Aeromagnetic probe system of unmanned aerial vehicle and unmanned aerial vehicle equipped with aeromagnetic probe system
By adopting a sliding connection and positioning component design in the UAV aeromagnetic probe system, combined with clamping parts and sealing structure, the problems of insufficient rigidity and poor sealing of folding probes are solved, improving data stability and portability, and reducing maintenance costs.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- QINGDAO HAIYUEHUI TECH CO LTD
- Filing Date
- 2025-07-16
- Publication Date
- 2026-05-08
AI Technical Summary
In existing UAV aeromagnetic probe systems, the folding probes lack rigidity when unfolded, are prone to vibration, and have unstable data quality. Furthermore, the folding joints have poor sealing, are easily worn, have reduced waterproof and dustproof performance, and exposed cables are easily damaged, increasing maintenance costs.
The first probe is installed inside the electronic compartment assembly and slidably connected to the second probe. The overall length is infinitely adjustable through the positioning component. Combined with clamping, locking and sealing structures, the positional accuracy and stability of the probe in the locked state are ensured, thereby improving the protection performance.
This has improved the stability and data quality of the UAV aeromagnetic probe system, reduced displacement caused by vibration, enhanced portability and protection performance, and lowered maintenance costs.
Smart Images
Figure CN224216884U_ABST
Abstract
Description
Technical Field
[0001] This application belongs to the field of unmanned aerial vehicle (UAV) equipment technology, and in particular relates to a UAV aeromagnetic probe system and a UAV equipped with it. Background Technology
[0002] Unmanned aerial vehicle (UAV) aeromagnetic surveying is a technology that utilizes UAV platforms to detect and measure the Earth's magnetic field. It is widely used in fields such as geological exploration, mineral resource surveys, and environmental monitoring. The airborne magnetometer is the core equipment in aeromagnetic surveying, capable of recording subtle changes in the Earth's magnetic field at a high precision.
[0003] Existing technologies typically use drones with probes carrying airborne magnetometers to reduce electromagnetic interference and improve detection accuracy. Drone airborne magnetometer probes mainly include fixed probes and folding probes. Fixed probes have an inadjustable length, which affects data quality, and they occupy a lot of space during transportation and storage, resulting in poor portability. In contrast, folding probes can adjust their length according to different tasks such as low-altitude high-precision detection or high-altitude rapid scanning, thus ensuring good data quality, enhancing portability, and occupying less space.
[0004] However, the folding probe lacks rigidity when unfolded, and it is prone to vibration when the drone flies at high speed, making it difficult to stabilize the data quality. Furthermore, the sealing at the folding joint is weak, and it is prone to wear after long-term use, resulting in a decrease in waterproof and dustproof performance and making it easy to cause signal interference or equipment damage. In addition, the exposed cables after folding are easily damaged, increasing subsequent maintenance costs. Utility Model Content
[0005] To address the shortcomings of related technologies, this application provides an unmanned aerial vehicle (UAV) aeromagnetic probe system and an UAV equipped with it. By placing the first probe inside the electronic compartment assembly and sliding it relative to the second probe, the overall structure is stabilized, avoiding the problem of insufficient rigidity after deployment. Furthermore, the overall length of the first and second probes can be infinitely adjusted through a positioning component, improving adaptability to different tasks, further ensuring stable and reliable data, and avoiding a series of problems caused by folding joint designs.
[0006] On the one hand, this application provides an unmanned aerial vehicle (UAV) aeromagnetic probe system, comprising:
[0007] The electronic compartment component is hollow inside and has two through holes on each of its two opposite side walls;
[0008] The first probe is located inside the electronic compartment assembly and extends outward through the two through holes at both ends;
[0009] The second probe is slidably connected to both ends of the first probe.
[0010] A positioning component is sleeved on the first probe and the second probe and located at their connection point. The positioning component is used to stop or release the relative sliding of the first probe and the second probe, so as to adjust the distance between the end of the second probe away from the first probe and the electronic compartment assembly.
[0011] In some embodiments, the positioning component includes:
[0012] The clamping element has one end fixedly sleeved on the outside of the first probe or the second probe, and the other end is provided with a clamping structure;
[0013] A locking element is slidably sleeved on the second probe or the first probe relative to the clamping element. One end of the locking element is used to slide to wrap around the clamping structure or to slide away from the clamping structure, so as to stop or release the relative sliding between the first probe and the second probe.
[0014] In some embodiments, the first probe is hollow inside, the second probe is slidably disposed inside the first probe, one end of the clamping member is fixedly sleeved on the end of the first probe away from the electronic compartment assembly, the other end of the clamping member is provided with the clamping structure, the locking member is slidably sleeved on the outside of the second probe, and the end of the locking member near the clamping member is used to slide to wrap around the clamping structure, or to slide away from the clamping structure, so as to stop or release the relative sliding of the first probe and the second probe.
[0015] In some embodiments, the second probe is hollow inside, the first probe is slidably disposed inside the second probe, one end of the clamping member is fixedly sleeved on the end of the second probe near the electronic compartment assembly, the other end of the clamping member is provided with the clamping structure, and the locking member is slidably sleeved on the outside of the first probe. The end of the locking member near the clamping member is used to slide to wrap around the clamping structure, or to slide away from the clamping structure, so as to stop or release the relative sliding between the first probe and the second probe.
