Emergency rescue engineering structural column and mounting and recycling method

Abstract

The invention relates to an emergency rescue engineering structural column and a mounting and recycling method. The emergency rescue engineering structural column comprises a folding type annular air bag and a plurality of annular air bag bodies, wherein the folding type annular air bag is composed of a plurality of overlapped air bag ring bodies; the air bag bearing frame is arranged between at least two adjacent air bag ring bodies of the plurality of overlapped air bag ring bodies; the unmanned aerial vehicle flight system comprises a rack and a flight control system, the rack is installed on the air bag bearing frame, and the flight control system is arranged on the rack; the automatic air inflation system comprises automatic air inflation equipment and an air inflation control system, the automatic air inflation equipment is arranged on the air bag bearing frame, and the air inflation control system is arranged on the rack; and the power supply system is used for supplying power to the unmanned aerial vehicle flight system and the automatic inflation system. The invention aims to solve the problem of urgency in emergency rescue in a disaster area so as to effectively improve the temporary emergency supporting capacity for an endangered collapse structure.

Description

Technical Field

[0001] The present invention belongs to the technical field of emergency rescue equipment, and more particularly relates to an emergency rescue engineering structural column and an installation and recovery method thereof. Background Art

[0002] In the emergency rescue in disaster areas, there is a risk of secondary collapse in collapsed buildings. When rescuers carry out rescue operations, they need to manage the safety of the rescue site and support and protect the rescue passage and the rescue operation space to resolve the problems of possible further injuries to trapped people and the safety of the rescuers themselves caused by secondary collapse.

[0003] Existing temporary supports are usually made of steel pipes or steel plates and connected into a whole through connectors, but there is a problem that they are not convenient and difficult to transport to the disaster site. There is an urgent need in the field of emergency rescue for a column support that can maintain support and is lightweight and convenient.

[0004] The air automatic inflation technology is currently mainly applied in the fields of aerospace, such as the tire automatic inflation system of airplanes. The development of aerospace technology provides important technical support for the air automatic inflation device. And the automatic control technology is one of the core technologies of the air automatic inflation device. By adopting automatic control algorithms and sensors, the air automatic inflation device can monitor the air pressure of the object to be inflated in real time and automatically adjust the inflation amount according to the preset threshold to ensure that the object to be inflated is maintained in a safe state.

[0005] In view of this, the present invention is specifically proposed. Summary of the Invention

[0006] In view of the above analysis, the present invention aims to solve the urgent problems faced in the emergency rescue in disaster areas, that is, how to effectively improve the temporary emergency support ability for structures on the verge of collapse.

[0007] To solve the above problems, the technical solution of the present invention is as follows:

[0008] The first aspect of the present invention provides an emergency rescue engineering structural column, including:

[0009] A foldable annular airbag, which is composed of a plurality of superimposed airbag rings. The interior of the plurality of superimposed airbag rings is used to fill a light gas and can form an airbag support column after filling;

[0010] An airbag carrier, which is installed between at least two adjacent airbag rings of the plurality of superimposed airbag rings and is used to carry the foldable annular airbag;

[0011] The drone flight system includes a frame and a flight control system. The frame is mounted on the airbag carrier, and the flight control system is arranged on the frame for controlling flight.

[0012] The automatic inflation system includes an automatic inflation device and an inflation control system. The automatic inflation device is provided on the airbag carrier, and the inflation control system is arranged on the frame for controlling the automatic inflation and deflation of the foldable annular airbag by the automatic inflation device. And

[0013] The power supply system is used to supply power to the drone flight system and the automatic inflation system.

[0014] In an optional embodiment, eight nozzles are provided on the foldable annular airbag, including two inflation nozzles and two deflation nozzles at the top, and two inflation nozzles and two deflation nozzles at the bottom. The inflation nozzles and deflation nozzles are evenly and alternately arranged.

[0015] In an optional embodiment, the airbag carrier is a carbon fiber annular frame, with an outer shape consistent with the airbag ring of the foldable annular airbag, and is superimposed between adjacent airbag rings.

[0016] In an optional embodiment, the frame is connected and fixed to the center of the annular frame of the airbag carrier through multiple connecting rods. One end of each of the multiple connecting rods is connected and fixed to the frame, and the other end is connected and fixed to the inner wall of the airbag carrier.

[0017] In an optional embodiment, the flight control system consists of two core parts: a power system and a flight controller. The power system is a four-plus-four rotor, that is, four large rotors and four small rotors, which are arranged on the frame and are switched for use between the large rotors and the small rotors in a predetermined state.

[0018] In an optional embodiment, the automatic inflation device includes a small air pump and a compressed gas cylinder. Both the small air pump and the compressed gas cylinder are embedded in the groove of the airbag carrier. The small air pump and the compressed gas cylinder are respectively connected to the inflation nozzle and the deflation nozzle provided on the foldable annular airbag through an air pump hose and a gas cylinder hose, and the automatic inflation and deflation of the foldable annular airbag are controlled by the inflation control system.

