A protective frame body of a thickness measuring unmanned aerial vehicle

Abstract

The utility model discloses a kind of protective frame body of thickness measuring unmanned plane, it is related to unmanned plane technical field.The utility model includes protective frame main part, protective frame main part top is connected with control assembly, control assembly includes control bin and steering wheel, steering wheel output end is connected with limit plate, control bin inside is equipped with system control unit and battery, control bin top is connected with placing bin, reset frame is connected with pull rod in placing bin inside through spring, reset frame inner wall is connected with pull rod, umbrella bag is placed in reset frame top, and umbrella bag one end is fixed on pull rod, placing bin both sides are connected with flap through rotating rod, and rotating rod outside is sleeved with torsion spring.The utility model is triggered to open parachute program quickly when unmanned plane is out of control and falls by setting control assembly, flap, torsion spring, spring and umbrella bag, combined with the automatic judgment and remote manual trigger mechanism of system control unit, and avoid secondary danger by rotor brake stop, significantly improve high-altitude operation safety.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, specifically a protective frame for a thickness measuring UAV. Background Technology

[0002] Thickness measurement drones are unmanned aerial platforms that integrate non-contact thickness detection sensors (such as ultrasonic, laser, or electromagnetic induction probes). They are widely used in the thickness detection and corrosion assessment of large structural components such as bridges, pipelines, storage tanks, and ships. The protective frame, as a key component of the thickness measurement drone, is mainly used to fix and protect the thickness sensor, buffer collisions and impacts during flight, and maintain a stable distance between the sensor and the surface to be measured, thereby ensuring the accuracy of data acquisition and the service life of the equipment.

[0003] Currently, most protective frames for thickness measurement drones are made of rigid materials (such as carbon fiber and aluminum alloy), with simple structures and only basic sensor installation functions. Although some protective frames have added simple buffer pads, they can only cope with low-altitude falls and have no active intervention capabilities. High-altitude, high-speed falls still cannot prevent the equipment from being scrapped, and may even cause secondary dangers due to the rotor not stopping. They are difficult to meet the equipment safety requirements, especially in high-altitude inspection scenarios. Utility Model Content

[0004] Therefore, the purpose of this utility model is to provide a protective frame for a thickness measuring drone to solve the technical problems mentioned above.

[0005] To achieve the above objectives, this utility model provides the following technical solution: a protective frame for a thickness measuring drone, comprising a protective frame body, a control component connected to the top of the protective frame body, the control component comprising a control compartment and a servo motor, the output end of the servo motor being connected to a limit plate, a system control unit and a battery installed inside the control compartment, a placement compartment connected to the top of the control compartment, a reset frame connected inside the placement compartment via a spring, a pull rod connected to the inner wall of the reset frame, a parachute placed on the top of the reset frame, one end of the parachute being fixed to the pull rod, and flip covers connected to both sides of the placement compartment via rotating rods, with torsion springs sleeved on the outside of the rotating rods.

[0006] Furthermore, the main body of the protective frame includes a fixing frame and a protective frame. The fixing frame is clamped at the middle position on the top of the drone, and both the fixing frame and the protective frame are made of elastic plastic.

[0007] By adopting the above technical solutions, the elastic plastic material combines lightweight and impact resistance: on the one hand, it can reduce the overall load of the drone, avoiding affecting flight endurance and maneuverability; on the other hand, in daily inspections, if the drone slightly touches the structure under test (such as bridge railings or the outer wall of storage tanks), the protective frame can buffer the impact force through its own deformation, preventing the thickness sensor from being damaged by rigid collisions; at the same time, the clamping design of the fixed frame can ensure that the protective frame is firmly connected to the drone body, avoiding loosening and displacement during flight, and ensuring the stability of the sensor detection distance.

[0008] Furthermore, the system control unit is electrically connected to the servo motor, and the system control unit is also electrically connected to the remote control terminal.

[0009] By adopting the above technical solution, the system control unit is a single circuit board that integrates an IMU, MCU, and barometer, with the barometer extending from the back of the control compartment. The system control unit and servo motors are independently powered by a battery. The system control unit communicates bidirectionally with the servo motors, IMU, barometer, and MCU, while the MCU communicates unidirectionally with the UAV flight control system. Furthermore, the system control unit establishes a highest-priority communication channel with a dedicated emergency switch on the remote control terminal. The system control unit can simultaneously receive commands from the remote control terminal, IMU / barometer monitoring data, and MCU judgment results, ensuring zero-delay information transmission. The unidirectional communication design between the MCU and the flight control system prevents emergency command transmission from being affected by flight control failures. The highest-priority communication channel ensures that the pilot can interrupt the automatic logic at any time and directly trigger the emergency procedure via the emergency switch, maximizing controllability.