[0016] In some embodiments, the clamping structure further includes:
[0017] The clamping portion, at least two of the clamping portions are arranged around the axis of the first probe or the second probe, one end of the two clamping portions is connected to the clamping member, and the other end is used to move closer to or away from the axis of the first probe or the second probe;
[0018] A guide portion is provided on the end face of the clamping portion away from the first probe or the second probe, and the guide portion is used to make the thickness of the clamping portion gradually increase from one end away from the clamping member to the other end.
[0019] In some embodiments, the positioning component further includes:
[0020] The clamping structure and the clamping member are provided with external threads, and the inner wall of the locking member is provided with corresponding internal threads, so that after the clamping structure extends into the locking member, it is then threadedly connected to the clamping member.
[0021] In some embodiments, the positioning component further includes:
[0022] The first sealing groove is located between the external thread and the clamping member;
[0023] The first sealing element is disposed within the sealing groove and located between the clamping element and the locking element.
[0024] In some embodiments, the electronic compartment assembly further includes:
[0025] The container body is hollow inside and has two mounting openings on two adjacent outer walls. The through hole is provided in the container body and the through hole is perpendicular to the two mounting openings.
[0026] The two mounting covers are respectively placed over the two mounting openings and connected to the compartment body;
[0027] The limiting cover, the second of which is sleeved on the outside of the first probe and connected to the chamber body respectively, and the limiting cover is placed on the through hole;
[0028] The second sealing groove is located at one end of the mounting cover and the limiting cover near the chamber body;
[0029] The second seal is disposed in the second sealing groove, and the second seal is located between the mounting cover and the chamber body, or between the limiting cover and the chamber body.
[0030] In some embodiments, the UAV aeromagnetic probe system further includes:
[0031] The two end caps are respectively sleeved on the two second probe rods and located at the end of the second probe rod away from the first probe rod. The end caps are threadedly connected to the second probe rods.
[0032] A third sealing groove is provided inside the end cap;
[0033] The third sealing element is disposed in the third sealing groove and located between the end cap and the second probe.
[0034] On the other hand, this application also provides an unmanned aerial vehicle (UAV) equipped with any of the above-described UAV aeromagnetic probe systems.
[0035] In summary, this application provides an aeromagnetic probe system for unmanned aerial vehicles (UAVs) and a UAV equipped with it. The design of placing the first probe within the electronic compartment assembly and sliding it relative to the second probe ensures overall structural stability and avoids insufficient rigidity after deployment. Furthermore, the positioning assembly allows for stepless adjustment of the overall length of the first and second probes, improving adaptability to different tasks and further ensuring stable and reliable data, avoiding a series of problems caused by folding joint designs. The synergistic action of the clamping components, clamping structure, and locking components ensures the positional accuracy and stability of the first and second probes in the locked state, preventing displacement due to vibration during flight. The surrounding design of at least two clamping parts enables uniform clamping of either the first or second probe, resulting in more stable and reliable positioning. The gradually thickening guide section allows for more precise control of the clamping force, enabling fine-tuning and ensuring stable clamping of the first or second probe rod. A threaded connection securely integrates the locking element with the clamping structure, ensuring clamping stability and reliability. The cooperation between the first seal and the first sealing groove effectively enhances the protective performance and service life of the positioning components, preventing external environmental factors from corroding the clamping structure and threaded connections. The chamber body is sealed to the mounting cover and the limiting cover using corresponding numbers of second seals, achieving effective sealing and protection of the internal environment of the chamber body, significantly improving the system's protection level and reliability. The threaded connection of the end cap and the cooperation of the third seal provide effective sealing protection, significantly improving the environmental protection performance inside the second probe rod.
[0036] Other features and advantages of this application will be set forth in the description which follows, and in part will be obvious from the description or may be learned by practicing the invention. The objectives and other advantages of this application may be realized and obtained by means of the structures pointed out in the description, claims and drawings. Attached Figure Description
[0037] The accompanying drawings, which are included to provide a further understanding of this application and form part of this application, illustrate exemplary embodiments and are used to explain this application, but do not constitute an undue limitation of this application. In the drawings:
[0038] Figure 1 This is a perspective view of the UAV aeromagnetic probe system of this application;
[0039] Figure 2 This is a partial exploded view of the UAV aeromagnetic probe system of this application;
[0040] Figure 3 A perspective view of the positioning components of the UAV aeromagnetic probe system of this application;
[0041] Figure 4This is a front view of the positioning components of the UAV aeromagnetic probe system of this application;
[0042] Figure 5 This is a side view of the positioning components of the UAV aeromagnetic probe system of this application;
[0043] Figure 6 For the UAV aeromagnetic probe system of this application Figure 5 AA section diagram;
[0044] Figure 7 This is a perspective view of the connection relationship of the second probe in the UAV aeromagnetic probe system of this application;
[0045] Figure 8 This is a front view of the connection relationship of the second probe in the UAV aeromagnetic probe system of this application;
[0046] Figure 9 For the UAV aeromagnetic probe system of this application Figure 8 Middle BB section view;
[0047] Figure 10 A schematic diagram of the UAV aeromagnetic probe system installed for the UAV of this application.
