Aircraft cabin door system and opening method

Abstract

The invention provides an aircraft cabin door system and an opening method, and relates to the technical field of high-speed aircrafts, the cabin door system comprises a cabin body, a driving mechanism is arranged in the cabin body, the two sides of the cabin body are rotationally connected with split cabin doors, and the two split cabin doors can be driven by the driving mechanism to overturn towards the two sides of the cabin body; an undercarriage assembly is rotationally connected into the cabin body and can be driven by a driving mechanism to descend; the cabin body is rotationally connected with a front cabin door, and the front cabin door is fixed with the undercarriage assembly and can be driven by the undercarriage assembly to overturn towards the advancing direction of the aircraft; by arranging the front cabin door fixedly connected with the undercarriage assembly, the front cabin door and the two oppositely-opened cabin doors can jointly seal the cabin body, and the front cabin door can turn over when the driving mechanism drives the undercarriage assembly to descend, participate in energy management in the landing stage of the aircraft and assist a speed brake of the aircraft in decelerating the aircraft, reducing the landing speed and shortening the sliding distance. The aircraft is decelerated to a safe speed in a short distance, and the stability and reliability of the aircraft during landing are ensured.

Description

Technical Field

[0001] The present application relates to the technical field of high-speed aircraft, and in particular to an aircraft cabin door system and an opening method. Background Art

[0002] High-speed aircraft generally refers to aircraft whose maximum speed exceeds the speed of sound. The main purpose of the design and development of high-speed aircraft is to cover long distances in a short time and improve the efficiency and convenience of air transportation. In practical applications, high-speed aircraft are mainly used for long-distance flights and some short-distance flights, which can significantly shorten the flight time, so that passengers and cargo can reach their destinations in a shorter time. With the increase in the speed of high-speed aircraft, traditional landing gear equipment can no longer meet the demand. It is necessary to develop new landing gear devices to reduce the landing speed, shorten the taxiing distance, reduce the wear and time of the aircraft on the runway, and decelerate the aircraft to a safe speed in a short distance to ensure stability and reliability during high-speed flight and landing. Summary of the invention

[0003] The purpose of this application is to provide an aircraft cabin door system and an opening method in order to solve the above problems.

[0004] In a first aspect, the present application provides an aircraft door system, comprising: A cabin body, wherein a driving mechanism is provided in the cabin body; Two split doors, the two split doors are rotatably connected to the two sides of the cabin body, and can be turned to the two sides of the cabin body respectively under the drive of the driving mechanism; A landing gear assembly, which is accommodated in the cabin and rotatably connected to the cabin, and can be lowered from the cabin under the drive of the driving mechanism; A front door is rotatably connected to the cabin body and fixed to the landing gear assembly. The front door can be flipped in the forward direction of the aircraft driven by the landing gear assembly to form an angle with the horizontal direction; the front door and the two double doors can jointly close the cabin body.

[0005] According to the technical solution provided in certain embodiments of the present application, the driving mechanism includes a first actuator cylinder, a fixed end of which is rotatably connected to the cabin body and is connected to an air source device, a driving end of the first actuator cylinder is rotatably connected to the landing gear assembly, and the landing gear assembly is fixed to the front door close to the cabin body through a fixed support rod; the rotation axes of the landing gear assembly and both ends of the first actuator cylinder extend in the same direction.

[0006] According to the technical solution provided in certain embodiments of the present application, the driving mechanism includes two second actuator cylinders, the two second actuator cylinders are symmetrically arranged, and the fixed ends of the two are rotatably connected to the cabin body, the driving ends of the two second actuator cylinders are respectively rotatably connected to the first connecting rod, the first ends of the two first connecting rods are both rotatably connected to the cabin body, the second ends of the two are respectively rotatably connected to the second connecting rod, and the free ends of the two second connecting rods are respectively rotatably connected to the two double-leaving doors; the two second actuator cylinders are also connected to the air source device; the rotation axes of the two ends of the second actuator cylinder, the two ends of the first connecting rod and the two ends of the second connecting rod all extend in the same direction.

