Integral maintenance cabin door

Abstract

The invention belongs to the technical field of aircraft structure design, and particularly relates to an integral maintenance cabin door. The cabin door comprises a cabin door body structure (1), a hinge joint (2), a power assisting device (3), a handle mechanism (4) and a fixed pull rod (5), the cabin door body structure (1) is provided with a longitudinal and transverse framework, the upper portion of the cabin door body structure (1) is connected with a machine body through the hinge joint (2), the lower portion of the cabin door body structure (1) is connected with the machine body through the fixed pull rod (5), and the side portion of the cabin door body structure (1) is connected with the machine body through the handle mechanism (4); the handle mechanism (4) is provided with a rotating handle (41), and the rotating handle (41) is rotated to drive a bolt (44) to lock the side edge of the cabin door body structure (1); one end of the power assisting device (3) is fixed on a fixing structure (6) in the machine body, and the other end is connected with the cabin door body structure (1) through a gas spring. The integral maintenance cabin door is high in bearing efficiency, and the opening time of the cabin door can be shortened.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft structure design, and in particular relates to an integrated maintenance door. Background Art

[0002] Traditional main landing gear maintenance doors of large transport aircraft mostly use a combination of multiple doors, with complex assembly levels and large assembly deviations. During the aircraft assembly phase, a large amount of resources are required to adjust the door installation status to meet the clearance and step difference requirements of the aircraft's outer surface.

[0003] The traditional main landing gear maintenance door has different stiffness and aerodynamic loads in each section, and the deformation of each section is not coordinated in the air, so a significant step difference is formed in the air, which is not good for the aircraft's aerodynamic shape and aerodynamic noise.

[0004] Traditional landing gear maintenance doors are mostly connected to the landing gear bracket or fuselage by pull rods. Due to the inherent deformation of the fuselage structure causing internal assembly forces, it is extremely difficult to remove these pull rods. In addition, there are many doors, which results in a long time required to open the entire maintenance channel, affecting the working time required for aircraft landing gear maintenance and wheel disassembly and assembly.

[0005] The traditional landing gear maintenance door adopts a segmented design, and the overall rigidity is weak. It needs to adopt a hyperstatic constraint with multiple tie rods, which has a large assembly stress. During the use of the aircraft, the assembly stress is gradually released, which will cause the intersection of the downstream assembly to shift, and the related structural gap may be out of tolerance, requiring secondary adjustment, which increases the user's maintenance workload. Summary of the invention

[0006] In order to solve the above problems, the present application provides an integrated maintenance door, which mainly includes:

[0007] The door structure has a longitudinal and transverse frame and a skin laid on the outer surface of the longitudinal and transverse frame. One side of the door structure extending in the length direction is connected to the fuselage through a plurality of hinged joints, and the other side is connected to the fuselage through a plurality of fixed tie rods. Both sides of the door structure extending in the width direction are connected to the fuselage through a plurality of handle mechanisms.

[0008] The handle mechanism comprises a rotating handle, the rotating handle is connected to the latch pin through a hinged rod, and the latch pin is driven to move linearly by rotating the rotating handle so as to be inserted into or pulled out of the latch pin hole located on the side of the machine body;

[0009] The power assist device has one end fixed to a fixed structure inside the fuselage, and the other end connected to the cabin door structure through a gas spring.

[0010] Preferably, the longitudinal and transverse frames of the hatch door body structure include an upper side beam, a lower side beam extending along the length direction and a plurality of T-beams located between the upper side beam and the lower side beam, and the longitudinal and transverse frames of the hatch door body structure also include a plurality of transverse frames and long beams extending along the width direction.

[0011] Preferably, the transverse frame and the long stringer are connected to the T-beam via a connecting belt plate.

[0012] Preferably, at least five hinged joints are evenly distributed on one side of the hatch door structure extending along the length direction.

[0013] Preferably, at least three fixed tie rods are evenly distributed on the other side of the hatch door structure extending in the length direction.

[0014] Preferably, the plug end has a tapered guide head.

[0015] Preferably, the latch has an elongated hole, and the door body structure has a column, which is located in the elongated hole to guide the latch to move in a straight line.

[0016] Preferably, the rotating handle is arranged in a handle box, and its rotational freedom is locked by the handle box. The handle box is fixed to the inner surface of the cabin door body structure. The rotating handle is unlocked by pressing. After pressing, it is popped out of the handle box by a pressing spring, releasing its rotational freedom.