[0048] In the picture:
[0049] 100. Electronic compartment assembly; 101. Compartment body; 102. Mounting cover; 103. Limiting cover; 104. Second sealing groove; 105. Second sealing element; 200. First probe; 300. Second probe; 400. Positioning assembly; 401. Clamping element; 402. Locking element; 403. Clamping structure; 4031. Clamping part; 4032. Guide part; 404. First sealing groove; 405. First sealing element; 500. End cap; 600. Third sealing groove; 700. Third sealing element; 800. UAV body. Detailed Implementation
[0050] The technical solutions in the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of them. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the scope of protection of this application.
[0051] In the description of this application, it should be understood that the terms "center", "lateral", "longitudinal", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.
[0052] The terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined as "first," "second," or "third" may explicitly or implicitly include one or more of that feature.
[0053] In the description of this application, it should be noted that, unless otherwise expressly specified and limited, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal communication between two components. Those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances. Specific Implementation Example 1
[0055] Reference Appendix Figure 1 To be continued Figure 10 , Figure 1 This is a perspective view of the UAV aeromagnetic probe system of this application; Figure 2 This is a partial exploded view of the UAV aeromagnetic probe system of this application; Figure 3 A perspective view of the positioning components of the UAV aeromagnetic probe system of this application; Figure 4 This is a front view of the positioning components of the UAV aeromagnetic probe system of this application; Figure 5 This is a side view of the positioning components of the UAV aeromagnetic probe system of this application; Figure 6 For the UAV aeromagnetic probe system of this application Figure 5 AA section diagram; Figure 7 This is a perspective view of the connection relationship of the second probe in the UAV aeromagnetic probe system of this application; Figure 8 This is a front view of the connection relationship of the second probe in the UAV aeromagnetic probe system of this application; Figure 9 For the UAV aeromagnetic probe system of this application Figure 8 Middle BB section view; Figure 10 A schematic diagram of the UAV aeromagnetic probe system installed on the UAV of this application; the following is in conjunction with the attached diagram. Figure 1 To be continued Figure 10 Specific embodiments are described below.
[0056] Reference Appendix Figure 1 This application provides an unmanned aerial vehicle (UAV) aeromagnetic probe system, including an electronic compartment assembly 100, a first probe 200, a second probe 300, and a positioning assembly 400.
[0057] The electronic compartment assembly 100 is hollow inside and has two through holes on its two opposite side walls. A first probe 200 is disposed inside the electronic compartment assembly 100 and extends outward through the two through holes at both ends. Two second probes 300 are slidably connected to the two ends of the first probe 200. A positioning component 400 is sleeved on the first probe 200 and the second probe 300 and is located at the connection between them. The positioning component 400 is used to stop or release the relative sliding of the first probe 200 and the second probe 300, so as to adjust the distance between the end of the second probe 300 away from the first probe 200 and the electronic compartment assembly 100.
[0058] Specifically, the hollow interior of the electronic compartment component 100 is used to install electronic components and equipment such as the data acquisition host, GNSS / IMU integrated navigation system, power management system, and wireless transmission module.
[0059] The electronic housing assembly 100 is designed with an internal hollow structure and has two opposing through holes. The first probe 200 is located inside the electronic housing assembly 100 and passes through the through holes. This connection method is used to lay the foundation for the stability of the overall structure of the UAV aeromagnetic probe system.
[0060] The first probe 200 and the second probe 300 are hollow rod-shaped components. Preamplifiers, connecting cables and other hardware devices can be installed inside the first probe 200 and the second probe 300, so as to integrate various hardware devices inside in conjunction with the electronic compartment assembly 100, reduce the probability of hardware damage and avoid the problem of exposed cables after the folding probe is retracted.
[0061] The first probe 200 and the second probe 300 are made of lightweight, high-strength engineering plastics, primarily PC (polycarbonate) and carbon fiber, which reduces weight and volume, increases range, and lowers manufacturing costs.
[0062] The two ends of the first probe 200 extend outward through through holes and slide to connect with the second probe 300. The distance between the two ends of the second probe 300 and the electronic compartment assembly 100 can be adjusted according to actual needs, thereby adjusting the overall length of the UAV aeromagnetic probe system to meet different flight and detection requirements.
[0063] With other hardware remaining the same, the pull-out structure of the first probe 200 and the second probe 300 will have a further reduction in length and width compared to the fixed probe and the folding probe, thereby reducing the overall size of the equipment, reducing the space occupied during transportation and storage, and enhancing portability.
[0064] The positioning component 400 is located at the connection between the first probe 200 and the second probe 300. The positioning component 400 can lock or release the sliding position. The specific positioning operation can be quickly adjusted and fixed according to the actual application scenario.
[0065] Compared to fixed probes and folding probes whose lengths are fixed after unfolding, the overall length of the first probe 200 and the second probe 300 can be freely set and adjusted through the positioning component 400. This allows for rapid response and adaptation to various UAV carriers and magnetic detection equipment, reducing operation time and improving work efficiency.
[0066] Based on the cooperation of the electronic housing component 100, the first probe 200, the second probe 300 and the positioning component 400, the overall length of the UAV aeromagnetic probe system can be flexibly adjusted, making it suitable for aeromagnetic measurement tasks with different altitudes and different accuracy requirements.
[0067] Furthermore, the structural design combining sliding connection and positioning component 400 makes the adjustment process more convenient and faster, and the positioning effect is stable and reliable, thereby significantly improving the efficiency and accuracy of aeromagnetic exploration missions.