[0007] According to the technical solutions provided in some embodiments of the present application, a first solenoid valve is provided between the two second actuators and the air source device, and a second solenoid valve is further provided between the first actuator and the first solenoid valve.

[0008] According to the technical solution provided in certain embodiments of the present application, the landing gear assembly includes a support shaft and a rotating shaft, the support shaft is rotatably connected to the cabin, the support shaft is rotatably connected to the driving end of the first actuator cylinder, the rotating shaft is coaxially arranged with the support shaft and rotatably connected to the end of the support shaft away from the cabin, the end of the rotating shaft away from the support shaft is provided with a wheel fork, and the wheel fork is rotatably connected to an organic wheel; a driving member is provided on the outer periphery of the support shaft, the driving end of the driving member extends along the length direction of the support shaft and is fixed with a transmission rod, the free end of the transmission rod is rotatably connected with a rotating connecting rod, and the rotating connecting rod is fixed to the rotating shaft.

[0009] According to the technical solution provided in certain embodiments of the present application, the landing gear assembly includes a shimmy damper, which is used to prevent the wheels from shimmying when the aircraft lands.

[0010] According to the technical solution provided in certain embodiments of the present application, a sealing structure is provided between the cabin body, the front cabin door and the two opposing cabin doors.

[0011] According to the technical solution provided in certain embodiments of the present application, it also includes explosive bolts, and a plurality of the explosive bolts respectively fix the cabin body and the front door and the cabin body and the two opposing doors to lock and fix the front door and the two opposing doors.

[0012] In a second aspect, the present application provides a method for opening an aircraft cabin door, using an aircraft cabin door system as described above, the method comprising the following steps: Open the first solenoid valve to drive the two split doors to flip to the two sides of the cabin to their corresponding open positions; Open the upper lock of the first actuator; Open the second solenoid valve to drive the front door to flip to its corresponding open position; Close the first solenoid valve.

[0013] According to the technical solutions provided in some embodiments of the present application, before the first solenoid valve is opened, the method further includes: Detonate multiple explosive bolts to unlock the front hatch and two side hatches.

[0014] Compared with the prior art, the present application has the following beneficial effects: the present application provides an aircraft door system, comprising a cabin, a driving mechanism is provided in the cabin, two sides of the cabin are respectively connected with split doors in rotation, and the two split doors can be flipped to the two sides of the cabin under the driving of the driving mechanism; a landing gear assembly is stored in the cabin, the landing gear assembly is connected with the cabin in rotation, and can be lowered from the cabin under the driving of the driving mechanism; a front door is connected with the cabin in rotation, the front door is fixed with the landing gear assembly, and can be flipped in the forward direction of the aircraft under the driving of the landing gear assembly to form an angle with the horizontal direction, and the front door and the two split doors can close the cabin together; by providing a front door fixedly connected with the landing gear assembly, the front door can close the cabin together with the two split doors, and can also be flipped open when the driving mechanism drives the landing gear assembly to be lowered, so as to participate in the energy management of the landing stage of the aircraft, assist the deceleration plate of the aircraft to decelerate the aircraft, reduce the landing speed, shorten the taxiing distance, and decelerate the aircraft to a safe speed within a short distance, so as to ensure the stability and reliability of the aircraft when landing.

[0015] It should be understood that the description of technical features, technical solutions, beneficial effects or similar language in this application does not imply that all features and advantages can be realized in any single embodiment. On the contrary, it is understood that the description of features or beneficial effects means that specific technical features, technical solutions or beneficial effects are included in at least one embodiment. Therefore, the description of technical features, technical solutions or beneficial effects in this specification does not necessarily refer to the same embodiment. Furthermore, the technical features, technical solutions and beneficial effects described in the present embodiment can also be combined in any appropriate manner. Those skilled in the art will understand that the embodiment can be realized without one or more specific technical features, technical solutions or beneficial effects of a specific embodiment. In other embodiments, additional technical features and beneficial effects can also be identified in a specific embodiment that does not embody all embodiments. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings required for use in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0017] Figure 1 A schematic diagram of the structure of an aircraft door system provided in Example 1 of the present application; Figure 2 A schematic diagram of the structure of a front door and a side door of an aircraft door system provided in Example 1 of the present application when they are closed; Figure 3 A schematic diagram of the structure of the interior of a cabin of an aircraft cabin door system provided in Example 1 of the present application; Figure 4 A schematic flow chart of a method for opening an aircraft door provided in Example 2 of the present application.

