Vehicle-mounted flying stretcher

Abstract

The invention discloses a vehicle-mounted flight stretcher which is composed of a rescue vehicle platform and a vehicle-mounted rescue aircraft, the vehicle-mounted rescue aircraft comprises a rescue aircraft body and a ground rescue vehicle platform, and a special lifting type take-off and landing cabin is arranged on the ground rescue vehicle platform; the vehicle-mounted rescue aircraft body adopts a double-row serial heterogeneous duct layout, a streamline battery cabin is fixedly connected right below a main body frame of the aircraft body through hanging points, and an energy module is packaged in the streamline battery cabin; a load management system is integrated on the abdomen of the vehicle body main body frame, namely between the energy module and the vehicle body main body frame, and a medical stretcher is arranged under the load management system. A specially-designed large-load, compact and disassembly-free ducted aircraft serves as a connection aircraft to achieve the function similar to a stretcher, and the problem that vehicles cannot pass through and cannot be driven in harsh rescue environments such as dense forest mountains, traffic jam highways and urban blocked streets is solved.

Description

Technical Field

[0001] This invention relates to the field of vehicle-mounted flight stretcher technology, and more particularly to a vehicle-mounted flight stretcher. Background Technology

[0002] With the increasing frequency of natural disasters and rapid urbanization, the need for emergency rescue in complex and confined spaces such as densely forested mountain valleys, congested highways, and blocked urban streets is becoming increasingly urgent. These scenarios require aircraft with vertical takeoff and landing capabilities, sufficient payload capacity to transport the injured, and a compact fuselage size to adapt to confined spaces. Current rescue aircraft mainly include traditional helicopters, multi-rotor drones, and ducted fan aircraft.

[0003] Currently, the most common solutions for emergency rescue applications are standalone rescue aircraft, which are designed or modified to achieve specific rescue functions. For example, patent CN223432455U discloses a general-purpose casualty transport platform based on an unmanned aerial vehicle (UAV). A rescue cabin is mounted under the UAV via a connecting mechanism, achieving modular transport. This solution is based on a traditional multi-rotor platform, requiring a large rotor disk area to meet load requirements, which limits its operation in narrow spaces such as forests and urban streets. Furthermore, the under-mounted rescue cabin places high demands on anti-roll control during flight. Patent CN120057331A discloses an all-terrain rescue UAV, placing the rescue cabin on top of the fuselage with a telescopic support rod, attempting to solve terrain adaptability issues. However, its top-mounted rescue cabin layout results in a relatively high center of gravity, posing challenges to the attitude control system. The safety of the traditional rotor layout in limited spaces still needs further optimization. Patent CN120840869A proposes an aircraft and its material and personnel transport module, focusing on achieving precise control of the rope winding mechanism. This solution possesses basic hoisting capabilities, but lacks a rigid locking mechanism after load recovery. The flexible connection method poses challenges to the stability of casualty transport and the aircraft's attitude control during high-speed level flight or under turbulent airflow. Combining a ground vehicle platform with an aircraft to form rescue equipment offers advantages such as rapid response, high maneuverability, and a large operational range. Patent CN121201430A proposes a "flying elevator" concept, utilizing a ducted propeller device in conjunction with a power supply platform vehicle for vertical lifting. This solution addresses the range issue, but its configuration is primarily designed for fixed-point lifting scenarios, relying solely on single-dimensional vertical power. This results in low energy efficiency for long-distance horizontal transport missions and lacks safety design considerations for casualty transport.

[0004] This invention proposes a vehicle-mounted "flying stretcher" solution based on ambulances and dual-row tandem ducted aircraft. The vehicle serves as a platform for large-scale operation and en route rescue, while the specially designed, heavy-duty, compact, and non-disassembly-required ducted aircraft acts as a connecting aircraft to achieve a stretcher-like function. This solves the problem of vehicles being unable to pass through or arrive in time in harsh rescue environments such as densely forested mountain valleys, congested highways, and blocked streets in urban areas. Summary of the Invention

[0005] The purpose of this invention is to solve the technical problems existing in the prior art and to provide a vehicle-mounted flying stretcher.

[0006] To achieve the above objectives, the technical solution provided by the present invention is: a vehicle-mounted flying stretcher, comprising a rescue vehicle platform and a vehicle-mounted rescue flying vehicle. The vehicle-mounted rescue flying vehicle includes a rescue flying vehicle body and a ground rescue vehicle platform. A dedicated lifting and landing cabin is provided on the ground rescue vehicle platform. The rescue flying vehicle body is longitudinally elongated and has a lateral width D ≤ 2.4 meters. A skid-type landing gear is provided at the bottom of the rescue flying vehicle body. The skid-type landing gear is used to park in the dedicated lifting and landing cabin of the ground rescue vehicle platform.