[0068] The positioning component 400 also improves the overall safety and stability of the UAV aeromagnetic probe system, effectively preventing unexpected position changes caused by vibration or impact, and enhancing the adaptability of the UAV aeromagnetic probe system in complex flight environments.
[0069] Reference Appendix Figure 1 , Figures 3 to 6 In some embodiments, the positioning component 400 includes a clamping member 401 and a locking member 402. One end of the clamping member 401 is fixedly sleeved on the outside of the first probe 200 or the second probe 300, and the other end is provided with a clamping structure 403. The locking member 402 is slidably sleeved on the outside of the second probe 300 or the first probe 200 relative to the clamping member 401. One end of the locking member 402 is used to slide to wrap around the clamping structure 403, or to slide away from the clamping structure 403, so that the relative sliding of the first probe 200 and the second probe 300 stops or is released.
[0070] Specifically, both clamping component 401 and locking component 402 are cylindrical parts, made of lightweight, high-strength engineering plastics, primarily PC polycarbonate (PC) and carbon fiber, which reduces weight and volume, increases range, and lowers manufacturing costs.
[0071] The clamping member 401 is fixed to the outside of the first probe rod 200 or the second probe rod 300, and its other end is provided with a clamping structure 403 for cooperating with the locking member 402.
[0072] The locking member 402 is slidably disposed on the second probe 300 or the first probe 200 relative to the clamping member 401, and the locking member 402 and the clamping structure 403 are engaged or disengaged through relative sliding.
[0073] When the locking member 402 slides to the clamping structure 403, the clamping structure 403 is squeezed by the locking member 402, thereby tightly clamping the probe rod, stopping the relative sliding between the first probe rod 200 and the second probe rod 300, and achieving stable positioning.
[0074] When the locking member 402 slides away from the clamping structure 403, the clamping structure 403 returns to its original state to release the first probe 200 or the second probe 300, allowing both to slide and readjust their length.
[0075] The clamping member 401 and the locking member 402 have a simple and reliable structure, which can quickly lock or release the relative position of the second probe 300 and the first probe 200, making the operation convenient and efficient; and it will not restrict the relative position of the second probe 300 and the first probe 200 in the opposite direction. Locking can be achieved when the two slide relative to each other to any position, thereby achieving the function of stepless adjustment.
[0076] Meanwhile, the synergistic effect of the clamping structure 403 and the locking element 402 can ensure the positional accuracy and stability of the probe in the locked state, and prevent the first probe 200 and the second probe 300 from being displaced due to vibration during flight, which significantly improves the reliability and measurement accuracy of the UAV aeromagnetic probe system.
[0077] In some embodiments, the first probe 200 is hollow inside, the second probe 300 is slidably disposed inside the first probe 200, one end of the clamping member 401 is fixedly sleeved on the end of the first probe 200 away from the electronic compartment assembly 100, the other end of the clamping member 401 is provided with a clamping structure 403, and the locking member 402 is slidably sleeved on the outside of the second probe 300. The end of the locking member 402 near the clamping member 401 is used to slide to wrap around the clamping structure 403, or to slide away from the clamping structure 403, so that the relative sliding between the first probe 200 and the second probe 300 stops or is released.
[0078] Specifically, the first probe 200 is designed with a hollow structure, allowing the second probe 300 to slide into the first probe 200, thus enabling the length adjustment function between the first probe 200 and the second probe 300.
[0079] The clamping member 401 is fixed to the end of the first probe 200 away from the electronic compartment assembly 100 and extends outward to provide a clamping structure 403; the locking member 402 is slidably sleeved on the outer surface of the second probe 300.
[0080] When the locking member 402 slides along the second probe 300 toward the clamping structure 403, it applies an external force to the clamping structure 403, causing the clamping structure 403 to retract and clamp the second probe 300, thereby restricting the relative sliding between the first probe 200 and the second probe 300, achieving a fast and stable positioning effect.
[0081] When the locking member 402 slides away from the clamping structure 403, the clamping structure 403 releases the second probe 300, and the second probe 300 can slide freely within the first probe 200, thereby adjusting the length.
[0082] By sliding the second probe 300 inside the first probe 200, a more compact and stable overall structure is formed, which effectively reduces wind resistance and vibration during flight, and improves the flight stability and aeromagnetic detection accuracy of the system. Furthermore, through the cooperation of the clamping structure 403 and the locking element 402, the precise adjustment and firm fixation of the extension position of the second probe 300 can be achieved quickly, making the operation convenient and efficient.
[0083] In other embodiments, the second probe 300 is hollow inside, the first probe 200 is slidably disposed inside the second probe 300, one end of the clamping member 401 is fixedly sleeved on the end of the second probe 300 near the electronic compartment assembly 100, the other end of the clamping member 401 is provided with a clamping structure 403, and the locking member 402 is slidably sleeved on the outside of the first probe 200. The end of the locking member 402 near the clamping member 401 is used to slide to wrap around the clamping structure 403, or to slide away from the clamping structure 403, so that the relative sliding between the first probe 200 and the second probe 300 stops or is released.
[0084] Specifically, the second probe 300 is designed as a hollow structure, and the first probe 200 is slidably inserted into the second probe 300 to realize the length adjustment function between the first probe 200 and the second probe 300.
