off the fuselage, resulting in damage or loss of expensive equipment. In addition, when the drone completes its operation and lands for recovery, the overall weight increases due to the additional flow meter equipment, resulting in a greater impact force on the ground upon landing. Most existing deployment and recovery devices lack effective buffering designs, and the rigid impact force from the ground is directly transmitted to the connection points of the aircraft and the inside of the precision flow meter. Long-term exposure to such hard landing impacts can easily lead to deformation of the connecting parts of the aircraft or a decrease in the sensitivity of the measuring instrument, thereby shortening the service life of the equipment. Therefore, this utility model proposes a non-contact flowmeter drone launch and take-off device to address the shortcomings of existing technologies. Utility Model Content

[0003] In view of the problems that existing non-contact current meter mounting devices mostly use simple snap-fit ​​connections, the snap-fits are prone to loosening or even falling off when the drone encounters turbulence during flight, resulting in deviation of the measurement attitude or loss of the equipment. In addition, the impact force of the ground during landing directly acts on the body and precision instruments, which can easily cause damage. This utility model aims to provide a non-contact current meter drone launch and take-off device with an improved structure, a stable connection and a buffer protection function.

[0004] This utility model provides a non-contact current meter drone launch and take-off device, comprising: a body, a support frame fixedly connected to the bottom of the body, and a measuring instrument. A clamping mechanism is provided between the body and the measuring instrument.

[0005] The clamping mechanism includes a fixing plate fixedly connected to the bottom of the machine body and a fixing block fixedly connected to the top of the measuring instrument. A square groove is formed inside the bottom end of the fixing plate, and a fixing ring is fixedly connected inside the square groove. An inner groove is formed inside the fixing block, and a push block is slidably connected within the inner groove, with one end of the push block passing through and extending outside the inner groove.

[0006] Furthermore, a long plate is fixedly connected to one end of the push block within the inner groove, and a spring is fixedly connected between the two long plates. A limiting assembly is fixedly connected to the top of each long plate, the limiting assembly including a connecting rod vertically fixed to the long plate and a barb fixedly connected to the top of the connecting rod. The connecting rod passes through the fixing ring, and the barb is engaged with the top surface of the fixing ring under the elastic force of the spring, thereby achieving a stable connection between the measuring instrument and the machine body through internal tension.

[0007] Preferably, the push blocks are symmetrically distributed on both sides of the fixed block, and the two ends of the spring are respectively fixedly connected to the inner sidewalls of the two long plates. When the push blocks are pressed and move inward, they can drive the long plates to compress the spring, thereby realizing the simultaneous unlocking operation on both sides and the force is more balanced.

[0008] Preferably, the outer wall contour of the fixing block is adapted to the inner wall contour of the square groove, and the fixing block is tightly inserted into the square groove. The shape fit restricts the relative rotation of the measuring instrument around the vertical axis, ensuring the accuracy of the measurement direction.

[0009] Preferably, the bottom of the support frame is provided with a buffer mechanism, which includes a connecting plate and a base plate located below the connecting plate. A limiting ring is fixedly sleeved at the bottom end of the support frame, and the bottom end of the limiting ring is fixedly connected to the top end of the connecting plate, so as to absorb the impact energy during landing through the buffer mechanism.

[0010] Preferably, a fixing rod is fixedly connected to the middle position of the bottom end of the connecting plate, and a spring is sleeved on the outer periphery of the fixing rod. An inner ring is fixedly connected to the middle position of the top end of the bottom plate, and an outer ring is slidably sleeved on the outer periphery of the inner ring. The top end of the outer ring is fixedly connected to the bottom end of the connecting plate, and the outer ring slides vertically along the outer wall of the inner ring to guide and prevent lateral tilting.

[0011] Preferably, the outer ring is sleeved on the outside of the fixing rod and the second spring, the top end of the second spring abuts against the bottom of the connecting plate, and the bottom end of the second spring abuts against the inner bottom surface of the inner ring or the base plate, thereby providing a limiting and protective function for the second spring.

[0012] Preferably, two springs are fixedly connected between the connecting plate and the base plate. The springs are symmetrically arranged on both sides of the outer ring and together with the springs form a multi-point buffer support structure to evenly distribute the impact load.