[0018] The text annotations in the figure represent: 1. Cabin body; 2. Double doors; 3. Front door; 4. First actuator; 5. Second actuator; 6. First connecting rod; 7. Second connecting rod; 8. Support shaft; 9. Rotating shaft; 10. Wheel; 11. Explosive bolt; 12. Support seat; 13. Rotating bracket; 14. First support; 15. Second support; 16. Third support. DETAILED DESCRIPTION

[0019] In order to enable those skilled in the art to better understand the technical solution of the present application, the technical solution in the embodiments of the present application will be clearly and completely described below in conjunction with the accompanying drawings. The description in this section is only exemplary and explanatory and should not have any limiting effect on the protection scope of the present application. Specifically, the described embodiments are only embodiments of a part of the present application, not all embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in the field without making creative work should fall within the scope of protection of the present application.

[0020] It should be noted that similar reference numerals and letters represent similar items in the following figures, so once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures. In addition, the terms "including" and "having" and any variations thereof are intended to cover non-exclusive inclusions, for example, a process, method, system, product or device that includes a series of steps or units is not necessarily limited to those steps or units clearly listed, but may include other steps or units that are not clearly listed or inherent to these processes, methods, products or devices.

[0021] Example 1 As mentioned in the background technology, in order to solve the problems in the prior art, this embodiment provides an aircraft door system, including: A cabin 1, wherein a driving mechanism is provided in the cabin 1; The two split doors 2 are rotatably connected to the two sides of the cabin body 1 and can be flipped to the two sides of the cabin body 1 under the drive of the driving mechanism; The landing gear assembly is stored in the cabin 1 and is rotatably connected to the cabin 1. The landing gear assembly can be lowered from the cabin 1 under the drive of the driving mechanism; The front door 3 is rotatably connected to the cabin body 1 and fixed to the landing gear assembly. The front door 3 can be flipped in the forward direction of the aircraft driven by the landing gear assembly to form an angle with the horizontal direction; the front door 3 and the two opposing doors 2 can jointly close the cabin body 1.

[0022] like Figure 1-3 As shown, the cabin 1 is opened below the fuselage, and a support seat 12 is provided in the cabin 1. The landing gear assembly is rotatably connected to the support seat 12, and the rotation direction is a first direction, which is the width direction of the cabin. That is, it can be understood as follows Figure 3 The two split doors 2 are respectively connected to the left and right sides of the cabin body 1 by rotating brackets 13, so that the two split doors 2 can be turned relative to the cabin body 1 under the drive of the driving mechanism. The rotation direction is the second direction, and the second direction is the length direction of the cabin body, which can be understood as follows. Figure 3 In the horizontal direction shown in , a first support 14 is provided in the cabin 1 near the front of the aircraft, and one end of the front door 3 away from the two split doors 2 is connected to the first support 14 with a pin and fixed to the landing gear assembly, and the front door 3 can rotate relative to the first support 14, and the rotation direction is a first direction; the front door 3 and the two split doors 2 are both machined by TC4, and each door is provided with a reinforcing rib, the door body is 3mm thick, the reinforcing rib is 5mm wide and 8mm high; initially, the landing gear assembly is stored in the cabin 1, and the front door 3 and the two split doors 2 jointly close the cabin 1, when the aircraft lands, the driving mechanism drives the two split doors 2 to flip to both sides of the cabin 1 respectively until the two split doors 2 are fully opened, and then the driving mechanism drives the landing gear assembly to be lowered from the cabin 1, and the landing gear assembly simultaneously drives the front door 3 to flip to the front of the aircraft, so that the front door 3 is fully opened.