[0019] In an optional embodiment, the inflation control system includes:

[0020] A temperature detection module, which is used to monitor the external environmental temperature to determine whether the current environmental conditions are suitable for performing the operation task;

[0021] A ranging module, which is used to accurately measure the height of the frame from the ground to determine whether the airbag strut is on the ground;

[0022] A barometric pressure detection module is disposed inside the foldable annular airbag and is used to sense the change in air pressure inside the airbag in real time;

[0023] A control module serves as a control center to control the automatic start and stop of the automatic inflation device, so as to start the automatic inflation device when the height of the rack from the ground reaches a threshold value, and at the same time perform command control on each module.

[0024] In an alternative embodiment, the emergency rescue engineering structural column further includes one or more of the following:

[0025] A remote control system, which includes a remote control platform, an unmanned aerial vehicle (UAV) flight system operator, and an automatic inflation system operation button. The remote control platform is equipped with a signal transmitter and a signal receiver, and displays the current air pressure value inside the airbag, the external environmental temperature value, the height value from the ground, the position information value, and the battery power value. The UAV flight system operator includes a direction operation lever, an emergency rotor switching button, and a one-key return button. The automatic inflation system operation button includes an emergency brake button, an inflation button, and a deflation button;

[0026] A GPS positioning system is used to transmit position information to the remote control platform;

[0027] An autonomous obstacle avoidance system that uses a vision sensor (depth camera) for flight route planning to perform autonomous obstacle avoidance.

[0028] The second aspect of the present invention provides an installation method for the emergency rescue engineering structural column according to the above, including:

[0029] Equipment installation;

[0030] System initialization;

[0031] The flight control system issues an instruction to guide the rack with the foldable annular airbag to fly to a designated position;

[0032] The control module instructs the distance measurement module to measure the distance between the rack and the ground. If the distance does not reach the preset value, a signal is immediately sent to the flight control system, and the flight control system adjusts the rotation speed and angle of the rotor to change the distance between the rack and the ground. Conversely, if the distance reaches the preset value, the inflation control system activates a small air pump to perform an automatic inflation operation on the foldable annular airbag;

[0033] The air pressure detection module operates synchronously to continuously monitor the air pressure changes inside the airbag. When it detects that the air pressure rises to the first threshold, the control module immediately sends a signal to the flight control system, and the flight control system switches the four large rotors to four small rotors. If the air pressure inside the airbag has not reached the first threshold, the inflation operation continues until the air pressure inside the airbag reaches the first threshold, completing the above rotor switching;

[0034] After the rotor switching, the inflation control system continues to drive the small air pump to work until the air pressure inside the airbag rises to the second threshold, and then shuts down the inflation equipment. The folded annular airbag inflates to form airbag struts, providing stable support for the structure on the verge of collapse.

[0035] The third aspect of the present invention provides a method for recycling the emergency rescue engineering structural column according to the above, including:

[0036] System initialization;

[0037] The inflation control system immediately starts the automatic deflation mechanism and activates the small air pump to perform automatic deflation operation on the folded annular airbag;

[0038] The air pressure detection module operates synchronously to continuously monitor the air pressure changes inside the airbag. When it detects that the air pressure drops to the first threshold, the control module immediately sends a signal to the flight control system, and the flight control system switches the four small rotors to four large rotors. If the air pressure inside the airbag has not reached the first threshold, the deflation operation continues until the air pressure inside the airbag reaches the first threshold, completing the above rotor switching;

[0039] After the rotor switching, the inflation control system continues to drive the small air pump to work until the air pressure inside the airbag drops to the second threshold, the airbag struts contract to the original state, and then shuts down the inflation equipment, completing the recycling of the folded annular airbag.

[0040] Beneficial effects: The present invention proposes to provide an emergency rescue engineering structural column to support buildings or temporary construction sites on the verge of collapse. This device is an efficient rescue equipment integrating characteristics such as rapid flight, air pressure adaptive control, multi-functional emergency response, strong structure, and simple operation, and is designed to provide timely, stable, and effective support in emergency situations. Specifically, at least the following beneficial effects can be obtained:

[0041] (1) With the help of the airbag bearing technology, the folded annular airbag (airbag column) provides support. By selecting appropriate airbag materials and calculating the ratio of air pressure to the upper pressure it can bear, the role of firmly supporting the building can be achieved.

[0042] (2) By means of UAV flight technology, the UAV flight system ensures the flight performance and safety of the UAV; in particular, the flight control system realizes a stable connection design through a solid UAV frame and an airbag carrier. The detachable connection method not only ensures the firmness of the connection, but also facilitates quick disassembly, assembly and maintenance.

[0043] (3) By means of air automatic inflation technology, the automatic inflation system integrates a variety of key components, including a control module and various sensors, to real-time sense data such as flight altitude, air temperature, air pressure, etc., and comprehensively judge and start automatic inflation of the airbag.

