A heat treatment device suitable for unmanned aerial vehicle landing gear processing

Abstract

The application relates to the technical field of unmanned aerial vehicle landing gear heat treatment, in particular to a heat treatment device suitable for unmanned aerial vehicle landing gear processing, which comprises supporting legs, a box body, a control panel, a top cover, a handle, supporting blocks, a heating assembly and a gas quenching assembly. The box body is fixedly installed on the supporting legs, the control panel is fixedly installed on the front outer wall of the box body, the top cover is hingedly connected to the top of the box body, the handle is fixedly installed above the top cover, the supporting blocks are fixedly installed on the two sides of the top of the box body, the heating assembly is fixedly installed in the box body, and the gas quenching assembly is fixedly installed in the box body. The application solves the problem that the heating speed and the cooling speed of the thin wall and the thick wall of the unmanned aerial vehicle landing gear are inconsistent when the unmanned aerial vehicle landing gear is heated and cooled, the whole part organization transformation is out of synchronization, the part is warped, deformed, even cracked, the heated landing gear needs to be taken out and transferred to a quenching workbench, the whole process is relatively complicated, and the time consumption is relatively long.

Description

Technical Field

[0001] This invention relates to the field of heat treatment technology for unmanned aerial vehicle (UAV) landing gear, and in particular to a heat treatment apparatus suitable for processing UAV landing gear. Background Technology

[0002] Unmanned aerial vehicle (UAV) landing gear is typically made of high-strength steel, titanium alloy, or ultra-high-strength aluminum alloy. The core purpose of its heat treatment is to achieve a perfect combination of high strength, high toughness, high fatigue strength, and good corrosion resistance to withstand the impact loads and cyclic stresses during takeoff, landing, and taxiing.

[0003] In existing heat treatment processes, landing gear is usually heated in a furnace and then quenched in liquid. However, the complex structure of landing gear, with cross-sections of varying thicknesses, results in inconsistent heating and cooling rates between thin and thick walls. This leads to asynchronous microstructural transformation of the entire part, producing uneven martensitic structures. This causes significant internal stress, resulting in warping, deformation, and even cracking of the parts. Furthermore, the heated landing gear must be removed and transferred to a quenching workbench, making the entire process cumbersome and time-consuming. Summary of the Invention

[0004] The technical objective of this invention is to solve the problem that in existing heat treatment devices for UAV landing gear, due to the varying cross-sections of the landing gear, the heating and cooling rates of thin and thick walls are inconsistent, leading to asynchronous microstructural transformation and uneven martensitic structure, causing warping, deformation, and even cracking of the parts. Furthermore, the heated landing gear must be removed and transferred to a quenching workbench, a cumbersome and time-consuming process. This invention enables uniform heating and cooling of the UAV landing gear during heat treatment without the need for transfer, simplifying the process and saving time.

[0005] To solve the above-mentioned technical problems, the present invention provides the following technical solution:

[0006] A heat treatment device suitable for processing UAV landing gear includes: legs, housing, control panel, top cover, handle, support block, heating component and gas quenching component;

[0007] A housing is fixedly installed on multiple of the aforementioned legs. A control panel is fixedly installed on the front outer wall of the housing. A top cover is hinged to the top of the housing. A handle is fixedly installed on the top cover. Support blocks are fixedly installed on both sides of the top of the housing. A heating component is fixedly installed inside the housing. An air quenching component is fixedly installed inside the housing.

[0008] The landing gear body is uniformly heated by the heating component, and then uniformly quenched by the air quenching component.

[0009] As a preferred embodiment of the heat treatment device for processing UAV landing gear according to the present invention, the air quenching assembly includes a rotating motor, a rotating shaft, a sleeve, an air filling pipe, a disc, rotating blades, a water-cooled exchange box, and an air box.

[0010] Four rotating motors are fixedly mounted on the housing. Two of the rotating motors are vertically fixed inside the housing, and the other two are horizontally fixed on support blocks on both sides of the housing. Each of the four rotating motors has a rotating shaft fixedly mounted on it. Each of the four rotating shafts has a sleeve rotatably mounted on it. Each of the four sleeves has an air inlet pipe fixedly mounted on it. Each of the four rotating shafts has a disc rotatably mounted on it. Each of the four discs is fixedly connected to the housing. Multiple rotating blades are arranged in a circular array around the axis of rotation on the four rotating shafts. Each of the four discs is located between the four sleeves and the four rotating blades. Multiple water-cooled exchange boxes are fixedly mounted inside the housing, and the multiple water-cooled exchange boxes are arranged at intervals from the two rotating motors inside the housing. Multiple air boxes are fixedly mounted on the multiple water-cooled exchange boxes.

[0011] As a preferred embodiment of the heat treatment device for processing UAV landing gear according to the present invention, wherein: multiple rectangular through holes are arranged in a ring array around the axis on the four rotating shafts, and the multiple rectangular through holes are located inside the sleeve and are connected to the air inlet pipe; a circular cavity is provided at the end of the four rotating shafts away from the rotating motor, and the circular cavity is interconnected with the multiple rectangular through holes.