[0085] The outer diameter of the second probe 300 is larger than the outer diameter of the first probe 200 and the inner diameter of the through hole. When the second probe 300 slides into the electronic compartment assembly 100, the through hole can restrict the second probe 300 from sliding into the electronic compartment assembly 100, thereby preventing the second probe 300 from leaving the normal sliding track and damaging the electronic components inside the electronic compartment assembly 100.
[0086] The clamping member 401 is fixed to one end of the second probe 300 near the electronic compartment assembly 100, and the other end of the clamping member 401 is provided with a clamping structure 403; the locking member 402 is slidably sleeved on the outside of the first probe 200.
[0087] When the locking member 402 slides toward the clamping structure 403, it will press the clamping structure 403 to clamp the first probe 200, thereby fixing the relative position between the first probe 200 and the second probe 300.
[0088] When the locking member 402 slides away from the clamping structure 403, the clamping structure 403 releases the first probe 200, and the first probe 200 can slide freely within the second probe 300 to quickly adjust the length.
[0089] By designing the second probe 300 to be fitted outside the first probe 200, the overall rigidity and stability of the system are improved, effectively reducing the risk of vibration and deformation during flight.
[0090] The external design of the clamping structure 403 and the locking element 402 facilitates quick operation and intuitive control, ensuring the precise positioning and stable fixation of the overall length of the first probe 200 and the second probe 300.
[0091] Reference Appendix Figure 6 In some embodiments, the clamping structure 403 further includes a clamping portion 4031 and a guiding portion 4032. At least two clamping portions 4031 are arranged around the axis of the first probe 200 or the second probe 300. One end of the two clamping portions 4031 is connected to the clamping member 401, and the other end is used to move closer to or away from the axis of the first probe 200 or the second probe 300. The guiding portion 4032 is provided on the end face of the clamping portion 4031 away from the first probe 200 or the second probe 300. The guiding portion 4032 is used to make the thickness of the clamping portion 4031 gradually increase from the end away from the clamping member 401 to the other end.
[0092] Specifically, the clamping part 4031 is a flexible sheet-like component, and there is a movable gap between two adjacent clamping parts 4031, so that the movement of the two clamping parts 4031 does not affect each other.
[0093] The locking member 402 presses against the clamping part 4031, causing it to store elastic potential energy and move in the pressing direction until the locking member 402 moves away from the clamping part 4031 to release it. Then, the clamping part 4031 releases its elastic potential energy to automatically reset to a state parallel to the axis of the first probe 200 or the second probe 300.
[0094] The clamping structure 403 is arranged around the axis of the first probe 200 or the second probe 300 by at least two clamping parts 4031. One end of the clamping part 4031 is fixedly connected to the clamping member 401, and the other end is free to move, and can move closer to or away from the axis of the first probe 200 or the second probe 300.
[0095] When the locking member 402 slides toward the clamping part 4031, the guide part 4032 on the clamping part 4031 contacts the inner wall of the locking member 402. Since the thickness of the guide part 4032 gradually increases from one end away from the clamping member 401 to the other end along the axial direction, the locking member 402 will squeeze the clamping part 4031 toward the axial direction of the first probe 200 or the second probe 300 through the guide part 4032 during the sliding process, thereby achieving tight clamping of the first probe 200 or the second probe 300, and thus fixing the relative position of the first probe 200 and the second probe 300.
[0096] When the locking member 402 slides away from the clamping structure 403, the clamping part 4031 releases its elastic stored energy to automatically move away from the axis of the first probe 200 or the second probe 300, thereby releasing the first probe 200 or the second probe 300 and realizing the function of quickly adjusting the relative position of the first probe 200 and the second probe 300.
[0097] It should be noted that the number of clamping parts 4031 should be set according to the actual situation, and the number of guide parts 4032 corresponds to the number of clamping parts 4031. The more clamping parts 4031 there are, the better the effect of their force on fixing the first probe rod 200 or the second probe rod 300.
[0098] The multiple clamping parts 4031 surround design can achieve uniform clamping of the first probe 200 or the second probe 300, making the positioning and fixing more stable and reliable.
[0099] The gradually thickening structure of the guide section 4032 makes the control of clamping force more precise and enables fine adjustment, ensuring that the clamping section 4031 can smoothly clamp the first probe 200 or the second probe 300 and avoid local stress concentration.
[0100] Optionally, the inner wall of the locking member 402 is provided with a tapered surface structure to cooperate with the clamping structure 403. The tapered surface structure is used to make the inner diameter of the locking member 402 gradually decrease from its open end to its closed end, thereby cooperating with the clamping structure 403 that gradually extends into the locking member 402 to press against the first probe 200 or the second probe 300.
[0101] Reference Appendix Figure 3 , Figure 4 as well as Figure 6 In some embodiments, the clamping structure 403 and the clamping member 401 are provided with external threads, and the inner wall of the locking member 402 is provided with corresponding internal threads, so that after the clamping structure 403 extends into the locking member 402, it is then threadedly connected to the clamping member 401.
[0102] Specifically, the clamping structure 403 and the clamping member 401 are provided with external threads, and the inner wall of the locking member 402 is provided with internal threads. The locking member 402 and the clamping member 401 are connected by the combination of internal and external threads.
[0103] The pitch and thread specifications of external and internal threads should be adjusted according to actual usage requirements and clamping force.