[0017] The integrated maintenance hatch of the present application has high load-bearing efficiency and can shorten the hatch opening time. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 It is a structural axial view of a preferred embodiment of the integrated maintenance hatch of the present application.

[0019] Figure 2 This application Figure 1 Front view of the illustrated embodiment.

[0020] Figure 3 It is a schematic diagram of the external restraint of the hatch.

[0021] Figure 4 It is a schematic diagram of the handle mechanism structure.

[0022] Figure 5 This is a diagram of the hatch opening.

[0023] Among them, 1-door structure, 11-skin, 12-lower beam, 13-upper beam, 14-cross frame, 15-handle box, 16-long girder, 17-connecting strip plate, 18-T-beam, 2-hinge joint, 3-power assist device, 4-handle mechanism, 41-rotating handle, 42-pressing spring, 43-hinge rod, 44-latch, 5-fixed pull rod, 6-fixed structure. DETAILED DESCRIPTION

[0024] In order to make the purpose, technical scheme and advantages of the implementation of this application clearer, the technical scheme in the implementation of this application will be described in more detail in combination with the drawings in the implementation of this application. In the drawings, the same or similar reference numerals throughout represent the same or similar elements or elements with the same or similar functions. The described implementation is a part of the implementation of this application, not all of the implementations. The implementation described below with reference to the drawings is exemplary and is intended to be used to explain this application, and cannot be understood as a limitation on this application. Based on the implementation in this application, all other implementations obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. The implementation of this application is described in detail below in combination with the drawings.

[0025] The present application provides an integrated maintenance hatch, such as Figure 1-Figure 4 As shown, it mainly includes:

[0026] The hatch door structure 1 has a longitudinal and transverse frame and a skin 11 laid on the outer surface of the longitudinal and transverse frame. One side of the hatch door structure 1 extending in the length direction is connected to the fuselage through a plurality of hinged joints 2, and the other side is connected to the fuselage through a plurality of fixed tie rods 5. Both sides of the hatch door structure 1 extending in the width direction are connected to the fuselage through a plurality of handle mechanisms 4.

[0027] The handle mechanism 4 has a rotating handle 41, which is connected to a latch 44 via a hinge rod 43. The rotating handle 41 is rotated to drive the latch 44 to move linearly, so as to be inserted into or pulled out of a latch hole located on the side of the machine body;

[0028] The booster device 3 has one end fixed to a fixed structure 6 in the fuselage, and the other end connected to the door structure 1 via a gas spring.

[0029] The hatch of the present application has no inner skin, the assembly space is open, compensation measures are designed on various mating surfaces, and the processability is good. When the hatch is closed and subjected to aerodynamic loads, the hatch can be constrained by multiple hinged joints 2 at the top, multiple front and rear handle mechanisms 4, and multiple fixed pull rods 5 at the bottom, so that the aerodynamic load can be evenly diffused to the surrounding fuselage structure. Figure 3 Through the combined means of this constraint method and structural arrangement method, the load-bearing efficiency of the door structure is high and the relative deformation is significantly reduced.

[0030] This application relies on gas springs arranged at the front and rear ends of the door to achieve assistance. By reasonably designing the intersection of the mechanism and the input force of the gas spring, the balance point of the gas spring opening torque and the door closing torque formed by the door gravity is set to the middle of the door movement stroke. It can be achieved that no matter whether the door needs to be opened or closed, as long as a slight manual force is applied to make it pass the balance point, the door can automatically move into place under the action of the torque.

[0031] like Figure 5 As shown, the specific steps for opening the cabin door are: first disconnect the fixed pull rod 5, and retract the pin 44 by rotating the handle 41, then manually lift the cabin door above the balance point, and the gas spring of the power assist device 3 automatically lifts the cabin door. The total time is 18 minutes. Compared with the cabin door of the same size of a certain type of aircraft, the present application shortens the cabin door opening time from 45 minutes to 19 minutes.

[0032] In some optional embodiments, the longitudinal and transverse frames of the cabin door body structure 1 include an upper side beam 13 and a lower side beam 12 extending along the length direction, and a plurality of T-beams 18 located between the upper side beam 13 and the lower side beam. The longitudinal and transverse frames of the cabin door body structure 1 also include a plurality of cross frames 14 and long beams 16 extending along the width direction.

[0033] In some optional embodiments, the transverse frame 14 and the long stringer 16 are connected to the T-beam 18 via a connecting strip 17 .