[0044] (4) In particular, by means of the HC-SR04 ultrasonic ranging module to provide high-precision distance information, the single-chip microcomputer can intelligently evaluate the current flight altitude and send a signal to the flight control system. Subsequently, the flight control system precisely adjusts the rotation speed of the rotor to reach the preset ideal altitude. Once the preset altitude is reached, the single-chip microcomputer activates the compressed gas cylinder and the DC mini air pump to start working, and starts the automatic inflation system.

[0045] (5) By means of the detected external environment temperature data, the single-chip microcomputer judges whether the current environmental conditions are suitable for continuing to execute the operation task. At the same time, the single-chip microcomputer will also accurately calculate the maximum duration that the equipment can continuously work safely under the current external temperature conditions according to the measured specific temperature value, greatly improving the safety and efficiency of the operation task.

[0046] (6) By means of remote monitoring, the aerial operation situation is timely fed back to the remote control platform of the remote control system, and the on-site situation can be comprehensively grasped. In addition, the device has the ability of large-scale deployment, and can efficiently operate and dispatch the aircraft fleet on the remote control platform, so as to accurately realize the core function of supporting buildings.

[0047] It should be understood that the implementation of any embodiment of the present invention does not mean that multiple or all of the above beneficial effects need to be simultaneously possessed or achieved. BRIEF DESCRIPTION OF THE DRAWINGS

[0048] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following will briefly introduce the drawings required for the description of the embodiments or the prior art. Obviously, the drawings described below are only exemplary, and for those of ordinary skill in the art, other implementation drawings can be obtained according to the provided drawings without creative labor.

[0049] The structures, ratios, sizes, etc. shown in this specification are only used to cooperate with the content disclosed in the specification for those who are familiar with this technology to understand and read, and are not used to limit the implementation conditions of the present invention. Therefore, they do not have substantial technical significance. Any modification of the structure, change in the ratio relationship, or adjustment of the size, without affecting the effects that the present invention can produce and the purposes that can be achieved, should still fall within the scope covered by the technical content disclosed in the present invention.

[0050] Figure 1 It is a schematic diagram of the overall structure of a structural column for an emergency rescue project provided by an embodiment of the present invention;

[0051] Figure 2 It is a schematic diagram (front view) of the airbag carrier structure provided by an embodiment of the present invention;

[0052] Figure 3 It is a side view of the airbag carrier provided by an embodiment of the present invention;

[0053] Figure 4 It is a schematic diagram (back view) of the airbag carrier structure provided by an embodiment of the present invention;

[0054] Figure 5 It is a schematic diagram of the UAV flight system structure provided by an embodiment of the present invention;

[0055] Figure 6 It is a schematic diagram of the detailed structure of the control panel provided by an embodiment of the present invention;

[0056] Figure 7 It is a schematic diagram of the application scenario provided by an embodiment of the present invention;

[0057] Figure 8 It is a schematic diagram of the installation method (automatic inflation control) process provided by an embodiment of the present invention;

[0058] Figure 9 It is a schematic diagram of the disassembly method (automatic deflation control) process provided by an embodiment of the present invention.

[0059] Explanation of reference numerals:

[0060] 1. Foldable annular airbag; 11. Airbag ring body; 12. Inflation nozzle; 13. Deflation nozzle;

[0061] 2. Airbag carrier;

[0062] 3. UAV flight system; 31. Frame; 32. Large rotor; 33. Small rotor; 34. Large rotor protective shell; 35. Small rotor protective shell; 36. Flight control damping plate; 37. Flight controller;

[0063] 4. Automatic inflation system; 41. Small air pump; 42. Compressed gas cylinder; 43. Temperature detection module; 44. Distance measurement module; 45. Control module; 46. Air pump hose; 47. Gas cylinder hose;

[0064] 5. Power supply system; 51. Hydrogen energy battery; 52. Battery carrier;

[0065] 6. GPS positioning system;

[0066] 7. Autonomous obstacle avoidance system.

[0067] The same or corresponding marks in the figure represent the same or corresponding parts. Detailed implementation manners

[0068] To make the objectives, technical solutions and advantages of the embodiments of the present invention clearer and more understandable, the embodiments of the present invention will be further described in detail below in conjunction with the embodiments and the accompanying drawings. Herein, the illustrative embodiments of the present invention and their descriptions are used to explain the present invention, but not to limit the present invention.

[0069] In the present invention, unless otherwise clearly specified and defined, terms such as "installation", "connection", "connection", "fixation" and other terms should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or integrated; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the communication inside two components or the interaction relationship between two components. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0070] It should be understood that the terms "including / containing", "consisting of...", or any other variant are intended to cover non-exclusive inclusion, so that a product, device, process or method including a series of elements not only includes those elements, but also includes other elements that are not explicitly listed when needed, or also includes elements inherent to such product, device, process or method. Without further limitations, the elements defined by the statement "including / containing...", "consisting of..." do not exclude the existence of other identical elements in the product, device, process or method including the said elements.

