An unmanned aerial vehicle launching device

Abstract

The application discloses a kind of unmanned plane launching device, comprising: support, barrel, driving part and monitoring component, barrel is movably connected to support, and with the first state of folding relative to support and the second state of unfolding relative to support, driving part is connected to barrel, and can be movable relative to barrel, for propelling unmanned plane launch in barrel, monitoring component is connected to barrel, for real-time monitoring the stress size that the lateral wall of barrel suffers.The application can effectively solve the problem that the health state of the launching barrel cannot be perceived in real time in the prior art, resulting in the lack of fault diagnosis based on real-time data for unmanned plane launching barrel.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) launch technology, and more specifically to a UAV launch device. Background Technology

[0002] Unmanned aerial vehicle (UAV) launch platforms are key equipment for enabling rapid and mobile deployment of fixed-wing UAVs.

[0003] For example, Chinese utility model patent CN210258868U, entitled "A Launching Cylinder for Unmanned Aerial Vehicles," currently uses a single propellant cartridge as its energy source. During launch, it generates significant light, sound, smoke, and heat, which is detrimental to battlefield concealment. Furthermore, the device cannot adjust the firing angle, making it unsuitable for various terrain conditions and firing angle requirements. This new device includes a cylinder and a support structure. The cylinder has a retaining ring and a shear cap sequentially installed at the launch outlet. Inside the cylinder is a piston, and an integrated valve and a protective cap are fixed to the rear end of the cylinder. The integrated valve's main body is a valve block, with an incendiary explosive assembly, a gas cylinder, and a gas control valve mounted on its bottom surface, and a one-way valve mounted on its top surface. This device is simple in structure, lightweight, easy to operate, and reusable.

[0004] However, existing technologies for monitoring the health status of the launch tube itself are mostly post-launch or off-site detection, which cannot detect dynamic responses in real time during launch, and lack the ability to diagnose faults and adjust launch decisions based on real-time data. Summary of the Invention

[0005] The purpose of this invention is to overcome the above-mentioned technical deficiencies and propose a drone launch device that solves the technical problem that the existing technology cannot perceive the health status of the launch tube in real time, resulting in the lack of fault diagnosis of the drone launch tube based on real-time data.

[0006] To achieve the above-mentioned technical objectives, the present invention adopts the following technical solution: This invention provides a drone launching device, comprising: support; The cylindrical body is movably connected to the support and has a first state folded relative to the support and a second state unfolded relative to the support. A drive unit, connected to the cylinder and movable relative to the cylinder, is used to propel the drone inside the cylinder for launch; and A monitoring component, connected to the cylinder, is used to monitor the stress on the sidewall of the cylinder in real time.

[0007] In some embodiments, the UAV launching device further includes a launching frame and at least one connecting rod. The launching frame is spaced apart from the support. The connecting rod includes a first connecting rod and a second connecting rod, which are spaced apart from each other. The two ends of the first connecting rod and the second connecting rod are rotatably connected to the launching frame and the support, respectively, so that the launching frame can rotate relative to the support.

[0008] In some embodiments, the UAV launching device further includes a first linear drive unit, which has a fixed end and a movable end. The fixed end of the first linear drive unit is hinged to the bracket, and the movable end is hinged to the launching frame. The movable end of the first linear drive unit moves relative to its fixed end to drive the launching frame to rotate relative to the bracket by a preset angle.

[0009] In some embodiments, the interior of the cylinder is hollow and open at one end. The driving member includes at least one sliding rod and a second linear driving part. One end of the sliding rod is built into the cylinder and can slide relative to the cylinder. The second linear driving part is connected to the launch frame and the sliding rod, and is used to drive the sliding rod to slide relative to the cylinder and push the UAV to slide out relative to the opening of the cylinder.

[0010] In some embodiments, the cylinder includes an inner cylinder, an intermediate layer, and an outer cylinder arranged sequentially from the inside out and connected to each other, wherein the hardness of the materials of the inner cylinder, the intermediate layer, and the outer cylinder decreases in that order.

