Interior trimming panel of small aircraft cockpit and fixing method of interior trimming panel

Abstract

The invention belongs to the technical field of structural design in an aircraft cockpit, and discloses a small-sized aircraft cockpit interior trim panel and a fixing method thereof.The interior trim panel comprises an interior trim panel assembly, an installation strip and an angle piece with a cloud-shaped spring, the installation strip is fixedly installed on the edge of a control board groove-shaped piece in the aircraft cockpit, the installation strip extends upwards to form an insertion piece, and the insertion piece is fixed to the interior trim panel assembly; the corner piece with the cloud-shaped spring is fixedly installed on the edge of an opening frame beam in an aircraft cockpit, the corner piece with the cloud-shaped spring extends downwards, and a quick-release hole is formed in the extending part of the corner piece with the cloud-shaped spring. The interior trim panel assembly is installed between the control board groove-shaped piece and the opening frame beam, the bottom of the interior trim panel assembly is connected with the installation strip in an inserted mode through a clamping piece structure, and the top of the interior trim panel assembly is detachably and fixedly connected with the corner piece with the cloud-shaped spring through a quick-release nail. The installation tolerance in a cabin can be compensated by utilizing an inserting method, the elasticity of the interior trim panel assembly and the like, and meanwhile, the requirements of reliable connection and quick disassembly and assembly of the interior trim panel of a small aircraft can be met.

Description

Technical Field

[0001] This invention belongs to the field of aircraft cockpit interior structure design technology, and relates to an interior panel for a small aircraft cockpit, specifically to an interior panel for a small aircraft cockpit and its fixing method. Background Technology

[0002] Interior trim panels are used to decorate the interior of aircraft cockpits. In addition to providing a beautifying cabin environment by covering and covering, the smooth and soft surface of the cabin interior trim can also reduce the risk of injury caused by personnel touching the sharp corners, protrusions, sharp edges, etc. on the structural frame, clamps, screws and nuts during operation, thus providing a certain degree of protection.

[0003] Interior panels on small aircraft can be made of single or multiple materials such as metal, plastic, fiberglass, carbon fiber, and leather, and are connected to the structure by screws or clips.

[0004] Screw connections are generally used in interior trim panels that are primarily made of metal or composite materials. The clamping force of the screws and nuts secures the trim panels. The advantages of screw connections are simplicity, intuitiveness, stability, reliability, and low cost. The disadvantages are time-consuming installation and removal, and the vulnerability of the lock nuts to damage with frequent disassembly and reassembly. Clip connections are generally used in interior trim panels that are primarily made of plastic. The elastic deformation of localized structures within the clips secures the trim panels. The advantages of clip connections are aesthetic appeal and quick installation. However, because the clip points are not visible after installation and the clips themselves are relatively fragile, the disadvantages are difficulty in disassembly and susceptibility to damage with frequent disassembly and reassembly.

[0005] Meanwhile, because small aircraft are produced in small batches and have complex assembly relationships, there are some structures in the cockpit with low positioning accuracy, such as the control panel bracket. Screw connections and snap-fit ​​connections cannot provide sufficient tolerance to match the tolerance of the cockpit environment, resulting in unsatisfactory installation results of the two connection methods on the aircraft. Summary of the Invention

[0006] To address the aforementioned problems, this invention provides a small aircraft cockpit interior panel and its fixing method, which combines plug-in and quick-release connections to fix the small aircraft cockpit interior panel and compensate for installation tolerances within the cockpit.

[0007] The technical solution of the present invention is as follows: A small aircraft cockpit interior panel includes an interior panel assembly, a mounting strip, and a corner piece with a cloud-shaped spring. The mounting strip is fixedly installed on the edge of a control panel groove in the aircraft cockpit, extending upward to form an insert. The corner piece with the cloud-shaped spring is fixedly installed on the edge of a frame beam in the aircraft cockpit, extending downward, and the extended portion of the corner piece with the cloud-shaped spring has a quick-release hole. The interior panel assembly is installed between the control panel groove and the frame beam, wherein the bottom of the interior panel assembly is inserted into the mounting strip via a clip structure, and the top of the interior panel assembly is detachably fixedly connected to the corner piece with the cloud-shaped spring via a quick-release pin.