[0071] It should also be understood that terms such as "upper", "lower", "front", "rear", "left", "right", "top", "bottom", "inner", "outer", etc. indicating the orientation or positional relationship are based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device, component or structure referred to must have a specific orientation, be constructed or operated in a specific orientation, and cannot be understood as a limitation to the present invention.

[0072] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Thus, features defined with "first" and "second" may explicitly or implicitly include one or more of such features. In the description of the present invention, "a plurality of" means two or more unless otherwise specifically defined.

[0073] The implementation of the present invention will be described in detail below in conjunction with preferred embodiments.

[0074] As Figures 1-4 shown, there is shown an overall structure of a structural column for emergency rescue engineering in an embodiment. The structural column for emergency rescue engineering, or what is also called an air rescue emergency support column, mainly consists of a foldable annular airbag 1, an airbag carrier 2, a drone flight system 3, an automatic inflation system 4, and a power supply system 5. The foldable annular airbag 1 serves as the main structure of the column support body, providing support strength to carry the on-the-verge-of-collapse building structure; the airbag carrier 2 carries the foldable annular airbag 1 and at the same time mounts the drone flight system 3, and the foldable annular airbag 1 is carried to a designated position by the drone flight; the drone flight system 3 provides the flight power and flight control for the entire support body; the automatic inflation system 4 automatically inflates and deflates the foldable annular airbag 1; and the power supply system 5 provides power guarantee for the power consumption requirements of the drone flight system 3 and the automatic inflation system 4.

[0075] Regarding the foldable annular airbag 1, specifically, referring to Figure 1 , the foldable annular airbag 1 is a combined foldable hollow structure composed of several superimposed airbag rings 11. By "foldable" it means that when the inside of the airbag ring 11 is filled with a light gas, it can be propped up to form an airbag pillar, and in the deflated state, it can be contracted and folded, similar to the propping up and compression of a spring. Through experiments to measure the air pressure that the airbag material itself can withstand, calculate the ratio of the air pressure to the upper pressure it can withstand, and determine the air pressure value to be set through induction, so as to achieve the effect of firmly supporting the building (as Figure 7 ).

[0076] The foldable annular airbag 1 can be reasonably composed of several airbag rings 11 according to factors such as the size of the support space, the support height, and the support strength. In this embodiment, the foldable annular airbag 1 has four airbag rings 11. The airbag ring 11 is made of TPU material and is externally wrapped with a polyester protective sleeve; the outer diameter of the ring is preferably designed to be 100 cm, the inner diameter is 60 cm, and the height is 40 cm.

[0077] To meet the needs of inflation and deflation, several air nozzles should be provided on the foldable annular airbag 1. In this embodiment, eight air nozzles are provided, as Figures 2-4As shown, there are two inflation nozzles 12 and two deflation nozzles 13 at the top, and also two inflation nozzles 12 and two deflation nozzles 13 at the bottom. The inflation nozzles 12 and the deflation nozzles 13 are arranged at uniform intervals alternately, so as to facilitate the rapid and uniform inflation and deflation operations of the airbag, ensuring the use in emergency operations.

[0078] For the airbag carrier 2, continue to refer to Figures 1-4 , the airbag carrier 2 is installed between at least two adjacent airbag loops 11 of the foldable annular airbag 1, and is used to carry the airbag struts.

[0079] Preferably, the airbag carrier 2 is an annular frame, whose shape is consistent with the airbag loop 11 of the foldable annular airbag 1, and is installed at the center of the foldable annular airbag 1.

[0080] The airbag carrier 2 is made of carbon fiber material and is wrapped with a polyester protective sleeve on the outside to create a stable and lightweight carrier frame.

[0081] As Figure 1 shown, there are two airbag loops 11 in the upper part, two airbag loops 11 in the lower part, and an airbag carrier 2 is clamped in the middle. The airbag carrier 2 and the airbag loop 11 are connected in a soft manner, such as being adhered together.

[0082] For the UAV flight system 3, as Figures 3-6 shown, the UAV flight system 3 first includes a frame 31. The frame 31 is installed on the airbag carrier 2, and the frame 31 is used to arrange UAV-related components and carry the flight control system.

[0083] In the embodiment of the present invention, the frame 31 adopts a star-shaped planar shape to arrange a plurality of rotors thereon. The frame 31 is connected and fixed to the center of the annular frame of the airbag carrier 2 through a plurality of connecting rods. One end of the plurality of connecting rods is connected and fixed to the frame 31, such as by threaded connection or welding fixation, and the other end is welded or point-threaded to the airbag carrier 2 for fixation, taking into account both the firmness of the connection and the convenience of disassembly, assembly and maintenance.

[0084] In the embodiment of the present invention, the angular relationship between the flight controller nose and the frame is an X-shaped structure and a cross-shaped structure, and the frame design includes the above two structures.

[0085] The UAV flight system 3 further includes a flight control system. The flight control system is arranged on the frame 31 and is used to control the flight of the UAV, including providing flight power, controlling the flight direction, altitude, speed, etc.