[0011] In some embodiments, the sidewalls of the intermediate layer have a hollowed-out structure.

[0012] In some embodiments, the cross-sectional area of ​​the intermediate layer gradually increases in the direction away from the second linear drive portion.

[0013] In some embodiments, the monitoring component includes a stress monitoring element, which includes at least one first stress monitoring unit and at least one second stress monitoring unit. The first stress monitoring unit is connected to the open end of the outer cylinder and is spaced apart along the circumferential sidewall of the outer cylinder. The second stress monitoring unit is connected to the circumferential sidewall of the intermediate layer and is disposed near the second linear drive unit relative to the first stress monitoring unit.

[0014] In some embodiments, the stress monitoring device further includes two connecting seats and at least two third stress monitoring units. The two connecting seats are respectively disposed on both sides of the outer cylinder and connected to the launching frame and the outer cylinder. The third stress monitoring units are connected to the connection between the connecting seats and the outer cylinder.

[0015] In some embodiments, the monitoring component further includes at least one status monitoring element and a control unit. The status monitoring element is connected to the circumferential inner wall of the inner cylinder and is disposed near the second linear drive unit relative to the first stress monitoring unit. The control unit is electrically connected to the status monitoring element, the first stress monitoring unit, the second stress monitoring unit, and the third stress monitoring unit.

[0016] Compared with existing technologies, the beneficial effects of the UAV launch device provided by this invention include: a cylinder is movably connected to a support and has a first state folded relative to the support and a second state unfolded relative to the support; a drive component is connected to the cylinder and can move relative to the cylinder to propel the UAV inside the cylinder for launch; and a monitoring component is connected to the cylinder for real-time monitoring of the stress on the sidewall of the cylinder. Compared with existing technologies, the UAV inside the cylinder is propelled to launch relative to the cylinder by a drive component, and a monitoring component is also provided on the cylinder. The monitoring component can monitor the stress on the sidewall of the cylinder in real time, thereby sensing the health status of the launch cylinder in real time. This allows for fault diagnosis of the UAV launch cylinder using real-time data, enabling the UAV launch cylinder to have the ability to make launch decisions and adjustments based on real-time data. This solves the technical problem in existing technologies where the health status of the launch cylinder cannot be sensed in real time, resulting in a lack of fault diagnosis based on real-time data. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of a drone launching device according to an embodiment of the present invention; Figure 2 This is a schematic diagram from another perspective of a drone launching device provided in an embodiment of the present invention; Figure 3 This is a cross-sectional view of the cylinder and the monitoring component connected according to an embodiment of the present invention; Figure 4 This is a schematic diagram of an intermediate layer provided in an embodiment of the present invention; Figure 5 This is a schematic diagram showing the electrical connection between the control unit and the first stress monitoring unit, the second stress monitoring unit, the third stress monitoring unit, and the condition monitoring device according to an embodiment of the present invention; Figure 6 This is a flowchart of a health diagnosis and control algorithm for a control unit provided in an embodiment of the present invention; Figure 7 This is a flowchart of the health diagnosis and control algorithm of the control unit provided in another embodiment of the present invention.

[0018] Explanation of reference numerals in the attached figures: Support 100; cylinder 200; inner cylinder 210; intermediate layer 220; outer cylinder 230; drive component 300; sliding rod 310; second linear drive unit 320; monitoring component 400; stress monitoring component 410; first stress monitoring unit 411; second stress monitoring unit 412; connecting seat 413; third stress monitoring unit 414; status monitoring component 420; control unit 430; launching frame 500; connecting rod 600; first connecting rod 610; second connecting rod 620; first linear drive unit 700. Detailed Implementation

[0019] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the invention.

