A manned eVTOL aircraft with high-altitude fixed rescue function and its docking method

Abstract

This invention discloses a manned eVTOL aircraft with high-altitude fixed rescue function and its docking method, relating to the field of aircraft docking technology. The manned eVTOL aircraft includes a fuselage structure and a vacuum adsorption fixing device; the deployable support platform includes an electro-hydraulic telescopic device, a pull rod, a sleeve, and a crankshaft; the vacuum adsorption fixing device includes a folding telescopic robotic arm and a vacuum generating unit; the support platform can quickly provide a safe passage in emergency rescue situations, improving rescue efficiency and safety. The vacuum adsorption fixing device can create a negative pressure environment when in contact with a wall, thereby firmly fixing the eVTOL aircraft to the target position. A rotor protection ring is also provided on the arm to ensure flight safety. The electro-hydraulic robotic arm can automatically adjust the angle of the adsorption device through electric adjustment, making it fit against the wall, compensating for the control error of the UAV's flight attitude, and ensuring the stability and reliability of adsorption docking.

Description

Technical Field

[0001] This invention relates to the field of aircraft docking technology, specifically to a manned eVTOL aircraft with high-altitude fixed rescue function and its docking method. Background Technology

[0002] With the increasing demand for urban rescue, traditional rescue methods face numerous challenges, such as insufficient stability and rapid response capabilities in high-altitude environments. Existing aircraft suffer from insufficient high-altitude fixation capabilities: many aircraft cannot provide a stable support platform when docking at high altitudes, affecting rescue efficiency. Poor adaptability to complex environments: In urban high-altitude environments with dense buildings, aircraft need flexible docking capabilities, a requirement that current technology often cannot meet. Insufficient safety: During high-altitude rescues, the stability of the aircraft directly affects the safety of rescue personnel, and current technology lacks adequate safeguards in this regard.

[0003] Researchers have conducted long-term explorations into methods for securing aircraft at high altitudes, proposing various improvement schemes. For example, invention CN110329495A discloses a drone adsorption docking device and its docking method, which uses an adsorption landing gear to allow the drone to dock directly on vertical or inclined walls, greatly enhancing the drone's environmental adaptability. Its self-adjusting adsorption component can automatically adhere to the wall surface by pushing the self-adjusting push rod. However, adsorption landing gear is difficult to use on vertical walls. Summary of the Invention

[0004] The purpose of this invention is to overcome the shortcomings of the prior art and provide a manned eVTOL aircraft with high-altitude fixed rescue function and its docking method.

[0005] The objective of this invention is achieved through the following technical solution: In a first aspect, the present invention provides a manned eVTOL aircraft with high-altitude fixed rescue function, including an airframe structure and a vacuum adsorption fixing device; The front hatch of the fuselage structure is equipped with a deployable support platform, which includes a door panel and a door frame. An electro-hydraulic drive mechanism is provided between the door panel and the door frame. The electro-hydraulic drive mechanism includes a first fixed seat, an electro-hydraulic telescopic device, a second fixed seat, and a pull rod. The first fixed seat is located at the bottom of the fuselage structure and is hinged to one end of the electro-hydraulic telescopic device. The other end of the electro-hydraulic telescopic device is hinged to the pull rod. A limit device is also provided. A crankshaft is provided in the door panel, and the pull rod is fixedly connected to the crankshaft. The crankshaft is drivenly connected to a sleeve provided in the door frame, and the diameter of the crankshaft is smaller than the diameter of the sleeve. The second fixed seat is located at the bottom plate of the fuselage structure and is hinged to the pull rod. The vacuum adsorption fixing device includes a folding telescopic robotic arm, a vacuum generating unit, and an electric pneumatic circuit module. The folding telescopic robotic arm is fixed on the vacuum adsorption block, and the vacuum adsorption block has a groove. The vacuum generating unit is disposed on the groove partition. A pressure control mechanism is disposed outside the vacuum generating unit. The electric pneumatic circuit module is disposed on the bottom plate of the machine body structure and is electrically connected to the pressure control mechanism.