[0086] In the embodiment of the present invention, the flight control system consists of two core parts, namely the power system and the flight controller 37. The power system is a four-plus-four rotor layout, that is, four large rotors 32 and four small rotors 33, which are arranged on the frame 31. The large rotors 32 and the small rotors 33 are switched for use under a predetermined state, which will be described in detail later.

[0087] In the embodiment of the present invention, the four large rotors 32 are equipped with large rotor protective shells 34. Similarly, the four small rotors 33 are equipped with small rotor protective shells 35. The protective shells provide protection for the rotors to prevent the airbag or carbon fiber propeller blades from being damaged out of control. All of these are arranged on the frame 31.

[0088] The flight controller 37 and various detection components are arranged on the flight control damping plate 36, which will be described in detail later.

[0089] Preferably, the protective shell is a carbon fiber ring-shaped protective outer shell, and the large and small rotors are accommodated in the ring-shaped protective shell.

[0090] For the automatic inflation system 4, it first includes an automatic inflation device. The automatic inflation device is arranged on the airbag carrier 2, that is, carried by the airbag carrier 2, and is used for automatically inflating and deflating the foldable ring-shaped airbag 1.

[0091] In the embodiment of the present invention, as Figure 2 、 Figure 3 shown, the automatic inflation device is composed of a small air pump 41 and a compressed gas cylinder 42. Since the airbag carrier 2 is a ring-shaped structure, similar to a hollow tire, with a ring-shaped groove in the middle, the small air pump 41 and the compressed gas cylinder 42 are both embedded in the groove of the airbag carrier 2. The small air pump 41 is connected to the compressed gas cylinder 42 through a gas cylinder hose 47, and is connected to the inflation nozzle 12 and the deflation nozzle 13 provided on the foldable ring-shaped airbag 1 through an air pump hose 46, so as to automatically inflate and deflate the foldable ring-shaped airbag 1 in the control mode. One or more small air pumps 41 can be provided. For example, eight 5V DC inflation small air pumps are used in cooperation with the compressed gas cylinder and connected to the above-mentioned foldable ring-shaped airbag 1. Some of the small air pumps are used for inflation and some are used for deflation, that is, some are used as inflation pumps and some are used as deflation pumps. One or more compressed gas cylinders 42 can also be provided according to actual situations.

[0092] A plurality of airbag rings 11 can be interconnected. Nozzles are provided on the upper and lower airbag rings 11 in contact with the airbag carrier 2 to facilitate the connection between the nozzles and the air pump hose 46. For example, in the form of male-female docking, female nozzles are provided on the airbag rings 11, and corresponding male nozzles are provided on the airbag carrier 2. The male nozzles are connected to the air pump hose 46, or the air pump hose 46 is directly inserted into the female nozzles.

[0093] The automatic inflation system 4 further includes an inflation control system, which is arranged on the frame 31 and is used to control the automatic inflation and deflation of the foldable annular airbag 1 by the automatic inflation device.

[0094] In the embodiment of the present invention, the inflation control system includes a temperature detection module 43, a ranging module 44, a pressure detection module, and a control module 45. These modules are ingeniously embedded in the control module 45 to form a compact and fully functional system. All of these are installed on the flight control damping plate 36, as Figure 6 shown.

[0095] Among them, the temperature detection module 43 is used to monitor the external environmental temperature; the temperature detection module 43 uses a temperature detection sensor.

[0096] As Figure 4 shown, the ranging module 44 is used to accurately measure the height from the ground; the ranging module 44 uses an HC-SR04 ultrasonic ranging module.

[0097] The pressure detection module is arranged inside the foldable annular airbag 1 and is used to sense the real-time pressure change inside the airbag; the pressure detection module uses a PS002 pressure detection sensor.

[0098] The control module 45 serves as the control center, controls the automatic start and stop of the automatic inflation device, and conducts command control on each sensor. The control module 45 uses an STM32 single-chip microcomputer.

[0099] The temperature detection sensor transmits the real-time external temperature data to the STM32 single-chip microcomputer. The single-chip microcomputer receives the temperature data and conducts intelligent analysis based on these data to judge whether the current environmental conditions are suitable for continuing to execute the operation task. At the same time, the single-chip microcomputer will also accurately calculate the maximum duration for which the device can continuously and safely operate under the measured specific temperature value. Subsequently, the single-chip microcomputer timely feeds back these important temperature information and the predicted maximum working duration to the control center to ensure that the control center can comprehensively grasp the on-site situation and make reasonable scheduling and decisions based on this. This process not only demonstrates the intelligent processing ability of the single-chip microcomputer but also greatly improves the safety and efficiency of the operation task.

[0100] The HC-SR04 ultrasonic ranging module measures the distance between the drone flight system carried by the airbag strut and the ground by emitting ultrasonic pulses and receiving their echoes. With the high-precision distance information provided by the HC-SR04 ultrasonic ranging module, the single-chip microcomputer can intelligently evaluate the current flight altitude and determine an optimal flight altitude accordingly. And it can judge whether the airbag strut is currently on the ground according to the threshold set by the system. If the set threshold is not reached, it will transmit a signal to the above-mentioned flight control system to adjust the flight altitude. Specifically, the flight control system precisely adjusts the rotation speed of the rotor to reach the ideal altitude.