[0023] By setting a front door 3 fixedly connected to the landing gear assembly, the front door 3 can close the cabin body 1 together with the two opening doors 2, and can also be flipped open when the driving mechanism drives the landing gear assembly to be lowered, participating in the energy management of the aircraft landing phase, assisting the aircraft's air brake to decelerate the aircraft, reduce the landing speed, shorten the taxiing distance, and decelerate the aircraft to a safe speed within a short distance, so as to ensure the stability and reliability of the aircraft during landing.

[0024] Specifically, when the front door 3 is flipped open, it forms an angle with the horizontal direction, and the front door 3 is equivalent to an air resistance surface. When the aircraft lands and glides, the air acts on the front door 3 to generate backward resistance. According to the principle of aerodynamics, when an object moves in the air, the contact area and relative speed with the air will affect the magnitude of the resistance. The area of ​​the front door 3 and its specific flip angle enable it to effectively increase the air resistance suffered by the aircraft during the landing phase. This additional resistance assists the aircraft's speed brake to slow down the aircraft, thereby reducing the landing speed. In addition, the front door 3 works in conjunction with the aircraft's speed brake to decelerate the aircraft. During the landing process of the aircraft, the speed brake itself increases the resistance by changing the air flow field, but the addition of the front door 3 further enhances the deceleration effect. The two cooperate with each other to increase the resistance of the aircraft from different parts and methods, so that the aircraft can be decelerated to a safe speed more efficiently within a short distance. During the actual landing, the front door 3 and the speed brake work at the same time, greatly shortening the gliding distance.

[0025] In a preferred embodiment, the driving mechanism includes a first actuator cylinder 4, a fixed end of which is rotatably connected in the cabin body 1 and is connected to an air source device, a driving end of the first actuator cylinder 4 is rotatably connected to a landing gear assembly, and the landing gear assembly is fixed to a side of the front door 3 close to the cabin body 1 through a fixed support rod; the rotation axes of both ends of the landing gear assembly and the first actuator cylinder 4 extend in the same direction.

[0026] like Figure 1 As shown, a second support 15 is provided in the middle position of the cabin body 1, and the fixed end of the first actuator 4 is rotatably connected to the second support 15, and the rotation direction is the first direction. The piston rod of the first actuator 4 is its driving end, and the piston rod of the first actuator 4 is rotatably connected to one side of the landing gear assembly, and the rotation direction is the first direction. At the same time, the landing gear assembly is fixedly connected to the front door 3 through two fixed support rods; initially, the first actuator 4 is in a retracted state, and the front door 3 is closed on the cabin body 1. When the air source device fills the rod cavity of the first actuator 4 with high-pressure nitrogen, the piston rod of the first actuator 4 extends from the rod cavity, and the extending direction is perpendicular to the first direction, pushing the landing gear assembly to fall, and at the same time driving the front door 3 to flip, so that the front door 3 is opened.

[0027] In a preferred embodiment, the driving mechanism includes two second actuator cylinders 5, the two second actuator cylinders 5 are symmetrically arranged, and the fixed ends of the two are rotatably connected in the cabin body 1, the driving ends of the two second actuator cylinders 5 are respectively rotatably connected to the first connecting rod 6, the first ends of the two first connecting rods 6 are both rotatably connected in the cabin body 1, and the second ends of the two are respectively rotatably connected to the second connecting rod 7, and the free ends of the two second connecting rods 7 are respectively rotatably connected to the two opposing doors 2; the two second actuator cylinders 5 are also connected to the air source device; the rotation axes of the two ends of the second actuator cylinder 5, the two ends of the first connecting rod 6 and the two ends of the second connecting rod 7 extend in the same direction.