[0020] To address the problem in existing technologies where the health status of the launch tube cannot be perceived in real time, resulting in a lack of fault diagnosis based on real-time data for UAV launch tubes, this invention provides a UAV launch device. This device enables the launch of a UAV within a tube 200 relative to the tube 200 via a drive component 300. Simultaneously, a monitoring component 400 is installed on the tube 200, which monitors the stress on the sidewalls of the tube 200 in real time. This allows for real-time perception of the launch tube's health status, enabling fault diagnosis of the UAV launch tube using real-time data and providing the launch tube with the ability to make launch decisions and adjustments based on real-time data.

[0021] Please see Figure 1 , Figure 1 , Figure 2 This is a schematic diagram of a drone launching device according to an embodiment of the present invention. The drone launching device includes: a support 100, a cylinder 200, a drive component 300, and a monitoring component 400. The cylinder 200 is movably connected to the support 100 and has a first state folded relative to the support 100 and a second state unfolded relative to the support 100. The drive component 300 is connected to the cylinder 200 and can move relative to the cylinder 200 to push the drone inside the cylinder 200 to launch. The monitoring component 400 is connected to the cylinder 200 and is used to monitor the stress on the side wall of the cylinder 200 in real time.

[0022] In this device, compared to existing technologies, the driving component 300 propels the drone inside the cylinder 200 to launch relative to the cylinder 200. Simultaneously, a monitoring component 400 is installed on the cylinder 200. This monitoring component 400 can monitor the stress on the sidewall of the cylinder 200 in real time, thereby providing real-time perception of the launch cylinder's health status. Real-time data is used to assist in fault diagnosis of the drone launch cylinder, enabling the drone launch cylinder to make launch decisions and adjustments based on real-time data. This solves the technical problem in existing technologies where the health status of the launch cylinder cannot be perceived in real time, resulting in a lack of real-time data-based fault diagnosis for drone launch cylinders.

[0023] Furthermore, the support 100 here is a frame structure with a receiving cavity. The cylinder 200 can be stored in the receiving cavity of the support 100 after folding, and the cylinder 200 can be placed outside the receiving cavity after unfolding, forming a foldable structure. The material of the support 100 here is a common and readily available material on the market, such as stainless steel, which will not be described in detail here.

[0024] In this embodiment, as Figure 1 , Figure 2 As shown, the UAV launching device also includes a launching frame 500 and at least one connecting rod 600, and a first linear drive unit 700.

[0025] Among them, such as Figure 1 , Figure 2 As shown, the launch frame 500 and the bracket 100 are spaced apart. The connecting rod 600 includes a first connecting rod 610 and a second connecting rod 620. The first connecting rod 610 and the second connecting rod 620 are spaced apart from each other, and the two ends of the first connecting rod 610 and the second connecting rod 620 are respectively rotatably connected to the launch frame 500 and the bracket 100, so that the launch frame 500 can rotate relative to the bracket 100.

[0026] The launch frame 500 and the support 100 are connected by a link member 600 consisting of at least one first link 610 and at least one second link 620, so that the cylinder 200 can rotate relative to the support 100.

[0027] Furthermore, the bracket 100 and the launch frame 500 are spaced apart, the first link 610 and the second link 620 are spaced apart from each other, and the bracket 100, the launch frame 500, the first link 610 and the second link 620 are hinged to each other to form a link structure similar to a parallelogram.

[0028] In addition, in some embodiments, in order to improve the stability of the cylinder 200 rotating relative to the support 100, connecting rods 600 are provided on both sides of the launch frame 500, which will not be described in detail here.

[0029] One implementation method is, for example Figure 2 As shown, the first linear drive unit 700 has a fixed end and a movable end. The fixed end of the first linear drive unit 700 is hinged to the bracket 100, and the movable end is hinged to the launch frame 500. The movable end of the first linear drive unit 700 moves relative to its fixed end, and is used to drive the launch frame 500 to rotate relative to the bracket 100 by a preset angle.

[0030] The fixed end and the movable end are respectively hinged to the bracket 100 and the launch frame 500 to drive the launch frame 500 to rotate relative to the bracket 100.

[0031] Furthermore, by adjusting the position of the hinge point between the fixed end or the movable end of the first linear drive unit 700 and the bracket 100 and the launch frame 500, the preset angle can be adjusted, which will not be elaborated here.