[0101] The PS002 pressure detection sensor is used to detect the air pressure inside the airbag strut. The measurement range of this sensor is relatively wide, with a pressure measurement range of 0 - 400 kPa. According to the magnitude of the pressure, the resistance value of the piezoresistor will change. The PS002 pressure detection sensor is connected to a fixed interface of the STM32 single-chip microcomputer, and outputs an analog voltage signal to the single-chip microcomputer. Inside the single-chip microcomputer, an analog-to-digital conversion is performed, and it is compared with the set threshold to judge whether the air pressure value inside the airbag strut is sufficient to shut down the automatic inflation device.

[0102] After the PS002 pressure detection sensor transmits a signal to the single-chip microcomputer, when the air pressure inside the airbag strut reaches the first set air pressure threshold, the flight control system switches the large rotor to a small rotor to ensure the endurance ability;

[0103] After the PS002 pressure detection sensor transmits a signal to the single-chip microcomputer, when the air pressure inside the airbag strut reaches the second set air pressure threshold (i.e., the ideal air pressure value), several inflation air pumps driven by the single-chip microcomputer stop working;

[0104] When recovering the airbag strut, the STM32 single-chip microcomputer drives the above-mentioned several deflation air pumps to operate and deflate the airbag strut;

[0105] During the deflation process of the airbag strut, when the air pressure signal inside the airbag strut transmitted by the PS002 pressure detection sensor to the single-chip microcomputer reaches the above first threshold, the small rotor of the drone switches to the large rotor to ensure that the drone flight system can maintain stable flight;

[0106] After the airbag column deflates to the specified air pressure, the STM32 single-chip microcomputer issues an instruction to control the device to reach the next working surface or return to the base.

[0107] For the power supply system 5, it is used to supply power to the drone flight system 3 and the automatic inflation system 4. As Figure 6As shown in the figure, in order to ensure the long-lasting battery life of the device, the power supply system adopts a hydrogen energy battery 51, which not only has a high energy density but also is environmentally friendly and efficient. The hydrogen energy battery 51 is carried by a battery carrier 52, and the battery carrier 52 is integrated with the flight control damping plate 36, and the hydrogen energy battery 51 is arranged between the two. In addition, the battery shell is specially made of high-temperature resistant materials, which further improves the safety performance during operation.

[0108] In addition, the emergency rescue engineering structural column provided by the embodiment of the present invention further includes a remote control system (not shown in the figure), and the remote control system includes a remote control platform, a drone flight system operator, and an automatic inflation system operation button, all of which are integrated on a physical operator.

[0109] The remote control platform is equipped with a signal transmitter and a signal receiver, and displays the internal air pressure value, external environmental temperature value, height from the ground value, position information value, and battery power value inside the airbag support column. The remote control platform clearly displays the monitored information on the screen of the operator. In addition, the platform also cleverly incorporates a voice alarm system. Once it receives a signal that the internal air pressure of the airbag support column is abnormal or the external temperature value deviates from the normal range, it will immediately activate the voice alarm to remind the ground operator to take corresponding measures in time and conduct precise operation command.

[0110] The drone flight system operator includes a direction operation lever, an emergency rotor switch button, and a one-key return button;

[0111] The automatic inflation system operation button includes an emergency brake button, an inflation button, and a deflation button.

[0112] In addition, as Figure 6 , the emergency rescue engineering structural column provided by the embodiment of the present invention further includes a GPS positioning system 6, and the GPS positioning system is used to transmit position information to the remote control platform.

[0113] In addition, the emergency rescue engineering structural column provided by the embodiment of the present invention further includes an autonomous obstacle avoidance system 7. The autonomous obstacle avoidance system uses a visual sensor (depth camera) for drone flight route planning to achieve autonomous obstacle avoidance. The visual sensor (depth camera) can accurately capture and analyze extremely detailed information in the environment, including the shape, size, exact position of the obstacle, and core data such as the relative distance from the drone, and transmit the data to the flight controller. The flight controller adjusts the rotation of the motor, thereby realizing efficient autonomous obstacle avoidance of the drone in a complex and changing dynamic environment. The depth camera can continuously monitor the surrounding environment and respond quickly. By accurately capturing and analyzing the characteristics of obstacles, the drone can flexibly adjust its flight path, make autonomous decisions, and execute obstacle avoidance actions, effectively avoiding potential risks, ensuring the smooth progress of the flight mission, and thus greatly improving the safety and reliability of the flight.