[0013] Preferably, the hook head of the barb extends in a direction away from the center line of the connecting rod, and the inner diameter of the fixing ring is greater than the outer distance when the two connecting rods are close to each other, so as to ensure that the connecting rod can pass smoothly through the fixing ring after retraction and can open outward for locking after release.

[0014] This utility model has the following beneficial effects: 1. This utility model solves the problem in the prior art where some retraction and extension devices rely solely on simple buckles or slots for fixation. When the drone encounters turbulent airflow during flight, the buckles easily loosen, the gaps widen, and the flow meter falls off or becomes unstable. This achieves a stable internal expansion rigid connection between the measuring instrument and the drone body, effectively preventing the equipment from loosening due to flight vibrations. Moreover, the disassembly and assembly process requires no auxiliary tools, making the operation convenient and efficient.

[0015] 2. This utility model solves the problem that when a UAV carrying a precision current meter lands on a platform, the ground impact force directly acts on the body and equipment, easily causing component deformation or damage to the precision instrument, by setting a buffer mechanism at the bottom of the support frame. It utilizes the vertical sliding guide cooperation between the inner and outer rings and the combined elastic damping effect of the central spring and the auxiliary springs on both sides. It achieves the technical effect of converting the rigid impact at the moment of landing into elastic potential energy and dissipating it, greatly reducing the vibration transmitted to the body and measuring instrument. At the same time, the guide structure prevents the support frame from tilting or twisting when compressed and buffered by force, ensuring a smooth and safe landing process.

[0016] 3. This utility model solves the problem that traditional cylindrical interfaces are prone to relative rotation during UAV flight and hovering, causing the flow meter probe to deviate from the preset angle and thus affecting measurement accuracy, by adapting the shape of the fixing block and the square groove at the bottom of the fixing plate. It achieves the technical effect of strictly limiting the rotational freedom of the measuring instrument around the vertical axis, ensuring that the flow meter always maintains the correct measurement orientation, thereby ensuring the accuracy of non-contact flow velocity measurement data. Attached Figure Description

[0017] Figure 1 This is a three-dimensional schematic diagram of the non-contact flow meter drone launch and take-up device proposed in this utility model. Figure 2This is a schematic diagram of the structure of the non-contact flow meter UAV launch and take-up device proposed in this utility model. Figure 3 This is a schematic diagram of the support frame for the non-contact flowmeter drone launch and take-off device proposed in this utility model. Figure 4 for Figure 3 Enlarged view of point A in the middle; Figure 5 for Figure 3 Enlarged view of point B in the middle.

[0018] Legend: 1. Organism; 2. Clamping mechanism; 21. Fixing plate; 22. Square groove; 23. Fixing ring; 24. Fixing block; 25. Inner groove; 26. Push block; 27. Long plate; 28. Spring 1; 29. Limiting component; 291. Linkage rod; 292. Barb; 3. Buffer mechanism; 31. Connecting plate; 32. Fixing rod; 33. Spring 2; 34. Inner ring; 35. Outer ring; 36. Spring 3; 37. Base plate; 38. Restricting ring 4. Support frame; 5. Measuring instrument. Detailed Implementation

[0019] Example: Reference Figures 1 to 5 This utility model provides a non-contact flow meter drone launch and take-off device, which aims to solve the problems in the prior art where the connection between the flow meter and the drone is only fixed by simple buckles, which is easy to loosen when the airflow is turbulent, causing the measurement attitude to shift or fall off, and the impact force of the drone landing can easily cause damage to the equipment.

[0020] like Figure 1 and Figure 2 As shown, the non-contact flow meter UAV launch and take-off device includes a body 1 and a support frame 4 fixedly connected to the bottom of the body 1. The body 1 serves as the main carrier of the flight platform, used to carry the control system and power system. The support frame 4 is symmetrically distributed on both sides of the bottom of the body 1, used to support the body 1 for take-off and landing on the ground. A measuring instrument 5 can also be detachably connected to the bottom of the body 1. The measuring instrument 5 is used to perform non-contact measurement of flow velocity. A clamping mechanism 2 is provided between the measuring instrument 5 and the body 1. The clamping mechanism 2 is used to realize the quick installation and secure locking of the measuring instrument 5 to prevent loosening during flight.

