Inboard sliding translational door for an aircraft

Abstract

This invention belongs to the field of aircraft cabin door design, and particularly relates to an inward sliding cabin door for aircraft. It can more effectively prevent accidental opening of the cabin door, improving safety; the sliding opening effectively avoids the cabin door encroaching on internal space when opened, reducing the impact on emergency evacuation; and the use of a motor-driven opening reduces manpower requirements and improves automation.

Description

Technical Field

[0001] This invention belongs to the field of aircraft cabin door design, and particularly relates to an inward sliding cabin door for aircraft. Background Technology

[0002] Cabin doors are the main passageways for personnel, cargo and equipment to enter and exit an aircraft. Most current aircraft models adopt semi-blocking or non-blocking cabin door schemes. The cabin doors open outwards, which has relatively low security and a more complex internal mechanism. Summary of the Invention

[0003] To address the above issues, this invention provides an electrically operated, sliding, inward-opening aircraft cabin door solution. The blocking design employed in this invention more effectively prevents accidental door opening, improving safety; the sliding opening effectively avoids the door encroaching on cabin space when open, reducing the impact on emergency evacuation; and the motor-driven opening reduces manpower requirements and increases automation.

[0004] To address the problems existing in the prior art, this invention provides an inward sliding aircraft door. A bottom-mounted hollow rotary motor drives a cam to pull the door into the cabin; a central rotary motor, acting as a power source, drives the door to slide open via a rack and pinion mechanism. This invention offers advantages such as convenient operation and high safety and reliability.

[0005] The present invention adopts the following technical solution:

[0006] This invention provides an inward sliding aircraft door, comprising a door structure, guide rails, sliders, a central rack, a central rotary motor, a cam, a hollow rotary motor, a bottom splined shaft, continuous stop blocks on the door frame, fuselage skin, a P-type sealing strip, a door frame, continuous stop blocks on the door, a blade-type sealing strip, a door skin, a locking arc segment, gears, rollers, an initial inward sliding rail, a sliding rail, and hollow mounting holes. The upper part of the door structure has four sliders that slide within the guide rails to control the door's attitude during the inward sliding and sliding opening process. The hollow rotary motor drives the inward sliding of the door, enabling the door to slide inward or close outward. The central rotary motor drives the opening of the door, enabling the door to slide horizontally open or close.

[0007] Furthermore, a central rack is arranged in the middle of the hatch. When the hatch slides into place, the central rack will mesh with the teeth of the central rotary motor, and then the central rotary motor will drive the hatch to slide and open on the guide rail.

[0008] Furthermore, a hollow rotary motor and a cam mechanism are arranged at the bottom of the hatch. The hollow rotary motor drives the cam to slide the hatch inward, and a locking function is integrated on the cam to lock the hatch in the closed position.

[0009] Furthermore, the hatch body structure mainly includes a skin, crossbeam, frame, intermediate short frame, continuous stop, and sealing strip. The continuous stop bears the pressurization load, and the continuous structure can effectively reduce the relative deformation of the hatch under pressurization, while meeting the high reliability sealing requirements under large pressure differentials. The sealing strip includes a double-layer sealing strip, consisting of a blade-type sealing strip and a P-type sealing strip. The blade-type sealing strip is arranged on the outside of the hatch close to the hatch skin, and when the hatch is closed, it fits against the hatch frame skin to achieve the sealing requirement and tends to be compressed under the pressurization load; the P-type sealing strip is arranged on the outside of the continuous stop, and when the hatch is closed, it is pressed against the fuselage stop, achieving the sealing requirement and tending to be compressed under the pressurization load.

[0010] The beneficial effects of this invention are as follows:

[0011] (1) The present invention is simple in form and easy to operate. It uses two rotary motors to realize the sliding and opening functions of the hatch respectively. Compared with the semi-blocking hatch, the mechanism is greatly simplified.

[0012] (2) The present invention has good airtightness. The use of continuous baffles can reduce the deformation of the hatch relative to the door frame under a large pressure difference. The double-layer sealing strip can more effectively ensure the sealing performance of the hatch.