[0012] As a preferred embodiment of the heat treatment device for processing UAV landing gear according to the present invention, wherein: a rectangular cavity is formed inside the plurality of rotating blades, and the rectangular cavity and the circular cavity are interconnected; a plurality of air jet holes are formed on the side of the plurality of rotating blades away from the disk.

[0013] As a preferred embodiment of the heat treatment device for processing UAV landing gear according to the present invention, wherein: the plurality of water-cooled exchange boxes are of a serpentine structure, and the bottom of the plurality of water-cooled exchange boxes are respectively provided with a water inlet main pipe and a water outlet main pipe; the plurality of air boxes are of a serpentine structure, and the plurality of air boxes cooperate and lock with the plurality of water-cooled exchange boxes; the bottom of the plurality of air boxes is respectively provided with an air outlet pipe; the top of the air boxes on both sides inside the box body is respectively provided with an air inlet pipe; and a T-shaped pipe is provided on the air box in the middle of the box body.

[0014] As a preferred embodiment of the heat treatment device for processing UAV landing gear according to the present invention, wherein: a plurality of rectangular slots are respectively opened inside the box body, and a plurality of water-cooled exchange boxes and a plurality of air boxes are respectively located in the plurality of rectangular slots; a plurality of cylindrical cavities are respectively opened inside the box body, and the plurality of cylindrical cavities and the plurality of rectangular slots are arranged at intervals; an installation cavity is opened at the bottom of the box body, the installation cavity is connected to the plurality of cylindrical cavities, and two rotary motors are respectively installed in the installation cavity; the discs on the two rotary motors are sealed to the bottom of the cylindrical cavities; an arc-shaped groove is respectively opened between the top of the box body and the bottom of the top cover, and the plurality of cylindrical cavities and the arc-shaped groove are interconnected; and brackets are respectively provided on the inner sides of both ends of the arc-shaped groove on the top of the box body.

[0015] As a preferred embodiment of the heat treatment device for processing UAV landing gear according to the present invention, wherein: a connecting hole is provided between adjacent rectangular grooves, a round hole is provided at the top of the rectangular groove in the middle of the box, and the round hole communicates with the arc groove, one end of the connecting hole on both sides of the rectangular groove in the middle of the box and the round hole at the top are respectively connected to the T-shaped pipe on the middle air box, and the other end of the connecting hole on the inner side of the rectangular groove on both sides is respectively connected to the air inlet pipe on the air box on both sides.

[0016] As a preferred embodiment of the heat treatment device for processing UAV landing gear according to the present invention, the heating component includes a first heating wire and a second heating wire; a plurality of first heating wires are respectively fixedly installed on the inner walls of a plurality of cylindrical cavities, and the second heating wire is fixedly installed on the inner walls of two arc-shaped grooves; the first heating wire and the second heating wire are respectively electrically connected to the control panel.

[0017] As a preferred embodiment of the heat treatment device for processing UAV landing gear described in this invention, the second heating wire is a split structure, with one half located in the arc-shaped groove at the top of the housing and the other half located in the arc-shaped groove at the bottom of the top cover, and the upper and lower parts are in contact with each other.

[0018] As a preferred embodiment of the heat treatment device for processing UAV landing gear according to the present invention, wherein: the plurality of air outlet pipes and the plurality of air inlet pipes are respectively connected to an air pump, and the water inlet main pipe and the water outlet main pipe are respectively connected to a water pump.

[0019] The beneficial effects of this invention are:

[0020] 1. This invention provides a heating component and an air quenching component inside the housing. Through the cooperation of the heating component and the air quenching component, the landing gear is uniformly heated in a vacuum and uniformly cooled by the air quenching component, thus completing the entire air quenching process. This eliminates the need to transfer the landing gear for quenching again, simplifying the process and saving time.

[0021] 2. The present invention has a first heating wire and a second heating wire inside the housing, and the diameters of the first heating wire and the second heating wire are matched with the diameters of the cylindrical rods of the landing gear, thereby ensuring that the cylindrical rods of different thicknesses can be heated evenly during the heating process, thereby improving the efficiency of heat treatment.

[0022] 3. This invention provides an air quenching component inside the housing. Through the interaction between the rotating blades on the air quenching component and the inert gas, when the high-speed flowing inert gas is introduced, the rotating blades generate high-speed, uniform turbulence, thereby uniformly cooling the landing gear parts of different thicknesses and completing the air quenching of the landing gear, which greatly improves the air quenching efficiency of the landing gear.

[0023] 4. This invention incorporates a water-cooled exchange box and an air box within the housing. Through the cooperation of the water-cooled exchange box and the air box, heat is exchanged on the inert gas, allowing the inert gas to circulate and perform cyclic gas quenching on the landing gear. Attached Figure Description

[0024] Figure 1 This is a schematic diagram of the overall three-dimensional structure in an embodiment of this disclosure.