[0010] Furthermore, the longitudinal section of the reset frame is in the shape of an inverted "[", and the top of the reset frame abuts against the flip cover.

[0011] By adopting the above technical solution, the inverted "[" shaped structure can form a closed parachute placement cavity, preventing the parachute from shifting during flight and ensuring smooth parachute deployment during ejection; at the same time, the top of the reset frame abuts against the flip cover, and the flip cover can be opened faster under the action of spring force.

[0012] Furthermore, the top of the reset frame extends through the placement chamber, and the reset frame is slidably connected to the placement chamber.

[0013] By adopting the above technical solution, the sliding connection between the reset frame and the placement compartment restricts the movement trajectory, allowing it to move only up and down along the axis of the placement compartment, thus avoiding deviation that could cause the parachute launch direction to deviate (such as oblique launch being blocked by the drone propellers).

[0014] Furthermore, the flip cover is provided in two sets, and the two sets of flip covers are symmetrically distributed.

[0015] By adopting the above technical solution, the symmetrically distributed flaps can flip synchronously to both sides along the rotating rod when triggered, forming an unobstructed top opening, ensuring that the parachute can be launched vertically upwards; the torsion spring is in a pre-tightened state when not triggered, and when the limiting plate disengages from the limiting groove, the torsion spring can release the torque instantly, causing the flaps to fully open within 0.3 seconds, greatly shortening the parachute opening preparation time and securing the best parachute opening opportunity in high-speed fall scenarios.

[0016] Furthermore, the spring is made of 304 stainless steel, and the top of the spring abuts against the reset frame.

[0017] By adopting the above technical solution, the 304 stainless steel spring has excellent corrosion resistance and elastic fatigue strength, and can maintain a pre-compressed state for a long time (the spring that presses down on the reset frame when not triggered). When triggered, it can stably release the elastic force, push the reset frame to move upward at a sufficient speed, and ensure that the parachute can be quickly deployed after it pops out of the placement compartment.

[0018] Furthermore, the outer surface and back of the flip cover are provided with limiting grooves, and the limiting grooves are quarter-circular.

[0019] By adopting the above technical solution, in the non-triggered state, the limiting plate is embedded in the limiting groove, and the locking force of the servo motor restricts the flip cover from flipping, ensuring that the flip cover is tightly closed; when triggered, the servo motor drives the limiting plate to rotate 180 degrees quickly, and the limiting plate completely disengages from the limiting groove without any residual jamming, avoiding delay in opening the flip cover due to jamming.

[0020] Furthermore, the limiting plate is arranged in a fan shape, and the limiting plate contacts the flip cover through the limiting groove.

[0021] By adopting the above technical solution, the compact structure of the fan-shaped limiting plate can reduce the space occupied during rotation, and can be embedded in the limiting groove to limit both flip covers at the same time, preventing the flip covers from flipping over on their own under the action of the torsion spring.

[0022] Furthermore, a buffer pad is connected to the lower part of the inner wall of the placement chamber, and the buffer pad is in contact with the reset frame.

[0023] By adopting the above technical solution, the buffer pad is made of high-density elastic rubber. Under the action of spring force, when the reset frame moves to the top of the placement chamber and contacts the top wall of the placement chamber, the buffer pad relieves the force on the reset frame. In the triggered state, the impact force of the reset frame can be buffered, avoiding wear caused by rigid contact between the reset frame and the top of the placement chamber, and extending the service life of the device.

[0024] In summary, the present invention has the following main advantages:

[0025] 1. This utility model, by setting up control components, a flip cover, a torsion spring, a spring and a parachute, combined with the automatic judgment and remote manual triggering mechanism of the system control unit, can quickly trigger the parachute opening procedure when the drone loses control and crashes, and avoid secondary danger by stopping the rotor, thus significantly improving the safety of high-altitude operations;

[0026] 2. This utility model uses elastic plastic material to make the main body of the protective frame, which is both lightweight and has a buffering performance, effectively protecting the thickness sensor from collision damage. At the same time, the sliding reset frame and symmetrical flip-top design ensure that the parachute is launched in an accurate direction and unfolds quickly, improving the success rate of rescue.