[0008] Furthermore, the interior panel assembly includes an interior panel, a connector piece, and connecting screws. The upper end of the connector piece is connected to the interior panel via the connecting screws, and the lower end of the connector piece forms a clamping structure with the interior panel.

[0009] Furthermore, the interior trim panel is thickened at the location where the connecting screws are installed to form a boss, and the insert piece has a bending structure that matches the shape of the boss; when the top of the mounting strip is inserted into the clip structure, the top of the mounting strip presses the insert piece tightly against the bottom of the boss of the interior trim panel, further reinforcing the mutual position fixation of the insert piece and the interior trim panel.

[0010] Furthermore, the lower half of the connector is elastic.

[0011] Furthermore, the corner piece with cloud-shaped spring includes a corner piece and a cloud-shaped spring. The corner piece is fixed to the back edge of the frame beam, and a quick-release hole is provided on the corner piece. A cloud-shaped spring is provided on the back of the corner piece corresponding to the quick-release hole.

[0012] Furthermore, the interior panel assembly includes an interior panel and a quick-release pin. The quick-release pin is rotatably positioned laterally on the upper edge of the interior panel. The small end of the quick-release pin has a spiral groove. After the spiral groove of the quick-release pin is inserted into a cloud-shaped spring, it rotates at a preset angle. The cloud-shaped spring will form a limiting structure to restrict the forward and backward movement of the quick-release pin.

[0013] Furthermore, it also includes a rubber gasket, which is fitted over the quick-release pin and is located on the back of the interior trim panel; the small end of the quick-release pin has a boss structure, the outer diameter of which is larger than the rubber gasket and the quick-release pin hole on the interior trim panel.

[0014] A method for fixing a small aircraft cockpit interior panel, using the aforementioned small aircraft cockpit interior panel, includes the following steps: S1, Rivet the corner piece with cloud-shaped spring to the frame beam according to the positioning dimensions, and rivet the mounting strip to the control panel groove according to the positioning dimensions; S2, the interior panel assembly is clamped and fixed to the control panel slot and mounting strip by a plug-in connection on the side of the aircraft control panel near the control panel; S3. Connect the interior panel assembly to the corner piece with cloud-shaped spring on the frame beam using a quick-release connection on the side closest to the frame beam, and then rotate the quick-release pin to complete the fixing of the interior panel assembly.

[0015] The advantages of this invention are as follows: This invention utilizes the plug-in method and the elasticity of the interior panel assembly to compensate for installation tolerances in the cockpit, while also meeting the requirements for reliable connection and quick assembly / disassembly of interior panels in small aircraft. Attached Figure Description

[0016] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. The drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0017] Figure 1 This is a diagram showing the connection.

[0018] Figure 2 This is a diagram of a quick-release connection.

[0019] Figure 3 This is a schematic diagram of the front mounting of the present invention.

[0020] Figure 4 This is a schematic diagram of the reverse side installation of the present invention.

[0021] Among them, 1—interior panel assembly, 1-1—interior panel, 1-2—plug-in piece, 1-3—connecting screw, 1-4—quick-release screw, 1-5—rubber gasket and other structures, 2—mounting strip, 3—control panel groove piece, 4—control panel connecting corner piece, 5—frame beam, 6—corner piece with cloud-shaped spring, 6-1—corner piece, 6-2—cloud-shaped spring. Detailed Implementation

[0022] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0023] The features and illustrative embodiments of various aspects of the present invention will now be described in detail. Numerous specific details are set forth in the following detailed description to provide a thorough understanding of the invention. However, it will be apparent to those skilled in the art that the invention may be practiced without requiring some of these specific details. The following description of embodiments is merely intended to provide a better understanding of the invention by illustrating examples of the invention. The invention is by no means limited to any specific setups and methods set forth below, but covers any improvements, substitutions, and modifications to structures, methods, and devices without departing from the spirit of the invention. Well-known structures and techniques are not shown in the drawings and the following description to avoid unnecessarily obscuring the invention.