[0025] Figure 2 This is a schematic diagram of a portion of the three-dimensional structure inside the box in an embodiment of this disclosure.

[0026] Figure 3 This is a three-dimensional structural diagram of the air quenching component inside the housing in an embodiment of this disclosure.

[0027] Figure 4 This is a three-dimensional structural diagram of the water-cooled exchange box and the air box in the embodiments of this disclosure.

[0028] Figure 5 This is a three-dimensional structural diagram of the water-cooled exchange box inside the enclosure in an embodiment of this disclosure.

[0029] Figure 6 This is a three-dimensional structural diagram of the heating assembly inside the housing in an embodiment of this disclosure.

[0030] Figure 7 This is a three-dimensional structural diagram of the second heating wire at the top of the housing in an embodiment of this disclosure.

[0031] Figure 8This is a cross-sectional view of the housing in an embodiment of this disclosure.

[0032] Figure 9 This is a three-dimensional structural diagram of the rotating blade, sleeve, and inflation tube in an embodiment of this disclosure.

[0033] Figure 10 This is a three-dimensional structural diagram of the rotating shaft in an embodiment of this disclosure.

[0034] Figure 11 This is a three-dimensional structural diagram of the landing gear in an embodiment of this disclosure.

[0035] Reference numerals: 1. Support leg; 2. Housing; 21. Rectangular groove; 22. Cylindrical cavity; 23. Arc groove; 24. Connecting hole; 25. Circular hole; 26. Bracket; 27. Mounting cavity; 3. Control panel; 4. Top cover; 5. Handle; 6. Support block; 7. Heating assembly; 71. First heating wire; 72. Second heating wire; 8. Air quenching assembly; 81. Rotating motor; 82. Rotating shaft; 821. Rectangular through hole; 822. Circular cavity; 83. Sleeve; 84. Air inlet pipe; 85. Disc; 86. Rotating blade; 861. Rectangular cavity; 862. Air jet hole; 87. Water cooling exchange box; 871. Water inlet main pipe; 872. Water outlet main pipe; 88. Air box; 881. Air outlet pipe; 882. Air inlet pipe; 883. T-tube; 9. Landing gear body. Detailed Implementation

[0036] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings.

[0037] like Figures 1 to 11 As shown, a heat treatment device suitable for processing UAV landing gear includes: a support leg 1, a housing 2, a control panel 3, a top cover 4, a handle 5, a support block 6, a heating component 7, and an air quenching component 8.

[0038] A housing 2 is fixedly installed on multiple support legs 1. A control panel 3 is fixedly installed on the front outer wall of the housing 2. A top cover 4 is hinged to the top of the housing 2. A handle 5 is fixedly installed on the top cover 4. Support blocks 6 are fixedly installed on both sides of the top of the housing 2. A heating component 7 is fixedly installed inside the housing 2. An air quenching component 8 is fixedly installed inside the housing 2.

[0039] The landing gear body 9 is uniformly heated by the heating component 7, and then uniformly quenched by the air quenching component 8.

[0040] The support leg 1 is made of wear-resistant alloy material and has anti-slip rubber pads on the bottom. It not only provides stable support for the entire device and prevents displacement due to vibration during operation, but also cushions the impact force generated when the equipment is working, while preventing ground wear.

[0041] The enclosure 2 is constructed from double-layered high-temperature resistant stainless steel, with an inner wall covered by a heat-insulating layer. This combination of double-layer structure and insulation not only prevents heat loss from the cylindrical cavity 22, reducing energy consumption, but also prevents excessive external temperature, ensuring operator safety. The enclosure 2 contains space for the drone's landing gear, and a corresponding positioning structure is pre-installed within to ensure stability during handling.

[0042] Operators can intuitively monitor the device's operating status through the control panel 3, and accurately set parameters such as heating temperature, holding time, and quenching gas flow rate, achieving one-button control of the heat treatment process and reducing operational difficulty. The top cover 4 is hinged to the top of the chamber 2 via high-strength hinges, allowing for 180° rotation and convenient access to the landing gear. A sealing strip is provided on the inside of the top cover 4, ensuring a tight seal with the top of the chamber 2 when closed, guaranteeing the airtightness of the vacuum environment inside the chamber.

[0043] The heating component 7 is electrically connected to the control panel 3. After the operator sets the target temperature through the control panel 3, the heating wire can heat up quickly and the temperature data is fed back in real time through the temperature sensor inside the box 2 to ensure that the temperature inside the box is uniform and stable, so as to achieve all-round and uniform heating of the drone landing gear without dead angles and avoid uneven material performance of the landing gear due to local temperature differences.

