Fire-fighting reconnaissance unmanned plane with heat shield

Abstract

The application discloses a fire-fighting reconnaissance unmanned plane with a heat protection cover and relates to the technical field of fire-fighting unmanned planes. The fire-fighting reconnaissance unmanned plane with the heat protection cover comprises a support, a heat protection mechanism, a connecting rod, a detection mechanism, a static mechanism, a second motor shell and a rotor. The heat protection mechanism is fixedly connected to the top of the support. The heat protection mechanism is provided. The first air bag is inflated and deflated. The heat protection mechanism has the dual functions of a self-adaptive clamp and an intelligent buffer. The heat protection mechanism realizes the leap from static protection to dynamic intelligent adaptation, improves the task flexibility and survival ability in an extreme fire environment, and sets the detection mechanism. Through cooperation of a miniature ultrasonic probe and a laser vibration meter, the heat protection mechanism breaks through the limitation of traditional unmanned planes which only make external observation or single detection and realizes diagnosis of the internal health state of a building structure in an extreme fire environment, thereby forming a complete intelligent evaluation closed loop of discovery, locking and diagnosis.

Description

Technical Field

[0001] This invention relates to the field of firefighting drone technology, specifically a firefighting reconnaissance drone with a heat shield. Background Technology

[0002] Fire reconnaissance drones equipped with thermal shields are special drones designed specifically for reconnaissance missions deep into the high-temperature core areas of fire scenes. Through a dedicated thermal protection system, they protect their electronic equipment and sensors, enabling them to replace firefighters in entering the most dangerous areas and obtaining critical information.

[0003] In the field of traditional firefighting drones, the thermal shield and the fuselage are mostly rigidly connected. During high-speed flight, the stress is transmitted due to wind resistance. During impact, the impact is easily transmitted directly to the precision body. It is difficult to combine the dual functions of "adaptive clamp" and "intelligent buffer": low-pressure contact to reduce drag during flight, high-pressure clamping to enhance heat insulation when hovering, and energy absorption buffer when encountering danger. Therefore, it is difficult to achieve the leap from static protection to dynamic intelligent adaptation, which reduces the mission flexibility and survivability in extreme fire environment.

[0004] Furthermore, existing technologies, during use, struggle to quickly pinpoint suspected damage points by analyzing the overall structural vibration modes, and to conduct close-range contact with these points to obtain the precise depth and extent of internal defects. This makes it difficult to overcome the limitations of traditional drones, which only perform external observations or single-item inspections. Consequently, it is difficult to achieve aerial, in-situ, and quantitative diagnosis of the internal health status of building structures in extreme fire environments, and to form a complete "discovery-locking-diagnosis" intelligent assessment closed loop. In use, existing technologies rely on rigid impact techniques, which can easily cause secondary damage to damaged walls. Moreover, it is difficult to accurately invert the opening, expansion trend, and bonding strength between the surface and the substrate of wall cracks. This makes it difficult to achieve a breakthrough in the multi-dimensional quantitative assessment of wall damage from "qualitative identification" to "crack-strength," reducing the accuracy and reliability of fire-related structural risk assessments.

[0005] Finally, when drones are close to walls for precision measurements, existing technologies have difficulty converting some of the rotor's kinetic energy into controllable frictional resistance and elastic potential energy. This makes it difficult to achieve a stable and safe transition of the drone from aerial flight mode to a "quasi-static" wall operation mode, and further makes it difficult to avoid interference with the detection accuracy and the drone's own attitude caused by high-speed airflow impact from the rotor or fuselage vibration. Summary of the Invention

[0006] Therefore, in order to overcome the above-mentioned shortcomings, the present invention provides a fire reconnaissance drone with a heat shield.

[0007] The present invention is implemented as follows: a fire reconnaissance drone with a thermal protection shield is constructed. The device includes a bracket, a thermal protection mechanism is fixedly connected to the top of the bracket, six sets of connecting rods are fixedly connected to the outer wall of the thermal protection mechanism, a detection mechanism is fixedly connected to the outer side of the two sets of connecting rods on the back of the thermal protection mechanism, a static mechanism is fixedly connected to the bottom of the detection mechanism, a second motor housing is fixedly connected to the top of the detection mechanism, and a motor is fixedly connected inside the second motor housing. A rotor is fixedly connected to the top output shaft of the motor inside the second motor housing.