[0024] In the description of this invention, it should be noted that the directions or positional relationships indicated by terms such as "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer" are based on the directions or positional relationships shown in the accompanying drawings and are only for the convenience of describing and simplifying the invention, and should not be construed as limiting the invention. Furthermore, the use of ordinal numbers (e.g., "first and second," etc.) is for distinguishing objects and is not limited to this order, and should not be construed as indicating or implying relative importance.

[0025] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly, encompassing both direct connection and indirect connection via an intermediate medium. Those skilled in the art can understand the specific meaning of these terms in this invention based on the specific circumstances.

[0026] It should be noted that, unless otherwise specified, the embodiments of the present invention and the features thereof can be combined with each other, and the various embodiments can be referenced and cited in each other. The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0027] Example 1: A small aircraft cockpit interior panel includes an interior panel assembly 1, a mounting strip 2, and a corner piece 6 with a cloud-shaped spring. The mounting strip 2 is fixedly installed on the edge of a control panel groove 3 inside the aircraft cockpit, and the mounting strip 2 extends upward to form an insert. The corner piece 6 with a cloud-shaped spring is fixedly installed on the edge of a frame beam 5 inside the aircraft cockpit, and the corner piece 6 with a cloud-shaped spring extends downward. The extended part of the corner piece 6 with a cloud-shaped spring is provided with a quick-release hole. The interior panel assembly 1 is installed between the control panel groove 3 and the frame beam 5. The bottom of the interior panel assembly 1 is inserted into the mounting strip 2 through a clip structure, and the top of the interior panel assembly 1 is detachably fixedly connected to the corner piece 6 with a cloud-shaped spring through quick-release pins 1-4.

[0028] The interior panel assembly 1 includes an interior panel 1-1, a connector 1-2, and a connecting screw 1-3. The upper end of the connector 1-2 is connected to the interior panel 1-1 by the connecting screw 1-3, and the lower end of the connector 1-2 forms a clamping structure with the interior panel 1-1.

[0029] The interior panel 1-1 is thickened to form a boss at the location of the mounting screws 1-3. The insert piece 1-2 has a bending structure that matches the shape of the boss. When the top of the mounting strip 2 is inserted into the clamping structure, the top of the mounting strip 2 presses the insert piece 1-2 against the bottom of the boss of the interior panel 1-1, further reinforcing the mutual position fixation of the insert piece 1-2 and the interior panel 1-1.

[0030] The lower half of the connector 1-2 is elastic.

[0031] The corner piece 6 with cloud-shaped spring includes a corner piece 6-1 and a cloud-shaped spring 6-2. The corner piece 6-1 is fixed to the back edge of the frame beam 5. The quick-release hole is set on the corner piece 6-1. The cloud-shaped spring 6-2 is provided on the back of the corner piece 6-1 corresponding to the quick-release hole.

[0032] The interior panel assembly 1 includes an interior panel 1-1 and quick-release pins 1-4. The quick-release pins 1-4 are rotatably and laterally positioned on the upper edge of the interior panel 1-1. The small end of the quick-release pins 1-4 is provided with a spiral groove. After the spiral groove of the quick-release pins 1-4 is inserted into the cloud-shaped spring 6-2, it rotates by a preset angle. The cloud-shaped spring 6-2 will form a limiting structure to restrict the forward and backward movement of the quick-release pins 1-4.

[0033] It also includes a rubber gasket 1-5, which is fitted over the quick-release pin 1-4 and is located on the back of the interior panel 1-1; the small end of the quick-release pin 1-4 is provided with a boss structure, and the outer diameter of the boss structure at the small end of the quick-release pin 1-4 is larger than the quick-release pin hole on the rubber gasket 1-5 and the interior panel 1-1.