[0006] Based on the first aspect, the folding telescopic robotic arm includes a connecting block, a third fixed base, a fourth fixed base, a first robotic arm, and a second robotic arm; the third fixed base is fixedly mounted on the base plate, one end of the connecting block is fixed to the third fixed base, and the other end is connected to one end of the first robotic arm via a hinge device; the other end of the first robotic arm is hinged to one end of the second robotic arm, and the other end of the second robotic arm is hinged to one end of the fourth fixed base; the other end of the fourth fixed base is fixed to a vacuum adsorption block; the first and second robotic arms are internally equipped with clamping plates for fixing the pneumatic circuits and servo motor wires of the vacuum adsorption fixing device, and a hydraulic pump and a hydraulic cylinder are also installed at the bottom of the folding telescopic robotic arm.

[0007] Based on the first aspect, the pressure control mechanism includes a pressure detection unit, an air pump and a gas reversing valve, and the air pump's ventilation valve is connected to the vacuum generating unit; the folding telescopic robotic arm adjusts the angles of the first robotic arm and the second robotic arm based on feedback from the pressure detection unit.

[0008] Based on the first aspect, the vacuum generating unit is provided with a buckle inside for fixing the gas passage, and the vacuum generating unit is provided with a cover plate, which is a sealing ring and has multiple air holes. The vacuum generating unit is connected to the air pump through the air holes.

[0009] Based on the first aspect, the electric pneumatic circuit module includes an electric vacuum pump, a vacuum main pipe, an electromagnetic reversing valve, a first one-way valve, a second one-way valve, a pressure relief valve, a vacuum buffer tank, and a filter; the suction end of the electric vacuum pump is connected to the vacuum main pipe via the filter, one end of the vacuum main pipe is connected to the vacuum buffer tank via the first one-way valve, and the other end is connected to the electromagnetic reversing valve; the output end of the electromagnetic reversing valve is connected to the air port via a flexible hose; the vacuum main pipe is connected to the second one-way valve and the pressure relief valve in sequence, and then connected to the outside.

[0010] Based on the first aspect, the electric pneumatic circuit module is also provided with an electrical control module. The electric pneumatic circuit module is electrically connected to the pressure detection unit through the electrical control module. The electrical control module includes a power driver for controlling the operation of the electric vacuum pump and the electromagnetic reversing valve.

[0011] Based on the first aspect, an intelligent identification device is provided above the door frame, which is used to identify the surrounding environment during flight.

[0012] Based on the first aspect, it also includes a rotor structure, which includes a semi-circular protective ring, and the semi-circular protective ring is fixedly connected to the end of the arm through three support columns.

[0013] Based on the first aspect, handrail devices are provided on both sides of the door panel, and an electric hydraulic drive mechanism is provided on each side of the door frame.

[0014] Secondly, this application discloses a docking method for a manned eVTOL aircraft with high-altitude fixed rescue function as described above, comprising the following steps: Step 1: When the distance between the eVTOL aircraft body and the target wall is within the preset range, the flight control system sends a signal to determine the extension and retraction amount of the folding telescopic robotic arm through the intelligent identification device. The first robotic arm adjusts the vacuum generating unit to the vicinity of the target wall, and the second robotic arm adjusts the angle so that the edge of the cover plate of the vacuum generating unit contacts the target surface. The pressure sensor of the pressure control mechanism detects the pressure. If the pressure is within the preset range, the system enters the vacuum preparation stage. Step 2: The air pump is activated to extract air from inside the vacuum generating unit, creating negative pressure to ensure the vacuum generating unit is fixed to the target surface. At the same time, the pressure detection unit continuously monitors the air pressure during vacuum adsorption. If a drop in air pressure is detected, the flight control system will automatically adjust the working state of the air pump to maintain a stable adsorption force. The equipped acceleration sensor and tilt sensor monitor the stability of the eVTOL aircraft in real time. If an unstable state is detected, the flight control system will automatically adjust the altitude and attitude of the deployable support platform. Step 3: Start the electro-hydraulic drive mechanism. The electro-hydraulic telescopic device starts to operate. Hydraulic oil is delivered to the hydraulic cylinder. The piston of the hydraulic cylinder extends under the push of the hydraulic oil, pushing the second fixed seat and causing the door frame to unfold outward.