[0013] (3) The present invention is highly safe, saves space and weight, and adopts the form of sliding inward first and then moving horizontally to open. The opening method is opposite to the pressurization load, which can effectively improve safety. Through the design of the horizontal opening scheme, the problems of traditional flip-type inward opening doors occupying cabin space and hindering stress relief are solved. Attached Figure Description

[0014] Figure 1 This is an isometric schematic diagram of the sliding hatch of the present invention;

[0015] Figure 2 This is a schematic diagram of the hatch sliding into its final position according to the present invention;

[0016] Figure 3 This is a schematic diagram of the hatch of the present invention in its fully open state;

[0017] Figure 4 This is a schematic diagram of the upper guide mechanism of the present invention;

[0018] Figure 5 This is a schematic diagram of the central translation-driven opening mechanism of the present invention;

[0019] Figure 6 This is a cross-sectional view of the cam in the locked state of the present invention;

[0020] Figure 7 This is a cross-sectional view of the inner sliding position state of the present invention;

[0021] Figure 8 This is a cross-sectional view of the double sealing strip and continuous stop block in the closed state of the present invention.

[0022] In the diagram: 1. Door structure; 2. Guide rail; 3. Slider; 4. Central rack; 5. Central rotary motor; 6. Cam; 7. Hollow rotary motor; 8. Bottom splined shaft; 9. Door frame continuous stop; 10. Fuselage skin; 11. P-type sealing strip; 12. Door frame; 13. Door continuous stop; 14. Blade-type sealing strip; 15. Door skin; 16. Locking arc segment; 17. Gear; 18. Roller; 19. Initial inner sliding rail; 20. Translation rail; 21. Hollow mounting hole. Detailed Implementation

[0023] The present application is described in detail below with reference to the embodiments, but the present application is not limited to these embodiments.

[0024] Example 1

[0025] like Figure 1-8 As shown, the present invention provides an aircraft sliding door with four sets of sliders 3 fixedly connected to the upper part of the door structure 1. A guide rail 2 is fixedly connected to the upper door frame structure, and the sliders 3 are installed inside the guide rail 2, allowing them to slide within it. Rollers 18 are fixedly connected to the lower part of the door structure 1, and the rollers 18 are installed inside the cam grooves of cams 6. There are two cams 6, distributed in the front-rear direction of the door, and the two cams 6 are fixedly connected by a bottom splined shaft 8, which has an external spline design. A hollow rotary motor 7 includes a rotary motor and a hollow mounting hole 21. The hollow rotary motor 7 is fixedly connected to the door frame structure, and its rotary motor can drive the hollow mounting hole 21 to rotate. The bottom splined shaft 8 is installed inside the hollow mounting hole 21 of the hollow rotary motor 7, and the hollow mounting hole 21 has an internal spline keyway feature that meshes with the external spline of the bottom splined shaft 8. The hollow rotary motor 7 drives the bottom splined shaft 8 and cam 6 to rotate, causing the roller 18 and the door structure 1 to slide inward along the slide rail 2. A central rack 4 is fixedly connected to the middle of the door structure 1; a central rotary motor 5 is arranged at the corresponding position on the door frame, and the central rotary motor 5 is fixedly connected to the door frame structure, with a gear 17 fixedly connected to it. When the door structure 1 slides in to its final position, the hollow rotary motor 7 stops rotating, and the central rack 4 meshes with the gear 17 of the central rotary motor 5. The rotation of the central rotary motor 5 drives the gear 17 to rotate, and the gear 17 drives the central rack 4 to translate. In this state, the slider 3 slides inside the guide slide rail 2, and the bottom splined shaft 8 slides inside the hollow mounting hole 21, jointly controlling the translational opening posture of the door structure 1.