[0104] When the locking member 402 is fitted onto the clamping structure 403 and rotates relative to the clamping member 401, the internal thread on the inner wall of the locking member 402 engages with the corresponding external thread, causing the locking member 402 to approach the clamping member 401 and gradually apply radial pressure to the clamping structure 403, forcing the clamping structure 403 to contract radially, thereby achieving the clamping and fixing of the first probe 200 or the second probe 300.
[0105] When the probe length needs to be adjusted, the locking member 402 is rotated in the opposite direction to disengage the thread, the clamping structure 403 returns to its original state, and the first probe 200 or the second probe 300 is released so that the first probe 200 and the second probe 300 can slide relative to each other for length adjustment.
[0106] Reference Appendix Figures 3 to 6 In some embodiments, the positioning component 400 further includes a first sealing groove 404 and a first sealing member 405. The first sealing groove 404 is located between the external thread and the clamping member 401; the first sealing member 405 is located in the sealing groove and between the clamping member 401 and the locking member 402.
[0107] Specifically, a first sealing groove 404 is provided between the external thread and the clamping member 401, and a first sealing member 405 is installed in the sealing groove, thereby achieving a seal between the clamping member 401 and the locking member 402.
[0108] The first seal 405 includes an O-ring, a V-ring, or a rectangular cross-section seal to meet different sealing requirements.
[0109] The material of the first seal 405 should be selected from high-temperature resistant, wear-resistant, and corrosion-resistant rubber or elastomer materials according to the actual environmental requirements.
[0110] When the locking member 402 is tightened to the clamping structure 403, the first sealing member 405 deforms under axial compression. The sealing member fits tightly against the inner surfaces of the clamping member 401 and the locking member 402, effectively preventing external dust, moisture or other foreign objects from entering the positioning assembly 400, thereby protecting the threaded connection from corrosion or contamination.
[0111] When the locking element 402 is released, the seal returns to its original state, ensuring that the sealing effect can be reused.
[0112] By setting the first seal 405, the protective performance and service life of the positioning component 400 are effectively improved, avoiding the erosion of the clamping structure 403 and threaded connection parts by external environmental factors such as moisture, dust or corrosive substances. In addition, the sealing effect is stable and reliable, easy to maintain and replace, and can significantly reduce the frequency and cost of maintenance, further enhancing the adaptability and reliability of the UAV aeromagnetic probe system.
[0113] The design of the threaded locking and pressing first seal 405 enhances the rigid connection performance, increases friction, and reduces mechanical vibration, thereby improving the overall stability of the first probe 200 and the second probe 300 in high-speed flight or complex terrain. Furthermore, the threaded retraction and pull-out structure design of the first probe 200 and the second probe 300 avoids the problem of snap-on aging in traditional connection methods, reducing risks and lowering later maintenance costs.
[0114] Reference Appendix Figure 1 and Figure 2 In some embodiments, the electronic compartment assembly 100 further includes: a compartment body 101, a mounting cover 102, a limiting cover 103, a second sealing groove 104, and a second sealing element 105. The compartment body 101 is hollow inside and has two mounting openings through adjacent outer walls. Through holes are provided on the compartment body 101, and the through holes are perpendicular to the through directions of the two mounting openings. The two mounting covers 102 are respectively placed on the two mounting openings and connected to the compartment body 101. The two limiting covers 103 are sleeved on the outside of the first probe 200 and respectively connected to the compartment body 101. The limiting covers 103 are placed on the through holes. The second sealing groove 104 is provided at one end of the mounting cover 102 and the limiting cover 103 near the compartment body 101. The second sealing element 105 is provided in the second sealing groove 104 and is located between the mounting cover 102 and the compartment body 101, or between the limiting cover 103 and the compartment body 101.
[0115] Specifically, the internal structure of the compartment 101 is hollow, and two mounting ports are provided on the two adjacent outer walls to facilitate the installation and maintenance of internal electronic components; the through holes provided on the compartment 101 are perpendicular to the direction of the two mounting ports to facilitate the installation and positioning of the first probe 200.
[0116] Mounting cover 102 is used to close the mounting opening, while limiting cover 103 is used to fix the first probe 200 and close the through hole.
[0117] The second sealing groove 104 and the second sealing element 105 are disposed at the connection between the mounting cover 102, the limiting cover 103 and the chamber 101. When the mounting cover 102 or the limiting cover 103 is fixedly connected to the chamber 101, the second sealing element 105 is subjected to axial compression to produce a sealing effect, effectively preventing external moisture, dust and other foreign objects from entering the interior of the chamber 101, and ensuring the stable operation of the electronic components inside the chamber 101.
[0118] The connection methods for the mounting cover 102 and the limiting cover 103 include threaded connection, snap-fit connection or quick-plug connection, to meet different maintenance convenience requirements.
[0119] The second seal 105 should be a sealing ring made of different materials, including silicone, fluororubber or other high-performance sealing materials, depending on the actual sealing requirements.
[0120] The position and size of the through holes and mounting openings should also be flexibly adjusted according to specific needs to adapt to the installation requirements of different electronic components, or to match the connection method of the first probe 200.
[0121] The compartment body 101, mounting cover 102, and limiting cover 103 are made of lightweight, high-strength engineering plastics, mainly PC polycarbonate (PC) and carbon fiber, which reduces weight and volume, increases endurance, and improves protective performance.
[0122] The hopper 101 is sealed to the mounting cover 102 and the limiting cover 103 by a corresponding number of second sealing elements 105, which effectively seals and protects the internal environment of the hopper 101, and significantly improves the system protection level and reliability.
