Fuselage structure of hybrid power aircraft

Abstract

The invention discloses a hybrid aircraft fuselage structure, and belongs to the field of aircraft fuselages. A fuselage structure of a hybrid aircraft comprises a fuselage shell and a baffle fixedly connected in the fuselage shell, and further comprises a flexible shaft fixing seat fixedly connected to the baffle, a driven wheel is rotationally installed in the flexible shaft fixing seat, the driven wheel is in transmission connection with a shaft body rotationally installed in the flexible shaft fixing seat, and the flexible shaft fixing seat is fixedly connected with the baffle. The firewall fixing rib is fixedly connected into the machine body shell, a spray head is fixedly connected to the firewall fixing rib, an air supply part for controlling the spray head to spray air and a permeable plate fixedly connected to the firewall fixing rib are arranged on the driven wheel, and a brush plate is installed on the permeable plate in a sliding mode; gas is conveyed to the spray head through the inflator, effective heat dissipation of the engine and the motor is achieved, the heat dissipation effect of the engine is enhanced, and therefore the performance and safety of an aircraft in the high-temperature environment are improved.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft fuselages, and in particular to a hybrid power aircraft fuselage structure. Background Art

[0002] In the prior art, the design of an aircraft fuselage structure usually needs to consider multiple factors, including but not limited to strength, weight, aerodynamic characteristics, and ease of maintenance. The layout of the hybrid power system is the core of the fuselage structure design of a hybrid aircraft. The system usually consists of a fuel engine, an electric drive system, a battery pack, and a related control system. As an aircraft that combines a traditional fuel engine and an electric drive system, its fuselage structure design needs to take into account the advantages of fuel efficiency and electric drive, while ensuring the safety and reliability of the structure.

[0003] The fuselage of current hybrid aircraft only dissipates heat from the engine and motor through air inlet ribs during flight, but there is a problem of insufficient heat dissipation efficiency, especially in high temperature environments, which may affect the performance and safety of the aircraft. In addition, when there is a lot of dust or pollutants and the air filter plate at the engine is blocked, the heat dissipation effect of the engine and motor is further affected, making it easy to fail. Summary of the invention

[0004] The purpose of the present invention is to solve the problem in the prior art that when there is a lot of dust or pollutants, the air permeable filter plate at the engine is blocked, which further affects the heat dissipation effect of the engine and the motor and is prone to malfunction, and a hybrid aircraft fuselage structure is proposed.

[0005] In order to achieve the above object, the present invention adopts the following technical solutions: A hybrid aircraft fuselage structure comprises a fuselage shell and a baffle fixedly connected to the fuselage shell, and further comprises: a flexible shaft fixing seat fixedly connected to the baffle, wherein a driven wheel is rotatably installed in the flexible shaft fixing seat, and the driven wheel is drivingly connected to a shaft body rotatably installed in the flexible shaft fixing seat; a firewall fixing rib fixedly connected to the fuselage shell, wherein a nozzle is fixedly connected to the firewall fixing rib, and an air supply part for controlling the nozzle to spray air is arranged on the driven wheel; a breathable plate fixedly connected to the firewall fixing rib, wherein a brush plate is slidably installed on the breathable plate, and a driving part for driving the brush plate to slide is arranged in the flexible shaft fixing seat.

[0006] Preferably, the firewall fixing ribs are fixedly connected to the engine fixing ribs, the engine fixing ribs are fixedly connected to the reinforcing corner ribs, the firewall fixing ribs are fixedly connected to the lower air inlet ribs, the engine fixing ribs are provided with the engine, and the nozzles are provided on both sides of the engine.

[0007] For the heat dissipation of the motor, preferably, the air supply part includes a runner rotatably installed in the flexible shaft fixing seat. The runner is in transmission connection with a driven wheel. A rocker arm is rotatably installed on the runner, and a piston rod is rotatably connected to the rocker arm. An air cylinder is fixedly connected to the flexible shaft fixing seat. The piston rod is slidably installed in the air cylinder, and the output end of the air cylinder is fixedly connected to a nozzle.

[0008] To drive the air cylinder to discharge air, further, a transmission shaft is fixedly connected to the runner. The transmission shaft is rotatably installed in the flexible shaft fixing seat. A rotating shaft is rotatably installed in the flexible shaft fixing seat. Belt pulleys are fixedly connected to both the rotating shaft and the transmission shaft. The two belt pulleys are in transmission connection through a transmission belt. The runner is fixedly connected to the rotating shaft.