[0026] like Figure 1-8As shown, the guide rail 2 comprises two parts: an initial inner slide rail 19 and a translation slide rail 20. The slide rail grooves of the two parts are perpendicular to each other, and the guide rail 2 is arranged in upper and lower layers. The slider 3 is a cross-shaped cylindrical structure with the cylindrical axes in the vertical and horizontal directions, respectively. In the closed position of the hatch, the vertical cylindrical parts of the four sets of sliders 3 are all inserted into the interior of the initial inner slide rail of the guide rail 2; the horizontal cylindrical parts of the two sets of sliders 3 are inserted between the two layers of guide rail 2, with their cylindrical axes perpendicular to the initial inner slide rail 19, and their cylindrical surfaces contacting and engaging with the end faces of the upper and lower layers of guide rail 2; the horizontal cylindrical parts of the other two sets of sliders 3 are inserted between the upper and lower layers of guide rail 2, with their cylindrical axes parallel to the initial inner slide rail 19, and their cylindrical surfaces contacting and engaging with the end faces of the upper and lower layers of guide rail 2. Four sliders 3 can slide freely on the guide rail 2. In the closed position and during the inward sliding process, two sets of sliders 3 arranged with the cylindrical axis perpendicular to the initial inward sliding rail 19 bear the weight of the hatch. During the translational sliding process, two sets of sliders 3 arranged with the cylindrical axis parallel to the initial inward sliding rail 19 bear the weight of the hatch.

[0027] like Figure 1-8 As shown, a locking arc segment 16 is provided on the cam 6, and its trajectory is in the form of an arc, with the center passing through the rotation axis of the cam. When the hatch is fully closed, if the door structure 1 tends to move inward, the roller 18 contacts the locking arc segment 16. The force exerted by the roller 18 on the cam 6 passes through the rotation axis of the cam 6 and cannot drive the cam 6 to rotate. This design achieves the locking of the hatch in the closed position.

[0028] like Figure 1-8 As shown, the continuous door stop 13 is fixedly connected to the door frame 12 and is continuously arranged around the door. The continuous door frame stop 9 is fixedly connected to the door frame structure and is continuously arranged around the door frame. In the closed position, the continuous door stop 13 and the continuous door frame stop 9 are pressed together to transfer the pressurized load on the aircraft door.

[0029] like Figure 1-8 As shown, the present invention is designed with double-layer sealing strips. The blade-type sealing strip 14 is installed on the hatch frame 12 and adheres to the fuselage skin 10 when the hatch is closed, achieving the sealing requirements and tending to be compressed under the action of pressurized load. The P-type sealing strip 11 is arranged on the outside of the hatch continuous block 13 and is pressed against the door frame continuous block 9 when the hatch is closed, achieving the sealing requirements and tending to be compressed under the action of pressurized load.

[0030] This invention features a simple structure and convenient operation, utilizing two rotary motors to drive the hatch's inward sliding and opening respectively. The invention boasts a reliable structure and high safety; the continuous stop block can withstand pressurized loads under large pressure differentials, reducing the deformation of the hatch relative to the door frame, while the double-layer sealing strip more effectively ensures the hatch's sealing performance. This invention is compact, saving space and weight; the inward sliding followed by horizontal opening effectively ensures a clear opening space, and the simple and direct mechanism layout allows for better control of the hatch's weight.

[0031] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any modifications or substitutions made by those skilled in the art within the scope of the technology disclosed in this application should be covered within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. An aircraft internal sliding door, characterized in that, Includes door structure (1), guide rail (2), slider (3), central rack (4), central rotary motor (5), cam (6), hollow rotary motor (7), bottom spline shaft (8), door frame continuous stop block (9), fuselage skin (10), P-type sealing strip (11), hatch frame (12), hatch continuous stop block (13), blade-type sealing strip (14), hatch skin (15), locking arc segment (16), gear (17), roller (18), initial inner sliding rail (19), translation rail (20), hollow mounting hole (21).