[0123] The chamber body 101 and the first probe 200 are securely connected by a limiting cover 103, which can effectively prevent the first probe 200 from loosening and improve the stability of the overall structure.
[0124] The detachable structure design of the mounting cover 102 and the limiting cover 103 facilitates quick disassembly and maintenance of electronic components inside the housing 101, further improving the maintenance efficiency and adaptability of the UAV aeromagnetic probe system.
[0125] Reference Appendix Figure 1 , Figures 7 to 9 In some embodiments, two end caps 500 are respectively sleeved on the two second probe rods 300 and located at the end of the second probe rod 300 away from the first probe rod 200. The end caps 500 are threadedly connected to the second probe rods 300. A third sealing groove 600 is provided inside the end caps 500. A third sealing element 700 is provided inside the third sealing groove 600 and located between the end caps 500 and the second probe rods 300.
[0126] Specifically, the end cap 500 is threaded to the end of the second probe 300 away from the first probe 200 to seal the port of the second probe 300 and achieve closed protection inside the second probe 300.
[0127] The material and shape of the third seal 700 should be flexibly selected according to the specific requirements of the application environment, including O-rings, V-rings or composite seals.
[0128] The end cap 500 is made of corrosion-resistant aluminum alloy, engineering plastics, or composite materials to further improve the structure's lightweight and durability.
[0129] A third sealing groove 600 is provided inside the end cap 500 and a third sealing element 700 is installed. When the end cap 500 is tightened with the second probe rod 300, the third sealing element 700 undergoes elastic deformation under axial compressive force, tightly fitting the contact surface between the end cap 500 and the second probe rod 300, thereby forming a reliable sealing structure. This effectively prevents foreign objects such as water vapor and dust from entering the probe rod, protects the internal components of the probe rod, extends the overall service life of the UAV aeromagnetic probe rod system, and enhances the system stability.
[0130] The threaded connection of the end cap 500 and the cooperation of the third seal 700 provide effective sealing protection for the second probe 300, significantly improving the environmental protection performance inside the second probe 300.
[0131] The 500 end cap sealing structure is simple to operate and easy to install, with excellent sealing performance, effectively reducing corrosion or pollution problems caused by external environmental factors.
[0132] The threaded connection ensures that the end cap 500 is securely installed, effectively preventing accidental detachment or loosening during flight, and further improving the safety and reliability of the UAV aeromagnetic probe system. Specific Implementation Example 2
[0134] This application also provides a drone that uses the drone aeromagnetic probe system in the above-described specific embodiment to carry detection equipment. The drone includes a drone body 800, a drone aeromagnetic probe system, and an airborne magnetometer.
[0135] Specifically, the types of drone bodies 800 include fixed-wing drones, multi-rotor drones, or vertical take-off and landing drones.
[0136] Reference Appendix Figure 10 The UAV aeromagnetic probe system is installed at the bottom of the UAV body 800. The housing 101 of the UAV aeromagnetic probe system is connected to the UAV body 800 through the first probe 200, and the aeromagnetic meter is installed on the first probe 200 or the second probe 300.
[0137] When mounted on the second probe 300, the relative positions of the first probe 200 and the second probe 300 are adjusted by the positioning component 400, thereby adjusting the position of the airborne magnetometer according to different flight detection missions.
[0138] By setting up an aeromagnetic probe system, the UAV can accurately locate the airborne magnetometer. After the UAV is equipped with the aeromagnetic probe system, the total length of the first probe 200 and the second probe 300 can be flexibly adjusted according to different detection altitude requirements and accuracy needs, so as to achieve more accurate and efficient magnetic field detection tasks.
[0139] By mounting the UAV aeromagnetic probe system onto the UAV body 800, detection operations can be carried out quickly and flexibly, significantly improving operational efficiency and detection accuracy. Furthermore, the UAV aeromagnetic probe system has a reliable structure and is easy to maintain, reducing the overall maintenance cost and complexity of the UAV system, improving the stability and safety of UAV operations, and enhancing its adaptability and competitive advantage in complex flight environments.
[0140] This application provides an aeromagnetic probe system for unmanned aerial vehicles (UAVs) and a UAV equipped with it. The system features a design where the first probe 200 is positioned within the electronic compartment assembly 100 and slides relative to the second probe 300, ensuring overall structural stability and avoiding insufficient rigidity after deployment. Furthermore, the positioning assembly 400 allows for stepless adjustment of the overall length of the first probe 200 and the second probe 300, improving adaptability to different tasks and further ensuring stable and reliable data, avoiding a series of problems caused by folding joint designs. The synergistic action of the clamping member 401, clamping structure 403, and locking member 402 ensures the positional accuracy and stability of the first probe 200 and the second probe 300 in the locked state, preventing displacement due to vibration during flight. The at least two clamping parts 4031, arranged in a ring, achieve uniform clamping of the first probe 200 or the second probe 300, resulting in more stable and reliable positioning. The guide part 4032 gradually... The thickened design allows for more precise control of the clamping force, enabling fine-tuning. Combined with the clamping part 4031, it can smoothly clamp the first probe 200 or the second probe 300. The threaded connection ensures a secure bond between the locking element 402 and the clamping structure 403, guaranteeing clamping stability and reliability. The cooperation between the first sealing element 405 and the first sealing groove 404 effectively enhances the protective performance and service life of the positioning component 400, preventing external environmental factors from corroding the clamping structure 403 and the threaded connection. The chamber 101 is sealed to the mounting cover 102 and the limiting cover 103 by corresponding numbers of second sealing elements 105, achieving effective sealing and protection of the internal environment of the chamber 101, significantly improving the system's protection level and reliability. The threaded connection of the end cover 500 and the cooperation of the third sealing element 700 provide effective sealing protection, significantly improving the environmental protection performance inside the second probe 300.