[0114] See Figure 8 , the installation method of the emergency rescue engineering structural column provided by the embodiment of the present invention includes the following steps:

[0115] First, perform equipment installation. After the airbag and each component are transported to the disaster area, they are quickly assembled on-site;

[0116] System initialization, start the inflation program;

[0117] The drone flight system (specifically the flight control system) issues an instruction to guide the drone carrying the foldable ring-shaped airbag to fly to the designated position;

[0118] After arriving, the single-chip microcomputer instructs the ranging module to measure the distance between the rack (i.e., the center of the airbag support column) and the ground. If the distance does not reach the preset value, the single-chip microcomputer immediately sends a signal to the drone flight system, and the drone flight system adjusts the rotation speed and angle of the rotor to change the distance between the rack and the ground. Conversely, if the distance reaches the preset value, the inflation control system activates the small air pump to start the inflation operation;

[0119] During the inflation process, the air pressure detection module runs synchronously and continuously monitors the air pressure change in the airbag support column. When it detects that the air pressure rises to the first threshold (i.e., one standard atmospheric pressure), the system immediately sends a signal to the drone flight system, and the drone flight system switches the four large rotors to four small rotors to extend the endurance time. If the air pressure in the airbag has not reached the first threshold, the inflation operation continues until the air pressure in the airbag reaches the first threshold and the above rotor switching is completed;

[0120] After the rotor switching, the inflation control system continues to drive the small air pump to work until the air pressure in the airbag rises to the second threshold (i.e., the ideal air pressure state), shuts down the inflation equipment, and the foldable ring-shaped airbag is inflated to form an airbag support column, providing stable support for the structure on the verge of collapse, as Figure 7 shown.

[0121] See Figure 9 , the recovery method (or disassembly method) of the emergency rescue engineering structural column provided by the embodiment of the present invention includes the following steps:

[0122] System initialization, start the deflation program;

[0123] The automatic inflation system immediately starts the automatic deflation mechanism and activates several small deflation pumps to perform automatic deflation operations on the foldable ring-shaped airbag;

[0124] The air pressure detection module runs synchronously, continuously monitoring the air pressure change inside the airbag. When it detects that the air pressure drops to the first threshold, the system immediately sends a signal to the UAV flight system, instructing it to switch the four small rotors to four large rotors to ensure that the UAV can maintain a stable hovering state. If the air pressure inside the airbag has not reached the first threshold before this, the deflation operation continues until the air pressure inside the airbag reaches the first threshold, and then the above-mentioned rotor switching is completed.

[0125] After the rotor switching, the inflation control system does not stop immediately, but continues to drive the small air deflation pump until the air pressure inside the airbag further drops to the second threshold. At this time, the air pressure detection module quickly feeds this information back to the single-chip microcomputer, and the single-chip microcomputer then instructs to close several running DC air deflation pumps, thus completing the entire automatic deflation process, and the airbag struts contract to the original state, completing the recovery of the foldable annular airbag.

[0126] Regarding the specific circuit diagram design details inside each system, this article does not elaborate on them in detail here. However, it is worth mentioning that such a precise design ensures that all system components can operate under a stable and reliable power supply, and under the intelligent scheduling of the STM32 single-chip microcomputer, the components cooperate seamlessly to jointly complete all the predetermined functions of the dynamic inflation control system successfully.

[0127] In summary, the present invention aims to solve the urgent problems faced in disaster area emergency rescue, that is, how to effectively improve the temporary emergency support ability for structures on the verge of collapse, and provides an air rescue emergency intelligent inflation column support body to support buildings or temporary building sites on the verge of collapse. This device is an efficient rescue equipment integrating characteristics such as fast flight, air pressure adaptive control, multi-functional emergency response, strong structure, and simple operation, and is designed to provide timely, stable, and effective support in emergency situations. The device is applicable to emergency scenarios and can quickly reach the disaster area to serve as a temporary rescue equipment. The device also has the ability of large-scale deployment and can efficiently operate and schedule a fleet of aircraft on a remote control platform, thus accurately realizing the core function of supporting buildings.

[0128] Finally, it should be noted that the above are only the preferred embodiments of this application and are not used to limit this application. Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or perform equivalent replacements for some of the technical features. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of this application shall be included within the protection scope of this application.

Claims

1. An emergency rescue engineering structural column, characterized in that, Including: A foldable annular airbag, which is composed of several superimposed airbag rings. The interior of the several superimposed airbag rings is used to fill with light gas and can form an airbag support column after filling; An airbag carrier, which is installed between at least two adjacent airbag rings of the several superimposed airbag rings and is used to carry the foldable annular airbag; A drone flight system, including a frame and a flight control system. The frame is installed on the airbag carrier, and the flight control system is arranged on the frame for controlling flight; An automatic inflation system, including an automatic inflation device and an inflation control system. The automatic inflation device is arranged on the airbag carrier, and the inflation control system is arranged on the frame for controlling the automatic inflation and deflation of the foldable annular airbag by the automatic inflation device; and A power supply system, which is used to supply power to the drone flight system and the automatic inflation system.

2. The emergency rescue engineering structural column according to claim 1, characterized in that: Eight air nozzles are arranged on the foldable annular airbag, including two inflation air nozzles and two deflation air nozzles at the top, and two inflation air nozzles and two deflation air nozzles at the bottom. The inflation air nozzles and the deflation air nozzles are arranged alternately and evenly.