[0032] In some embodiments, the first linear drive unit 700 is a commonly available and readily procurable push rod motor, cylinder, or hydraulic cylinder, which will not be described in detail here.

[0033] In this embodiment, as Figure 1 As shown, the interior of the cylinder 200 is hollow and open at one end. The driving member 300 includes at least one sliding rod 310 and a second linear driving part 320. One end of the sliding rod 310 is built into the cylinder 200 and can slide relative to the cylinder 200. The second linear driving part 320 is connected to the launch frame 500 and the sliding rod 310, and is used to drive the sliding rod 310 to slide relative to the cylinder 200 and push the UAV to slide out relative to the opening of the cylinder 200.

[0034] Through the cooperation of the sliding rod 310 and the second linear drive unit 320, the sliding rod 310 can slide linearly relative to the cylinder 200, and the sliding rod 310 can generate a thrust to push the drone after sliding.

[0035] Furthermore, in order to increase the contact area between the sliding rod 310 and the drone, an abutment block is also provided at the end of the sliding rod 310, which will not be described in detail here.

[0036] In some embodiments, the second linear drive unit 320 is a high-pressure push rod that can quickly push the sliding rod 310 to slide relative to the cylinder 200.

[0037] Furthermore, the second linear drive unit 320 here can also be a cylinder or a push rod motor, which will not be elaborated here.

[0038] In this embodiment, as Figure 3 , Figure 4As shown, the cylinder 200 includes an inner cylinder 210, an intermediate layer 220 and an outer cylinder 230 arranged sequentially from the inside to the outside and connected to each other, and the hardness of the materials of the inner cylinder 210, the intermediate layer 220 and the outer cylinder 230 decreases.

[0039] By adopting a three-layer structure and combining it into a single structure through curing or bonding processes, it is possible to decouple and break through the limitations of single material performance. This design allows each layer of material to perform at its best in its most advantageous performance dimension, and achieves linear superposition or even nonlinear enhancement of overall performance through interface synergy. Compared with the traditional homogeneous cylinder 200, it can achieve higher stiffness and better buffer performance under the same weight constraints, realizing the synergistic optimization of load-bearing efficiency and energy management efficiency, and providing a new technical path for the lightweight and high-performance of UAV layered progressive firing barrels.

[0040] Furthermore, the outer cylinder 230 is made of high-strength, high-modulus carbon fiber reinforced resin composite material. The main function of this layer is to serve as an overall load-bearing skeleton, providing the main axial and bending stiffness for the firing barrel, maintaining the stability of the geometry, and resisting external operational and environmental loads.

[0041] Furthermore, the intermediate layer 220 is composed of multiple independent hollow cylindrical damping structural units arranged in a circumferential and axial array. The material can be made of high-loss viscoelastic damping materials such as polyurethane or silicone rubber.

[0042] Furthermore, the inner cylinder 210 is in direct contact with the UAV's projectile body and is made of a polymer composite material with a low coefficient of friction and high wear resistance, such as high molecular weight polyethylene. Its inner surface is smooth, and the main function of this layer is to provide a low-resistance guiding channel for the UAV, reduce friction and wear during the launch process, and protect the surface of the launching UAV.

[0043] In one embodiment, such as Figure 3 , Figure 4 As shown, the sidewalls of the intermediate layer 220 have a hollow structure.

[0044] The middle layer 220, with its hollow structure, serves as the main buffer structure, absorbing and dissipating a large amount of impact kinetic energy.

[0045] Furthermore, when the shock wave is launched from the bottom, the gradient medium breaks the transient stiffness response mode of the uniform structure. The shock wave first encounters the low impedance region, where some of the kinetic energy is rapidly absorbed, the wavefront expands, and the duration of action is prolonged. Subsequently, as the wave propagates towards the high impedance region, it undergoes reflection, transmission, and mode conversion, further dissipating and homogenizing the energy. This gradient design, which matches the spatiotemporal distribution of the attenuated kinetic energy, can actively guide and mitigate the impact load, significantly reducing the peak overload transmitted to the UAV body and the key connection parts of the layered progressive launch barrel, and effectively filtering out the mid-to-high frequency vibration components that are harmful to the UAV's precision equipment, providing the UAV with a more stable and consistent launch environment.