[0034] A method for fixing a small aircraft cockpit interior panel, using the aforementioned small aircraft cockpit interior panel, includes the following steps: S1, Rivet the corner piece with cloud-shaped spring to the frame beam according to the positioning dimensions, and rivet the mounting strip to the control panel groove according to the positioning dimensions; S2, the interior panel assembly is clamped and fixed to the control panel slot and mounting strip by a plug-in connection on the side of the aircraft control panel near the control panel; S3. Connect the interior panel assembly to the corner piece with cloud-shaped spring on the frame beam using a quick-release connection on the side closest to the frame beam. Then rotate the quick-release pin to complete the fixing of the interior panel assembly. Example 2: The technical solution adopted by this invention to solve its technical problem is as follows: one side of the interior trim panel adopts a plug-in connection, using elastic plug-in tabs to clamp and fix the mounting strip on the aircraft; the other side of the interior trim panel adopts a quick-release pin connection, locking and fixing it to the bracket on the aircraft. The combination of plug-in and quick-release connections achieves the fixation of the fighter jet's interior trim panel.

[0035] Structural description: Interior panel assembly 1 includes interior panel 1-1, insert piece 1-2, connecting screw 1-3, quick-release pin 1-4, rubber gasket 1-5, etc.

[0036] The insert pieces 1-2 are made of elastic materials such as plastic or spring steel, and are located on the side of the interior panel assembly near the control panel. There are multiple pieces arranged at certain intervals, and they are fixed to the interior panel assembly 1 by connecting screws 1-3 and limiting blocks on the interior panel 1-1.

[0037] The quick-release studs 1-4 have countersunk heads that can be embedded in countersunk holes on the interior trim panel 1-1. A circular rubber pad 1-5 is located at the neck of the quick-release stud shank to prevent it from detaching from the interior trim panel 1-1 after unlocking, and also to provide vibration damping. The tail of the quick-release stud 1-4 has a spiral groove; after rotating 90°, it can hook onto the cloud-shaped spring 6-2 for fixation. The quick-release studs 1-4 are located on the side of the interior trim panel assembly near the frame beam, and are arranged at regular intervals.

[0038] The corner piece 6 with the cloud-shaped spring is composed of corner piece 6-1, cloud-shaped spring 6-2, and washer, etc., riveted together.

[0039] Preliminary steps: Rivet the corner piece 6 with cloud-shaped spring to the frame beam according to the positioning dimensions, and rivet the mounting strip 2 to the control panel groove 3 according to the positioning dimensions.

[0040] like Figure 1 As shown, the interior trim panel 1-1 near the control panel uses a plug-in connection. The gap between the plug-in piece 1-2 and the interior trim panel 1-1 is just enough to accommodate the insertion of the mounting strip 2. The elastic force of the plug-in piece 1-2 acts on the mounting strip 2 to achieve clamping and fixation.

[0041] like Figure 2 As shown, the side of the interior panel 1-1 near the frame beam adopts a quick-release connection. The spiral groove at the end of the quick-release nail 1-4 is fixed by hooking the cloud-shaped spring 6-2 after rotating 90°.

[0042] Example: See Figure 3 , Figure 4 .

[0043] Three plug-in pieces 1-2 are arranged at the lower end of the interior panel 1-1 to plug into the mounting strip 2 on the control panel, and three quick-release pins 1-4 with parallel axes are arranged at the upper end to quickly connect with the corner piece 6 with cloud-shaped spring on the frame beam 5.

[0044] Installation steps: After inserting the side of the interior panel 1-1 closest to the control panel into the mounting strip 2, align the quick-release pins 1-4 arranged on the side of the interior panel 1-1 closest to the frame beam, and then tighten them to complete the installation.

[0045] Disassembly steps: Perform in reverse order of the installation steps.

[0046] The above detailed embodiments are a description of the present invention. It should not be considered that the specific embodiments of the present invention are limited to these descriptions. For those skilled in the art, several simple deductions and substitutions can be made without departing from the concept of the present invention, and all of these should be considered to fall within the protection scope of the present invention.