[0008] The thermal protection mechanism includes a thermal protection cover. The thermal protection cover is fixedly connected to the top of the bracket, and the drone fuselage is located at the center of the thermal protection cover. A mounting frame is fixedly connected to the bottom of the thermal protection cover. Eight sets of high-temperature resistant flexible limiting straps are equidistantly arranged on the outer wall of the mounting frame. A first airbag is located inside the mounting frame. A composite layer is adhesively connected to the outside of the first airbag. A connecting pipe is fixedly connected to the bottom of the first airbag. A reversing valve is fixedly connected to the delivery port of the connecting pipe. A first miniature pressure sensor is fixedly connected to the top of the mounting frame, and the bottom sensor head of the first miniature pressure sensor is connected to the first airbag.

[0009] Preferably, the detection mechanism includes a first mounting shell. The outer sides of the two sets of connecting rods on the back of the thermal shield are fixedly connected to the first mounting shell. A micro motor is fixedly connected to the left end of the first mounting shell. A turntable is fixedly connected to the output shaft of the micro motor on the right end. A first protruding rod is eccentrically provided on the right end of the turntable. The outer wall of the first protruding rod is intermittently engaged with a grooved wheel. A fixing rod is fixedly connected to the right end of the grooved wheel. A mounting block is fixedly connected to the right end of the fixing rod. A micro ultrasonic probe is fixedly connected to one end of the mounting block. A mating mechanism is fixedly connected to the other end of the mounting block. The outer wall of the mounting block is rotatably connected to a connecting seat. A first motor housing is provided at the bottom of the connecting seat. A laser vibrometer is fixedly connected to the lower back of the first motor housing.

[0010] Preferably, the mating mechanism includes a mounting rod. The other end of the mounting block and the upper back of the first motor housing are both fixedly connected to one end of the mounting rod. The other end of the mounting rod is slidably connected to the outer wall of the sliding rod. A second airbag is fixedly connected to the back of the sliding rod above the back of the first motor housing. A second pressure sensor is fixedly connected to the left end of the sliding rod above the back of the first motor housing. The other end of the mounting block is fixedly connected to an elastic V-shaped rod. The elastic V-shaped rod is fixedly connected to both ends of an electric spring, and the electric spring is electrically connected to an external power supply. Resistance strain gauges are attached to the spring wire axis of the electric spring in the ±45° direction. Six sets of electromagnetic blocks are equidistantly arranged inside the mounting rod, and the electromagnetic blocks are magnetically attracted to the sliding rod.

[0011] Preferably, the static mechanism includes a second mounting shell, the bottom of which is fixedly connected to the second mounting shell, and the back of the second mounting shell is provided with a slot. A first fixing block is fixedly connected to the bottom left end of the second mounting shell, and a first torsion spring is fixedly connected to the upper right end of the first fixing block. The right end of the first torsion spring is fixedly connected to the left edge of the rotating block. A second protruding rod is fixedly connected to the right edge of the rotating block. A sliding groove plate is slidably connected to the outer wall of the second protruding rod. The back of the sliding groove plate is fixedly connected to the inner gear plate of the gear tooth plate component. A second torsion spring is fixedly connected to the right end of the inner gear of the gear tooth plate component, and a second fixing block is fixedly connected to the right end of the second torsion spring. The outer wall of the inner gear plate of the gear tooth plate component is slidably connected to a limiting plate. A connecting frame is fixedly connected to the back of the inner gear plate of the gear tooth plate component, and a friction block is adhesively connected to the back of the connecting frame.

[0012] Preferably, the composite layer is composed of a flexible nano-aerogel felt and a silicone pad with a raised dot array, and a composite aramid fiber mesh is adhered and connected inside the first airbag.

[0013] Preferably, the first miniature pressure sensor is electrically connected to an external display screen, and the connecting pipe is connected to an external air pump.

[0014] Preferably, a motor is fixedly connected to the bottom of the first motor housing, and a connecting seat is fixedly connected to the top output shaft of the motor. The miniature ultrasonic probe and the laser vibrometer are both electrically connected to an external display screen.

[0015] Preferably, the right end of the grooved wheel is rotatably connected to the left end of the connecting seat, and the back of the first mounting shell is provided with a hollow groove.

[0016] Preferably, the back sensor head of the second pressure sensor is connected to the second airbag, and the second pressure sensor is electrically connected to an external display screen.

[0017] Preferably, the bottom of the second fixing block is fixedly connected to the right end of the bottom of the second mounting shell, the bottom of the limiting plate is fixedly connected to the center of the bottom of the second mounting shell, and the left end of the gear inside the gear plate is rotatably connected to the left end of the second mounting shell through a gear rod.