[0044] The air quenching assembly 8 is electrically connected to the control panel 3. After the heating stage is completed, the operator starts the air quenching assembly 8 through the control panel 3. The air pump pressurizes the inert gas and delivers it through the air filling pipe 84 to the circular cavity 822 inside the rotating shaft 82. The gas is then evenly sprayed out through the air jet holes 862 on the rotating blades 86. At the same time, the rotating motor 81 drives the rotating blades 86 to rotate at high speed, causing the inert gas to form a high-speed turbulent flow inside the box, which washes the landing gear surface from all directions, achieving rapid cooling. In addition, the water-cooled exchange box 87 in the air quenching assembly 8 works in conjunction with the air box 88. It can quickly absorb the heat of the inert gas in the air box 88 through water circulation, ensuring that the inert gas is always kept at a low temperature, improving the air quenching effect, and ensuring that the landing gear is not prone to deformation or cracking during the cooling process.

[0045] like Figures 1 to 10 As shown, the air quenching assembly 8 includes a rotating motor 81, a rotating shaft 82, a sleeve 83, an air filling pipe 84, a disc 85, rotating blades 86, a water-cooled exchange box 87, and an air box 88.

[0046] Four rotating motors 81 are fixedly installed on the housing 2. Two of the rotating motors 81 are vertically fixed inside the housing 2, and the other two are horizontally fixed on the support blocks 6 on both sides of the housing 2. Rotating shafts 82 are fixedly installed on each of the four rotating motors 81. Sleeves 83 are rotatably installed on each of the four rotating shafts 82. Air inlet pipes 84 are fixedly installed on each of the four sleeves 83. Discs 85 are rotatably installed on each of the four rotating shafts 82. The four discs 85 are fixedly connected to the housing 2. Multiple rotating blades 86 are arranged in a circular array around the axis on the four rotating shafts 82. The four discs 85 are located between the four sleeves 83 and the four rotating blades 86. Multiple water-cooled exchange boxes 87 are fixedly installed inside the housing 2, and the multiple water-cooled exchange boxes 87 and the two rotating motors 81 inside the housing 2 are arranged at intervals. Multiple air boxes 88 are fixedly installed on the multiple water-cooled exchange boxes 87.

[0047] Four rotating motors 81 are installed in a three-dimensional configuration, two vertically and two horizontally, to adapt to the internal space of the housing 2 and the structure of the landing gear. Two of the rotating motors 81 are vertically fixed inside the housing 2, providing air-quenching power to the vertical cylindrical rod area of ​​the landing gear; the other two rotating motors 81 are horizontally fixed on the top of the support blocks 6 on both sides of the housing 2, corresponding to the positions of the horizontal cylindrical rods of the landing gear. This allows subsequent airflow to envelop the landing gear from multiple directions, avoiding cooling dead zones.

[0048] A sealing ring is provided between the inner wall of the sleeve 83 and the outer wall of the rotating shaft 82, which ensures that the rotating shaft 82 can rotate freely within the sleeve 83 while preventing inert gas from leaking out of the gaps. An inflation pipe 84 is welded and fixed to the side wall of each sleeve 83. One end of the inflation pipe 84 is connected to the inside of the sleeve 83, and the other end is connected to the output of the air pump via a flexible hose. The input amount of inert gas is adjusted via the control panel 3.

[0049] The surface of the disc 85 is provided with a sealing gasket and is sealed to the cylindrical cavity 22. It is also sealed to the rotating shaft 82 by a bearing. Its main function is to separate the area of ​​the sleeve 83 and the rotating blade 86.

[0050] When the rotating shaft 82 drives the rotating blade 86 to rotate at high speed, the inert gas enters the rectangular cavity 861 of the rotating blade 86 from the circular cavity 822 of the rotating shaft 82, and is then ejected at high speed through the jet hole 862. Combined with the centrifugal force generated by the rotation of the blade, the airflow forms a spiral turbulence, which wraps around the landing gear surface in all directions and achieves uniform cooling.

[0051] During gas quenching, inert gas carrying heat from the landing gear enters the gas chamber 88 through the connecting holes 24 and 25 inside the chamber 2, transferring heat to the gas chamber 88. The heat is then carried away by the cooling water inside the water-cooled exchanger 87, causing the inert gas temperature to drop rapidly. The gas is then discharged through the outlet pipe 881 for recycling. Meanwhile, the water that has absorbed heat is discharged through the main water outlet pipe 872, completing the water-cooling cycle. The close cooperation between the gas chamber 88 and the water-cooled exchanger 87 achieves efficient heat exchange, ensuring that the inert gas remains at a low temperature throughout the gas quenching process and improving the cooling effect.

[0052] like Figure 9 and Figure 10 As shown, multiple rectangular through holes 821 are arranged in a ring around the axis on the four rotating shafts 82, and the multiple rectangular through holes 821 are located inside the sleeve 83. The multiple rectangular through holes 821 are connected to the air tube 84. A circular cavity 822 is opened at the end of the four rotating shafts 82 away from the rotating motor 81, and the circular cavity 822 is interconnected with the multiple rectangular through holes 821.

[0053] When the sleeve 83 is fitted onto the rotating shaft 82 via the bearing, the rectangular through hole 821 is completely enclosed by the sleeve 83, preventing direct contact with the outside. This prevents leakage of inert gas during transport while ensuring that all gas can enter the rotating shaft 82, improving transport efficiency. The sleeve 83 achieves a seal by enclosing the rectangular through hole 821 without affecting shaft rotation, and the annular array of through holes ensures that gas enters the circular cavity 822 from multiple directions.