[0021] like Figure 2 , Figure 3 and Figure 4As shown, the clamping mechanism 2 mainly consists of a fixed part and a movable locking part. The fixed part includes a fixed plate 21 fixedly connected to the bottom of the body 1. A square groove 22 is opened inside the bottom end of the fixed plate 21. A fixed ring 23 is fixedly connected inside the square groove 22. The fixed ring 23 serves as a locking force point. The square groove 22 is used to restrict the rotational freedom of the installed components. The movable locking part is set on the measuring instrument 5 and includes a fixed block 24 fixedly connected to the top of the measuring instrument 5. The outer contour of the fixed block 24 matches the inner contour of the square groove 22. The fixed block 24 is inserted into the square groove 22. Through the shape matching between the fixed block 24 and the square groove 22, the relative rotation of the measuring instrument 5 during the flight of the body 1 is prevented, ensuring the directional accuracy of the measurement data.

[0022] like Figure 4 As shown, the fixed block 24 has an inner groove 25 inside, and a push block 26 is slidably connected inside the inner groove 25. There are two push blocks 26, which are located on opposite sides of the fixed block 24. One end of the push block 26 passes through and extends out of the inner groove 25, so that the operator can press it to drive the internal mechanism to move. One end of the push block 26 inside the inner groove 25 is fixedly connected to a long plate 27. The two long plates 27 are symmetrically arranged inside the fixed block 24. A spring 28 is fixedly connected between the opposite inner sidewalls of the two long plates 27. The spring 28 is used to provide restoring elasticity so that the two long plates 27 maintain the tendency to open outward.

[0023] A limiting component 29 is fixedly connected to the top of the long plate 27. The limiting component 29 includes a connecting rod 291 that is vertically fixed to the long plate 27. A barb 292 is fixedly connected to the top of the connecting rod 291. The hook head of the barb 292 extends outward from the center line of the connecting rod 291. The connecting rod 291 passes through the fixing ring 23 in its natural state. The barb 292 is engaged with the top surface of the fixing ring 23 under the elastic force of the spring 28. The vertical locking is achieved by the engagement of the barb 292 and the fixing ring 23. The horizontal and rotational directions are limited by the engagement of the fixing block 24 and the square groove 22.

[0024] Reference Figure 1 , Figure 3 and Figure 5 The buffer mechanism 3 is located at the bottom of the support frame 4. A limiting ring 38 is fixedly sleeved at the bottom of the support frame 4. The bottom of the limiting ring 38 is fixedly connected to the top of the connecting plate 31. The connecting plate 31 is used to bear the downward pressure transmitted from the support frame 4. A base plate 37 is provided below the connecting plate 31. The base plate 37 serves as a landing component that contacts the ground. An inner ring 34 is fixedly connected to the middle position of the top of the base plate 37. An outer ring 35 is fixedly connected to the bottom of the connecting plate 31. The outer diameter of the inner ring 34 is adapted to the inner diameter of the outer ring 35. The outer ring 35 is slidably sleeved on the outer wall of the inner ring 34 in the vertical direction.

[0025] The sliding fit structure of the inner ring 34 and the outer ring 35 forms a guide assembly, which restricts the relative lateral displacement between the connecting plate 31 and the base plate 37 when the buffer mechanism 3 is compressed, ensuring that the buffering action is carried out in the vertical direction, preventing the support frame 4 from tilting or twisting when it is impacted by the ground, thereby improving the stability of the landing process.

[0026] Meanwhile, a fixing rod 32 is fixedly connected to the middle of the bottom end of the connecting plate 31. The fixing rod 32 is located at the inner axis of the outer ring 35. A second spring 33 is sleeved on the outer periphery of the fixing rod 32. The outer ring 35 is sleeved on the outside of the fixing rod 32 and the second spring 33, which plays a protective and limiting role for the second spring 33. The top of the second spring 33 abuts against the bottom of the connecting plate 31, and the bottom of the second spring 33 abuts against the inner bottom surface of the inner ring 34 or the base plate 37. A third spring 36 is also fixedly connected between the connecting plate 31 and the base plate 37. There are two third springs 36, which are symmetrically arranged on both sides of the outer ring 35. Through the combined action of the second spring 33 and the third spring 36, the rigid impact of the body 1 during landing is converted into elastic potential energy and dissipated, thereby achieving a shock absorption and buffering effect and protecting the body 1 and the measuring instrument 5 from the impact of hard landing.