2. The aircraft internal sliding door according to claim 1, characterized in that, The upper part of the door structure (1) is fixedly connected with 4 sets of sliders (3), and the upper door frame structure is fixedly connected with guide rails (2). The sliders (3) are installed inside the guide rails (2) and can slide inside the guide rails (2). The lower part of the door structure (1) is fixedly connected to a roller (18), which is installed in the cam groove of the cam (6). There are two cams (6), which are distributed in the front and rear directions of the door. The two cams (6) are fixedly connected by a bottom spline shaft (8), which is designed with an external spline. The hollow rotary motor (7) includes a rotary motor and a hollow mounting hole (21). The hollow rotary motor (7) is fixedly connected to the door frame structure. Its rotary motor can drive the hollow mounting hole (21) to rotate. The bottom spline shaft (8) is installed inside the hollow mounting hole (21) of the hollow rotary motor (7). The hollow mounting hole (21) is designed with an inner spline keyway feature, which meshes with the outer spline of the bottom spline shaft (8). The hollow rotary motor (7) drives the bottom spline shaft (8) and the cam (6) to rotate, which drives the roller (18) and the door structure (1) to slide inward along the slide rail 2. The door structure (1) is fixedly connected to a central rack (4); a central rotary motor (5) is arranged at the corresponding position of the door frame, and the central rotary motor (5) is fixedly connected to the door frame structure, and a gear (17) is fixedly connected to it; when the door structure (1) slides into place, the hollow rotary motor (7) stops rotating, the central rack (4) meshes with the gear (17) of the central rotary motor (5), the central rotary motor (5) rotates and drives the gear (17) to rotate, and the gear (17) drives the central rack (4) to move in translation. In this state, the slider (3) slides inside the guide rail (2) and the bottom spline shaft (8) slides inside the hollow mounting hole (21), which together control the translational opening posture of the door structure (1).

3. The aircraft internal sliding door according to claim 2, characterized in that, The guide rail (2) comprises two parts: an initial inner slide rail (19) and a translation slide rail (20). The slide rail grooves of the two are perpendicular to each other. The guide rail (2) is arranged in two layers, upper and lower. The slider (3) is a cross-shaped cylindrical structure with the cylindrical axes in the vertical and horizontal directions respectively. In the closed position of the hatch, the vertical cylindrical parts of the four sliders (3) are all installed inside the initial inner slide rail of the guide rail (2). The horizontal cylindrical parts of the two sliders (3) are installed between the two layers of guide rail (2), with their cylindrical axes arranged perpendicular to the initial inner slide rail (19), and the cylindrical surfaces contacting and fitting with the end faces of the upper and lower guide rails (2). The horizontal cylindrical parts of the other two sliders (3) are installed between the upper and lower guide rails (2), with their cylindrical axes arranged parallel to the initial inner slide rail (19), and the cylindrical surfaces contacting and fitting with the end faces of the upper and lower guide rails (2). The four sliders (3) can slide freely on the guide rail (2). In the closed position and during the inner sliding process, the two sets of sliders (3) arranged with the cylindrical axis perpendicular to the initial inner sliding rail (19) bear the weight of the hatch. During the translational sliding process, the two sets of sliders (3) arranged with the cylindrical axis parallel to the initial inner sliding rail (19) bear the weight of the hatch.

4. The aircraft internal sliding door according to claim 3, characterized in that, A locking arc segment (16) is provided on the cam (6), and its trajectory is in the form of an arc with the center passing through the rotation axis of the cam. When the hatch is fully closed, when the door structure (1) has an inward tendency, the roller (18) contacts the locking arc segment (16), and the force of the roller (18) acting on the cam (6) passes through the rotation axis of the cam (6) and cannot drive the cam (6) to rotate, thereby locking the closed position of the hatch.

5. The aircraft internal sliding door according to claim 4, characterized in that, The continuous door stop 13 is fixedly connected to the door frame (12) and is continuously arranged around the door. The continuous stop block (9) of the door frame is fixedly connected to the door frame structure and is continuously arranged around the door frame; When the cabin door is closed, the continuous stop block (13) of the cabin door is pressed against the continuous stop block (9) of the door frame to transmit the pressurized load on the aircraft cabin door; double-layer sealing strips are arranged around the door structure (1), and the blade-type sealing strip (14) is installed on the cabin door frame (12). When the cabin door is closed, it is pressed against the fuselage skin (10) to achieve the sealing requirements and tends to be pressed under the pressurized load; the P-type sealing strip (11) is arranged on the outside of the continuous stop block 13 of the cabin door. When the cabin door is closed, it is pressed against the continuous stop block (9) of the door frame to achieve the sealing requirements and tends to be pressed under the pressurized load.

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