[0018] The present invention has the following advantages: The present invention provides a fire reconnaissance drone with a thermal shield, which, compared with similar equipment, has the following improvements:

[0019] This invention discloses a fire reconnaissance drone with a thermal protection shield. It incorporates a thermal protection mechanism that, through the inflation and deflation of a first airbag, functions as both an "adaptive clamp" and an "intelligent buffer," achieving a leap from static protection to dynamic intelligent adaptation. This enhances mission resilience and survivability in extreme fire environments. A detection mechanism, utilizing a combination of a miniature ultrasonic probe and a laser vibrometer, overcomes the limitations of traditional drones that only perform external observation or single-function detection. This enables the diagnosis of the internal health status of building structures in extreme fire environments, forming a complete "discovery-lock-confirmation" intelligent assessment closed loop. A cooperating mechanism, through a second airbag... The system applies flexible micro-pressure to areas suspected of severe damage in stages to prevent secondary damage to the damaged surface. Then, through the combination of resistance strain gauges and electric springs, the damaged surface is detected more accurately, achieving a breakthrough from "qualitative identification" to multi-dimensional quantitative assessment of "crack-strength" damage, thus improving the accuracy and reliability of fire site structural risk assessment. A static mechanism is set up, with friction blocks contacting the surface to be tested, to achieve a stable and safe transition of the UAV from aerial flight mode to "quasi-static" damaged surface operation mode. The combination of the second torsion spring and the first torsion spring avoids interference with the detection accuracy and the UAV's own attitude caused by rotor airflow impact or fuselage vibration. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of the structure of the present invention;

[0021] Figure 2 This is a three-dimensional exploded view of the thermal protection mechanism of the present invention;

[0022] Figure 3 This is a three-dimensional exploded view of the detection mechanism of the present invention;

[0023] Figure 4 This is the present invention. Figure 3 Enlarged structural diagram at point A;

[0024] Figure 5 This is the present invention. Figure 3 Enlarged structural diagram at point B;

[0025] Figure 6 This is a three-dimensional exploded view of the mounting rod and sliding rod of the present invention;

[0026] Figure 7 This is a three-dimensional exploded structural diagram of the static mechanism of the present invention.

[0027] The components include: bracket-1, thermal protection mechanism-2, thermal protection cover-21, mounting bracket-22, high-temperature resistant flexible limiting strap-23, first airbag-24, composite layer-25, connecting pipe-26, reversing valve-27, first miniature pressure sensor-28, connecting rod-3, detection mechanism-4, first mounting shell-41, miniature motor-42, turntable-43, first protruding rod-44, grooved wheel-45, fixing rod-46, mounting block-47, miniature ultrasonic probe-48, mating mechanism-49, mounting rod-491, sliding rod-492, second airbag-493. Second pressure sensor-494, elastic V-bar-495, electric spring-496, resistance strain gauge-497, electromagnetic block-498, connecting seat-410, first motor housing-411, laser vibration meter-412, static mechanism-5, second mounting housing-51, first fixing block-52, first torsion spring-53, rotating block-54, second protruding rod-55, sliding plate-56, gear tooth plate-57, second torsion spring-58, second fixing block-59, limiting plate-510, connecting frame-511, friction block-512, second motor housing-6, rotor-7. Detailed Implementation

[0028] The following is in conjunction with the appendix Figures 1-7 The principles and features of the present invention are described below. The examples given are for illustrative purposes only and are not intended to limit the scope of the invention. The invention is described more specifically in the following paragraphs by way of example with reference to the accompanying drawings. It should be noted that the drawings are in a very simplified form and use non-precise proportions, and are only used to facilitate and clarify the illustration of the embodiments of the present invention.

[0029] In the description of this invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing the invention and for 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 the invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0030] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "setting" 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 mechanical connection or an electrical 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 invention based on the specific circumstances. The embodiments of this invention will now be described according to its overall structure.

[0031] Example 1:

[0032] Please see Figures 1-2 The present invention discloses a fire reconnaissance drone with a heat shield, comprising a support 1, a heat protection mechanism 2 fixedly connected to the top of the support 1, six sets of connecting rods 3 fixedly connected to the outer wall of the heat protection mechanism 2, a detection mechanism 4 fixedly connected to the outer side of the two sets of connecting rods 3 on the back of the heat protection mechanism 2, a static mechanism 5 fixedly connected to the bottom of the detection mechanism 4, a second motor housing 6 fixedly connected to the top of the detection mechanism 4, and a motor fixedly connected inside the second motor housing 6, and a rotor 7 fixedly connected to the top output shaft of the motor inside the second motor housing 6.