[0027] As a preferred embodiment, to facilitate the operator's unlocking and locking operations on the clamping mechanism 2, please refer to... Figure 2 and Figure 4 The push blocks 26 are symmetrically distributed on opposite sides of the fixed block 24, and both push blocks 26 pass through and extend outside the inner groove 25 to form a double-sided pressing structure. When the push blocks 26 are pressed inward, they can drive the internally connected long plates 27 to overcome the resistance of the spring 28 and move closer to each other. This double-sided symmetrical operation design not only makes it easy for the hand to apply force at the same time, but also ensures the balance of force, so that the internal connecting rod 291 can retract smoothly.

[0028] As another preferred embodiment, to enhance the stability of the measuring instrument 5 after installation and prevent it from shaking or rotating during the flight of the aircraft 1, please refer to... Figure 2 The outer contour of the fixing block 24 is precisely matched with the inner contour of the square groove 22 at the bottom of the fixing plate 21. When the measuring instrument 5 is installed in place, the fixing block 24 is completely embedded in the square groove 22. The geometry of the square groove 22 restricts the rotational freedom of the fixing block 24 and the measuring instrument 5 around the vertical axis, ensuring that the measuring instrument 5 always maintains the predetermined measurement direction.

[0029] As a further preferred embodiment, in order to improve the stability and load-bearing capacity of the buffer mechanism 3, please refer to... Figure 5There are two springs 36, which are respectively set on both sides of the outer ring 35. Together with the spring 2 33 in the center, they form a three-point support structure. This distribution can more evenly distribute the weight and landing impact force from the body 1. Combined with the central guiding effect of the inner ring 34 and the outer ring 35, it further prevents the connecting plate 31 from tilting during the buffering process.

[0030] As another preferred embodiment, to ensure the reliability of the clamping mechanism 2 locking and its automatic reset function, please refer to... Figure 4 The hook 292 extends outward from the center line of the connecting rod 291, and the inner diameter of the fixing ring 23 is designed to be greater than the outer distance when the two connecting rods 291 are close to each other, but less than the outer distance of the hook 292 when the two connecting rods 291 are in their natural reset state. This ensures that after the operator presses the push block 26 to retract the connecting rod 291, it can pass smoothly through the fixing ring 23. After releasing the hand, the spring 28 resets and drives the hook 292 to open outward and reliably hook the top surface of the fixing ring 23.

[0031] The working principle is as follows: When the measuring instrument 5 needs to be installed at the bottom of the machine body 1, the operator presses the push blocks 26 extending from both sides of the fixing block 24. The push blocks 26 slide inward in the inner groove 25, causing the connected long plate 27 to move closer to the center. At this time, the spring 28 between the two long plates 27 is compressed, and the connecting rod 291 above the long plate 27 moves closer to each other, so that the maximum outer diameter between the two barbs 292 at the top of the connecting rod 291 is smaller than the inner diameter of the fixing ring 23.

[0032] While maintaining the pressing state, align the fixing block 24 at the top of the measuring instrument 5 with and insert it into the square groove 22 of the fixing plate 21 at the bottom of the body 1. At the same time, make the connecting rod 291 and the barb 292 in the retracted state pass through the fixing ring 23. After the fixing block 24 is fully embedded in the square groove 22, release the pressing on the push block 26. Under the action of the spring 28's restoring force, the two long plates 27 drive the connecting rod 291 and the barb 292 to reset and open outward. At this time, the outward extension of the hook head of the barb 292 abuts against and locks onto the top surface of the fixing ring 23, thereby completing the vertical locking. With the square groove 22 limiting the circumferential position of the fixing block 24, a stable connection between the measuring instrument 5 and the body 1 is achieved, effectively preventing loosening or falling off caused by flight turbulence.

[0033] When it is necessary to disassemble the measuring instrument 5, press the push blocks 26 on both sides again to make the barb 292 retract inward and disengage from the top surface of the fixing ring 23, and then pull the measuring instrument 5 downward.

[0034] When the aircraft 1 completes its flight mission and lands on the ground or platform, the bottom plate 37 of the support frame 4 first contacts the ground. The impact force of the ground acts on the bottom plate 37, or the gravity of the aircraft 1 acts on the connecting plate 31, causing the connecting plate 31 to move downward relative to the bottom plate 37. During this process, the connecting plate 31 drives the fixing rod 32 and the outer ring 35 to move downward.