[0027] 3. With its buffer pad and resettable structure design, this utility model allows for quick reset after emergency use. Simply replace the parachute and press down the reset frame to drive the limit plate to relock the flip cover via the servo motor. This eliminates the need to disassemble the entire device, greatly reducing maintenance time and costs. Attached Figure Description

[0028] Figure 1 This is a schematic diagram of the structure of this utility model;

[0029] Figure 2 This is a schematic diagram of the flip-top structure of this utility model;

[0030] Figure 3 This is a schematic diagram of the cross-sectional structure of the control cabin of this utility model;

[0031] Figure 4 This is a schematic diagram of the cross-sectional structure of the placement compartment of this utility model;

[0032] Figure 5 For the present utility model Figure 1 Enlarged structural diagram at point A in the middle;

[0033] Figure 6 For the present utility model Figure 4 Enlarged structural diagram at point B.

[0034] In the diagram: 1. Main body of the protective frame; 101. Fixing frame; 102. Protective frame; 2. Control components; 201. Control compartment; 202. System control unit; 203. Battery; 204. Servo motor; 3. Storage compartment; 4. Spring; 5. Reset frame; 6. Pull rod; 7. Flip cover; 8. Rotating rod; 9. Torsion spring; 10. Limiting plate; 11. Limiting groove; 12. Parachute; 13. Buffer pad. Detailed Implementation

[0035] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and should not be construed as limiting the present invention.

[0036] The embodiments of this utility model will be described below based on its overall structure.

[0037] Example 1: A protective frame for a thickness measuring drone, such as Figures 1-6 As shown, the device includes a protective frame body 1. A control component 2 is connected to the top of the protective frame body 1. The control component 2 includes a control compartment 201 and a servo motor 204. The output end of the servo motor 204 is connected to a limit plate 10. A system control unit 202 and a battery 203 are installed inside the control compartment 201. A placement compartment 3 is connected to the top of the control compartment 201. A reset frame 5 is connected to the inside of the placement compartment 3 via a spring 4. A pull rod 6 is connected to the inner wall of the reset frame 5. A parachute 12 is placed on the top of the reset frame 5, and one end of the parachute 12 is fixed to the pull rod 6. Flip covers 7 are connected to both sides of the placement compartment 3 via rotating rods 8, and torsion springs 9 are sleeved on the outside of the rotating rods 8. The protective frame body 1 includes a fixing frame 101 and a protective cover 202. The protective frame 102 and the fixing frame 101 are clamped at the middle of the top of the drone. Both the fixing frame 101 and the protective frame 102 are made of elastic plastic. The elastic plastic material is both lightweight and impact-resistant: on the one hand, it can reduce the overall load of the drone and avoid affecting flight endurance and maneuverability; on the other hand, in daily inspection, if the drone slightly touches the structure under test (such as bridge railings or the outer wall of storage tanks), the protective frame 102 can buffer the impact force through its own deformation to prevent the thickness sensor from being damaged by rigid collision; at the same time, the clamping design of the fixing frame 101 can ensure that the protective frame is firmly connected to the drone body, avoid loosening and displacement during flight, and ensure the stability of the sensor detection distance.

[0038] See Figure 3 In the above embodiment, the system control unit 202 is electrically connected to the servo motor 204 and to the remote control terminal. The system control unit 202 is a circuit board that integrates an IMU, MCU, and barometer. The barometer extends out from the back of the control compartment 201. The system control unit 202 and the servo motor 204 are independently powered by the battery 203. The system control unit 202 communicates bidirectionally with the servo motor 204, IMU, barometer, and MCU, while the MCU communicates unidirectionally with the UAV flight control system. The system control unit 202 establishes a highest priority communication channel with the dedicated emergency switch of the remote control terminal. The system control unit 202 can simultaneously receive commands from the remote control terminal, IMU / barometer monitoring data, and MCU judgment results, ensuring that information transmission is without delay. The unidirectional communication design between the MCU and the flight control system can prevent the MCU from sending emergency commands when the flight control system malfunctions. The highest priority communication channel ensures that the pilot can interrupt the automatic logic at any time and directly trigger the emergency procedure through the emergency switch, maximizing controllability.