[0033] The thermal protection mechanism 2 includes a thermal protection cover 21. The thermal protection cover 21 is fixedly connected to the top of the bracket 1, and the drone fuselage is located at the center of the thermal protection cover 21. The mounting frame 22 is fixedly connected to the bottom of the thermal protection cover 21. Eight sets of high-temperature resistant flexible limiting straps 23 are equidistantly arranged on the outer wall of the mounting frame 22. The mounting frame 22 contains a first airbag 24. The high-temperature resistant flexible limiting straps 23 are convenient to prevent the first airbag 24 from completely separating from the thermal protection cover 21 or swinging randomly when the first airbag 24 is under low pressure or depressurized. When the first airbag 24 is impacted, the deformation range of the first airbag 24 is constrained to prevent excessive displacement.

[0034] A composite layer 25 is adhesively connected to the outside of the first airbag 24, and a connecting tube 26 is fixedly connected to the bottom of the first airbag 24. The connecting tube 26 is T-shaped and has an air inlet and an air outlet.

[0035] A reversing valve 27 is fixedly connected to the delivery port of the connecting pipe 26, and the reversing valve 27 is electrically connected to an external control terminal.

[0036] The top of the mounting bracket 22 is fixedly connected to a first miniature pressure sensor 28, and the bottom sensor head of the first miniature pressure sensor 28 is connected to the first airbag 24. The first miniature pressure sensor 28 can detect the pressure inside the first airbag 24 and transmit it to an external display screen to realize real-time feedback of the pressure inside the first airbag 24.

[0037] The composite layer 25 is composed of a flexible nano-aerogel felt and a silicone pad with a raised dot array. A composite aramid fiber mesh is adhered to the inside of the first airbag 24. The first micro pressure sensor 28 is electrically connected to the external display screen. The connecting tube 26 is connected to the external air pump.

[0038] The working principle of a fire reconnaissance drone with a heat shield based on Embodiment 1 is as follows:

[0039] First, when using this device, place it in the work area, and then connect it to an external power source to provide the power required for its operation.

[0040] Secondly, when hovering and heat insulation are required, the external air pump is started and the reversing valve 27 is opened. Gas enters the first airbag 24 through the air inlet of the connecting pipe 26, and the pressure inside the first airbag 24 is detected by the first micro pressure sensor 28. The detection data is transmitted to the external display screen for real-time feedback on the pressure inside the first airbag 24 until the set high pressure is reached. At this time, the first airbag 24 presses tightly against the drone body, and the high-temperature resistant flexible limiting strap 23 is in a taut state. When high-speed drag reduction is required, the reversing valve 27 is reversed through the external control terminal, so that the gas inside the first airbag 24 is discharged through the air outlet of the connecting pipe 26, and the pressure is reduced. At this time, through The high-temperature resistant flexible limiting strap 23 prevents the first airbag 24 from detaching from or swinging randomly from the thermal shield 21, allowing the thermal shield 2 to have slight displacement relative to the UAV body to dissipate aerodynamic loads. During use, the first airbag 24 ensures uniform pressure transmission and increases friction under high pressure through the silicone pad with a raised array on the composite layer 25, preventing relative slippage. Under low pressure, the gaps between the raised points allow a small amount of airflow to assist in heat dissipation. By inflating and deflating the first airbag 24, it has the dual functions of "adaptive clamp" and "intelligent buffer", realizing the leap from static protection to dynamic intelligent adaptation, and improving mission flexibility and survivability in extreme fire environments.

[0041] Example 2:

[0042] Please see Figures 3-4 The present invention provides a fire reconnaissance drone with a heat shield. Compared with the first embodiment, this embodiment further includes a detection mechanism 4. The detection mechanism 4 includes a first mounting shell 41. The outer sides of the two sets of connecting rods 3 on the back of the heat shield 21 are fixedly connected to the first mounting shell 41. A micro motor 42 is fixedly connected to the left end of the first mounting shell 41. The micro motor 42 facilitates the rotation of the turntable 43.