[0007] The vehicle-mounted rescue aircraft adopts a dual-row tandem heterogeneous ducted fan layout. The fuselage of the vehicle-mounted rescue aircraft includes a main fuselage frame, on which a power unit is installed. The power unit includes a lift propulsion system that provides lift and a horizontal propulsion system that provides thrust. The lift propulsion system includes eight large-diameter lift ducted fans, which are arranged symmetrically in two rows along the longitudinal axis of the main fuselage frame and rigidly connected to both sides of the main fuselage frame by high-strength cantilever beams. The horizontal propulsion system consists of two independent small-diameter thrust ducted fans, located at the rear of the vehicle-mounted rescue aircraft fuselage. The thrust axis of the small-diameter thrust ducted fans is parallel to the longitudinal axis of the main fuselage frame. A streamlined battery compartment is fixedly connected to the lower part of the main fuselage frame through a mounting point, and the streamlined battery compartment encapsulates the energy module.

[0008] The load management system is integrated between the power module and the main fuselage frame. The load management system includes a rigging traction mechanism, a guide rail, and a rigid locking mechanism. The guide rail is mounted on the rigging traction mechanism. The rigid locking mechanism is hinged to the rear and sides of the lower part of the main fuselage frame to secure the medical stretcher. The rigid locking mechanism forms a connection between the medical stretcher and the main fuselage frame. The medical stretcher is located directly below the load management system. The rigidly locked medical stretcher and the power module above it together form the structural reinforcement ribs at the bottom of the rescue aircraft body to improve the torsional stiffness of the rescue aircraft body.

[0009] Preferably, the ground rescue vehicle platform is designed to be adapted to the mounting requirements of the corresponding vehicle-mounted rescue aircraft; the rescue vehicle is selected as a special ambulance or modified fire truck with off-road capabilities, and its interior is equipped with an automatic lifting platform; a dedicated lifting and landing cabin is installed on the automatic lifting platform, which integrates a fast charging interface and a positioning guidance device, and the width of the automatic lifting platform is... Length S The device is designed to accommodate the size requirements of the vehicle-mounted rescue aircraft. The positioning and guidance device consists of two wedge-shaped platforms fixed to the automatic lifting platform. The distance between the two platforms is greater than the width of the skid-type landing gear. When the fuselage of the rescue aircraft moves left and right on the automatic lifting platform, the gradient of the wedge-shaped platform is used to create horizontal resistance for the lateral movement of the rescue aircraft, thereby achieving the positioning effect. The fast charging interface is equipped with a dedicated charging box and charging cable, which is fixed to the surface of the automatic lifting platform to prevent the aircraft from shaking due to vehicle bumps.

[0010] Preferably, the rigging traction mechanism consists of a winch, a rigid rope, and a load-bearing shaft; both the winch and the load-bearing shaft are fixedly installed on the body of the rescue aircraft, and a movable pulley mechanism is installed on the top of the medical stretcher; one end of the rigid rope is fixed to the load-bearing shaft, and after the rigid rope passes downward around the movable pulley mechanism on the top of the medical stretcher, the other end is wound upward around the drum of the winch; the winch is the power core, the winch adopts a two-gear reduction structure and integrates an electromagnetic braking unit and a torque adjustment module, the rigid rope is woven from high-strength aramid fiber, and the surface of the rigid rope is coated with a wear-resistant coating;

[0011] The rigid locking mechanism consists of a telescopic mini electromagnetic lock, an L-shaped rigid limiting mechanical device, and an annular fixing component. The telescopic mini electromagnetic lock is hinged to the main frame of the machine body. One end of the L-shaped rigid limiting mechanical device is directly fixed to the telescopic lock core of the telescopic mini electromagnetic lock and extends and retracts with the telescopic lock core. The annular fixing component is fixed at the load docking part, and the outer ring has a reserved limiting slot for engaging with the L-shaped rigid limiting mechanical device.

[0012] Preferably, the medical stretcher adopts a double-layer design, including a lifting layer and a pull-out layer; the bottom of the lifting layer is hinged with a pulley rail, and the pull-out layer is placed on the pulley rail and can be pulled and moved back and forth; the rigging traction mechanism is hinged to the lifting layer to realize the overall lifting and lowering movement of the medical stretcher; the injured person is placed in the embedded pull-out layer, and the door mechanism of the medical stretcher adopts a three-section unfolding design, with the two sides unfolding to the sides and the middle unfolding upward, so as to make full use of space and meet the needs of rapid transfer of the injured person.