[0009] To make the piston rod reciprocate, furthermore, a rocker is fixedly connected to the runner. The rocker arm is rotatably installed on the rocker. A pull rod is fixedly connected to the rocker arm. The piston rod is rotatably installed on the pull rod. A slide rail is fixedly connected to the flexible shaft fixing seat. The piston rod is slidably installed in the slide rail.

[0010] To convey the gas to the nozzle, furthermore, the output end of the air cylinder is fixedly connected to an air pipe. The output end of the air pipe is fixedly connected to the nozzle. Mounting seats are fixedly connected to both sides of the nozzle. The mounting seats are fixedly connected to the firewall fixing ribs.

[0011] To drive the brush plate to slide and clean, furthermore, the driving part includes a connecting plate fixedly connected to the piston rod. A lifting plate is fixedly connected to the connecting plate. A sliding plate is slidably installed in the lifting plate. The sliding plate is fixedly connected to the brush plate.

[0012] To make the brush plate swing and scrub, furthermore, resisting rods are fixedly connected to both sides of the brush plate. Spheres are fixedly connected to the resisting rods. A number of convex blocks are fixedly connected to both sides of the air permeable plate. The spheres are matched with the convex blocks.

[0013] To increase the swing frequency, furthermore, a chute is formed in the lifting plate. A limiting plate is fixedly connected to the sliding plate. The limiting plate is slidably installed in the chute. A supporting spring is fixedly connected to the limiting plate. The free end of the supporting spring is fixedly connected to the chute.

[0014] For the sake of greater stability of the fuselage, further, an undercarriage fixing rib assembly is fixedly connected inside the fuselage shell. A central control rib is fixedly connected to the undercarriage fixing rib assembly. The baffle is fixedly connected to the central control rib. A bottom plate is fixedly connected to the central control rib. Among them, a frame is fixedly connected to the bottom plate. An instrument frame is fixedly connected to the frame. A landing light fixing plate is fixedly connected to the instrument frame. A longitudinal rib is fixedly connected to the bottom plate. A transverse rib is fixedly connected to the longitudinal rib. A hand operation fixing rib is fixedly connected to the transverse rib. A front landing gear fixing rib is fixedly connected to the hand operation fixing rib.

[0015] Compared with the prior art, the present invention provides a hybrid aircraft fuselage structure, which has the following beneficial effects: 1. In this hybrid aircraft fuselage structure, the driven wheel drives the rotating wheel to rotate, so that the rocker arm on the rotating wheel can drive the piston rod to reciprocate. Then, the gas is transported to the nozzle through the air cylinder, realizing effective heat dissipation for the engine and the motor. The gas ejected from the nozzle cooperates with the airflow generated by the lower air inlet rib during the flight of the aircraft, strengthening the heat dissipation effect of the engine, thereby improving the performance and safety of the aircraft in a high-temperature environment.

[0016] 2. In this hybrid aircraft fuselage structure, through the cooperation between the lifting plate and the brush plate, the cleaning of the breathable filter plate is realized, avoiding the problem of poor heat dissipation caused by blockage. Driven by the lifting plate, the brush plate can effectively brush the breathable plate, ensuring the cleanliness of the breathable plate, and thus maintaining the heat dissipation efficiency of the engine and the motor.

[0017] 3. In this hybrid aircraft fuselage structure, through the cooperation between the convex block and the sphere, the swinging brushing of the brush plate is realized. The convex blocks on both sides of the breathable plate can push the sphere, thereby driving the brush plate to swing, so as to achieve the purpose of cleaning the breathable plate. This not only improves the cleaning efficiency of the breathable plate, but also due to the cooperation between the convex block and the sphere, the swinging of the brush plate is more flexible, capable of adapting to the cleaning requirements at different angles and positions. In addition, through this structural design, the brush plate can cover a wider area during the swinging process, ensuring the cleanliness of the entire breathable plate, thereby effectively extending the service life of the engine and the motor and improving the overall performance and reliability of the hybrid aircraft.

[0018] Parts not involved in this device are the same as those in the prior art or can be implemented using the prior art. The present invention transports gas to the nozzle through the air cylinder to realize effective heat dissipation for the engine and the motor. The gas ejected from the nozzle cooperates with the airflow generated by the lower air inlet rib during the flight of the aircraft to strengthen the heat dissipation effect of the engine. Brief Description of the Drawings

[0019] Figure 1 It is a schematic diagram of the overall structure of a hybrid aircraft fuselage structure proposed by the present invention.