[0054] like Figure 9 and Figure 10 As shown, rectangular cavities 861 are respectively opened inside the multiple rotating blades 86, and the rectangular cavities 861 and the circular cavity 822 are interconnected. Multiple air jet holes 862 are respectively opened on the side of the multiple rotating blades 86 away from the disk 85.

[0055] When the rotating blades 86 are welded to the end of the rotating shaft 82 in a ring array, the rectangular cavity 861 port at the root of each blade is exactly aligned with the side wall opening of the circular cavity 822 of the rotating shaft 82, and the connection between the two is sealed by welding to prevent gas leakage.

[0056] Multiple jet nozzles 862 are located on the side of the rotating blades 86 facing the landing gear, ensuring that the ejected airflow flows directly to the landing gear surface. When the rotating blades 86 rotate at high speed driven by the rotating motor 81, the airflow ejected from the jet nozzles 862 will form a "spiral turbulence" under the action of centrifugal force. This turbulence can completely wrap around the surface of the UAV landing gear, achieving uniform and rapid cooling and ensuring that the material properties of all parts of the landing gear are consistent.

[0057] like Figure 3 , Figure 4 , Figure 5 and Figure 8 As shown, the plurality of water-cooled exchange boxes 87 have a serpentine structure, and the bottom of the plurality of water-cooled exchange boxes 87 is respectively provided with a water inlet main pipe 871 and a water outlet main pipe 872. The plurality of air boxes 88 have a serpentine structure, and the plurality of air boxes 88 cooperate and lock with the plurality of water-cooled exchange boxes 87. The bottom of the plurality of air boxes 88 is respectively provided with an air outlet pipe 881. The tops of the air boxes 88 on both sides inside the box body 2 are respectively provided with air inlet pipes 882. The air box 88 in the middle of the box body 2 is provided with a T-shaped pipe 883.

[0058] Multiple water-cooled heat exchangers 87 employ a serpentine structure design. This structure is not a simple bend, but rather a dense serpentine loop formed by multiple twists and turns of metal pipes. This maximizes the heat dissipation area within the limited space of the enclosure 2, allowing for more thorough contact with the high-temperature inert gas inside the gas chamber 88 and rapid heat absorption.

[0059] Each water-cooled heat exchanger 87 has an inlet main pipe 871 and an outlet main pipe 872 connected to its bottom. One end of the inlet main pipe 871 is connected to the output end of an external water pump, and the outlet main pipe 872 is connected to the serpentine pipe outlet of each water-cooled heat exchanger 87, collecting and discharging the hot water after it has absorbed heat.

[0060] The serpentine channels of the gas chamber 88 and the serpentine pipes of the exchange chamber are closely fitted and parallel to each other, allowing the high-temperature inert gas in the gas chamber 88 to achieve maximum contact area with the low-temperature water flow in the water-cooled exchange chamber 87, and to carry out efficient heat exchange. The synergistic work of the two provides a continuous supply of low-temperature, stable inert gas to the gas quenching assembly 8, ensuring the uniformity and efficiency of the UAV landing gear gas quenching process.

[0061] like Figure 3 , Figure 4 , Figure 5 and Figure 8As shown, the box body 2 has multiple rectangular slots 21 inside, and multiple water-cooled exchange boxes 87 and multiple air boxes 88 are located in the multiple rectangular slots 21. The box body 2 has multiple cylindrical cavities 22 inside, and the multiple cylindrical cavities 22 and the multiple rectangular slots 21 are arranged at intervals. The bottom of the box body 2 has an installation cavity 27, which is connected to the multiple cylindrical cavities 22. Two rotating motors 81 are installed in the installation cavity 27. The discs 85 on the two rotating motors 81 are sealed to the bottom of the cylindrical cavities 22. The top of the box body 2 and the bottom of the top cover 4 have arc-shaped slots 23, and the multiple cylindrical cavities 22 and the arc-shaped slots 23 are interconnected. The inner sides of the two ends of the arc-shaped slots 23 on the top of the box body 2 are respectively provided with brackets 26.

[0062] The number of rectangular slots 21 is exactly the same as the number of water-cooled exchange boxes 87 and air boxes 88, and the length, width, and height of each rectangular slot 21 are precisely matched with the combined dimensions of a single set of water-cooled exchange boxes 87 and air boxes 88. It should be noted that a heat insulation layer is provided on the inner wall of the rectangular slot 21 to prevent heat loss inside the cylindrical cavity 22 during the heating process.

[0063] The inner diameter of the cylindrical cavity 22 is slightly larger than the diameter of the vertical cylindrical rod of the landing gear body 9, ensuring that the cylindrical rod can be smoothly inserted. Arc-shaped grooves 23 are respectively formed between the top of the housing 2 and the bottom of the top cover 4, and the curvature of the two arc-shaped grooves 23 perfectly matches the outer curvature of the horizontal cylindrical rod of the landing gear body 9, ensuring that the cylindrical rod can be placed stably. The arc-shaped grooves 23 and the cylindrical cavity 22 are interconnected, ensuring that the inert gas can flow freely within these channels, achieving all-round encapsulation of the vertical and horizontal parts of the landing gear body 9.

