External shape-preserving handrail device of airplane

Abstract

The invention provides an aircraft external shape-preserving handrail device which comprises a bottom box, a handrail body, a handrail body, a handrail body, a handrail body, a handrail body and a handrail body, and the bottom box is embedded in an appearance skin of an aircraft empennage; the upper end of the movable opening cover is hinged to the upper portion of the opening of the bottom box, and the lower end of the movable opening cover can overturn towards the interior of the bottom box along the hinged position; the reset assembly is connected with the bottom box and the movable opening cover, and the reset assembly can enable the movable opening cover to seal the opening of the bottom box in a normal state. According to the external shape-preserving handrail device of the airplane, through the embedded structural design, the supporting requirement of external maintenance personnel of the airplane is met, and the pneumatic loss caused by an outwards-protruding handrail is avoided; the structural design of the holding space and the movable covering cap is adaptive to ergonomics, so that the use convenience and safety are improved; the drainage structure is in sealing fit with the magnet to ensure reliable waterproof performance; and the locking assembly further guarantees the structural stability in the flight process, and the whole unmanned aerial vehicle has high practicability and popularization value.

Description

Technical Field

[0001] This invention relates to the field of aviation structural device technology, specifically to an external conformal handrail device for aircraft. Background Technology

[0002] Due to practical needs, equipment maintenance is frequently required on the back of the aircraft. The presence of the rear dorsal fin and vertical stabilizer section makes passage difficult for personnel, necessitating handrails for support. While adding external handrails to the fuselage is feasible, it introduces aerodynamic drag and, due to its proximity to the tail vertical control surface, may adversely affect the aircraft's longitudinal control. This invention aims to provide a handrail device embedded in the fuselage's outer surface to address the aforementioned problems. Summary of the Invention

[0003] In view of this, the present invention provides an external conformal handrail device for aircraft, so as to facilitate the support and assistance of staff for walking.

[0004] The present invention provides the following technical solution: an external conformal armrest device for an aircraft, comprising: a base box, which is embedded in the outer skin of the tail of the aircraft, and the base box has an opening; a movable cover, the upper end of which is hinged to the upper part of the opening of the base box, and the lower end of the movable cover can be flipped toward the inside of the base box along the hinge; and a reset component, which is connected to both the base box and the movable cover, and the reset component can close the opening of the base box with the movable cover under normal conditions.

[0005] Compared with the prior art, the beneficial effects that the above-mentioned at least one technical solution adopted by the present invention can achieve include at least the following: the conformal armrest device for the aircraft exterior in this embodiment, through its embedded structural design, not only solves the support needs of aircraft exterior maintenance personnel, but also avoids the aerodynamic losses caused by protruding armrests; the structural design of the grip space and movable cover is ergonomic, improving ease of use and safety; the drainage structure and magnetic seal work together to ensure reliable waterproof performance; and the locking component further ensures the structural stability during flight, making the whole device highly practical and worthy of promotion. Attached Figure Description

[0006] To more clearly illustrate the technical solutions of the embodiments of this application, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0007] Figure 1 This is a schematic diagram of an embodiment of the present invention; Figure 2 This is a schematic diagram showing the connection between the movable cover and the bottom box in an embodiment of the present invention.

[0008] The attached diagram is labeled as follows: 1. Outer skin; 2. Hinge; 3. Movable cover; 4. Drainage pipe; 41. Rainwater diversion channel; 5. Base box. Detailed Implementation

[0009] The embodiments of this application will now be described in detail with reference to the accompanying drawings.

[0010] It should be noted that, unless otherwise specified, the embodiments and features described in this application can be combined with each other. The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0011] The conformal handrail device on the aircraft exterior in this embodiment is mainly used in the tail area of ​​the aircraft (including the dorsal fin, vertical stabilizer, and other upright structures) to provide support for maintenance personnel when passing through. The device is embedded within the outer skin 1 of the aircraft tail fin and does not protrude from the fuselage outline, ensuring both ease of human-machine operation and avoiding additional aerodynamic drag.

[0012] The device mainly consists of a base box 5, a movable cover 3, a reset component, a drainage pipe 4, a magnetic suction component, and a locking component. The components work together to achieve the functional requirements of "normally closed and shape-preserving, openable for gripping during use, efficient rainwater discharge, and locked in flight mode".

[0013] The bottom box 5 is made of lightweight, high-strength alloy material and has an overall groove-shaped structure. It is embedded inside the outer skin 1 of the aircraft tail and is fixedly connected to the outer skin 1 by riveting.