[0046] In one embodiment, such as Figure 4 As shown, the cross-sectional area of ​​the intermediate layer 220 gradually increases in the direction away from the second linear drive portion 320.

[0047] In this application, the geometric parameters of the intermediate layer 220 exhibit a continuous gradient change along the axial direction of the launch tube. In the bottom region of the tube, the wall thickness between adjacent units in the same ring of the intermediate layer 220 is thin, the unit diameter is large, and it exhibits low initial stiffness, making it easy to undergo shear deformation under the impact of the UAV launch to quickly start energy consumption.

[0048] Furthermore, as the wall thickness of the intermediate layer 220 increases towards the cylinder opening, the unit diameter decreases, thus achieving an axially increasing stiffness of the intermediate layer 220.

[0049] Furthermore, in some embodiments, such as Figure 3 As shown, since the outer diameter of the outer cylinder 230 is the same, the wall thickness of the outer cylinder 230 and the wall thickness of the intermediate layer 220 are set in opposite directions, which will not be elaborated here.

[0050] In this embodiment, as Figures 1 to 3 As shown, the monitoring component 400 includes a stress monitoring element 410, at least one condition monitoring element 420, and a control unit 430.

[0051] The stress monitoring unit 410 includes at least one first stress monitoring unit 411 and at least one second stress monitoring unit 412. The first stress monitoring unit 411 is connected to the open end of the outer cylinder 230 and is spaced apart along the circumferential sidewall of the outer cylinder 230. The second stress monitoring unit 412 is connected to the circumferential sidewall of the intermediate layer 220 and is disposed near the second linear drive part 320 relative to the first stress monitoring unit 411.

[0052] By setting at least one first stress monitoring unit 411 at the bottom of the intermediate layer 220, the high stress area at the bottom of the cylinder can be detected. The first stress monitoring unit 411 is a fiber Bragg grating sensor that is common and easy to purchase on the market. The optical fibers are densely arranged along the axial direction at the interface between the outer cylinder 230 and the intermediate layer 220 to monitor the axial strain, circumferential strain and vibration spectrum characteristics generated by the impact during the launch of the UAV in real time.

[0053] Furthermore, the second stress monitoring unit 412 is a fiber Bragg grating sensor that is common and readily available on the market. By setting the second stress monitoring unit 412 at the opening end of the outer cylinder 230, the top outlet area of ​​the cylinder can be detected. The optical fiber is laid out circumferentially on the outer surface of the outer load-bearing layer to monitor the residual vibration and sway of the cylinder opening at the moment the UAV leaves the cylinder.

[0054] In some embodiments, multiple first stress monitoring units 411 and second stress monitoring units 412 are evenly distributed along the circumferential direction of the launch tube.

[0055] As one example, such as Figure 1 As shown, the stress monitoring component 410 also includes two connecting seats 413 and at least two third stress monitoring units 414. The two connecting seats 413 are respectively disposed on both sides of the outer cylinder 230 and connected to the launch frame 500 and the outer cylinder 230. The third stress monitoring unit 414 is connected to the connection between the connecting seats 413 and the outer cylinder 230.

[0056] The connecting seat 413 is used to bond and fix the outer cylinder 230 to the launching cylinder.

[0057] Furthermore, the second stress monitoring unit 412 is a fiber Bragg grating sensor that is common and readily available on the market. By setting a third stress monitoring unit 414 at the connection between the connector 413 and the side wall of the outer cylinder 230, the stress concentration at the mechanical connection interface can be monitored.

[0058] In some embodiments, two physical connection points are formed between the connecting seat 413 on one side and the outer cylinder 230.