[0020] Figure 2 Schematic diagram of the internal structure of the fuselage shell of a hybrid aircraft fuselage structure proposed by the present invention.

[0021] Figure 3 Schematic diagram of the bottom plate structure of a hybrid aircraft fuselage structure proposed by the present invention.

[0022] Figure 4 Schematic diagram of the baffle structure of a hybrid aircraft fuselage structure proposed by the present invention.

[0023] Figure 5 Schematic diagram of the nozzle structure of a hybrid aircraft fuselage structure proposed by the present invention.

[0024] Figure 6 Schematic diagram of the internal structure of the flexible shaft fixing seat of a hybrid aircraft fuselage structure proposed by the present invention.

[0025] Figure 7 For a hybrid aircraft fuselage structure proposed by the present invention Figure 6 Enlarged view at position A.

[0026] Figure 8 Schematic diagram of the baffle structure of a hybrid aircraft fuselage structure proposed by the present invention.

[0027] Figure 9 For a hybrid aircraft fuselage structure proposed by the present invention Figure 8 Enlarged view at position B.

[0028] Wherein: 1 - Fuselage shell; 11 - Bottom plate; 12 - Central control rib; 13 - Instrument frame; 14 - Frame; 15 - Landing light fixing plate; 16 - Baffle; 17 - Flexible shaft fixing seat; 18 - Firewall fixing rib; 19 - Engine fixing rib; 110 - Reinforcing angle rib; 111 - Overall landing gear fixing rib; 112 - Lower air inlet rib; 113 - Longitudinal rib; 114 - Transverse rib; 115 - Manual operation fixing rib; 116 - Front landing gear fixing rib; 117 - Ventilation plate; 118 - Protrusion; 2 - Driven wheel; 21 - Lifting plate; 22 - Slide groove; 23 - Support spring; 24 - Air pipe; 25 - Transmission shaft; 26 - Pulley; 27 - Transmission belt; 28 - Rotating shaft; 29 - Runner; 210 - Rocker; 211 - Rocking arm; 212 - Pull rod; 213 - Piston rod; 214 - Slide rail; 215 - Connecting plate; 216 - Air cylinder; 217 - Slide plate; 218 - Limiting plate; 219 - Brush plate; 220 - Resistance rod; 221 - Sphere; 3 - Nozzle; 31 - Mounting seat. Detailed implementation manners

[0029] The technical solutions in the embodiments of the present invention will be described clearly and completely below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments.

[0030] In the description of the present invention, it is necessary to understand that the terms "upper", "lower", "front", "back", "left", "right", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship are based on the orientation or position relationship shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention. Example

[0031] Reference Figures 1-9 A hybrid aircraft fuselage structure includes a fuselage shell 1 and a baffle 16 fixedly connected to the fuselage shell 1, the baffle 16 is used to separate different functional areas and provide structural support, and also includes: a flexible shaft fixing seat 17 fixedly connected to the baffle 16, wherein a driven wheel 2 is rotatably installed in the flexible shaft fixing seat 17, the driven wheel 2 is drivingly connected to a shaft body rotatably installed in the flexible shaft fixing seat 17, and the rotation of the driven wheel 2 can be driven by the movement of the shaft body, and a fire wall fixing rib 18 fixedly connected to the fuselage shell 1 is used to strengthen the structure and serve as a part of the fire wall to prevent the spread of fire, wherein the fire prevention A nozzle 3 is fixedly connected to the wall fixed rib 18 for spraying gas to achieve a cooling function. An air supply portion for controlling the nozzle 3 to spray gas is provided on the driven wheel 2. The nozzle 3 can continuously spray gas to dissipate heat for the engine through the rotation of the driven wheel 2. A breathable plate 117 fixedly connected to the firewall fixed rib 18 improves the heat dissipation effect of the engine, wherein a brush plate 219 is slidably installed on the breathable plate 117 for cleaning dirt or impurities on the breathable plate 117 to maintain the breathability. A driving portion for driving the brush plate 219 to slide is provided in the flexible shaft fixing seat 17, so that the brush plate 219 can slide and brush on the breathable plate 117.