Claims

1. A small aircraft cockpit interior panel, characterized in that, The device includes an interior panel assembly (1), a mounting strip (2), and a corner piece (6) with a cloud-shaped spring. The mounting strip (2) is fixedly installed on the edge of the control panel slot (3) inside the aircraft cockpit. The mounting strip (2) extends upward to form an insert. The corner piece (6) with a cloud-shaped spring is fixedly installed on the edge of the frame beam (5) inside the aircraft cockpit. The corner piece (6) with a cloud-shaped spring extends downward. The extended part of the corner piece (6) with a cloud-shaped spring is provided with a quick-release hole. The interior panel assembly (1) is installed between the control panel slot (3) and the frame beam (5). The bottom of the interior panel assembly (1) is inserted into the mounting strip (2) through a clip structure. The top of the interior panel assembly (1) is detachably fixed to the corner piece (6) with a cloud-shaped spring through quick-release pins (1-4).

2. The interior panel for a small aircraft cockpit according to claim 1, characterized in that, The interior panel assembly (1) includes an interior panel (1-1), a plug-in piece (1-2), and a connecting screw (1-3). The upper end of the plug-in piece (1-2) is connected to the interior panel (1-1) by the connecting screw (1-3), and the lower end of the plug-in piece (1-2) forms a clamping structure with the interior panel (1-1).

3. The interior panel for a small aircraft cockpit according to claim 2, characterized in that, The interior panel (1-1) is thickened to form a boss at the location of the mounting screw (1-3), and the plug-in piece (1-2) has a bending structure that matches the shape of the boss. When the top of the mounting strip (2) is inserted into the clip structure, the top of the mounting strip (2) presses the plug-in piece (1-2) against the boss of the interior panel (1-1), further reinforcing the mutual position fixation of the plug-in piece (1-2) and the interior panel (1-1).

4. The interior panel for a small aircraft cockpit according to claim 3, characterized in that, The lower half of the connector (1-2) is elastic.

5. The interior panel for a small aircraft cockpit according to claim 1, characterized in that, The corner piece (6) with cloud-shaped spring includes a corner piece (6-1) and a cloud-shaped spring (6-2). The corner piece (6-1) is fixed on the back edge of the frame beam (5). The quick-release hole is set on the corner piece (6-1). The corner piece (6-1) is provided with a cloud-shaped spring (6-2) on the back side corresponding to the quick-release hole.

6. The interior panel for a small aircraft cockpit according to claim 5, characterized in that, The interior panel assembly (1) includes an interior panel (1-1) and a quick-release pin (1-4). The quick-release pin (1-4) is rotatably and laterally positioned on the upper edge of the interior panel (1-1). The small end of the quick-release pin (1-4) is provided with a spiral groove. After the spiral groove of the quick-release pin (1-4) is inserted into the cloud-shaped spring (6-2), it rotates by a preset angle. The cloud-shaped spring (6-2) will form a limiting structure to restrict the forward and backward movement of the quick-release pin (1-4).

7. The interior panel for a small aircraft cockpit according to claim 6, characterized in that, It also includes a rubber gasket (1-5), which is fitted over the quick-release pin (1-4) and is located on the back of the interior panel (1-1); the small end of the quick-release pin (1-4) is provided with a boss structure, and the outer diameter of the boss structure at the small end of the quick-release pin (1-4) is larger than the quick-release pin hole on the rubber gasket (1-5) and the interior panel (1-1).

8. A method for fixing a small aircraft cockpit interior panel, using a small aircraft cockpit interior panel as described in claim 1, characterized in that, Includes the following steps: S1, Rivet the corner piece with cloud-shaped spring to the frame beam according to the positioning dimensions, and rivet the mounting strip to the control panel groove according to the positioning dimensions; S2, the interior panel assembly is clamped and fixed to the control panel slot and mounting strip by a plug-in connection on the side of the aircraft control panel near the control panel; S3. Connect the interior panel assembly to the corner piece with cloud-shaped spring on the frame beam using a quick-release connection on the side closest to the frame beam, and then rotate the quick-release pin to complete the fixing of the interior panel assembly.

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