[0039] See Figure 3 and Figure 4In the above embodiment, the longitudinal section of the reset frame 5 is in the shape of an inverted "[", and the top of the reset frame 5 abuts against the flip cover 7. The inverted "[" structure can form a closed parachute 12 placement cavity to prevent the parachute 12 from shifting during flight and ensure that the parachute 12 unfolds smoothly during ejection. At the same time, the top of the reset frame 5 abuts against the flip cover 7, and the opening speed of the flip cover 7 can be accelerated under the action of the spring force 4.

[0040] See Figure 2 , Figure 3 and Figure 4 In the above embodiment, the top of the reset frame 5 passes through the placement compartment 3, and the reset frame 5 is slidably connected to the placement compartment 3. The sliding connection between the reset frame 5 and the placement compartment 3 restricts the movement trajectory, so that it can only move up and down along the axis of the placement compartment 3, avoiding deviation that would cause the parachute 12 to deviate in the ejection direction (such as being obliquely ejected and blocked by the drone propeller).

[0041] See Figures 1-5 In the above embodiment, the flip cover 7 is provided in two sets, and the two sets of flip covers 7 are symmetrically distributed. The symmetrically distributed flip covers 7 can be flipped to both sides synchronously along the rotating rod 8 when triggered, forming an unobstructed top opening, ensuring that the parachute pack 12 can be launched vertically upward. The torsion spring 9 is in a pre-tightened state when not triggered. When the limiting plate 10 is disengaged from the limiting groove 11, the torsion spring 9 can release the torque instantly, causing the flip cover 7 to fully open within 0.3 seconds, greatly shortening the parachute opening preparation time and securing the best parachute opening opportunity in high-speed fall scenarios.

[0042] See Figure 3 and Figure 4 In the above embodiment, the spring 4 is made of 304 stainless steel, and the top of the spring 4 abuts against the reset frame 5. The 304 stainless steel spring 4 has excellent corrosion resistance and elastic fatigue strength, and can maintain a pre-compressed state for a long time (the reset frame 5 presses down on the spring 4 when not triggered). When triggered, it can stably release the elastic force, push the reset frame 5 to move upward at a sufficient speed, and ensure that the parachute 12 can be quickly deployed after it pops out of the placement compartment 3.

[0043] See Figure 2 and Figure 5 In the above embodiment, the outer surface and back of the flip cover 7 are provided with limiting grooves 11, and the limiting grooves 11 are quarter-circular. In the non-triggered state, the limiting plate 10 is embedded in the limiting groove 11, and the locking force of the servo motor 204 restricts the flip cover 7 from flipping, ensuring that the flip cover 7 is tightly closed. When triggered, the servo motor 204 drives the limiting plate 10 to rotate 180 degrees quickly, and the limiting plate 10 completely disengages from the limiting groove 11 without any residual jamming, avoiding delay in opening the flip cover 7 due to jamming.

[0044] See Figure 2 , Figure 5 and Figure 6In the above embodiment, the limiting plate 10 is arranged in a fan shape, and the limiting plate 10 contacts the flip cover 7 through the limiting groove 11. The compact structure of the fan-shaped limiting plate 10 can reduce the space occupied during rotation, and can be embedded in the limiting groove 11 to limit the two flip covers 7 at the same time, preventing the flip covers 7 from flipping over on their own under the action of the torsion spring 9.

[0045] Example 2: To extend the service life of the device, Example 2 is an improvement on Example 1. (See attached document.) Figure 6 A buffer pad 13 is connected to the lower part of the inner wall of the placement chamber 3, and the buffer pad 13 is in contact with the reset frame 5. The buffer pad 13 is made of high-density elastic rubber. Under the action of the spring 4, when the reset frame 5 moves to the top of the placement chamber 3 and contacts the top wall of the placement chamber 3, the buffer pad 13 relieves the force on the reset frame 5. It can buffer the impact force of the reset frame 5 in the triggered state, avoid the rigid contact between the reset frame 5 and the top of the placement chamber 3 to avoid wear, and extend the service life of the device.

[0046] The implementation principle of this utility model is as follows: When a drone loses control due to flight control failure or severe impact, the IMU captures "attitude anomalies" in real time, and the barometer simultaneously calculates "high-speed descent." After the two types of data are transmitted to the MCU, they are cross-verified by a fusion algorithm. If the condition lasts for more than 0.5 seconds, the MCU sends a trigger command to the system control unit 202; or it can be manually triggered: the drone operator can send a trigger signal through a dedicated emergency switch. This signal is transmitted through the highest priority channel, and the signal interrupt module of the system control unit 202 immediately interrupts the MCU logic and directly starts the emergency procedure (which has a higher priority than automatic triggering and can override automatic judgment).