[0013] The preferred design of eight large-diameter lift ducted fans is based on the following criteria: meeting the requirements for safe hovering and heavy-load takeoff and landing under single-engine failure, and maximizing thrust. ≥800kgF; Each large-diameter lift ducted fan has a preset outward tilt angle towards the outer side of the fuselage of the rescue aircraft. , .

[0014] Preferably, the two small-diameter thrust ducted fans are designed using a heterogeneous power division of labor strategy: the large-diameter lift ducted fan is used to provide vertical lift and attitude control torque, while the small-diameter thrust ducted fan is used to provide thrust to overcome level flight aerodynamic drag; the total maximum thrust of the lift propulsion system is... Total maximum thrust of the horizontal propulsion system The relationship satisfies: Balancing heavy-load takeoff and landing capabilities with high-speed cruising energy efficiency.

[0015] Preferably, to meet the power and energy requirements of large-diameter lift ducted fans and small-diameter thrust ducted fans, the energy module uses a power lithium battery with a cell energy density of: And the proportion of battery mass W to the takeoff weight r of the rescue aircraft body satisfies: To maintain payload capacity while ensuring endurance; the vertical height of the energy module's center of gravity. Vertical height of the aerodynamic center of the rescue aircraft The relationship satisfies: < It utilizes the effect of gravity to form a passive stabilizing configuration, which is used to enhance hovering wind resistance.

[0016] Preferably, the main fuselage frame is constructed using aluminum alloy profiles combined with high-modulus carbon fiber tubing and metal connectors to form a space truss structure, with design rules adhering to high specific strength and lightweight; the length-to-width ratio R of the main fuselage frame satisfies R≥1.5, and the overall height H≤1.5m, length L≤5m, and width D≤2.4m of the rescue aircraft body.

[0017] Preferably, the ratio of takeoff weight to effective payload of the rescue aircraft is designed to be 15%≤η≤25%. The front of the rescue aircraft is equipped with an integrated photosensitive camera and an aerodynamic fairing to reduce forward aerodynamic drag and guide search and rescue.

[0018] Preferably, the attitude control of the rescue aircraft body adopts a combination of differential adjustment and vector thrust:

[0019] During vertical takeoff and landing and hovering, pitch and roll control are achieved by adjusting the speed difference of eight large-diameter lift ducted fans, and yaw stability is provided by the horizontal component force generated by the 5° outward tilt angle.

[0020] During the forward flight phase, the horizontal propulsion system is activated to provide thrust, while the lift propulsion system maintains a small angle of attack on the rescue aircraft to reduce drag. Turning is achieved through the differential thrust of the eight large-diameter lift ducted fans in the left and right rows.

[0021] Beneficial effects of this invention:

[0022] 1. The rescue aircraft body of the present invention adopts a double-row tandem heterogeneous ducted power layout, with large-diameter lift ducts arranged in two rows along the longitudinal direction of the fuselage, and an independent small-diameter horizontal propulsion duct configured. By using longitudinal space to exchange for lateral size, the lateral width of the whole machine is compressed to less than 2.4 meters, which can be arranged in a 2.5-meter-wide vehicle, significantly improving the passability and adaptability of the rescue aircraft body in narrow spaces such as forest areas and urban streets.

[0023] 2. The large-diameter lift ducted fan and the small-diameter thrust ducted fan in this invention adopt a thrust decoupling functional division design. The large-diameter lift ducted fan focuses on providing vertical lift, while the small-diameter thrust ducted fan focuses on providing level flight thrust. This greatly improves the aircraft's cruise efficiency and long-distance transport range. It also eliminates the unavoidable fuselage tilt during the level flight of traditional rotorcraft, ensuring the injured person's comfortable posture during flight and increasing the safety of the transport process.

[0024] 3. The large-diameter lift duct fan in this invention adopts an outward-inclination aerodynamic layout design, tilting the duct rotation axis towards the outside of the rescue aircraft body, and guiding the high-speed downwash airflow to both sides of the rescue aircraft body, effectively avoiding the direct impact and interference of the airflow on the medical stretcher in the middle of the rescue aircraft body, while creating a trapezoidal clearance inside the rescue aircraft body to accommodate the lifting and lowering of the medical stretcher.

[0025] 4. This invention constructs a load management system with rigid-flexible mode switching function. A rigid locking mechanism is added to the rigging traction mechanism. The mechanical locking after recovery eliminates the load degree of freedom, which solves the swaying problem that is easy to occur during flight in traditional flexible hoisting, and ensures the attitude stability and life safety of the injured during the transfer process.