[0028] like Figure 1 As shown, a third support 16 is provided in the cabin 1 at a position away from the front of the aircraft, two second actuators 5 are symmetrically arranged relative to the third support 16 and are rotatably connected to the third support 16, and the rotation direction is the second direction. Two fourth supports are also symmetrically provided in the cabin 1 at a position away from the front of the aircraft, a first end of the first connecting rod 6 is rotatably connected to the fourth support, and a second end thereof is rotatably connected to a second connecting rod 7, and free ends of the two second connecting rods 7 are rotatably connected to the corresponding rotating brackets 13 of the split cabin doors 2 (each split cabin door 2 corresponds to two rotating brackets 13 connected thereto, and only one rotating bracket 13 is connected to the second connecting rod 7), and the rotation directions are all in the second direction The piston rod of the second actuator cylinder 5 is its driving end, and the piston rods of the two second actuator cylinders 5 are respectively connected to the corresponding first connecting rods 6 in a rotation direction of the second direction; initially, the second actuator cylinder 5 is in a stretched state, and there is an angle between the first connecting rod 6 and the second connecting rod 7, and the two opposite doors 2 are closed on the cabin body 1. When the air source device fills the rodless cavity of the second actuator cylinder 5 with high-pressure nitrogen, the piston rod of the second actuator cylinder 5 retracts into the rod cavity, and at the same time drives the first connecting rod 6 to rotate, and then drives the second connecting rod 7 to make the opposite doors 2 flip relative to the cabin body 1. When the first connecting rod 6 and the second connecting rod 7 are in a coaxial state, the two opposite doors 2 are fully opened.

[0029] In a preferred embodiment, a first solenoid valve is provided between the two second actuators 5 and the air source device, and a second solenoid valve is further provided between the first actuator 4 and the first solenoid valve.

[0030] like Figure 1 As shown, the first solenoid valve and the second solenoid valve both adopt the normally closed solenoid valves in the prior art. The first solenoid valve is arranged at the output end of the air source device, and is used to control the on-off of the air path between the air source device and the first actuator cylinder 4 and the second actuator cylinder 5. The second solenoid valve is arranged at the rod chamber input end of the first actuator cylinder 4, and is used to control the on-off of the air path between the air source device and the first actuator cylinder 4.

[0031] In a preferred embodiment, the landing gear assembly includes a support shaft 8 and a rotating shaft 9. The support shaft 8 is rotatably connected in the cabin 1. The support shaft 8 is rotatably connected to the driving end of the first actuator 4. The rotating shaft 9 is coaxially arranged with the support shaft 8 and rotatably connected to the end of the support shaft 8 away from the cabin 1. A wheel fork is provided at the end of the rotating shaft 9 away from the support shaft 8, and a wheel 10 is rotatably connected to the wheel fork; a driving member is provided on the periphery of the support shaft 8, and the driving end of the driving member extends along the length direction of the support shaft 8 and is fixed with a transmission rod, and the free end of the transmission rod is rotatably connected with a rotating connecting rod, and the rotating connecting rod is fixed to the rotating shaft 9.

[0032] like Figure 1 As shown, the support shaft 8 is rotatably connected in the cabin 1 through the support seat 12, and the rotation direction is the first direction. The piston rod of the first actuator 4 is rotatably connected to the support shaft 8, which is used to drive the support shaft 8 to rotate. The support shaft 8 is also fixedly connected to the front cabin door 3 through two fixed support rods. The end of the support shaft 8 away from the support seat 12 is rotatably connected to the rotating shaft 9. The rotation axis of the rotating shaft 9 is perpendicular to the rotation axis of the support shaft 8, and its rotation direction is the extension direction of the support shaft 8. The end of the rotating shaft 9 away from the support shaft 8 is connected to a wheel fork, and the wheel fork is rotatably connected to the machine wheel 10; the driving member adopts the steering gear in the prior art, and the steering gear is arranged on one side of the support shaft 8. When the steering gear drives the transmission rod to rotate, the transmission rod drives the rotating connecting rod, and then drives the rotating shaft 9 to rotate, so that the machine wheel 10 turns.

[0033] In a preferred embodiment, the landing gear assembly includes a shimmy damper, which is used to prevent the wheels 10 from shimmying when the aircraft lands.

[0034] like Figure 1 As shown, one end of the shimmy damper is connected to the support shaft 8, and the other end is connected to the wheel fork, which is used to reduce the shimmy speed of the wheel 10 when the aircraft is taxiing, absorb the impact energy generated by the shimmy, and prevent the occurrence of shimmy vibration.

[0035] In a preferred embodiment, a sealing structure is provided between the cabin body 1 , the front cabin door 3 and the two side doors 2 .