[0015] The beneficial effects of this invention are: 1) The support platform provided in this application can quickly offer a safe passage in emergency rescue situations, improving rescue efficiency and safety. Through a vacuum adsorption fixing device, a negative pressure environment can be created upon contact with the wall, thereby firmly securing the eVTOL aircraft to the target location. Rotor protection effectively prevents the rotor from colliding with surrounding objects during flight and rescue, ensuring flight safety.

[0016] 2) The angle of the adsorption device is automatically adjusted by the electric adjustable robotic arm to make it fit the wall, which makes up for the control error of the drone's flight attitude and ensures the stability and reliability of adsorption and docking. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the structure of the deployable support platform according to an embodiment of the present invention; Figure 2 This is a schematic diagram of the structure of the electro-hydraulic drive device according to an embodiment of the present invention; Figure 3 This is a schematic diagram of the rotor protection ring according to an embodiment of the present invention; Figure 4 This is a schematic diagram of the structure of the vacuum generating unit according to an embodiment of the present invention; Figure 5 This is a schematic diagram of the structure of the electric pneumatic circuit module according to an embodiment of the present invention; In the diagram, 1-door panel, 2-door frame, 3-first fixed seat, 4-electric hydraulic telescopic device, 5-pull rod, 6-limiting device, 7-sleeve, 8-crankshaft, 9-second fixed seat, 10-semi-circular protective ring, 11-support column, 12-arm, 13-base plate, 14-third fixed seat, 15-connecting block, 16-hinge device, 17-first robotic arm, 18-second robotic arm, 19-fourth fixed seat, 20-vacuum generating unit, 21-pressure control mechanism, 22-vacuum main pipe, 25-filter, 26-vacuum buffer tank, 27-groove, 28-air hole, 29-cover plate, 30-handrail device, 31-intelligent identification device, 32-pressure relief valve, 33-second one-way valve, 34-first one-way valve, 35-electromagnetic reversing valve, 41-electric pneumatic circuit module. Detailed Implementation

[0018] The technical solution of the present invention will be clearly and completely described below with reference to the embodiments. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0019] See Figures 1-5 This invention provides a manned eVTOL aircraft with high-altitude fixed rescue capabilities and its docking method by introducing vacuum adsorption technology and an electro-hydraulic drive mechanism. This application enables the aircraft to dock stably in high-altitude environments and provides a safe working space for rescue personnel. The design of the vacuum adsorption block ensures stable fixation of the aircraft on various surfaces, greatly improving its applicability. The introduction of electro-hydraulic drive allows the support platform to be quickly deployed and retracted, improving rescue efficiency. Intelligent control enhances the aircraft's autonomous navigation and docking capabilities in complex environments. This provides an efficient, safe, and flexible solution for high-altitude rescue, significantly improving the response speed and success rate of urban rescue operations. The manned eVTOL aircraft includes a body structure and a vacuum adsorption fixing device. The front hatch of the fuselage structure is equipped with a deployable support platform, which includes a door panel 1 and a door frame 2. An electro-hydraulic drive mechanism is provided between the door panel 1 and the door frame 2. The electro-hydraulic drive mechanism includes a first fixed seat 3, an electro-hydraulic telescopic device 4, a second fixed seat 9, and a pull rod 5. The first fixed seat 3 is located at the bottom of the fuselage structure and is hinged to one end of the electro-hydraulic telescopic device 4. The other end of the electro-hydraulic telescopic device 4 is hinged to the pull rod 5. A limit device 6 is also provided. A crankshaft 8 is provided in the door panel 1, and the pull rod 5 is fixedly connected to the crankshaft 8. The crankshaft 8 is connected to the door frame. The sleeve 7 in body 2 is connected by a transmission, and the diameter of the crankshaft 8 is smaller than the diameter of the sleeve 7, forming a stable support structure to ensure that the door frame body 2 will not deform during the unfolding process; during operation, when the crankshaft 8 is driven to move in the sleeve 7 by the pull rod 5, the electro-hydraulic telescopic device 4 unfolds the door panel body 1. The limiting device 6 constrains the trajectory and endpoint of the electro-hydraulic telescopic device 4 during the process, and can maintain its function even in the event of an abnormal power failure, ensuring that the support platform does not bounce back or move twice under wind load and personnel load, thereby improving the repeatability and safety of unfolding and retraction; the second fixed seat 9 is set at the bottom plate 13 of the body structure, and the second fixed seat 9 is hinged to the pull rod 5; The vacuum adsorption fixing device includes a folding telescopic robotic arm, a vacuum generating unit 20, and an electric pneumatic circuit module 41. The folding telescopic robotic arm is fixed on the vacuum adsorption block, and the vacuum adsorption block is provided with two grooves 27. Four independent vacuum generating units 20 are provided on the partition of the grooves 27. Pressure control mechanisms 21 are respectively provided outside the four vacuum generating units 20. The electric pneumatic circuit module 41 is located on the bottom plate 13 of the machine body structure and is electrically connected to the pressure control mechanism 21.