[0026] 5. The main frame of the vehicle-mounted rescue aircraft is constructed using aluminum alloy profiles combined with high-modulus carbon fiber tubing and metal connectors to form a space truss structure. The design follows the principles of high specific strength and lightweight, achieving the goal of minimizing the weight of the fuselage structure and increasing the effective payload ratio while meeting the requirements of heavy-load rescue.

[0027] 6. In this invention, the front of the vehicle-mounted rescue aircraft is equipped with an integrated photosensitive camera and a medical box lifting mechanism. The integrated photosensitive camera is used to search for missing persons. When the location of the injured person is located, the medical box lifting mechanism can accurately deploy medical equipment, allowing medical personnel to carry no additional medical equipment during on-site rescue, thereby improving rescue efficiency and speed.

[0028] In summary, this invention uses vehicles as a platform for large-scale operation and en route rescue, and uses specially designed, heavy-duty, compact, and non-disassembly-removable ducted aircraft as a shuttle aircraft to achieve a function similar to a stretcher, solving the problem of vehicles being unable to pass through or arrive in time in harsh rescue environments such as densely forested mountain valleys, congested highways, and blocked streets in urban areas. Attached Figure Description

[0029] The accompanying drawings, which are provided to further illustrate the invention and constitute a part of this invention, are illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention.

[0030] Figure 1 This is a schematic diagram of the overall structure of the vehicle-mounted flight stretcher of the present invention;

[0031] Figure 2 This is an external view of the rescue aircraft body of the vehicle-mounted flying stretcher of the present invention;

[0032] Figure 3 This is a schematic diagram of the dimensions of the vehicle-mounted flight stretcher of the present invention.

[0033] Attached image captions:

[0034] 1-Rescue aircraft body, 2-Ground rescue vehicle platform, 3-Fuselage main frame, 4-Large diameter lift ducted fan, 5-Small diameter thrust ducted fan, 6-Energy module, 7-Payment management system, 8-Medical stretcher, 9-Skipter landing gear, 10-Dedicated lifting landing cabin, 11-Fast charging interface, 12-Positioning and guidance device. Detailed Implementation

[0035] This section will describe in detail specific embodiments of the present invention. Preferred embodiments of the present invention are shown in the accompanying drawings. The purpose of the drawings is to supplement the textual description with graphics, so that people can intuitively and vividly understand each technical feature and overall technical solution of the present invention, but they should not be construed as limiting the scope of protection of the present invention.

[0036] In the description of this invention, it should be understood that the orientation descriptions, such as up, down, front, back, left, right, etc., are based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and 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 limiting this invention.

[0037] In the description of this invention, "several" means one or more, "more than" means two or more, "greater than," "less than," and "exceeding" are understood to exclude the stated number, while "above," "below," and "within" are understood to include the stated number. The use of "first" and "second" in the description is merely for distinguishing technical features and should not be construed as indicating or implying relative importance, or implicitly indicating the number of indicated technical features, or implicitly indicating the order of the indicated technical features.

[0038] In the description of this invention, unless otherwise explicitly defined, terms such as "set up," "install," and "connect" should be interpreted broadly, and those skilled in the art can reasonably determine the specific meaning of the above terms in this invention in conjunction with the specific content of the technical solution.

[0039] Reference Figures 1-3 A preferred embodiment of the present invention provides a vehicle-mounted flying stretcher, comprising a rescue vehicle platform and a vehicle-mounted rescue flying vehicle. The vehicle-mounted rescue flying vehicle includes a rescue flying vehicle body 1 and a ground rescue vehicle platform 2. The ground rescue vehicle platform 2 is equipped with a dedicated lifting and landing cabin 10. The rescue flying vehicle body 1 is longitudinally elongated and has a lateral width D ≤ 2.4 meters, so that it can be completely installed into the vehicle without disassembly. Skid-type landing gear 9 is provided on both sides of the bottom of the rescue flying vehicle body 1 (preferably, the skid-type landing gear 9 is hinged to the bottom of the fuselage main frame 3). The skid-type landing gear 9 is used to park in the dedicated lifting and landing cabin 10 of the ground rescue vehicle platform 2.