[0043] The output shaft of the micro motor 42 is fixedly connected to a turntable 43. The right end of the turntable 43 is eccentrically provided with a first protruding rod 44. The outer wall of the first protruding rod 44 is intermittently engaged with the grooved wheel 45. The right end of the grooved wheel 45 is fixedly connected to a fixing rod 46. The right end of the fixing rod 46 is fixedly connected to a mounting block 47. The fixing rod 46 facilitates the adjustment of the tilt angle of the mounting block 47.

[0044] A miniature ultrasonic probe 48 is fixedly connected to one end of the mounting block 47, and a mating mechanism 49 is fixedly connected to the other end of the mounting block 47. The outer wall of the mounting block 47 is rotatably connected to the connecting seat 410. A first motor housing 411 is provided at the bottom of the connecting seat 410. A laser vibrometer 412 is fixedly connected to the lower back of the first motor housing 411. The laser vibrometer 412 facilitates rapid scanning of an area and plotting a vibration frequency / amplitude distribution map.

[0045] A motor is fixedly connected to the bottom of the first motor housing 411, and a connecting seat 410 is fixedly connected to the top output shaft of the motor. The miniature ultrasonic probe 48 and the laser vibrometer 412 are both electrically connected to the external display screen. The right end of the grooved wheel 45 is rotatably connected to the left end of the connecting seat 410. A slot is provided on the back of the first mounting housing 41.

[0046] In this embodiment:

[0047] When the drone hovers, a laser vibrometer 412 is first used to quickly scan an area, drawing a vibration frequency / amplitude distribution map, which is then transmitted to an external display screen. The operator quickly locates the area suspected of being severely damaged on the external display screen. Then, the motor inside the first motor housing 411 is activated. This motor drives the connecting seat 410 to rotate, which in turn drives the miniature ultrasonic probe 48 to rotate via the mounting block 47, positioning the probe towards the suspected severely damaged area. Next, the miniature motor 42 is activated, driving the turntable 43 to rotate. The turntable 43 then drives the first protruding rod 44 in a circular motion. The first protruding rod 44, through intermittent engagement with the grooved wheel 45, drives the grooved wheel 45 to rotate, which in turn drives the fixed... The rod 46 rotates, which in turn drives the mounting block 47 to rotate. The mounting block 47 then adjusts the tilt angle of the miniature ultrasonic probe 48, allowing the probe to be precisely pressed against the suspected severely damaged area for ultrasonic testing. This confirms the depth and extent of internal cavities or peeling, and the data is transmitted to an external display screen. Staff can then read the precise surface temperature on the external display screen and perform a micro-pressure test using the cooperating mechanism 49 to determine the surface strength. By integrating multi-sensor data through an external cloud algorithm, a risk assessment is generated. This overcomes the limitations of traditional drones that only perform external observation or single detection, enabling the diagnosis of the internal health status of building structures in extreme fire environments. This forms a complete "discovery-lock-confirmation" intelligent assessment closed loop.

[0048] Example 3:

[0049] Please see Figure 3 and Figures 5-6 The present invention provides a fire reconnaissance drone with a heat shield. Compared with embodiment one, this embodiment further includes a cooperating mechanism 49. The cooperating mechanism 49 includes a mounting rod 491. The other end of the mounting block 47 and the upper back of the first motor housing 411 are fixedly connected to one end of the mounting rod 491. The other end of the mounting rod 491 is slidably connected to the outer wall of the sliding rod 492. The mounting rod 491 facilitates the limiting movement of the sliding rod 492.

[0050] The back of the sliding rod 492 on the upper back of the first motor housing 411 is fixedly connected to the back of the second airbag 493. The left end of the sliding rod 492 on the upper back of the first motor housing 411 is fixedly connected to the second pressure sensor 494. The other end of the sliding rod 492 of the mounting block 47 is fixedly connected to the elastic V-shaped rod 495. The second pressure sensor 494 facilitates the detection of the internal pressure of the second airbag 493 when a micro-pressure is applied.

[0051] The elastic V-shaped rod 495 is fixedly connected to both ends of the electric spring 496, and the electric spring 496 is electrically connected to an external power supply device. Resistance strain gauges 497 are attached to each of the spring wire axes of the electric spring 496 in the ±45° direction. Six sets of electromagnetic blocks 498 are equidistantly arranged inside the mounting rod 491, and the electromagnetic blocks 498 are magnetically attracted to the sliding rod 492. The back sensor of the second pressure sensor 494 is connected to the second airbag 493. The second pressure sensor 494 is electrically connected to an external display screen, and the electromagnetic blocks 498 are electrically connected to an external current output device.