[0064] The bracket 26 is used to prevent the horizontal cylindrical rod of the landing gear body 9 from directly contacting the second heating wire 72 on the inner wall of the arc groove 23, reducing the contact area and ensuring that the surface of the horizontal cylindrical rod can be fully scourd by the airflow to achieve uniform cooling. Meanwhile...

[0065] like Figure 3 , Figure 4 , Figure 5 , Figure 6 and Figure 8 As shown, connecting holes 24 are respectively provided between adjacent rectangular grooves 21. A round hole 25 is provided at the top of the rectangular groove 21 in the middle of the box body 2, and the round hole 25 is connected to the arc groove 23. One end of the connecting hole 24 on both sides of the rectangular groove 21 in the middle of the box body 2 and the round hole 25 at the top are respectively connected to the T-shaped pipe 883 on the middle air box 88. The other end of the connecting hole 24 on the inner side of the rectangular groove 21 on both sides is respectively connected to the air inlet pipe 882 on the air boxes 88 on both sides.

[0066] When the inert gas forms turbulence in the rectangular slot 21 and the arc-shaped slot 23 and washes away the heat from the landing gear, the heat-carrying airflow needs to be orderly recovered and enter the air box 88 for heat exchange. The airflow in the middle region enters the T-shaped pipe 883 through the connecting hole 24 and the round hole 25 and quickly enters the middle air box 88; the airflow in the two side regions enters the intake pipe 882 through the connecting hole 24 and flows directly into the two side air boxes 88; this ensures that the airflow enters each air box 88 efficiently and evenly, and avoids the impact of airflow congestion on heat exchange efficiency.

[0067] like Figures 6 to 8 As shown, the heating assembly 7 includes a first heating wire 71 and a second heating wire 72; a plurality of first heating wires 71 are respectively fixedly installed on the inner walls of a plurality of cylindrical cavities 22, and the second heating wires 72 are fixedly installed on the inner walls of two arc-shaped grooves 23. The first heating wires 71 and the second heating wires 72 are respectively electrically connected to the control panel 3.

[0068] Multiple sets of the first heating wire 71 are provided, the number of which matches the number of cylindrical cavities 22 within the housing 2 used to accommodate the vertical cylindrical rod of the landing gear body 9. The second heating wire 72 is fixedly installed within the housing 2 on the inner walls of two arc-shaped grooves 23 that support the horizontal cylindrical rod of the landing gear body 9. Heating the horizontal cylindrical rod of the landing gear body 9, placed on the bracket 26 within the arc-shaped grooves 23, ensures that the horizontal and vertical parts of the landing gear body 9 are heated synchronously, avoiding the impact of localized temperature differences on the heat treatment effect.

[0069] The first heating wire 71 and the second heating wire 72 in the heating assembly 7 can also be electromagnetic induction coils, which generate eddy currents on the surface of the landing gear body 9 by utilizing the principle of electromagnetic induction, thereby heating the landing gear body 9.

[0070] like Figure 7 and Figure 8 As shown, the second heating wire 72 has a split structure, with one half located in the arc-shaped groove 23 at the top of the housing 2 and the other half located in the arc-shaped groove 23 at the bottom of the top cover 4, and the upper and lower parts are in contact with each other.

[0071] It should be noted that the second heating wire 72 is not a traditional one-piece design, but is clearly divided into two independent parts, upper and lower. The upper heating wire is composed of multiple arc-shaped segments, which work in conjunction with the lower heating wire. When the top cover 4 is closed, the upper heating wire on the top cover 4 will precisely align with the lower heating wire on the top of the housing 2, forming a complete arc-shaped heating ring that perfectly wraps around the landing gear horizontal cylindrical rod placed on the bracket 26 of the arc-shaped groove 23. Both the upper and lower heating wires are embedded and fixed in position, ensuring that when the top cover 4 is closed, the upper and lower heating wires can make precise contact and form a complete arc-shaped heating ring.

[0072] When the worker closes the top cover 4 and completes the seal by using handle 5, the upper half of the heating wire at the bottom of the top cover 4 will be in close contact with the lower half of the heating wire at the top of the box 2, which can ensure the integrity of the current circuit. The two heating wires form a series circuit through the contact point and can generate heat synchronously after being powered on.

[0073] The plurality of air outlet pipes 881 and the plurality of air inlet pipes 84 are respectively connected to an air pump, and the water inlet main pipe 871 and the water outlet main pipe 872 are respectively connected to a water pump.