[0040] The vehicle-mounted rescue aircraft body 1 adopts a double-row tandem heterogeneous ducted layout. The fuselage of the vehicle-mounted rescue aircraft body 1 includes a main fuselage frame 3, which serves as the main load-bearing structure. The main fuselage frame 3 is equipped with a power unit, which includes a lift propulsion system that provides lift and a horizontal propulsion system that provides thrust. The lift propulsion system includes eight large-diameter lift ducted fans 4, which are arranged symmetrically in two rows along the longitudinal axis of the main fuselage frame 3 and rigidly connected to both sides of the main fuselage frame 3 by high-strength cantilever beams. The horizontal propulsion system consists of two independent small-diameter thrust ducted fans 5, which are located at the rear of the fuselage of the vehicle-mounted rescue aircraft body 1. The thrust axis of the small-diameter thrust ducted fans 5 is parallel to the longitudinal axis of the main fuselage frame 3. A streamlined battery compartment is fixedly connected to the lower part of the main fuselage frame 3 through a mounting point. The streamlined battery compartment encapsulates an energy module 6.

[0041] The load management system 7 is integrated between the fuselage main frame 3 (the abdomen of which is the energy module 6) and the fuselage main frame 3. The load management system 7 includes a rigging traction mechanism, a guide rail, and a rigid locking mechanism. The guide rail is set on the rigging traction mechanism. The rigid locking mechanism is hinged to the rear and side of the lower part of the fuselage main frame 3 to firmly fasten the medical stretcher 8 below. The rigid locking mechanism forms an interconnection between the medical stretcher 8 and the fuselage main frame 3. The medical stretcher 8 is set directly below the load management system 7. The rigidly locked medical stretcher 8 and the energy module 6 above it together form the structural reinforcing ribs at the bottom of the rescue aircraft body 1 to improve the torsional stiffness of the rescue aircraft body 1. The whole aircraft follows the "bottom heavy, top light" center of gravity design rule, placing the energy module 6 and the medical stretcher 8 below the fuselage main frame 3, so that the center of gravity of the whole aircraft is significantly lower than the aerodynamic center.

[0042] Specifically, during use, the rescue vehicle platform 2 moves to the vicinity of the rescue site, the aircraft body 1 receives the command and takes off vertically from the vehicle platform, the lift propulsion system 4 provides lift, the horizontal propulsion system 5 provides forward thrust, and hovers after reaching the target point; the load management system 7 releases the rigging to lower the medical stretcher 8 to the ground, and lifts and recovers it after the injured person is secured; the rigid locking mechanism on the load management system 7 automatically closes after the medical stretcher 8 is in place, locking the medical stretcher 8 to the fuselage; then the aircraft body 1 returns to the vehicle platform, realizing the transfer of the injured person.

[0043] Furthermore, when performing a rescue mission, the rigging traction mechanism releases the medical stretcher 8 to the ground; during recovery, the medical stretcher 8 is lifted to the fuselage belly of the vehicle-mounted rescue aircraft body 1, and the rigid locking mechanism automatically closes, eliminating the rigging's degree of freedom and transforming the flexibly connected medical stretcher 8 into a rigid mass block fixed to the rescue aircraft body 1.

[0044] In this embodiment, the ground rescue vehicle platform 2 is adapted to the mounting requirements of the corresponding vehicle-mounted rescue aircraft body 1; the rescue vehicle is selected as a special ambulance or modified fire truck with off-road capability, and its interior is equipped with an automatic lifting platform; a dedicated lifting take-off and landing cabin 10 is installed on the automatic lifting platform, which integrates a fast charging interface and a positioning guidance device, and the width of the automatic lifting platform is... Length S This is to accommodate the size requirements of the vehicle-mounted rescue aircraft body 1.

[0045] Furthermore, the positioning and guidance device 12 consists of two wedge-shaped platforms fixed to the automatic lifting platform. The gap between the two platforms is greater than the width of the skid-type landing gear 9. When the fuselage of the rescue aircraft body 1 sways left and right on the automatic lifting platform, the gradient of the wedge-shaped platforms creates horizontal resistance for the lateral movement of the rescue aircraft body 1, thereby achieving the positioning effect. The fast charging interface 11 is equipped with a dedicated charging box and charging cable, and is fixed to the surface of the automatic lifting platform below to prevent the vehicle from shaking due to vehicle bumps.

[0046] In this embodiment, the design and selection of the eight large-diameter lift ducted fans 4 are based on the following criteria: meeting the requirements for safe hovering and heavy-load takeoff and landing under single-engine failure, and maximizing thrust. ≥800kgF; Each large-diameter lift duct fan 4 has a preset outward tilt angle towards the outer side of the fuselage of the rescue aircraft body 1. , .like Figure 3 As shown, the preferred angle is 5°. This design rule is used to ensure that the vertical lift loss is small, and to use the horizontal component force to guide the high-speed downwash airflow to both sides of the fuselage of the rescue aircraft body 1, so as to avoid the airflow directly impacting the energy module 6 in the middle of the fuselage of the rescue aircraft body 1 and the medical stretcher 8 below it, and to form a trapezoidal clearance that is narrow at the top and wide at the bottom between the two side ducts.