[0052] In this embodiment:

[0053] When a micro-pressure test is required on a suspected severely damaged area, an external current output device drives the six sets of electromagnetic blocks 498 inside the mounting rod 491 on the upper back of the first motor housing 411 to work in stages. This causes the sliding rod 492 inside the mounting rod 491 to move backward step by step due to the magnetic attraction of the six sets of electromagnetic blocks 498, thereby driving the second airbag 493 to move backward step by step. This applies a gradual, flexible micro-pressure to the suspected severely damaged area, preventing secondary damage to the damaged surface. Then, the external current output device drives the six sets of electromagnetic blocks 498 inside the mounting rod 491 at the other end of the mounting block 47 to work in stages. This causes the sliding rod 492 inside the mounting rod 491 at the other end of the mounting block 47 to move outward step by step due to the magnetic attraction of the six sets of electromagnetic blocks 498, thereby driving the elastic V-shaped rod 495 to insert into the suspected severely damaged area. Within the gaps in the area, when the second airbag 493 applies micro-pressure to the suspected severely damaged area, the electric spring 496 is activated by an external power source. The elastic V-shaped rod 495, affected by the micro-pressure, causes the electric spring 496 to extend or contract, generating a stress field around the electric spring 496. This stress field affects the resistance value of the strain gauge 497, causing the strain element inside the strain gauge 497 to deform under stress. This allows the operator to calculate the length change of the electric spring 496 based on the resistance value of the strain gauge 497, thereby indirectly determining the actual deformation of the surface of the measured area. This enables more accurate detection of the damaged surface, achieving a breakthrough from "qualitative identification" to multi-dimensional quantitative assessment of "crack-strength," and improving the accuracy and reliability of fire scene structural risk assessment.

[0054] Example 4:

[0055] Please see Figure 7 The present invention provides a fire reconnaissance drone with a heat shield. Compared with embodiment one, this embodiment further includes a static mechanism 5. The static mechanism 5 includes a second mounting shell 51. The bottom of the first mounting shell 41 is fixedly connected to the second mounting shell 51, and the back of the second mounting shell 51 is provided with a hollow groove. The bottom left end of the second mounting shell 51 is fixedly connected to a first fixing block 52, and the upper right end of the first fixing block 52 is fixedly connected to a first torsion spring 53. The second mounting shell 51 facilitates the installation and fixing of the first fixing block 52.

[0056] The right end of the first torsion spring 53 is fixedly connected to the left edge of the rotating block 54. The right edge of the rotating block 54 is fixedly connected to the second protruding rod 55. The outer wall of the second protruding rod 55 is slidably connected to the slide plate 56. The back of the slide plate 56 is fixedly connected to the inner tooth plate of the gear tooth plate 57. The inner tooth plate of the gear tooth plate 57 facilitates the movement of the slide plate 56.

[0057] A second torsion spring 58 is fixedly connected to the right end of the inner gear of the gear plate component 57, and a second fixing block 59 is fixedly connected to the right end of the second torsion spring 58. The outer wall of the inner gear plate of the gear plate component 57 is slidably connected to the limiting plate 510. A connecting frame 511 is fixedly connected to the back of the inner gear plate of the gear plate component 57. The connecting frame 511 facilitates the installation of the friction block 512.

[0058] Friction block 512 is glued to the back of connecting bracket 511. The bottom of second fixing block 59 is fixedly connected to the bottom right end of the second mounting shell 51. The bottom of limiting plate 510 is fixedly connected to the center of the bottom of the second mounting shell 51. The left end of the gear in gear tooth plate 57 is rotatably connected to the left end of the second mounting shell 51 through gear rod.

[0059] In this embodiment:

[0060] When the drone approaches the surface to be inspected, it contacts the surface via friction block 512. Then, the motor inside the second motor housing 6 drives the rotor 7 to slow down, converting the kinetic energy of the rotor 7 into controllable frictional resistance. This achieves a stable and safe transition of the drone from aerial flight mode to a "quasi-static" damaged surface operation mode. During use, due to the impact of airflow from the rotor 7 or the vibration of the fuselage, friction block 512 synchronously drives the inner gear plate of gear tooth plate component 57 to move backward. The inner gear plate of gear tooth plate component 57 drives the gear teeth to move backward. The internal gear of the gear plate 57 rotates, which drives the second torsion spring 58 to rotate. The second torsion spring 58 provides initial shock absorption for the friction block 512. As the internal gear plate of the gear plate 57 moves backward, it simultaneously drives the slide plate 56 to move backward. The slide plate 56 drives the rotating block 54 to rotate via the second protrusion 55. The rotating block 54 drives the first torsion spring 53 to rotate. The first torsion spring 53 provides secondary shock absorption for the friction block 512, preventing interference with the detection accuracy and its own attitude caused by the airflow impact of the rotor 7 or the vibration of the fuselage.