[0014] The top of the base box 5 is provided with an opening that fits the movable cover 3. The lower end of the opening is offset from the bottom surface of the inner cavity of the base box 5, forming an inwardly recessed gripping space. The height and width of this space are adapted to the size of an adult's palm, making it easy for staff to grip and apply force.

[0015] The movable cover 3 uses the same material and curved shape as the aircraft skin 1 to ensure a smooth transition with the fuselage contour when the device is closed.

[0016] In this embodiment, the movable cover 3 includes a first straight portion, a second straight portion, and an arc transition portion that are staggered. The first straight portion is located near the lower end of the opening of the bottom box 5 and inside the second straight portion. A ferromagnetic alloy sheet that is compatible with the magnetic suction assembly is fixed to its outer side. The second straight portion is located near the upper end of the opening of the bottom box 5 and is hinged to the upper part of the opening of the bottom box 5 by a hinge 2. The arc transition portion connects the first straight portion and the second straight portion, and has an outward protrusion structure that is aligned with the inlet of the rainwater diversion channel 41, so that rainwater can flow into the diversion channel along the arc surface.

[0017] The upper end of the movable cover 3 is riveted to one end of the hinge 2, and the other end of the hinge 2 is riveted to the upper part of the opening of the bottom box 5, so that the lower end of the movable cover 3 can be flipped open into the bottom box 5 along the hinge, with a flip angle range of 0-45° to meet the gripping operation requirements.

[0018] The reset component is a reset spring, one end of which is fixed to the inner cavity side wall of the bottom box 5 by a hook, and the other end is connected to the inner side of the second straight part of the movable cover 3.

[0019] The reset spring is always in a pre-tight state. Under normal conditions, the spring rebound force pushes the movable cover 3 tightly against the edge of the opening of the bottom box 5 to close the opening. When the staff presses the first flat part of the movable cover 3 inward, the spring is further compressed and the movable cover 3 opens. After it is released, the spring resets and drives the movable cover 3 to close the opening again.

[0020] A gap is reserved between the bottom box 5 and the outer skin 1 to form an annular rainwater diversion channel 41. The rainwater diversion channel 41 extends along the outer periphery of the bottom box 5, and its inlet corresponds to the arc transition part of the movable cover 3.

[0021] The drainage conduit 4 is made of corrosion-resistant rubber tubing, which is located inside the outer skin 1 and below the bottom box 5. One end of the conduit is connected to the lower end of the rainwater diversion channel 41 through a nozzle, and the other end is connected to the drain outlet at a lower position of the body through a nozzle.

[0022] Rainwater entering the rainwater diversion channel 41 flows along the channel to the drainage pipe 4 under the action of gravity, and is finally discharged through the body drain outlet, thus preventing rainwater from accumulating in the bottom box 5 or seeping into the body.

[0023] The locking assembly includes an electromagnetic lock and a control module. The electromagnetic lock is fixedly installed on the top of the inner cavity of the base box 5, and the control module is electrically connected to the aircraft's flight control system.

[0024] When the aircraft is in flight, the control module receives the flight signal and controls the electromagnetic lock to be locked. The latch of the electromagnetic lock extends and presses against the inner side of the second straight part of the movable cover 3, restricting the movable cover 3 from flipping and ensuring that the opening is always closed. When the aircraft lands and is at a stop, the control module receives the stop signal and controls the electromagnetic lock to unlock. The latch retracts and the movable cover 3 can be opened normally.

[0025] Preferably, a magnetic suction assembly is fixedly installed on the inner side of the lower end of the opening of the bottom box 5. The magnetic suction assembly uses a permanent magnet to cooperate with the magnetic metal of the movable cover 3 to enhance the sealing performance in the closed state.

[0026] Work process description: I. Normal closed state When the aircraft is not undergoing maintenance and is parked or taxiing, the return spring pushes the movable cover 3 to close the opening of the base box 5. The magnetic component and the magnetic metal adsorption further enhance the sealing effect. At this time, the movable cover 3 is smoothly connected to the fuselage skin 1, with no protruding structure and no aerodynamic drag.