[0074] It should be noted that the independent drives of the air pump and water pump, along with their respective piping systems, form a cyclical system that works in concert but does not interfere with each other:

[0075] An air pump drives inert gas from the inflation pipe 84 into the housing 2. After cooling the landing gear, the inert gas carrying heat exchanges heat through the air box 88 and returns to the air pump through the exhaust pipe 881. The air pump then repressurizes the gas and sends it back into the inflation pipe 84, thus realizing the recycling of inert gas and reducing gas consumption.

[0076] The water pump drives cold water from the inlet main pipe 871 into the water-cooled exchange box 87. After absorbing the heat of the gas in the gas box 88, the water becomes hot water and is discharged from the outlet main pipe 872. After being cooled externally, the water is drawn back into the water pump to continuously cool the gas box 88 and ensure the temperature control accuracy during the gas quenching process.

[0077] The working principle of this invention is as follows: When heat-treating the landing gear of a drone, firstly, the worker pulls the handle 5 to open the top cover 4 and places the drone landing gear body 9 inside the housing 2. The two parallel vertical cylindrical rods of the landing gear body 9 are inserted into the cylindrical cavity 22 inside the housing 2. The horizontal cylindrical rod of the landing gear is placed horizontally on the bracket 26 in the arc groove 23. Then, the top cover 4 is closed by the handle 5 to seal the handle 5 and the top cover 4. The worker controls the heating component 7 to start through the control panel 3, so that the first heating wire 71 and the second heating wire 72 inside the heating component 7 generate heat and heat the landing gear body 9. At the same time, the air pump is started and the internal cavity is extracted, so that the landing gear body 9 is heated in a vacuum. When the landing gear is heated to a certain temperature, the first heating wire 71 and the second heating wire 72 are stopped working through the control panel 3.

[0078] Subsequently, the worker again controlled the water pump, air pump, and rotating motor 81 to start via control panel 3. The air pump introduced inert gas through the inflation pipe 84, which then passed through the sleeve 83 into the circular cavity 822 inside the rotating shaft 82. From there, the gas entered the rectangular cavity 861 inside the rotating blade 86, and finally exited through the jet nozzle 862 on the rotating blade 86. Simultaneously, the rotating motor 81 rotated, driving the rotating shaft 82 to rotate and transmitting power to the rotating blade 86, causing the rotating blade 86 to rotate... During the operation, high-speed flowing inert gas is ejected. As the rotating blade 86 rotates, the inert gas will form a high-speed, uniform turbulent flow in the cylindrical cavity 22 and the two arc-shaped grooves 23. This airflow will wash over the surface of the landing gear body 9, thereby carrying away heat. The airflow inside the cylindrical cavity 22 and the arc-shaped grooves 23 will enter the interior of the intake pipe 882 and the T-shaped pipe 883 through the connecting hole 24 and the round hole 25 respectively, and then enter the interior of multiple air boxes 88 through the intake pipe 882 and the T-shaped pipe 883.

[0079] At the same time, the water pump will drive the water flow through the water inlet main pipe 871 into the water-cooled exchange box 87. Since the water-cooled exchange box 87 and the air box 88 are in contact with each other and locked together, the heat inside the air box 88 will be carried away by the water flow inside the water box and the heat exchange will be completed. The water that has absorbed the heat will be discharged through the water outlet main pipe 872 and the water cooling cycle will be completed. After the inert gas has completed the heat exchange through the air box 88, it will be discharged through the air outlet pipe 881 and circulated by the air pump to quench the landing gear body 9.

[0080] After the air quenching is completed, the air pump, water pump and rotating motor 81 are stopped by controlling the control panel 3. Then the top cover 4 is opened and the landing gear body 9 is taken out for subsequent processing.

[0081] The foregoing has only described certain exemplary embodiments of the present invention by way of illustration. Undoubtedly, those skilled in the art can modify the described embodiments in various ways without departing from the spirit and scope of the present invention. Therefore, the foregoing drawings and descriptions are illustrative in nature and should not be construed as limiting the scope of protection of the claims of the present invention.