[0061] This invention provides an improved fire reconnaissance drone with a thermal protection shield. It features a thermal protection mechanism 2 that, through the inflation and deflation of a first airbag 24, functions as both an "adaptive clamp" and an "intelligent buffer," achieving a leap from static protection to dynamic intelligent adaptation. This enhances mission resilience and survivability in extreme fire environments. A detection mechanism 4, through the cooperation of a miniature ultrasonic probe 48 and a laser vibrometer 412, overcomes the limitations of traditional drones that only perform external observation or single-function detection, enabling the diagnosis of the internal health status of building structures in extreme fire environments, forming a complete "discovery-lock-confirmation" intelligent assessment closed loop. A cooperating mechanism 49, through a second airbag 4... 93. Flexible micro-pressure is applied to suspected severely damaged areas in stages to prevent secondary damage to the damaged surface. Then, through the cooperation of resistance strain gauge 497 and electric spring 496, the damaged surface is detected more accurately, realizing a breakthrough from "qualitative identification" to multi-dimensional quantitative assessment of "crack-strength" damage, improving the accuracy and reliability of fire site structural risk assessment. A static mechanism 5 is set up, which contacts the surface to be tested through friction block 512, realizing a stable and safe transition of the UAV from aerial flight mode to "quasi-static" damaged surface operation mode. Then, through the cooperation of second torsion spring 58 and first torsion spring 53, the impact of airflow from rotor 7 or fuselage vibration on detection accuracy and its own attitude is avoided.

[0062] The above description shows and illustrates the basic principles, main features, and advantages of the present invention. Standard parts used in the present invention can be purchased from the market, and irregular parts can be customized according to the description and drawings. The specific connection methods of each part adopt conventional methods such as bolts, rivets, and welding that are mature in the prior art. The machinery, parts, and equipment adopt conventional models in the prior art, and the circuit connection adopts conventional connection methods in the prior art, which will not be described in detail here.

[0063] The above description of the disclosed embodiments enables those skilled in the art to make or use the invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the invention. Therefore, the invention is not to be limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A fire reconnaissance drone with a heat shield, comprising a support (1), a heat protection mechanism (2) fixedly connected to the top of the support (1), six sets of connecting rods (3) fixedly connected to the outer wall of the heat protection mechanism (2), a detection mechanism (4) fixedly connected to the outer side of the two sets of connecting rods (3) on the back of the heat protection mechanism (2), a static mechanism (5) fixedly connected to the bottom of the detection mechanism (4), a second motor housing (6) fixedly connected to the top of the detection mechanism (4), and a motor fixedly connected inside the second motor housing (6), and a rotor (7) fixedly connected to the top output shaft of the motor inside the second motor housing (6); Its features are: The thermal protection mechanism (2) includes a thermal protection cover (21). The thermal protection cover (21) is fixedly connected to the top of the bracket (1), and the drone body is located in the center of the thermal protection cover (21). The mounting frame (22) is fixedly connected to the bottom of the thermal protection cover (21). Eight sets of high-temperature resistant flexible limiting straps (23) are equidistantly arranged on the outer wall of the mounting frame (22). The mounting frame (22) contains a first airbag (24). A composite layer (25) is glued to the outside of the first airbag (24). A connecting pipe (26) is fixedly connected to the bottom of the first airbag (24). A reversing valve (27) is fixedly connected to the inlet of the connecting pipe (26). A first micro pressure sensor (28) is fixedly connected to the top of the mounting frame (22), and the sensor head at the bottom of the first micro pressure sensor (28) is connected to the first airbag (24). The detection mechanism (4) includes a first mounting shell (41). The outer sides of the two sets of connecting rods (3) on the back of the heat shield (21) are fixedly connected to the first mounting shell (41). A micro motor (42) is fixedly connected to the left end of the first mounting shell (41). A turntable (43) is fixedly connected to the output shaft of the right end of the micro motor (42). A first protruding rod (44) is eccentrically provided on the right end of the turntable (43). The outer wall of the first protruding rod (44) is intermittently engaged with the grooved wheel (45). The right end of the grooved wheel (45) is... A fixing rod (46) is fixedly connected to the end of the fixed rod (46), and a mounting block (47) is fixedly connected to the right end of the fixing rod (46). A miniature ultrasonic probe (48) is fixedly connected to one end of the mounting block (47), and a mating mechanism (49) is fixedly connected to the other end of the mounting block (47). The outer wall of the mounting block (47) is rotatably connected to the connecting seat (410). A first motor housing (411) is provided at the bottom of the connecting seat (410), and a laser vibrometer (412) is fixedly connected to the lower back of the first motor housing (411). The mating mechanism (49) includes a mounting rod (491). The other end of the mounting block (47) and the upper back of the first motor housing (411) are both fixedly connected to one end of the mounting rod (491). The other end of the mounting rod (491) is slidably connected to the outer wall of the sliding rod (492). A second airbag (493) is fixedly connected to the back of the sliding rod (492) above the back of the first motor housing (411). A second pressure sensor is fixedly connected to the left end of the sliding rod (492) above the back of the first motor housing (411). 494), the sliding rod (492) at the other end of the mounting block (47) is fixedly connected to the elastic V-shaped rod (495), the elastic V-shaped rod (495) is fixedly connected to both ends of the electric spring (496), and the electric spring (496) is electrically connected to the external power supply equipment. Resistance strain gauges (497) are attached to each of the ±45° directions of the spring wire axis of the electric spring (496). Six sets of electromagnetic blocks (498) are equidistantly arranged inside the mounting rod (491), and the electromagnetic blocks (498) are magnetically attracted to the sliding rod (492).