3. The emergency rescue engineering structural column according to claim 1, characterized in that: The airbag carrier is a carbon fiber annular frame, with an outer shape consistent with the airbag rings of the foldable annular airbag, and is superimposed between two adjacent airbag rings.

4. The emergency rescue engineering structural column according to claim 1, characterized in that: The frame is connected and fixed to the center of the annular frame of the airbag carrier through a plurality of connecting rods. One end of each of the plurality of connecting rods is connected and fixed to the frame, and the other end is connected and fixed to the inner wall of the airbag carrier.

5. The emergency rescue engineering structural column according to claim 1, characterized in that: The flight control system is composed of two core parts: a power system and a flight controller. The power system is a four-plus-four rotor, that is, four large rotors and four small rotors, which are arranged on the frame and are switched for use between the large rotors and the small rotors in a predetermined state.

6. The emergency rescue engineering structural column according to claim 1, characterized in that: The automatic inflation device includes a small air pump and a compressed gas cylinder. The small air pump and the compressed gas cylinder are both embedded in the grooves of the airbag carrier. The small air pump and the compressed gas cylinder are respectively connected to the inflation air nozzles and the deflation air nozzles arranged on the foldable annular airbag through an air pump hose and a gas cylinder hose, and are controlled by the inflation control system to perform automatic inflation and deflation of the foldable annular airbag.

7. The emergency rescue engineering structural column according to claim 1, characterized in that: The inflation control system includes: A temperature detection module, which is used to monitor the external environmental temperature to determine whether the current environmental conditions are suitable for performing the operation task; A ranging module, which is used to accurately measure the height of the frame from the ground to determine whether the airbag support column is on the ground; A barometric pressure detection module is disposed inside the foldable annular airbag and is used to sense the change in air pressure inside the airbag in real time; A control module, which serves as a control center, controls the automatic start and stop of the automatic inflation device, starts the automatic inflation device when the height of the frame from the ground reaches a threshold, and simultaneously controls each module with instructions.

8. The emergency rescue engineering structural column according to claim 1, wherein: This emergency rescue engineering structural column further includes one or more of the following: A remote control system, which includes a remote control platform, an unmanned aerial vehicle (UAV) flight system operator, and an automatic inflation system operation button. The remote control platform is equipped with a signal transmitter and a signal receiver, and displays the current air pressure value inside the airbag, the external environmental temperature value, the height from the ground value, the position information value, and the battery power value. The UAV flight system operator includes a direction operation lever, an emergency rotor switching button, and a one-key return button. The automatic inflation system operation button includes an emergency brake button, an inflation button, and a deflation button; A GPS positioning system, which is used to transmit position information to the remote control platform; An autonomous obstacle avoidance system, which uses a vision sensor (depth camera) to plan the flight route for autonomous obstacle avoidance.

9. A method for installing a structural column of an emergency rescue project according to any one of claims 1 to 8, characterized in that, Including: Equipment installation; System initialization; The flight control system issues instructions to guide the frame with the foldable annular airbag to fly to a specified position; The control module instructs the distance measurement module to measure the distance between the frame and the ground. If the distance does not reach the preset value, a signal is immediately sent to the flight control system, and the flight control system adjusts the rotation speed and angle of the rotors to change the distance between the frame and the ground. Conversely, if the distance reaches the preset value, the inflation control system activates a small air pump to perform an automatic inflation operation on the foldable annular airbag; The barometric pressure detection module runs synchronously and continuously monitors the change in air pressure inside the airbag. When it detects that the air pressure rises to the first threshold, the control module immediately sends a signal to the flight control system, and the flight control system switches the four large rotors to four small rotors. If the air pressure inside the airbag has not reached the first threshold, the inflation operation continues until the air pressure inside the airbag reaches the first threshold to complete the above rotor switching; After the rotor switching, the inflation control system continues to drive the small air pump to work until the air pressure inside the airbag rises to the second threshold, and the inflation device is shut down. The foldable annular airbag is inflated to form an airbag support column to stably support the structure on the verge of collapse.

10. A method for recycling the structural columns of an emergency rescue project according to any one of claims 1 to 8, characterized in that, Including: System initialization; The inflation control system immediately activates the automatic deflation mechanism and activates the small air pump to perform an automatic deflation operation on the foldable annular airbag; The barometric pressure detection module runs synchronously and continuously monitors the change in air pressure inside the airbag. When it detects that the air pressure drops to the first threshold, the control module immediately sends a signal to the flight control system, and the flight control system switches the four small rotors to four large rotors. If the air pressure inside the airbag has not reached the first threshold, the deflation operation continues until the air pressure inside the airbag reaches the first threshold to complete the above rotor switching; After the rotor is switched, the inflation control system continues to drive the small air pump to work until the air pressure in the airbag drops to the second threshold, the airbag strut contracts to the original state, and the inflation device is shut down to complete the recovery of the foldable annular airbag.

Images