[0020] Exemplarily, the folding telescopic robotic arm includes a connecting block 15, a third fixed base 14, a fourth fixed base 19, a first robotic arm 17, and a second robotic arm 18. The third fixed base 14 is fixedly mounted on the base plate 13. One end of the connecting block 15 is fixed to the third fixed base 14, and the other end is connected to one end of the first robotic arm 17 via a hinge device 16. The other end of the first robotic arm 17 is hinged to one end of the second robotic arm 18, and the other end of the second robotic arm 18 is hinged to one end of the fourth fixed base 19. The other end of the fourth fixed base 19 is fixed to a vacuum adsorption block. The first robotic arm 17 and the second robotic arm 18 are provided with clamping plates for fixing the pneumatic circuits and servo motor wires of the vacuum adsorption fixing device. A hydraulic pump and a hydraulic cylinder are also installed at the bottom of the folding telescopic robotic arm.

[0021] For example, the pressure control mechanism 21 includes a pressure detection unit, an air pump and a gas reversing valve, and the air pump's ventilation valve is connected to the vacuum generating unit 20; the folding telescopic robotic arm adjusts the angles of the first robotic arm 17 and the second robotic arm 18 based on feedback from the pressure detection unit.

[0022] For example, the vacuum generating unit 20 is provided with a buckle inside for fixing the gas passage, and the vacuum generating unit 20 is provided with a cover plate 29, which is a sealing ring and is provided with multiple air holes 28. The vacuum generating unit 20 is connected to the air pump through the air holes 28.

[0023] For example, the electric pneumatic circuit module 41 includes an electric vacuum pump, a vacuum manifold 22, an electromagnetic reversing valve 35, a first one-way valve 34, a second one-way valve 33, a pressure relief valve 32, a vacuum buffer tank 26, and a filter 25. The suction end of the electric vacuum pump is connected to the vacuum manifold 22 via the filter 25. One end of the vacuum manifold 22 is connected to the vacuum buffer tank 26 via the first one-way valve 34, and the other end is connected to the electromagnetic reversing valve 35. The output end of the electromagnetic reversing valve 35 is connected to the air port 28 via a flexible hose. The vacuum manifold 22 is connected to the second one-way valve 33 and the pressure relief valve 32 in sequence, and then connected to the outside. Emergency pressure relief and disconnection are achieved through the pressure relief valve 32. Backflow of outside air is prevented through the second one-way valve 33. The electromagnetic reversing valve 35 has a four-way independent control structure, which drives four vacuum generating units 20 respectively for time-sharing or synchronous adsorption. Each channel is connected to a one-way valve and a throttling orifice to suppress the impact of transient leakage on the manifold pressure. The filter 25 can be quickly installed and removed to filter out wall dust and debris; the electric pneumatic module 41 is also connected to the flight control system, and performs adsorption-maintenance-decompression state control based on the pressure data of the pressure control mechanism 21 and the body attitude data, and sends valve pump commands to the electric pneumatic module 41.