[0047] After receiving the trigger command, the system control unit 202 immediately sends a stop command marked with "forced execution" to the UAV flight control system via the MCU. The flight control system cuts off the motor power and stops the rotor. At the same time as the rotor stops, the system control unit 202 drives the servo motor 204 to rotate the limit plate 10 180 degrees quickly, so that the limit plate 10 is completely disengaged from the limit groove 11. The torsion spring 9 releases the torque, and the rotating rod 8 drives the two sets of flip covers 7 to flip to both sides simultaneously, so that the top opening of the placement compartment 3 is fully opened. The pre-compressed spring 4 releases the elastic force, pushing the reset frame 5 to move rapidly upward along the axis of the placement compartment 3. The reset frame 5 drives the parachute 12 to pop out of the placement compartment 3. The parachute 12 fully unfolds under the action of airflow and pulls the UAV through the lever 6, so that the UAV descends smoothly.

[0048] When resetting, the new parachute 12 is placed into the reset frame 5 and fixed on the pull rod 6. The reset frame 5 is pressed down to compress the spring 4 and close the flip cover 7. A "close command" is sent via remote control, and the servo motor 204 drives the limit plate 10 to engage with the limit groove 11 to complete the reset. The entire protective frame does not need to be disassembled, making maintenance convenient.

[0049] Although embodiments of the present invention have been shown and described, these specific embodiments are merely explanations of the present invention and are not intended to limit the invention. The specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. After reading this specification, those skilled in the art may make modifications, substitutions, and variations to the embodiments as needed without departing from the principles and spirit of the present invention, provided that such modifications, substitutions, and variations are within the scope of the claims of the present invention and are protected by patent law.

Claims

1. A protective frame for a thickness-measuring drone, comprising a protective frame body (1), characterized in that: The protective frame body (1) is connected to a control component (2) at the top. The control component (2) includes a control compartment (201) and a servo motor (204). The output end of the servo motor (204) is connected to a limit plate (10). The control compartment (201) is equipped with a system control unit (202) and a battery (203). The control compartment (201) is connected to a placement compartment (3) at the top. The placement compartment (3) is connected to a reset frame (5) through a spring (4). The inner wall of the reset frame (5) is connected to a pull rod (6). A parachute (12) is placed on the top of the reset frame (5), and one end of the parachute (12) is fixed to the pull rod (6). The two sides of the placement compartment (3) are connected to flip covers (7) through rotating rods (8), and torsion springs (9) are sleeved on the outside of the rotating rods (8).

2. The protective frame of a thickness-measuring drone according to claim 1, characterized in that: The main body (1) of the protective frame includes a fixing frame (101) and a protective frame (102). The fixing frame (101) is clamped in the middle of the top of the drone. Both the fixing frame (101) and the protective frame (102) are made of elastic plastic.

3. The protective frame of a thickness-measuring drone according to claim 1, characterized in that: The system control unit (202) is electrically connected to the servo motor (204), and the system control unit (202) is electrically connected to the remote control terminal.

4. The protective frame of a thickness-measuring drone according to claim 1, characterized in that: The longitudinal section of the reset frame (5) is inverted "[" shape, and the top of the reset frame (5) abuts against the flip cover (7).

5. The protective frame of a thickness-measuring drone according to claim 1, characterized in that: The top of the reset frame (5) passes through the placement chamber (3), and the reset frame (5) is slidably connected to the placement chamber (3).

6. The protective frame of a thickness-measuring drone according to claim 1, characterized in that: The flip cover (7) is provided in two sets, and the two sets of flip covers (7) are symmetrically distributed.

7. The protective frame of a thickness-measuring drone according to claim 1, characterized in that: The spring (4) is made of 304 stainless steel, and the top of the spring (4) abuts against the reset frame (5).

8. The protective frame of a thickness-measuring drone according to claim 6, characterized in that: The flip cover (7) has a limiting groove (11) on its outer surface and back, and the limiting groove (11) is a quarter circle.

9. The protective frame of a thickness-measuring drone according to claim 8, characterized in that: The limiting plate (10) is arranged in a fan shape, and the limiting plate (10) contacts the flip cover (7) through the limiting groove (11).

10. The protective frame of a thickness-measuring drone according to claim 1, characterized in that: A buffer pad (13) is connected to the lower part of the inner wall of the placement chamber (3), and the buffer pad (13) is in contact with the reset frame (5).

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