[0047] In this embodiment, the two small-diameter thrust ducted fans 5 are designed using a heterogeneous power division of labor strategy: the large-diameter lift ducted fan 4 is used to provide vertical lift and attitude control torque, while the small-diameter thrust ducted fan 5 is used to provide thrust to overcome level flight aerodynamic drag; the total maximum thrust of the lift propulsion system is... Total maximum thrust of the horizontal propulsion system The relationship satisfies: Balancing heavy-load takeoff and landing capabilities with high-speed cruising energy efficiency.

[0048] In this embodiment, to meet the power and energy requirements of the large-diameter lift ducted fan 4 and the small-diameter thrust ducted fan 5, the energy module 6 uses a power lithium battery with a cell energy density of: And the proportion of battery mass W to the takeoff weight r of the rescue aircraft body 1 satisfies: To ensure both endurance and payload capacity; the energy module 6 adopts a passive stabilization layout, and is the single component with the largest mass of the entire aircraft (accounting for approximately 40% of the takeoff weight); the vertical height of the center of gravity of the energy module 6... Vertical height of the aerodynamic center of the rescue aircraft body 1 The relationship satisfies: < It utilizes the effect of gravity to form a passive stabilizing configuration, which is used to enhance hovering wind resistance.

[0049] In this embodiment, the main body frame 3 is constructed using aluminum alloy profiles combined with high-modulus carbon fiber tubes and metal connectors to form a space truss structure. The design rules follow high specific strength and lightweight. The length-to-width ratio R of the main body frame 3 satisfies R≥1.5, and the overall height H≤1.5m, length L≤5m, and width D≤2.4m of the rescue aircraft body (1) are also as follows: With the double-row tandem layout of the power unit, the rescue aircraft body 1 can maintain a large load capacity while having a significantly smaller projected area than traditional multi-rotor aircraft of the same level, enabling it to operate in narrow gaps.

[0050] In this embodiment, the ratio of takeoff weight to effective payload of the rescue aircraft body 1 is designed to be 15%≤η≤25%. The front of the rescue aircraft body 1 is equipped with an integrated photosensitive camera and an aerodynamic shaping fairing to reduce forward aerodynamic drag and guide search and rescue.

[0051] In this embodiment, the medical stretcher 8 adopts a double-layer design, including a lifting layer and a pull-out layer; the bottom of the lifting layer is hinged with a pulley rail, and the pull-out layer is placed on the pulley rail and can be pulled and moved back and forth; the rigging traction mechanism is hinged to the lifting layer to realize the overall lifting and lowering movement of the medical stretcher 8; the injured person is placed in the embedded pull-out layer, and medical personnel can control the pull-out layer to transfer the injured person during rescue; the door mechanism of the medical stretcher 8 adopts a three-section unfolding design, with the two sides unfolding to the sides and the middle unfolding upward, in order to make full use of space and meet the needs of rapid transfer of the injured person.

[0052] In this embodiment, the attitude control of the rescue aircraft body 1 adopts a method combining differential adjustment and vector thrust:

[0053] During vertical takeoff and landing and hovering, pitch and roll control are achieved by adjusting the speed difference of the eight large-diameter lift ducted fans 4, and yaw stability is provided by the horizontal component force generated by the 5° outward tilt angle.

[0054] During the forward flight phase, the horizontal propulsion system is activated to provide thrust, while the lift propulsion system maintains a small angle of attack on the rescue aircraft body 1 to reduce drag; steering is achieved through the differential thrust of the eight large-diameter lift ducted fans 4 in the left and right rows.

[0055] The working principle of this invention is as follows: When performing an emergency rescue mission, the ground rescue vehicle platform 2 moves to the vicinity of the rescue site. The dedicated take-off and landing cabin 10 of the aircraft is raised on the automatic lifting platform by four hydraulic rods. The rescue aircraft body 1 receives the command and starts the large-diameter lift ducted fan 4 in the lift propulsion system, taking off vertically from the vehicle platform. It uses the small-diameter thrust ducted fan 5 of the horizontal propulsion system to provide forward thrust and quickly flies to the target point and hovers. After reaching the target position, the rigging traction mechanism in the load management system 7 is released, lowering the medical stretcher 8 to the ground. After the injured person is secured, the winch retracts, raising the medical stretcher 8 to the belly of the rescue aircraft body 1. At this time, the rigid locking mechanism in the load management system 7 is activated: the guide rail first restricts the lateral swing of the medical stretcher 8, and then the rigid locking mechanism closes synchronously to rigidly lock the medical stretcher 8 to the main frame 3 of the fuselage; after the mission is completed, the rescue aircraft body 1 flies back to the ground rescue vehicle platform 2 and slowly lands in the dedicated take-off and landing cabin 10 of the aircraft. The hydraulic rod retracts and stores the rescue aircraft body 1 into the vehicle body.