2. The fire reconnaissance drone with a thermal shield according to claim 1, characterized in that: The static mechanism (5) includes a second mounting shell (51), the bottom of the first mounting shell (41) is fixedly connected to the second mounting shell (51), and the back of the second mounting shell (51) is provided with a slot. The bottom left end of the second mounting shell (51) is fixedly connected to a first fixing block (52), the upper right end of the first fixing block (52) is fixedly connected to a first torsion spring (53), the right end of the first torsion spring (53) is fixedly connected to the left edge of the rotating block (54), and the right edge of the rotating block (54) is fixedly connected to a second protruding rod (55). 55) A sliding groove plate (56) is slidably connected to the outer wall. The back of the sliding groove plate (56) is fixedly connected to the inner tooth plate of the gear tooth plate (57). A second torsion spring (58) is fixedly connected to the right end of the inner gear of the gear tooth plate (57). A second fixing block (59) is fixedly connected to the right end of the second torsion spring (58). The outer wall of the inner tooth plate of the gear tooth plate (57) is slidably connected to the limiting plate (510). A connecting frame (511) is fixedly connected to the back of the inner tooth plate of the gear tooth plate (57). A friction block (512) is adhesively connected to the back of the connecting frame (511).

3. The fire reconnaissance drone with a thermal shield according to claim 2, characterized in that: The composite layer (25) is composed of a flexible nano-aerogel felt and a silicone pad with a raised dot array, and a composite aramid fiber mesh is bonded inside the first airbag (24).

4. A fire reconnaissance drone with a thermal shield according to claim 3, characterized in that: The first miniature pressure sensor (28) is electrically connected to an external display screen, and the connecting pipe (26) is connected to an external air pump.

5. A fire reconnaissance drone with a thermal shield according to claim 4, characterized in that: A motor is fixedly connected to the bottom of the first motor housing (411), and a connecting seat (410) is fixedly connected to the top output shaft of the motor. The miniature ultrasonic probe (48) and the laser vibrometer (412) are both electrically connected to the external display screen.

6. A fire reconnaissance drone with a thermal shield according to claim 5, characterized in that: The right end of the groove wheel (45) is rotatably connected to the left end of the connecting seat (410), and the back of the first mounting shell (41) is provided with a hollow groove.

7. A fire reconnaissance drone with a thermal shield according to claim 6, characterized in that: The second pressure sensor (494) is connected to the back sensor head of the second airbag (493), and the second pressure sensor (494) is electrically connected to the external display screen.

8. A fire reconnaissance drone with a thermal shield according to claim 7, characterized in that: The bottom of the second fixing block (59) is fixedly connected to the right end of the bottom of the second mounting shell (51), the bottom of the limiting plate (510) is fixedly connected to the center of the bottom of the second mounting shell (51), and the left end of the gear in the gear plate (57) is rotatably connected to the left end of the second mounting shell (51) through the gear rod.

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