[0032] Reference Figures 1-7The firewall fixing rib 18 is fixedly connected with an engine fixing rib 19 for fixing and supporting the engine. The engine fixing rib 19 is fixedly connected with a reinforcing angle rib 110 for enhancing the strength and stability of the engine fixing rib 19 to prevent structural damage caused by engine vibration or load changes. The firewall fixing rib 18 is fixedly connected with a lower air inlet rib 112 for guiding air into the engine and cooling system of the aircraft. The engine fixing rib 19 is provided with an engine. The nozzles 3 are provided on both sides of the engine for spraying cooling gas to provide heat dissipation effect for the engine. The air supply unit includes a rotating mounting The rotating wheel 29 in the flexible shaft fixing seat 17 is connected to the driven wheel 2 in a transmission manner. The rotation of the driven wheel 2 can drive the rotating wheel 29 to rotate. A rocker arm 211 is rotatably installed on the rotating wheel 29. A piston rod 213 is rotatably connected to the rocker arm 211 for converting the rotating motion of the rotating wheel 29 into the reciprocating motion of the piston rod 213. A gas cylinder 216 is fixedly connected to the flexible shaft fixing seat 17. The piston rod 213 is slidably installed in the gas cylinder 216. The output end of the gas cylinder 216 is fixedly connected to the nozzle 3. When the piston rod 213 slides in the gas cylinder 216, it compresses or releases the gas in the gas cylinder 216 and The gas is delivered to the nozzle 3 for spraying through the air pipe 24. The rotating wheel 29 is fixedly connected with a transmission shaft 25. The transmission shaft 25 is rotatably installed in the flexible shaft fixing seat 17. The rotating shaft 28 is rotatably installed in the flexible shaft fixing seat 17. The rotating shaft 28 and the transmission shaft 25 are both fixedly connected with pulleys 26. The two pulleys 26 are connected by a transmission belt 27. The rotational power of the driven wheel 2 is transmitted to the rotating wheel 29 through the pulley 26 and the transmission belt 27. The rotating wheel 29 is fixedly connected to the rotating shaft 28. The rotating wheel 29 is fixedly connected to a rocker 210. The rocker arm 211 is rotatably installed on the rocker arm 210. The rocker arm 2 A pull rod 212 is fixedly connected to 11, and a piston rod 213 is rotatably installed on the pull rod 212. A slide rail 214 is fixedly connected to the flexible shaft fixing seat 17, and the piston rod 213 is slidably installed in the slide rail 214, ensuring the stability and accuracy of the piston rod 213 during the reciprocating motion. The output end of the gas cylinder 216 is fixedly connected to the air pipe 24, and the output end of the air pipe 24 is fixedly connected to the nozzle 3. Both sides of the nozzle 3 are fixedly connected with mounting seats 31, and the mounting seats 31 are fixedly connected to the firewall fixing ribs 18, so that the nozzle 3 is firmly installed on the fuselage of the aircraft and ensures that it can stably spray gas.

[0033] Reference Figures 5-9, the driving part includes a connecting plate 215 fixedly connected to the piston rod 213. The reciprocating movement of the piston rod 213 will drive the connecting plate 215 to move together. A lifting plate 21 is fixedly connected to the connecting plate 215. When the piston rod 213 moves, the lifting plate 21 will also move up and down. A sliding plate 217 is slidably installed in the lifting plate 21, allowing the sliding plate 217 to move horizontally inside the lifting plate 21. The sliding plate 217 is fixedly connected to the brush plate 219. The movement of the sliding plate 217 will drive the brush plate 219 to slide on the air-permeable plate 117 together. Two support rods 220 are fixedly connected to both sides of the brush plate 219, and a sphere 221 is fixedly connected to the support rods 220. A number of protrusions 118 are fixedly connected to both sides of the air-permeable plate 117. At least four protrusions 118 are provided on one side, preferably 4. The sphere 221 cooperates with the protrusions 118. When the brush plate 219 slides on the air-permeable plate 117, the sphere 221 moves according to the radian of the protrusions 118 under the influence of the protrusions 118 during movement, thereby driving the brush plate 219 to slide left and right. A chute 22 is formed on the lifting plate 21. A limiting plate 218 is fixedly connected to the sliding plate 217. The limiting plate 218 is slidably installed in the chute 22 to ensure the stable horizontal movement of the sliding plate 217 inside the lifting plate 21. A support spring 23 is fixedly connected to the limiting plate 218. The free end of the support spring 23 is fixedly connected to the chute 22, which is used to provide a certain restoring force for the sliding plate 217. When the sliding plate 217 moves left and right through the cooperation of the sphere 221 and the protrusions 118, the support spring 23 provides a restoring force for it through elasticity, increasing the movement frequency and improving the cleaning effect.