[0059] As one example, such as Figures 1 to 3 and Figure 5 As shown, the monitoring component 400 further includes at least one status monitoring element 420 and a control unit 430. The status monitoring element 420 is connected to the circumferential inner wall of the inner cylinder 210 and is disposed near the second linear drive unit 320 relative to the first stress monitoring unit 411. The control unit 430 is electrically connected to the status monitoring element 420, the first stress monitoring unit 411, the second stress monitoring unit 412, and the third stress monitoring unit 414.

[0060] The status monitoring component 420 is connected to the inner wall of the inner cylinder 210 to monitor the status of the drone and help determine whether the drone is inside the launch tube.

[0061] Furthermore, the status monitoring component 420 is a common and readily available loading status detection sensor on the market. The loading status detection sensor is embedded in the inner surface of the inner cylinder 210, with its sensing surface flush with the guide surface. By detecting the capacitance change caused by the approach of the UAV body, it can accurately determine whether the UAV has reached the preset launch starting position in a non-contact manner.

[0062] Furthermore, in some embodiments, such as Figure 6 , Figure 7 As shown, the control unit 430 processes the parameters of the condition monitoring unit 420, the first stress monitoring unit 411, the second stress monitoring unit 412, and the third stress monitoring unit 414, and executes the following system health status diagnosis and control algorithm: Step 1: Load Readiness Check: Continuously read the signal from the status monitoring device 420. If the signal strength consistently exceeds the threshold T... load If the condition is met, the drone launch command will be triggered. Step 2, Data Synchronization Collection: When the launch command is triggered, the system synchronously starts the first stress monitoring unit 411, the second stress monitoring unit 412 and the third stress monitoring unit 414 to perform high-speed data acquisition. Step 3: Data Feature Extraction When the system is in transmission mode, the data from all the optical fiber sensors at all points in step two are demodulated in real time to obtain the strain value ε at each point. cur and vibration characteristic frequency band amplitude A vib ; Step 4, comparison of tiered thresholds: The processor will use the strain value ε cur and vibration characteristic frequency band amplitude A vib The data is compared with two preset safety thresholds. These thresholds are set based on calibration data of each location in a healthy state. The two safety thresholds are: 1. Attention threshold TH. caution 1. Indicates performance degradation or minor anomalies; 2. Warning threshold TH warning This indicates potential damage or malfunction; Step 5, State Decision and Output: 1. If all data are below TH caution The input status is HEALTHY; 2. If any data exceeds TH caution But lower than TH warningThe output status is CAUTION, and the location is recorded; 3. When the status is CAUTION, if the mission is urgent, the system can automatically calculate and reduce the initial launch pressure by 10-15% to reduce the impact load as a temporary safety measure. 4. If any data exceeds TH warning If multiple points trigger CAUTION simultaneously, the status WAENING and the highest level alarm will be output immediately, and system intervention will be recommended. Specifically, such as Figure 7 As shown, the cylinder 200 is configured with three failure modes and their handling methods: vibration-absorbing layer softening mode, continuous failure mode, and overall failure mode, as detailed below: 1. Vibration-absorbing layer softening mode: The strain peak value of the bottom hollow vibration-absorbing unit of the middle layer is abnormally high, but decays quickly; the decision of the control unit 430 is to trigger the alarm of "local performance degradation of vibration-absorbing layer", and recommend to give priority to the use of low kinetic energy load and shorten the maintenance cycle of the middle vibration-absorbing layer. 2. Continuous failure mode: The strain of adjacent monitoring points on the same layer of the first stress monitoring unit 411, the second stress monitoring unit 412, and the third stress monitoring unit 414 showed a step change; the decision of the control unit 430 was to trigger a warning of "suspected debonding of structural interface", immediately stop subsequent launches, and require non-destructive testing. 3. Overall failure mode: The energy decay curve of the mid-component layer deviates significantly from the health model; the decision of the control unit 430 is to trigger the "core buffer function failure" danger alarm, lock the system and prompt for overhaul or replacement.