[0034] In some optional embodiments, at least five hinged joints 2 are evenly distributed on one side of the cabin door structure 1 extending along the length direction.

[0035] In some optional embodiments, at least three fixed tie rods 5 are evenly distributed on the other side of the hatch door structure 1 extending along the length direction.

[0036] In some optional embodiments, the end of the plug 44 has a tapered guide head.

[0037] In some optional embodiments, the latch 44 has an elongated hole, and the hatch door structure 1 has a column, which is located in the elongated hole to guide the latch 44 to move in a straight line.

[0038] In some optional embodiments, the rotating handle 41 is arranged in the handle box 15, and its rotational freedom is locked by the handle box 15. The handle box 15 is fixed to the inner surface of the cabin door body structure 1. The rotating handle 41 is unlocked by pressing. After pressing, it is popped out of the handle box 15 by the pressing spring 42, releasing its rotational freedom.

[0039] like Figure 4As shown, when operating the handle mechanism 4 of the hatch, the push switch on the handle surface is pressed, the handle automatically pops up outward, and then the handle is rotated 60 degrees clockwise, and the latch can be pulled out of the support on the other side. When the hatch needs to be closed, the operation is reversed. In order to prevent the latch from not being completely aligned with the support, the end of the latch is opened to achieve a guiding function, which can guide the latch to be accurately inserted into the support.

[0040] In terms of safety, since the area where the personnel stand when operating the handle is within the sweep range of the hatch opening, the torque design of the present application ensures that when the hatch is unlocked, the hatch will not open immediately, and the personnel can wait until they move to a safe area before manually opening the door; and when the hatch is fully opened, the power assist device can be mechanically locked to prevent the hatch from accidentally closing. This achieves full protection for the operator. The mechanical locking of the power assist device can be achieved by simply rotating, with a simple principle and high reliability.

[0041] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. An integrated maintenance door, characterized in that: include: A hatch door structure (1) comprises longitudinal and transverse frames and a skin (11) laid on the outer surface of the longitudinal and transverse frames, wherein one side of the hatch door structure (1) extending in the length direction is connected to the fuselage via a plurality of hinged joints (2), and the other side is connected to the fuselage via a plurality of fixed tie rods (5), and both sides of the hatch door structure (1) extending in the width direction are connected to the fuselage via a plurality of handle mechanisms (4); The handle mechanism (4) comprises a rotating handle (41), wherein the rotating handle (41) is connected to a latch pin (44) via a hinge rod (43), and the latch pin (44) is driven to move linearly by rotating the rotating handle (41) so as to be inserted into or pulled out of a latch pin hole located on the side of the machine body; The booster device (3) has one end fixed to a fixed structure (6) in the machine body, and the other end connected to the cabin door structure (1) via a gas spring.

2. The integrated maintenance door according to claim 1, characterized in that: The longitudinal and transverse frames of the cabin door body structure (1) include an upper side beam (13) and a lower side beam (12) extending in the length direction, and a plurality of T-shaped beams (18) located between the upper side beam (13) and the lower side beam. The longitudinal and transverse frames of the cabin door body structure (1) also include a plurality of transverse frames (14) and long beams (16) extending in the width direction.

3. The integrated maintenance door according to claim 2, characterized in that: The transverse frame (14) and the long girder (16) are connected to the T-beam (18) via a connecting belt plate (17).

4. The integrated maintenance door according to claim 1, characterized in that: At least five hinge joints (2) are evenly distributed on one side of the door body structure (1) extending in the length direction.

5. The integrated maintenance door according to claim 1, characterized in that: At least three fixed pull rods (5) are evenly distributed on the other side of the cabin door body structure (1) extending in the length direction.

6. The integrated maintenance door according to claim 1, characterized in that: The end of the plug (44) has a tapered guide head.

7. The integrated maintenance door according to claim 1, characterized in that: The latch (44) is provided with a long strip hole, and the hatch door structure (1) is provided with a column, which is located in the long strip hole to guide the latch (44) to move linearly.

8. The integrated maintenance door according to claim 1, characterized in that: The rotating handle (41) is arranged in the handle box (15), and its rotational freedom is locked by the handle box (15). The handle box (15) is fixed to the inner surface of the cabin door structure (1). The rotating handle (41) is unlocked by pressing. After being pressed, it is ejected from the handle box (15) by the pressing spring (42), thereby releasing its rotational freedom.

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