[0056] Without causing conflict, those skilled in the art can freely combine and use the above-mentioned additional technical features.

[0057] The above description is only a preferred embodiment of the present invention. Any technical solution that achieves the purpose of the present invention by essentially the same means is within the protection scope of the present invention.

Claims

1. A vehicle-mounted flying stretcher, comprising a rescue vehicle platform and a vehicle-mounted rescue flying vehicle, characterized in that: The vehicle-mounted rescue aircraft includes a rescue aircraft body (1) and a ground rescue vehicle platform (2). The ground rescue vehicle platform (2) is equipped with a dedicated lift-type take-off and landing cabin (10). The rescue aircraft body (1) is longitudinally elongated and has a lateral width D≤2.4 meters. The bottom of the rescue aircraft body (1) is equipped with a skid-type landing gear (9), which is used to park in the dedicated lift-type take-off and landing cabin (10) of the ground rescue vehicle platform (2). The vehicle-mounted rescue aircraft body (1) adopts a double-row tandem heterogeneous ducted layout. The fuselage of the vehicle-mounted rescue aircraft body (1) includes the main fuselage frame (3). The main fuselage frame (3) is equipped with a power unit, which includes a lift propulsion system that provides lift and a horizontal propulsion system that provides thrust. The lift propulsion system includes eight large-diameter lift ducted fans (4). The eight large-diameter lift ducted fans (4) are arranged in two rows, left and right, symmetrically in series along the longitudinal axis of the main fuselage frame (3) and rigidly connected to both sides of the main fuselage frame (3) by a high-strength cantilever beam. The horizontal propulsion system consists of two independent small-diameter thrust ducted fans (5), which are arranged at the tail of the fuselage of the vehicle-mounted rescue aircraft body (1). The thrust axis of the small-diameter thrust ducted fans (5) is parallel to the longitudinal axis of the main fuselage frame (3). A streamlined battery compartment is fixedly connected to the bottom of the main fuselage frame (3) through a mounting point. An energy module (6) is encapsulated in the streamlined battery compartment. The main body frame (3) of the fuselage is connected to the power module (6) and the main body frame (3) of the fuselage. The load management system (7) includes a rigging traction mechanism, a guide rail and a rigid locking mechanism. The guide rail is set on the rigging traction mechanism. The rigid locking mechanism is hinged to the rear and side of the lower part of the main body frame (3) to firmly fasten the medical stretcher (8) below. The rigid locking mechanism forms the connection between the medical stretcher (8) and the main body frame (3). The medical stretcher (8) is set directly below the load management system (7). The rigidly locked medical stretcher (8) and the power module (6) above it together form the structural reinforcing rib at the bottom of the rescue aircraft body (1) to improve the torsional stiffness of the rescue aircraft body (1).

2. The vehicle-mounted flight stretcher according to claim 1, characterized in that: The ground rescue vehicle platform (2) is designed to be compatible with the mounting requirements of the corresponding vehicle-mounted rescue aircraft (1); the rescue vehicle is selected as a special ambulance or modified fire truck with off-road capability, and its cabin is equipped with an automatic lifting platform; a dedicated lifting take-off and landing cabin (10) is set on the automatic lifting platform, and the automatic lifting platform integrates a fast charging interface (11) and a positioning guidance device (12), and the width of the automatic lifting platform is... Length S The positioning and guiding device (12) is composed of two wedge-shaped platforms fixed on the automatic lifting platform. The gap between the two is greater than the width of the skid landing gear (9). When the fuselage of the rescue aircraft (1) is swaying left and right on the automatic lifting platform, the gradient of the wedge-shaped platform is used to form a horizontal resistance for the lateral movement of the rescue aircraft (1) to achieve the positioning effect. The fast charging interface (11) is equipped with a dedicated charging box and charging line, which is fixed to the surface of the automatic lifting platform to prevent the vehicle from shaking.