[0035] The outer ring 35 slides vertically downward along the outer wall of the inner ring 34, serving as a guide and limiting the lateral tilting of the connecting plate 31. At the same time, the fixing rod 32 compresses the second spring 33, and the connecting plate 31 compresses the third spring 36 on both sides. The impact energy is absorbed through the elastic deformation of the second spring 33 and the third spring 36, converting the rigid impact into elastic potential energy and dissipating it through buffering. This significantly reduces the vibration and impact transmitted to the machine body 1 and the measuring instrument 5, protecting the integrity and accuracy of the equipment structure.

Claims

1. A non-contact current meter drone launch and recovery device, comprising: The machine body (1), the support frame (4) fixedly connected to the bottom of the machine body (1), and the measuring instrument (5); The feature is that a clamping mechanism (2) is provided between the body (1) and the measuring instrument (5). The clamping mechanism (2) includes a fixing plate (21) fixedly connected to the bottom of the body (1) and a fixing block (24) fixedly connected to the top of the measuring instrument (5). A square groove (22) is provided inside the bottom end of the fixing plate (21), and a fixing ring (23) is fixedly connected inside the square groove (22). The fixed block (24) has an inner groove (25) inside, and two push blocks (26) are slidably connected inside the inner groove (25). One end of the push block (26) passes through and extends out of the inner groove (25). One end of each of the two push blocks (26) located in the inner groove (25) is fixedly connected to a long plate (27), and a spring (28) is fixedly connected between the two long plates (27). A limiting component (29) is fixedly connected to the top of the long plate (27). The limiting component (29) includes a connecting rod (291) vertically fixed to the long plate (27) and a barb (292) fixedly connected to the top of the connecting rod (291). The connecting rod (291) passes through the fixed ring (23) in its natural state, and the barb (292) is engaged with the top surface of the fixed ring (23) under the elastic force of the spring (28).

2. The non-contact current meter UAV launch and take-off device according to claim 1, characterized in that, The push block (26) is symmetrically distributed on both sides of the fixed block (24). The two ends of the spring (28) are respectively fixedly connected to the inner sidewalls of the two long plates (27). When the push block (26) is pressed and moves inward, it drives the long plate (27) to compress the spring (28).

3. The non-contact current meter UAV launch and take-off device according to claim 1, characterized in that, The outer contour of the fixing block (24) is adapted to the inner contour of the square groove (22), and the fixing block (24) is inserted into the square groove (22).

4. The non-contact current meter UAV launch and take-off device according to claim 1, characterized in that, The bottom of the support frame (4) is provided with a buffer mechanism (3), which includes a connecting plate (31) and a bottom plate (37) located below the connecting plate (31). The bottom end of the support frame (4) is fixedly fitted with a limiting ring (38), and the bottom end of the limiting ring (38) is fixedly connected to the top end of the connecting plate (31).

5. The non-contact current meter UAV launch and take-off device according to claim 4, characterized in that, A fixing rod (32) is fixedly connected to the middle position of the bottom end of the connecting plate (31), and a spring (33) is sleeved on the outer periphery of the fixing rod (32). An inner ring (34) is fixedly connected to the middle position of the top of the base plate (37), and an outer ring (35) is slidably sleeved on the outer periphery of the inner ring (34). The top of the outer ring (35) is fixedly connected to the bottom of the connecting plate (31).

6. The non-contact current meter UAV launch and take-off device according to claim 5, characterized in that, The outer ring (35) is sleeved on the outside of the fixed rod (32) and the second spring (33). The top end of the second spring (33) abuts against the bottom of the connecting plate (31), and the bottom end of the second spring (33) abuts against the inner bottom surface of the inner ring (34).

7. The non-contact current meter UAV launch and take-off device according to claim 5, characterized in that, A spring three (36) is also fixedly connected between the connecting plate (31) and the base plate (37). There are two spring threes (36) and they are symmetrically arranged on both sides of the outer ring (35).

8. The non-contact current meter UAV launch and take-off device according to claim 1, characterized in that, The hook head of the barb (292) extends in a direction away from the center line of the connecting rod (291), and the inner diameter of the fixing ring (23) is greater than the outer distance when the two connecting rods (291) are close to each other.

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