[0027] II. Maintenance and Usage Status When maintenance personnel pass through the tail area of ​​the aircraft, they hold the gripping space of the base box 5 and press the first flat part of the movable cover 3 inward to overcome the elastic force of the return spring and the magnetic attraction force of the magnetic component, causing the movable cover 3 to flip open into the base box 5. Personnel can hold the arc transition part of the movable cover 3 or the edge of the opening of the base box 5 for body support and movement; after releasing their hand, the return spring drives the movable cover 3 to return to its original position and re-close the opening.

[0028] III. Rainwater Drainage Process When it rains, some rainwater falls on the surface of the movable cover 3, flows into the rainwater guide channel 41 along the arc transition part, and is then guided to the body drain outlet through the drain pipe 4 to be discharged, so as to prevent rainwater from seeping into the bottom box 5 or other parts of the body.

[0029] IV. Flight Lock-On Status After the aircraft takes off, the electromagnetic lock of the locking component automatically locks, and the movable cover 3 cannot be opened, ensuring the stability of the device structure during flight and not affecting the longitudinal control and directional control efficiency of the aircraft.

[0030] The conformal handrail device for aircraft exteriors in this embodiment, through its embedded structural design, not only solves the support needs of aircraft exterior maintenance personnel but also avoids aerodynamic losses caused by protruding handrails. The ergonomic design of the grip space and movable cover enhances ease of use and safety. The drainage structure combined with magnetic sealing ensures reliable waterproof performance. The locking component further guarantees structural stability during flight. Overall, it has strong practicality and promotional value.

[0031] The above description is merely a specific embodiment of the present invention and should not be construed as limiting the scope of the invention. Therefore, any substitution of equivalent components or equivalent changes and modifications made within the scope of protection of this patent should still fall within the scope of this patent. Furthermore, the technical features, technical features and technical solutions, and technical solutions in this invention can be freely combined and used.

Claims

1. An external conformal armrest device for aircraft, characterized in that, include: The bottom box (5) is embedded in the outer skin (1) of the aircraft tail wing, and the bottom box (5) has an opening; The upper end of the movable cover (3) is hinged to the upper part of the opening of the bottom box (5), and the lower end of the movable cover (3) can be flipped towards the inside of the bottom box (5) along the hinge. The reset assembly is connected to both the bottom box (5) and the movable cover (3). The reset assembly can cause the movable cover (3) to close the opening of the bottom box (5) under normal conditions.

2. The aircraft external conformal armrest device according to claim 1, characterized in that, The lower end of the opening of the bottom box (5) is offset from the bottom surface of the inner cavity of the bottom box (5) to form a gripping space for the staff to hold.

3. The aircraft external conformal armrest device according to claim 1, characterized in that, The upper end of the movable cover (3) is hinged to the upper part of the opening of the bottom box (5) via a hinge (2).

4. The aircraft external conformal armrest device according to claim 3, characterized in that, The reset assembly includes a reset spring, the two ends of which are connected to the bottom box (5) and the movable cover (3), respectively.

5. The aircraft external conformal armrest device according to claim 1, characterized in that, The bottom box (5) and the outer skin (1) of the aircraft tail are spaced apart to form a rainwater guide channel (41). The aircraft external conformal handrail device also includes a drainage pipe (4), which is set inside the outer skin (1) of the aircraft tail and located below the bottom box (5). The rainwater guide channel (41) is connected to the drainage pipe (4).

6. The aircraft external conformal armrest device according to claim 5, characterized in that, The movable cover (3) has a first flat part and a second flat part that are staggered. The first flat part is close to the lower end of the opening of the bottom box (5), and the second flat part is close to the upper end of the opening of the bottom box (5). The first flat part is located inside the second flat part, and the first flat part and the second flat part are connected by an arc transition part.

7. The aircraft external conformal armrest device according to claim 6, characterized in that, The arc transition section is an outward convex structure facing outward, and the position of the arc transition section corresponds to the inlet position of the rainwater diversion channel (41).

8. The aircraft external conformal armrest device according to claim 6, characterized in that, A magnetic suction assembly is provided on the inner side of the lower end of the opening of the bottom box (5), and a magnetic metal that cooperates with the magnetic suction assembly is provided on the outer side of the first straight part.

9. The aircraft external conformal armrest device according to claim 1, characterized in that, The aircraft external conformal handrail device also includes a locking component, which is located inside the base box (5) and connected to the movable cover (3). When the aircraft is in flight, the locking component is locked and the movable cover (3) at the opening of the base box (5) remains closed. When the aircraft is stationary, the locking component is unlocked and the movable cover (3) at the opening of the base box (5) can be opened by staff.

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