3. The vehicle-mounted flight stretcher according to claim 1, characterized in that: The rigging traction mechanism consists of a winch, a rigid rope, and a load-bearing shaft. The winch and the load-bearing shaft are both fixedly installed on the body of the rescue aircraft (1). A movable pulley mechanism is installed on the top of the medical stretcher (8). One end of the rigid rope is fixed on the load-bearing shaft. After the rigid rope passes down around the movable pulley mechanism on the top of the medical stretcher (8), the other end is wound upwards on the drum of the winch. The winch is the power core. The winch adopts a two-gear reduction structure and integrates an electromagnetic braking unit and a torque adjustment module. The rigid rope is woven from high-strength aramid fiber and the surface of the rigid rope is coated with a wear-resistant coating. The rigid locking mechanism consists of a telescopic small electromagnetic lock, an L-shaped rigid limiting mechanical device and an annular fixing part. The telescopic small electromagnetic lock is hinged to the main frame (3) of the machine body. One end of the L-shaped rigid limiting mechanical device is directly fixed to the telescopic lock core of the telescopic small electromagnetic lock. As the telescopic lock core extends and retracts, the annular fixing part is fixed at the load docking part. The outer ring has a reserved limiting slot for engaging with the L-shaped rigid limiting mechanical device.

4. The vehicle-mounted flight stretcher according to claim 1, characterized in that: The medical stretcher (8) adopts a double-layer design, including a lifting layer and a pull-out layer; the bottom of the lifting layer is hinged with a pulley rail, and the pull-out layer is placed on the pulley rail and can be pulled and moved in the front and back directions; the rigging traction mechanism is hinged to the lifting layer to realize the overall lifting and lowering movement of the medical stretcher (8); the injured person is placed in the embedded pull-out layer. The door mechanism of the medical stretcher (8) adopts a three-section unfolding design, with the two sides unfolding to the sides and the middle unfolding upward, so as to make full use of space and meet the needs of rapid transfer of the injured person.

5. A vehicle-mounted flight stretcher according to claim 1, characterized in that: The design selection of 8 large-diameter lift ducted fans (4) is based on the following criteria: meeting the requirements for safe hovering and heavy-load take-off and landing under single-engine failure, and maximum thrust. ≥800kgF; Each large-diameter lift duct fan (4) has a preset outboard angle tilted towards the outer side of the fuselage of the rescue vehicle body (1). , .

6. A vehicle-mounted flight stretcher according to claim 5, characterized in that: The design rules of the two small-diameter thrust ducted fans (5) adopt a heterogeneous power division strategy: the large-diameter lift ducted fan (4) is used to provide vertical lift and attitude control torque, and the small-diameter thrust ducted fan (5) is used to provide thrust to overcome level flight aerodynamic drag; the total maximum thrust of the lift propulsion system Total maximum thrust of the horizontal propulsion system The relationship satisfies: Balancing heavy-load takeoff and landing capabilities with high-speed cruising energy efficiency.

7. A vehicle-mounted flight stretcher according to claim 6, characterized in that: To meet the power and energy requirements of the large-diameter lift ducted fan (4) and the small-diameter thrust ducted fan (5), the energy module (6) uses a power lithium battery with a cell energy density of: And the proportion of battery mass W to the takeoff weight r of the rescue aircraft body (1) satisfies: To maintain payload capacity while ensuring endurance; the vertical height of the center of mass of the energy module (6) Vertical height relative to the aerodynamic center of the rescue aircraft body (1) The relationship satisfies: < It utilizes the effect of gravity to form a passive stabilizing configuration, which is used to enhance hovering wind resistance.

8. The vehicle-mounted flight stretcher according to claim 1, characterized in that: The main frame of the fuselage (3) is made of aluminum alloy profiles combined with high modulus carbon fiber tubes and metal connectors to form a space truss structure. The design rules follow high specific strength and lightweight. The length-to-width ratio R of the main frame of the fuselage (3) satisfies R≥1.5, and the overall height H≤1.5m, length L≤5m, and width D≤2.4m of the rescue aircraft body (1) are also satisfied.

9. A vehicle-mounted flight stretcher according to claim 8, characterized in that: The ratio of takeoff weight to effective payload of the rescue aircraft body (1) is designed to be 15%≤η≤25%. The front of the rescue aircraft body (1) is equipped with an integrated photosensitive camera probe and an aerodynamic shaping fairing to reduce forward aerodynamic drag and guide search and rescue.

10. A vehicle-mounted flight stretcher according to claim 1, characterized in that: The attitude control of the rescue aircraft body (1) adopts a combination of differential adjustment and vector thrust: During vertical takeoff and landing and hovering, pitch and roll control are achieved by adjusting the speed difference of eight large-diameter lift ducted fans (4), and yaw stability is provided by the horizontal component force generated by the 5° outward tilt angle. During the forward flight phase, the horizontal propulsion system is activated to provide thrust, while the lift propulsion system maintains a small angle of attack on the rescue aircraft body (1) to reduce drag; the steering is achieved by the thrust differential of the eight large-diameter lift ducted fans (4) in the left and right rows.

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