[0141] Finally, it should be noted that the various embodiments in this specification are described in a progressive manner, with each embodiment focusing on the differences from other embodiments. The same or similar parts between the various embodiments can be referred to each other.
[0142] The above embodiments are only used to illustrate the technical solutions of this application and not to limit them; although this application has been described in detail with reference to preferred embodiments, those skilled in the art should understand that modifications can still be made to the specific implementation of this application or equivalent substitutions can be made to some technical features without departing from the spirit of the technical solutions of this application, and all such modifications and substitutions should be covered within the scope of the technical solutions claimed in this application.
Claims
1. A UAV aeromagnetic probe system, characterized in that, include: The electronic compartment component is hollow inside and has two through holes on each of its two opposite side walls; The first probe is located inside the electronic compartment assembly and extends outward through the two through holes at both ends; The second probe is slidably connected to both ends of the first probe. A positioning component is sleeved on the first probe and the second probe and located at their connection point. The positioning component is used to stop or release the relative sliding of the first probe and the second probe, so as to adjust the distance between the end of the second probe away from the first probe and the electronic compartment assembly.
2. The UAV aeromagnetic probe system according to claim 1, characterized in that, The positioning component includes: The clamping element has one end fixedly sleeved on the outside of the first probe or the second probe, and the other end is provided with a clamping structure; A locking element is slidably sleeved on the second probe or the first probe relative to the clamping element. One end of the locking element is used to slide to wrap around the clamping structure or to slide away from the clamping structure, so as to stop or release the relative sliding between the first probe and the second probe.
3. The UAV aeromagnetic probe system according to claim 2, characterized in that, The first probe is hollow inside, and the second probe is slidably disposed inside the first probe. One end of the clamping member is fixedly sleeved on the end of the first probe away from the electronic compartment assembly, and the other end of the clamping member is provided with the clamping structure. The locking member is slidably sleeved on the outside of the second probe. The end of the locking member near the clamping member is used to slide to wrap around the clamping structure, or to slide away from the clamping structure, so that the relative sliding between the first probe and the second probe stops or is released.
4. The UAV aeromagnetic probe system according to claim 2, characterized in that, The second probe is hollow inside, and the first probe is slidably disposed inside the second probe. One end of the clamping member is fixedly sleeved on the end of the second probe near the electronic compartment assembly, and the other end of the clamping member is provided with the clamping structure. The locking member is slidably sleeved on the outside of the first probe. The end of the locking member near the clamping member is used to slide to wrap around the clamping structure, or to slide away from the clamping structure, so that the relative sliding between the first probe and the second probe stops or is released.
5. The UAV aeromagnetic probe system according to claim 3 or 4, characterized in that, The clamping structure further includes: The clamping portion, at least two of the clamping portions are arranged around the axis of the first probe or the second probe, one end of the two clamping portions is connected to the clamping member, and the other end is used to move closer to or away from the axis of the first probe or the second probe; A guide portion is provided on the end face of the clamping portion away from the first probe or the second probe, and the guide portion is used to make the thickness of the clamping portion gradually increase from one end away from the clamping member to the other end.
6. The UAV aeromagnetic probe system according to claim 5, characterized in that, The positioning component also includes: The clamping structure and the clamping member are provided with external threads, and the inner wall of the locking member is provided with corresponding internal threads, so that after the clamping structure extends into the locking member, it is then threadedly connected to the clamping member.
7. The UAV aeromagnetic probe system according to claim 6, characterized in that, The positioning component also includes: The first sealing groove is located between the external thread and the clamping member; The first sealing element is disposed within the sealing groove and located between the clamping element and the locking element.
8. The UAV aeromagnetic probe system according to claim 1, characterized in that, The electronic compartment assembly further includes: The container body is hollow inside and has two mounting openings on two adjacent outer walls. The through hole is provided in the container body and the through hole is perpendicular to the two mounting openings. The two mounting covers are respectively placed over the two mounting openings and connected to the compartment body; The limiting cover, the second of which is sleeved on the outside of the first probe and connected to the chamber body respectively, and the limiting cover is placed on the through hole; The second sealing groove is located at one end of the mounting cover and the limiting cover near the chamber body; The second seal is disposed in the second sealing groove, and the second seal is located between the mounting cover and the chamber body, or between the limiting cover and the chamber body.
9. The UAV aeromagnetic probe system according to claim 1, characterized in that, Also includes: The two end caps are respectively sleeved on the two second probe rods and located at the end of the second probe rod away from the first probe rod. The end caps are threadedly connected to the second probe rods. A third sealing groove is provided inside the end cap; The third sealing element is disposed in the third sealing groove and located between the end cap and the second probe.
10. A drone, characterized in that, The UAV is equipped with the UAV aeromagnetic probe system as described in any one of claims 1-9.