Claims

1. A heat treatment device suitable for unmanned aerial vehicle landing gear processing, characterized in that, Include: Supporting leg (1), box (2), control panel (3), top cover (4), handle (5), support block (6), heating assembly (7) and gas quenching assembly (8); A plurality of said supporting leg (1) is fixedly installed with box (2), the front side outer wall of box (2) is fixedly installed with control panel (3), the top of box (2) is hingedly connected with top cover (4), the top of top cover (4) is fixedly installed with handle (5), the top of box (2) is fixedly installed with support block (6) on both sides, the inside of box (2) is fixedly installed with heating assembly (7), the inside of box (2) is fixedly installed with gas quenching assembly (8); The landing gear body (9) is uniformly heated by the heating assembly (7), and then the landing gear body (9) is uniformly gas quenched by the gas quenching assembly (8); The gas quenching assembly (8) comprises rotating motor (81), rotating shaft (82), sleeve (83), inflation pipe (84), disc (85), rotating blade (86), water cooling exchange box (87) and gas tank (88); Four rotating motors (81) are fixedly installed on the box (2), wherein two rotating motors (81) are fixedly installed vertically inside the box (2), and the other two rotating motors (81) are fixedly installed horizontally on the support blocks (6) on both sides of the box (2), four rotating shafts (82) are fixedly installed on the rotating motors (81), four sleeves (83) are rotatably installed on the rotating shafts (82), four inflation pipes (84) are fixedly installed on the sleeves (83), four discs (85) are rotatably installed on the rotating shafts (82), four discs (85) are fixedly connected with the box (2), four rotating blades (86) are arranged in an annular array around the axis on the rotating shafts (82), four discs (85) are located between four sleeves (83) and four rotating blades (86), a plurality of water cooling exchange boxes (87) are fixedly installed inside the box (2), and the water cooling exchange boxes (87) and the two rotating motors (81) inside the box (2) are arranged at intervals, and a plurality of gas tanks (88) are fixedly installed on the water cooling exchange boxes (87); The plurality of water cooling exchange boxes (87) are serpentine structures, the plurality of water cooling exchange boxes (87) are respectively provided with water inlet main pipes (871) and water outlet main pipes (872), the plurality of gas tanks (88) are serpentine structures, and the plurality of gas tanks (88) are locked with the plurality of water cooling exchange boxes (87), the plurality of gas tanks (88) are respectively provided with gas outlet pipes (881), the gas tanks (88) on both sides of the inside of the box (2) are respectively provided with gas inlet pipes (882), and the gas tank (88) in the middle of the box (2) is provided with a T-shaped pipe (883). A plurality of rectangular grooves (21) are formed in the box (2), and a plurality of water-cooled exchange boxes (87) and a plurality of air boxes (88) are respectively located in the plurality of rectangular grooves (21). A plurality of cylindrical cavities (22) are formed in the box (2), and the plurality of cylindrical cavities (22) and the plurality of rectangular grooves (21) are arranged at intervals. An installation cavity (27) is formed in the bottom of the box (2), the installation cavity (27) is in communication with the plurality of cylindrical cavities (22), and two rotating motors (81) are respectively installed in the installation cavity (27). The disc (85) on the two rotating motors (81) is sealingly installed at the bottom of the cylindrical cavity (22). An arc-shaped groove (23) is respectively formed between the top of the box (2) and the bottom of the top cover (4), and the plurality of cylindrical cavities (22) and the arc-shaped grooves (23) are in communication. The inner sides of the arc-shaped grooves (23) at both ends of the top of the box (2) are respectively provided with supports (26). The heating assembly (7) comprises first heating wires (71) and second heating wires (72). A plurality of first heating wires (71) are fixedly installed on the inner walls of a plurality of cylindrical cavities (22). The second heating wires (72) are fixedly installed on the inner walls of two arc-shaped grooves (23). The first heating wires (71) and the second heating wires (72) are electrically connected with the control panel (3).

2. The heat treatment device suitable for unmanned aerial vehicle landing gear processing of claim 1, wherein: A plurality of rectangular through holes (821) are formed in the four rotating shafts (82) in a ring array around the axis, and the plurality of rectangular through holes (821) are located on the inner side of the sleeve (83). The plurality of rectangular through holes (821) are in communication with the inflation pipe (84). A circular cavity (822) is formed at one end of the four rotating shafts (82) away from the rotating motor (81), and the circular cavity (822) is in communication with the plurality of rectangular through holes (821).

3. The heat treatment apparatus suitable for unmanned aerial vehicle landing gear processing according to claim 2, characterized in that: A plurality of rectangular cavities (861) are formed in the plurality of rotating blades (86), and the rectangular cavities (861) are in communication with the circular cavities (822). A plurality of air injection holes (862) are formed on one side of the plurality of rotating blades (86) away from the disc (85).

4. The heat treatment apparatus for unmanned aerial vehicle landing gear processing of claim 1, wherein: A communication hole (24) is formed between adjacent rectangular grooves (21). A circular hole (25) is formed in the top of the rectangular groove (21) in the middle of the box (2), and the circular hole (25) is in communication with the arc-shaped groove (23). One end of the communication hole (24) on the two sides of the rectangular groove (21) in the middle of the box (2) and the circular hole (25) on the top are in communication with the T-shaped pipe (883) on the middle air box (88). The other end of the communication hole (24) on the inner side of the rectangular groove (21) on the two sides is in communication with the air inlet pipe (882) on the air box (88) on the two sides.

5. The heat treatment apparatus for unmanned aerial vehicle landing gear processing of claim 1, wherein: The second heating wire (72) is of a split structure, one half of which is located in the arc-shaped groove (23) on the top of the box (2), and the other half is located in the arc-shaped groove (23) on the bottom of the top cover (4), and the upper and lower parts are in contact with each other.

6. The heat treatment apparatus suitable for unmanned aerial vehicle landing gear processing according to claim 5, characterized in that: A plurality of the air outlet pipes (881) and a plurality of the air charging pipes (84) are respectively communicated with an air pump, and the water inlet main pipe (871) and the water outlet main pipe (872) are respectively communicated with a water pump.

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