[0036] like Figure 2 As shown, the sealing structure includes a sealing groove with a size of 9mm*3mm. A sealing packing with a diameter of 6mm is arranged in the sealing groove. The sealing packing is made of quartz fiber and contains high-temperature alloy metal wire.

[0037] In a preferred embodiment, it also includes explosive bolts 11, and a plurality of explosive bolts 11 respectively fix the cabin body 1 and the front door 3 and the cabin body 1 and the two opposing doors 2, so as to lock and fix the front door 3 and the two opposing doors 2.

[0038] like Figure 1As shown, the front door 3 and the two side doors 2 are fixed to the fuselage and seal the cabin 1 with explosive bolts 11. At the same time, the compression rate of the sealing packing is ensured to reach 50% by the explosive bolts 11, so that the sealing structure can prevent hot air from entering the cabin from the overlap between the cabin 1 and the door.

[0039] Example 2 like Figure 4 As shown, this figure is a schematic flow chart of a method for opening an aircraft cabin door provided in this embodiment, using an aircraft cabin door system as described in Example 1, and the method includes the following steps: S1. Detonate multiple explosive bolts to unlock the front hatch and two side hatches; At the initial T0 moment, the intelligent controller determines that the aircraft meets the landing conditions and opens the pin pullers of the two biparting doors. At T0-1 moment: 1 second after T0, the intelligent controller detonates the explosive bolts of the front door, and the front door is unlocked. At T0-2 moment: 0.15 seconds after T0-1, the intelligent controller detonates the explosive bolts of the two biparting doors, and the two biparting doors are unlocked.

[0040] S2, opening the first solenoid valve to drive the two opposite doors to flip to the two sides of the cabin to their corresponding open positions; Moment T1: 0.15 seconds after moment T0-2, the intelligent controller issues a lowering command. After receiving the lowering command, the retracting and releasing controller opens the first solenoid valve, and the air source device fills the rodless cavities of the two second actuators with high-pressure nitrogen. The piston rods of the two second actuators retract, and then drive the two double-doors to open through the first connecting rod and the second connecting rod.

[0041] S3, opening the upper lock of the first actuator; T1-1 moment: 1 second after T1 moment, the retraction and extension controller opens the upper lock inside the first actuator cylinder to unlock the first actuator cylinder.

[0042] S4, opening the second solenoid valve to drive the front door to flip to its corresponding open position; Moment T1-2: 1 second after moment T1-1, the retraction and extension controller opens the second solenoid valve to connect the air path between the air source device and the first actuator cylinder. The air source device fills the rod chamber of the first actuator cylinder with high-pressure nitrogen, extending the piston rod of the first actuator cylinder, pushing the landing gear assembly downward and driving the front door to open at the same time.

[0043] S5. Close the first solenoid valve.

[0044] T1-3 moment: the retractable controller is also electrically connected to an in-place switch. When the landing gear and the cabin door are lowered into place, the in-place switch sends an in-place signal to the retractable controller. The retractable controller controls the first solenoid valve to cut off power and close, and the air source device stops working.

[0045] Furthermore, 20 seconds after time T1, the intelligent controller detects the retraction and extension status of the landing gear assembly. If the intelligent controller determines that the landing gear assembly is not lowered, it starts to execute the forced landing action.

[0046] This article uses specific examples to illustrate the principles and implementation methods of this application. The description of the above embodiments is only used to help understand the method and its core ideas of this application. The above is only the preferred implementation method of this application. It should be pointed out that due to the limitations of textual expression and the objective existence of infinite specific structures, ordinary technicians in this technical field can make several improvements, modifications or changes without departing from the principles of this application, and can also combine the above technical features in an appropriate manner; these improvements, modifications, changes or combinations, or the direct application of the concept and technical solution of the invention to other occasions without improvement, should be regarded as the scope of protection of this application.