[0024] For example, the electric pneumatic circuit module 41 is also provided with an electrical control module. The electric pneumatic circuit module 41 is electrically connected to the pressure detection unit through the electrical control module. The electrical control module includes a power driver for controlling the operation of the electric vacuum pump and the four-way electromagnetic reversing valve 35 to realize the selective pressure supply and fault isolation of the vacuum generating unit 20. For example, the electrical control module drives the electric vacuum pump and the electromagnetic reversing valve group to realize independent pressure building, pressure maintenance and pressure release control of the vacuum generating unit 20. If unit leakage or pump failure occurs, the electrical control module controls the vacuum buffer tank 26, the first one-way valve 34 and the second one-way valve 33 to maintain negative pressure and prevent backflow, thereby improving the reliability of adsorption docking.

[0025] For example, an intelligent identification device 31 is provided above the door frame 2, which is used to identify the surrounding environment during flight.

[0026] For example, it also includes a rotor structure, which includes a semi-circular protective ring 10, which is fixedly connected to the end of the arm 12 by three support columns 11.

[0027] For example, handrail devices 30 are provided on both sides of the door panel 1, and an electric hydraulic drive mechanism is provided on both sides of the door frame 2.

[0028] This application also discloses a docking method for a manned eVTOL aircraft with high-altitude fixed rescue function as described above, comprising the following steps: Step 1: When the distance between the eVTOL aircraft body and the target wall is within a preset range, the flight control system sends a signal to determine the extension and retraction amount of the folding telescopic robotic arm through the intelligent identification device 31. The first robotic arm 17 adjusts the vacuum generating unit 20 to the vicinity of the target wall, and the second robotic arm 18 adjusts the angle so that the edge of the cover plate 29 of the vacuum generating unit 20 contacts the target surface. The pressure sensor of the pressure control mechanism 21 detects the pressure. If the pressure is within a preset range, the system enters the vacuum preparation stage. Step 2: The air pump is activated to extract air from the vacuum generating unit 20, creating negative pressure to ensure that the vacuum generating unit 20 is fixed on the target surface. At the same time, the pressure detection unit continuously monitors the air pressure during vacuum adsorption. If a drop in air pressure is detected, the flight control system will automatically adjust the working state of the air pump to maintain a stable adsorption force. The acceleration sensor and tilt sensor equipped on the aircraft monitor the stability of the aircraft in real time. If an unstable state is detected, the system will automatically adjust the height and attitude of the deployable support platform. Step 3: Start the electro-hydraulic drive mechanism. The electro-hydraulic telescopic device 4 starts to operate. Hydraulic oil is delivered to the hydraulic cylinder. The piston of the hydraulic cylinder extends under the push of the hydraulic oil, pushing the second fixed seat 9, causing the door frame to unfold outward.

[0029] Specifically, step two includes: the pressure control mechanism 21 sends a command to the electric gas circuit module 41 to start the electric vacuum pump, and simultaneously switches the upper and lower diagonally arranged electromagnetic reversing valves 35 to connect to the vacuum main pipe for pre-evacuation; when the pressure of each chamber is less than the preset threshold, it is held for 1-2 seconds to detect micro-leakage; after the pre-evacuation is successful, the remaining electromagnetic reversing valves 35 are opened to evacuate air, so that the negative pressure of the four vacuum generating units 20 is synchronously established to the working threshold; if any passage has an excessive recovery rate or leakage, the pressure control mechanism 21 immediately closes the valve of that passage and sets it to "isolation", while the other passages maintain adsorption. Entering the pressure maintenance mode, the speed of the electric vacuum pump is adjusted in a closed loop according to the main pipe pressure; the vacuum buffer tank 26 and the one-way valve work together to suppress pressure fluctuations caused by micro-leakage; when the attitude change or wind load disturbance causes abnormal pressure in individual units, the pressure control mechanism 21 performs supplementary evacuation or continues isolation according to priority to ensure overall adsorption stability. The pressure control mechanism 21 periodically verifies the pressure, recovery rate and pump load current of each channel. After meeting the set threshold, it maintains the adsorption state and reports the "dock-hold" status to the flight control system. If a fault such as continuous pressure recovery or pump overload is detected, it automatically degrades to "three-way or two-way hold" and issues an alarm.