[0063] Step Six, Data Archiving: After each launch mission, the control unit 430 automatically stores key data such as peak strain, vibration energy, and health status of the launch to form a historical database for use in long-term performance trend analysis and predictive maintenance models.

[0064] Furthermore, in some embodiments, during conventional launch processes, some propulsion energy is wasted on exciting the intense elastic vibration and uncontrollable frictional heating of the entire layered progressive launch barrel, resulting in ineffective energy consumption. This application, through the efficient and directional energy dissipation of the gradient energy dissipation buffer sandwich gradient damping structure, confines more impact energy to the functional path that propels the UAV to accelerate along the axis, reducing energy loss in undesirable directions. Simulation and field tests show that this design can effectively improve energy utilization efficiency.

[0065] Furthermore, gradient buffering provides a controllable and repeatable load environment, which greatly suppresses the randomness of the launch process caused by factors such as propellant batch differences and slight changes in ambient temperature. This makes the overload curve of the UAV more consistent each time it is launched, thereby effectively reducing the initial velocity dispersion and attitude angle deviation of the UAV when it leaves the launch tube. This is of great value for improving the accuracy of coordinated launch and ensuring mission repeatability.

[0066] Furthermore, as a mobile deployment device, the UAV launch platform has extremely strict limitations on weight and volume. This application achieves the synergistic attainment of multiple high-performance indicators through ingenious radial functional layering and axial gradient control, without significantly increasing the radial dimension and total weight of the layered progressive launch barrel.

[0067] Furthermore, radial layering fully utilizes the wall thickness space to achieve the integration of load bearing, buffering, and guidance; axial gradient, without increasing weight, achieves active performance control through intelligent changes in material distribution or unit design; it also possesses extremely high stiffness and weight ratio, excellent broadband buffering and vibration reduction characteristics, deeply integrated intelligent self-sensing capabilities, good maintainability, and adaptability to diverse loads. It successfully finds the optimal balance point under multiple constraints such as weight, volume, performance, reliability, and intelligence, meeting the ultimate pursuit of comprehensive performance in modern high-end equipment.

[0068] To better understand this invention, the following is combined with... Figures 1 to 7 The technical solution of the present invention will be described in detail below: The launch tube 200 is movably connected to the support 100 and has a first folded state relative to the support 100 and a second unfolded state relative to the support 100. A drive component 300 is connected to the launch tube 200 and can move relative to the launch tube 200 to launch the drone inside the launch tube 200. A monitoring component 400 is connected to the launch tube 200 to monitor the stress on the sidewalls of the launch tube 200 in real time. Compared to existing technologies, the launch tube's health status is monitored in real time by the drive component 300, while the launch tube 200 is equipped with a monitoring component 400. The monitoring component 400 can monitor the stress on the sidewalls of the launch tube in real time, thereby providing real-time data-driven fault diagnosis of the launch tube and enabling the launch tube to make adjustments based on real-time data.

[0069] The specific workflow of this invention is based entirely on the passive physical properties of materials and structures, requiring no external energy input or active control. Its adaptive capability stems from the characteristic that the depth and range of the activated gradient unit automatically adjusts according to the magnitude of the input impact energy. This "on-demand response" characteristic enables the same layered progressive launch barrel to automatically adapt to various UAV models with different weights and propulsion forces, providing near-optimal buffering effects within a wide kinetic energy range, significantly enhancing the versatility and mission flexibility of the launch platform.

[0070] Furthermore, compared to traditional surface-mounted sensor monitoring methods, this application deeply integrates the sensor network into a clearly layered structure, achieving precise positioning of the monitored target and physical isolation of the signal source. This "functional layer-sensor" correspondence makes the physical meaning of the collected strain and vibration data clear, greatly reduces signal crosstalk, and obtains a high signal-to-noise ratio raw signal.