Claims

1. An aircraft door system, characterized in that: include: A cabin (1), wherein a driving mechanism is provided in the cabin (1); Two split doors (2), the two split doors (2) being rotatably connected to the two sides of the cabin body (1) and capable of being flipped toward the two sides of the cabin body (1) under the drive of the drive mechanism; a landing gear assembly, the landing gear assembly being housed in the cabin (1) and being rotatably connected to the cabin (1), the landing gear assembly being capable of being lowered from the cabin (1) under the drive of the driving mechanism; A front door (3), the front door (3) being rotatably connected to the cabin body (1) and being fixed to the landing gear assembly; the front door (3) can be turned in the forward direction of the aircraft driven by the landing gear assembly to form an angle with the horizontal direction; the front door (3) and the two split doors (2) can jointly close the cabin body (1).

2. An aircraft door system according to claim 1, characterized in that: The driving mechanism comprises a first actuator cylinder (4), a fixed end of the first actuator cylinder (4) being rotatably connected in the cabin body (1) and being connected to an air source device, a driving end of the first actuator cylinder (4) being rotatably connected to the landing gear assembly, and the landing gear assembly being fixed to a side of the front cabin door (3) close to the cabin body (1) via a fixed support rod; the rotation axes of both ends of the landing gear assembly and the first actuator cylinder (4) extend in the same direction.

3. An aircraft door system according to claim 2, characterized in that: The driving mechanism comprises two second actuating cylinders (5), the two second actuating cylinders (5) are symmetrically arranged, and the fixed ends of the two second actuating cylinders (5) are rotatably connected to the cabin body (1), the driving ends of the two second actuating cylinders (5) are respectively rotatably connected to the first connecting rods (6), the first ends of the two first connecting rods (6) are both rotatably connected to the cabin body (1), the second ends of the two second connecting rods (7) are respectively rotatably connected to the two split cabin doors (2), and the free ends of the two second connecting rods (7) are respectively rotatably connected to the two split cabin doors (2); the two second actuating cylinders (5) are also connected to the air source device; the rotation axes of the two ends of the second actuating cylinder (5), the two ends of the first connecting rod (6) and the two ends of the second connecting rod (7) all extend in the same direction.

4. An aircraft door system according to claim 3, characterized in that: A first solenoid valve is provided between the two second actuating cylinders (5) and the air source device, and a second solenoid valve is also provided between the first actuating cylinder (4) and the first solenoid valve.

5. The aircraft door system according to claim 2, characterized in that: The landing gear assembly comprises a support shaft (8) and a rotating shaft (9), wherein the support shaft (8) is rotatably connected in the cabin (1), the support shaft (8) is rotatably connected to the driving end of the first actuating cylinder (4), the rotating shaft (9) is coaxially arranged with the support shaft (8) and rotatably connected to an end of the support shaft (8) away from the cabin (1), a wheel fork is provided at an end of the rotating shaft (9) away from the support shaft (8), and a wheel (10) is rotatably connected to the wheel fork; a driving member is provided on the outer periphery of the support shaft (8), the driving end of the driving member extends along the length direction of the support shaft (8) and is fixed with a transmission rod, the free end of the transmission rod is rotatably connected to a rotating connecting rod, and the rotating connecting rod is fixed to the rotating shaft (9).

6. An aircraft door system according to claim 5, characterized in that: The landing gear assembly comprises a shimmy damper, which is used to prevent the wheel (10) from shimmying when the aircraft lands.

7. The aircraft door system according to claim 1, characterized in that: A sealing structure is provided between the cabin body (1), the front cabin door (3) and the two split cabin doors (2).

8. The aircraft door system according to claim 1, characterized in that: It also comprises explosive bolts (11), wherein a plurality of the explosive bolts (11) are respectively fixedly connected to the cabin body (1) and the front cabin door (3) and the cabin body (1) and the two split cabin doors (2), and are used to lock and fix the front cabin door (3) and the two split cabin doors (2).

9. A method for opening an aircraft door, characterized in that: Using an aircraft door system according to any one of claims 1 to 8, the method comprises the following steps: Open the first solenoid valve to drive the two split doors to flip to the two sides of the cabin to their corresponding open positions; Open the upper lock of the first actuator; Open the second solenoid valve to drive the front door to flip to its corresponding open position; Close the first solenoid valve.

10. The aircraft door opening method according to claim 9, characterized in that: Before the first solenoid valve is opened, the method further includes: Detonate multiple explosive bolts to unlock the front hatch and two side hatches.

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