[0030] The above description is merely a preferred embodiment of the present invention. It should be understood that the present invention is not limited to the forms disclosed herein and should not be construed as excluding other embodiments. It can be used in various other combinations, modifications, and environments, and can be altered within the scope of the concept described herein through the above teachings or related technologies or knowledge. Modifications and variations made by those skilled in the art that do not depart from the spirit and scope of the present invention should be within the protection scope of the appended claims.

Claims

1. A manned eVTOL aircraft with high-altitude fixed rescue function, characterized in that: Including the body structure and vacuum adsorption fixation device; The front hatch of the fuselage structure is provided with a deployable support platform, which includes a door panel (1) and a door frame (2). An electro-hydraulic drive mechanism is provided between the door panel (1) and the door frame (2). The electro-hydraulic drive mechanism includes a first fixed seat (3), an electro-hydraulic telescopic device (4), a second fixed seat (9), and a pull rod (5). The first fixed seat (3) is located at the bottom of the fuselage structure. The first fixed seat (3) is hinged to one end of the electro-hydraulic telescopic device (4), and the other end of the electro-hydraulic telescopic device (4) is hinged to the pull rod (5). A limit device (6) is also provided. A crankshaft (8) is provided in the door panel (1), and the pull rod (5) is fixedly connected to the crankshaft (8). The crankshaft (8) is connected to a sleeve (7) provided in the door frame (2), and the diameter of the crankshaft (8) is smaller than the diameter of the sleeve (7). The second fixed seat (9) is located at the bottom plate (13) of the fuselage structure. Hinged to the tie rod (5); The vacuum adsorption fixing device includes a folding telescopic robotic arm, a vacuum generating unit (20), and an electric pneumatic circuit module (41); the folding telescopic robotic arm is fixed on the vacuum adsorption block, the vacuum adsorption block is provided with a groove (27), and the vacuum generating unit (20) is provided on the groove partition; a pressure control mechanism (21) is provided outside the vacuum generating unit (20), and the electric pneumatic circuit module (41) is provided at the bottom plate (13) of the machine body structure, and the electric pneumatic circuit module (41) is electrically connected to the pressure control mechanism (21).

2. A manned eVTOL aircraft with high-altitude fixed rescue function according to claim 1, characterized in that: The folding telescopic robotic arm includes a connecting block (15), a third fixed seat (14), a fourth fixed seat (19), a first robotic arm (17), and a second robotic arm (18). The third fixed seat (14) is fixedly mounted on the base plate (13). One end of the connecting block (15) is fixed to the third fixed seat (14), and the other end is connected to one end of the first robotic arm (17) through a hinge device (16). The other end of the first robotic arm (17) is hinged to one end of the second robotic arm (18), and the other end of the second robotic arm (18) is hinged to one end of the fourth fixed seat (19). The other end of the fourth fixed seat (19) is fixed to the vacuum adsorption block. The first robotic arm (17) and the second robotic arm (18) are provided with a card plate inside for fixing the pneumatic circuit and the wire of the servo motor of the vacuum adsorption fixing device. A hydraulic pump and a hydraulic cylinder are also installed at the bottom of the folding telescopic robotic arm.

3. A manned eVTOL aircraft with high-altitude fixed rescue function according to claim 2, characterized in that: The pressure control mechanism (21) includes a pressure detection unit, an air pump and a gas reversing valve. The air pump's ventilation valve is connected to the vacuum generating unit (20). The folding telescopic robotic arm adjusts the angles of the first robotic arm (17) and the second robotic arm (18) based on feedback from the pressure detection unit.