[0071] Furthermore, this application can combine the spatiotemporal distribution strain field, vibration spectrum, and loading data generated during each launch process to form a complete "digital twin" record of the launch event; it changes the passive mode of traditional equipment relying on fixed-cycle preventive maintenance or post-failure repair, and realizes predictive maintenance based on actual conditions, which can significantly improve the equipment's combat readiness rate and reduce maintenance costs and downtime throughout the entire life cycle.

[0072] Furthermore, this application can solve the technical problem in the prior art that the health status of the launch tube cannot be perceived in real time, resulting in the lack of fault diagnosis of the UAV launch tube based on real-time data.

[0073] The specific embodiments of the present invention described above do not constitute a limitation on the scope of protection of the present invention. Any other corresponding changes and modifications made in accordance with the technical concept of the present invention should be included within the scope of protection of the claims of the present invention.

Claims

1. A drone launching device, characterized in that, include: support; The cylindrical body is movably connected to the support and has a first state folded relative to the support and a second state unfolded relative to the support. A drive unit, connected to the cylinder and movable relative to the cylinder, is used to propel the drone inside the cylinder to launch; as well as A monitoring component, connected to the cylinder, is used to monitor the stress on the sidewall of the cylinder in real time.

2. The UAV launching device according to claim 1, characterized in that, The UAV launching device further includes a launching frame and at least one connecting rod. The launching frame is spaced apart from the support. The connecting rod includes a first connecting rod and a second connecting rod. The first connecting rod and the second connecting rod are spaced apart from each other, and the two ends of the first connecting rod and the second connecting rod are respectively rotatably connected to the launching frame and the support, so that the launching frame can rotate relative to the support.

3. The UAV launching device according to claim 2, characterized in that, The UAV launching device further includes a first linear drive unit, which has a fixed end and a movable end. The fixed end of the first linear drive unit is hinged to the bracket, and the movable end is hinged to the launching frame. The movable end of the first linear drive unit moves relative to its fixed end, thereby driving the launching frame to rotate relative to the bracket by a preset angle.

4. The UAV launching device according to claim 2, characterized in that, The cylinder is hollow inside and open at one end. The driving component includes at least one sliding rod and a second linear driving part. One end of the sliding rod is built into the cylinder and can slide relative to the cylinder. The second linear driving part is connected to the launch frame and the sliding rod, and is used to drive the sliding rod to slide relative to the cylinder and push the UAV to slide out relative to the opening of the cylinder.

5. The UAV launching device according to claim 4, characterized in that, The cylinder includes an inner cylinder, an intermediate layer, and an outer cylinder arranged sequentially from the inside out and connected to each other, with the hardness of the materials of the inner cylinder, the intermediate layer, and the outer cylinder decreasing in that order.

6. The UAV launching device according to claim 5, characterized in that, The sidewalls of the intermediate layer have a hollow structure.

7. The UAV launching device according to claim 5, characterized in that, The cross-sectional area of ​​the intermediate layer gradually increases in the direction away from the second linear drive unit.

8. The UAV launching device according to claim 5, characterized in that, The monitoring component includes a stress monitoring element, which includes at least one first stress monitoring unit and at least one second stress monitoring unit. The first stress monitoring unit is connected to the open end of the outer cylinder and is spaced apart along the circumferential sidewall of the outer cylinder. The second stress monitoring unit is connected to the circumferential sidewall of the intermediate layer and is disposed near the second linear drive unit relative to the first stress monitoring unit.

9. The UAV launching device according to claim 8, characterized in that, The stress monitoring device further includes two connecting seats and at least two third stress monitoring units. The two connecting seats are respectively disposed on both sides of the outer cylinder and connected to the launching frame and the outer cylinder. The third stress monitoring units are connected to the connection between the connecting seats and the outer cylinder.

10. The UAV launching device according to claim 8, characterized in that, The monitoring component further includes at least one status monitoring element and a control unit. The status monitoring element is connected to the circumferential inner wall of the inner cylinder and is disposed near the second linear drive unit relative to the first stress monitoring unit. The control unit is electrically connected to the status monitoring element, the first stress monitoring unit, the second stress monitoring unit, and the third stress monitoring unit.

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