[0034] Refer to Figures 1-4The fuselage shell 1 is fixedly connected with a landing gear fixed rib as a whole 111, and its main function is to bear the weight and impact force of the aircraft during take-off and landing. The landing gear fixed rib as a whole 111 is fixedly connected with a central control rib 12, which may play a role in strengthening the fuselage structure, supporting other components, and serving as a reference for the direction of wiring or pipelines inside the aircraft. The baffle 16 is fixedly connected to the central control rib 12, and is used to separate different areas inside the fuselage and separate the cockpit from the engine compartment. The central control rib 12 is fixedly connected with a bottom plate 11, wherein a frame 14 is fixedly connected to the bottom plate 11, and an instrument frame 13 is fixedly connected to the frame 14, and is used to install various instruments and displays of the aircraft, such as a speedometer, an altimeter, The instrument frame 13 is fixedly connected with a landing light fixing plate 15 for installing a landing light to ensure that the aircraft can land safely at night or in low visibility conditions. The bottom plate 11 is fixedly connected with a longitudinal rib 113 to strengthen the longitudinal structure of the fuselage and improve the strength and rigidity of the fuselage. The longitudinal ribs 113 are fixedly connected with transverse ribs 114 to form a skeleton structure inside the fuselage together with the longitudinal ribs 113 to further strengthen the overall strength of the fuselage. The transverse ribs 114 are fixedly connected with a hand-operated fixing rib 115, and the hand-operated fixing rib 115 is fixedly connected with a front start fixing rib 116 to fix the front landing gear or related components to ensure that the front landing gear can stably support the front weight of the aircraft.

[0035] In the present invention, power is firstly generated by the operation of the engine, and cooling gas is sprayed by the nozzle 3 to dissipate the heat of the engine. When the engine is working, the rotating wheel 29 transmits the rotational power of the driven wheel 2 to the rotating wheel 29 through the transmission belt 27 and the pulley 26, and the rotating wheel 29 rotates accordingly. The rotational motion of the rotating wheel 29 is converted into reciprocating motion through the rocker arm 211 and the piston rod 213. The piston rod 213 slides in the air cylinder 216 to compress or release the gas, which is transported to the nozzle 3 through the air pipe 24 for spraying. The spraying action of the nozzle 3 can effectively provide cooling for the engine, ensuring that the engine can maintain good performance and stability even in a high-temperature working environment. At the same time, the coordinated movement of the lifting plate 21 and the brush plate 219, through the interaction between the sphere 221 and the protrusion 118, realizes the cleaning of the lifting and swinging of the air permeable plate 117, ensures smooth air circulation, and further improves the heat dissipation efficiency of the engine. The structural components such as the landing gear fixed rib 111, the center control rib 12, the baffle 16, the bottom plate 11, the frame 14, the instrument frame 13, the landing light fixing plate 15, the longitudinal rib 113, the transverse rib 114 and the hand-operated fixed rib 115 work together to not only strengthen the structural strength of the fuselage, but also provide guarantee for the stability and safety of the aircraft.

[0036] The above are only the preferred specific embodiments of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art within the technical scope disclosed by the present invention, according to the technical solution and inventive concept of the present invention, making equivalent substitutions or changes, shall be covered by the protection scope of the present invention.

Claims

1. A hybrid aircraft fuselage structure, comprising a fuselage shell (1) and a baffle (16) fixedly connected to the fuselage shell (1), characterized in that: Also includes: a flexible shaft fixing seat (17) fixedly connected to the baffle (16), Wherein, a driven wheel (2) is rotatably mounted in the flexible shaft fixing seat (17), and the driven wheel (2) is drivingly connected to a shaft body rotatably mounted in the flexible shaft fixing seat (17); a fire wall fixing rib (18) fixedly connected to the fuselage shell (1), The fire wall fixed rib (18) is fixedly connected to a nozzle (3), and the driven wheel (2) is provided with an air supply portion for controlling the nozzle (3) to spray air; a breathable plate (117) fixedly connected to the fire wall fixing rib (18), A brush plate (219) is slidably mounted on the air permeable plate (117), and a driving unit for driving the brush plate (219) to slide is provided in the flexible shaft fixing seat (17).