4. A manned eVTOL aircraft with high-altitude fixed rescue function according to claim 3, characterized in that: The vacuum generating unit (20) is provided with a buckle inside for fixing the gas passage. The vacuum generating unit (20) is provided with a cover plate (29), which is a sealing ring and is provided with multiple air holes (28). The vacuum generating unit (20) is connected to the air pump through the air holes (28).

5. A manned eVTOL aircraft with high-altitude fixed rescue function according to claim 4, characterized in that: The electric pneumatic circuit module (41) includes an electric vacuum pump, a vacuum manifold (22), an electromagnetic reversing valve (35), a first check valve (34), a second check valve (33), a pressure relief valve (32), a vacuum buffer tank (26), and a filter (25). The suction end of the electric vacuum pump is connected to the vacuum manifold (22) through the filter (25). One end of the vacuum manifold (22) is connected to the vacuum buffer tank (26) through the first check valve (34), and the other end is connected to the electromagnetic reversing valve (35). The output end of the electromagnetic reversing valve (35) is connected to the air port (28) through a hose. The vacuum manifold is connected to the second check valve (33) and the pressure relief valve (32) in sequence, and then connected to the outside.

6. A manned eVTOL aircraft with high-altitude fixed rescue function according to claim 5, characterized in that: The electric pneumatic circuit module (41) is also provided with an electrical control module. The electric pneumatic circuit module (41) is electrically connected to the pressure detection unit through the electrical control module. The electrical control module includes a power driver for controlling the operation of the electric vacuum pump and the electromagnetic reversing valve (35).

7. A manned eVTOL aircraft with high-altitude fixed rescue function according to claim 6, characterized in that: A smart identification device (31) is provided above the door frame (2), which is used to identify the surrounding environment during flight.

8. A manned eVTOL aircraft with high-altitude fixed rescue function according to claim 7, characterized in that: It also includes a rotor structure, which includes a semi-circular protective ring (10), and the semi-circular protective ring (10) is fixedly connected to the end of the arm (12) by three support columns (11).

9. A manned eVTOL aircraft with high-altitude fixed rescue function according to claim 8, characterized in that: Handrail devices (30) are provided on both sides of the door panel (1), and an electric hydraulic drive mechanism is provided on both sides of the door frame (2).

10. A docking method for a manned eVTOL aircraft with high-altitude fixed rescue function as described in claim 9, characterized in that, Includes the following steps: Step 1: When the distance between the eVTOL aircraft body and the target wall is within the preset range, the flight control system sends a signal to determine the extension and retraction amount of the folding telescopic robotic arm through the intelligent identification device (31). The first robotic arm (17) adjusts the vacuum generating unit (20) to the vicinity of the target wall, and the second robotic arm (18) adjusts the angle so that the edge of the cover plate (29) of the vacuum generating unit (20) contacts the target surface. The pressure sensor of the pressure control mechanism (21) detects the pressure. If the pressure is within the preset range, the system enters the air extraction preparation stage. Step 2: The air pump is started to extract the air inside the vacuum generating unit (20) to form a negative pressure, ensuring that the vacuum generating unit (20) is fixed on the target surface. At the same time, the air pressure during vacuum adsorption is continuously monitored by the pressure detection unit. If the air pressure drops, the flight control system will automatically adjust the working state of the air pump to maintain a stable adsorption force. The equipped acceleration sensor and tilt sensor monitor the stability of the eVTOL aircraft in real time. If an unstable state is detected, the flight control system will automatically adjust the height and attitude of the deployable support platform. Step 3: Start the electric hydraulic drive mechanism. The electric hydraulic telescopic device (4) starts to operate. Hydraulic oil is delivered to the hydraulic cylinder. The piston of the hydraulic cylinder extends under the push of the hydraulic oil, pushing the second fixed seat (9) and causing the door frame to unfold outward.

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