2. A hybrid aircraft fuselage structure according to claim 1, characterized in that: The fire wall fixing rib (18) is fixedly connected to an engine fixing rib (19), the engine fixing rib (19) is fixedly connected to a reinforcing corner rib (110), the fire wall fixing rib (18) is fixedly connected to a lower air inlet rib (112), an engine is arranged on the engine fixing rib (19), and the nozzles (3) are arranged on both sides of the engine.

3. A hybrid aircraft fuselage structure according to claim 2, characterized in that: The air supply unit comprises a rotating wheel (29) rotatably mounted in a flexible shaft fixing seat (17), the rotating wheel (29) being transmission-connected to a driven wheel (2), a rocker arm (211) being rotatably mounted on the rotating wheel (29), a piston rod (213) being rotatably connected to the rocker arm (211), an air cylinder (216) being fixedly connected to the flexible shaft fixing seat (17), the piston rod (213) being slidably mounted in the air cylinder (216), and an output end of the air cylinder (216) being fixedly connected to the nozzle (3).

4. A hybrid aircraft fuselage structure according to claim 3, characterized in that: The rotating wheel (29) is fixedly connected to a transmission shaft (25), the transmission shaft (25) is rotatably mounted in a flexible shaft fixing seat (17), a rotating shaft (28) is rotatably mounted in the flexible shaft fixing seat (17), a belt pulley (26) is fixedly connected to the rotating shaft (28) and the transmission shaft (25), the two belt pulleys (26) are connected in transmission via a transmission belt (27), and the rotating wheel (29) is fixedly connected to the rotating shaft (28).

5. A hybrid aircraft fuselage structure according to claim 4, characterized in that: The rotating wheel (29) is fixedly connected to a rocker (210), the rocker arm (211) is rotatably mounted on the rocker arm (210), the rocker arm (211) is fixedly connected to a pull rod (212), the piston rod (213) is rotatably mounted on the pull rod (212), the flexible shaft fixing seat (17) is fixedly connected to a slide rail (214), and the piston rod (213) is slidably mounted in the slide rail (214).

6. A hybrid aircraft fuselage structure according to claim 5, characterized in that: The output end of the gas cylinder (216) is fixedly connected to an air pipe (24), the output end of the air pipe (24) is fixedly connected to a nozzle (3), both sides of the nozzle (3) are fixedly connected to mounting seats (31), and the mounting seats (31) are fixedly connected to a firewall fixing rib (18).

7. A hybrid aircraft fuselage structure according to claim 5, characterized in that: The driving part comprises a connecting plate (215) fixedly connected to the piston rod (213), a lifting plate (21) fixedly connected to the connecting plate (215), a sliding plate (217) slidably mounted inside the lifting plate (21), and the sliding plate (217) is fixedly connected to a brush plate (219).

8. A hybrid aircraft fuselage structure according to claim 7, characterized in that: Both sides of the brush plate (219) are fixedly connected to push rods (220), and the push rods (220) are fixedly connected to spheres (221). Both sides of the air permeable plate (117) are fixedly connected to a plurality of protrusions (118), and the spheres (221) cooperate with the protrusions (118).

9. A hybrid aircraft fuselage structure according to claim 8, characterized in that: The lifting plate (21) is provided with a slide groove (22), the slide plate (217) is fixedly connected to a limit plate (218), the limit plate (218) is slidably installed in the slide groove (22), the limit plate (218) is fixedly connected to a support spring (23), and the free end of the support spring (23) is fixedly connected to the slide groove (22).

10. The hybrid aircraft fuselage structure according to claim 1, characterized in that: A landing gear fixing rib assembly (111) is fixedly connected inside the fuselage shell (1), a center control rib (12) is fixedly connected to the landing gear fixing rib assembly (111), the baffle (16) is fixedly connected to the center control rib (12), and a bottom plate (11) is fixedly connected to the center control rib (12). The bottom plate (11) is fixedly connected to a frame (14), the frame (14) is fixedly connected to an instrument frame (13), the instrument frame (13) is fixedly connected to a landing light fixing plate (15), the bottom plate (11) is fixedly connected to longitudinal ribs (113), the longitudinal ribs (113) are fixedly connected to transverse ribs (114), the transverse ribs (114) are fixedly connected to hand-operated fixing ribs (115), and the hand-operated fixing ribs (115) are fixedly connected to front fixing ribs (116).

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