A pad for easy instrument panel mounting

Abstract

This utility model discloses a mounting plate for easy instrument panel installation, used for in-situ, non-destructive installation of 3.15-inch display size aircraft instruments on aircraft instrument panels. The mounting plate body has a double-layer composite structure, with a lower layer being an aviation-grade aluminum alloy main base and an upper layer being a high-damping carbon fiber inner ring. The main base forms an embedded covering structure with the inner ring, and the thickness of the inner ring is higher than the outer frame of the main base, ensuring that the instrument display surface is flush with the panel. The main base is equipped with a heat dissipation structure (heat pipe or heat sink fins), and the inner ring is lined with a copper conductive strip that is conductive to the main base, achieving electromagnetic shielding in conjunction with grounding screws. This utility model solves the problems of poor vibration reduction, insufficient heat dissipation, and weak electromagnetic shielding in existing installation methods. It also utilizes existing mounting holes in situ, is low in cost, highly versatile, and meets the airworthiness requirements for aircraft retrofitting.

Description

Technical Field

[0001] This utility model belongs to the technical field of aircraft instrument installation auxiliary devices, specifically relating to a pad that facilitates the installation of instrument panels. Background Technology

[0002] Early general aviation aircraft were equipped with a large number of separate aviation instruments (such as spare airspeed indicators, altimeters, electric horizon indicators, etc.), most of which had a 3.15-inch display size. With the iteration of technology, the original instruments could not be repaired due to issues such as manufacturers ceasing technical support and component discontinuation. This resulted in aircraft being grounded due to a lack of spare equipment, necessitating the replacement of the original instruments with new ones.

[0003] From the perspective of aircraft modification and airworthiness certification, the installation of new instruments must meet the following core requirements:

[0004] (1) Vibration reduction and energy absorption and structural strength requirements: It is necessary to absorb the high-frequency vibration during the flight of the aircraft, avoid the vibration of the instrument and surrounding instruments, and not damage the instrument panel or cause permanent deformation under the load coefficient in all directions.

[0005] (2) Heat dissipation requirements: The instrument installation area is dense, and concentrated heat waves are easily generated during operation. In addition, the high external temperature in summer can easily cause the area temperature to rise. Good heat dissipation is required to avoid the new instrument triggering overheat protection.

[0006] (3) Electromagnetic shielding requirements: It must meet the requirements of lightning protection safety, prevent electromagnetic interference between instruments, and not reduce the electromagnetic compatibility of the avionics system.

[0007] The current conventional installation method is to "insert the new instrument from the back of the instrument panel into the front and fix it from the front with three screws." This method has obvious drawbacks:

[0008] (1) Poor energy absorption and vibration reduction effect may cause high-frequency vibration during flight, resulting in vibration of the instrument itself and its surrounding instruments, affecting the operation and display stability of the aircraft instruments;

[0009] (2) The weight of the new instrument increases and the structural strength of the existing instrument panel cannot meet the airworthiness requirements. Under the load coefficients required by regulations in all directions, the installation will cause damage or permanent deformation to the aircraft instrument panel.

[0010] (3) The instrument is directly attached to the instrument panel. When the instrument panel is directly exposed to sunlight, it will affect the heat dissipation function of the instrument.

[0011] (4) The existing instrument panel is old and the insulation layer is damaged. If the entire panel is replaced directly, the cost is high and the workload is large. At the same time, it cannot meet the electromagnetic shielding requirements of the new instrument. Summary of the Invention

[0012] This invention addresses the shortcomings of existing conventional installation methods, such as poor vibration reduction, insufficient heat dissipation, weak electromagnetic shielding, and high cost. It provides a pad that facilitates instrument panel installation, enabling in-situ, non-destructive installation of 3.15-inch display size aviation instruments on aircraft instrument panels. This also meets the airworthiness requirements for vibration reduction, energy absorption, heat dissipation, and electromagnetic shielding, and is versatile.

[0013] To achieve the above objectives, this utility model provides a pad for easy installation of instrument panels, comprising a pad body, wherein the pad body is a double-layer composite structure, the lower layer being a main base layer made of aviation aluminum alloy, and the upper layer being an inner ring structure made of high-damping carbon fiber material; the main base layer forms an embedded covering structure for the inner ring structure, and the thickness of the inner ring structure is higher than the outer frame thickness of the main base layer, so that the display surface of the aviation instrument is flush with the aircraft instrument panel after installation; the inner ring structure has three mounting holes for fixing the aviation instrument, and the main base layer has four mounting holes for fixing the pad body to the aircraft instrument panel, and the mounting holes are adapted to the original instrument mounting hole size, realizing in-situ non-destructive installation.

[0014] Furthermore, the pad body is also provided with a heat dissipation structure, which is a heat pipe embedded in the main base layer or a heat dissipation fin set on the four non-installation sides of the main base layer; the main base layer is made of high thermal conductivity aerospace aluminum alloy, and the heat generated by the aviation instrument is conducted to the surrounding air through the heat pipe or heat dissipation fin.

[0015] Furthermore, the pad body is also provided with an electromagnetic shielding structure, which includes a copper conductive strip laid inside the inner ring structure. The copper conductive strip forms an electrical connection with the main base layer. The mounting holes of the main base layer are provided with conductive bushings, and the screws used to fix the pad body are self-locking nuts that meet the shear strength requirements. The screws are also connected to the grounding post and connected to the aircraft fuselage.

[0016] Furthermore, the inner ring structure has a thickness of 5mm, and the outer frame of the main base layer has a thickness of 2mm; the size of the mounting hole is adapted to the mounting hole size of the original instruments of different aircraft models, so that the pad can be used for the modification of aircraft instruments of various aircraft.

[0017] Compared with the prior art, the present invention has the following beneficial effects:

[0018] 1. Vibration reduction and structural strength: The high-damping carbon fiber inner ring undergoes elastic deformation during vibration, tightly wrapping the fixing screws and effectively absorbing high-frequency vibration; the aerospace aluminum alloy main base layer ensures structural strength, avoids panel damage, and meets airworthiness requirements.

[0019] 2. High efficiency in heat dissipation: Heat pipes or heat dissipation fins, combined with a high thermal conductivity base layer, quickly conduct heat and prevent instrument overheating protection.

[0020] 3. Reliable electromagnetic shielding: Copper conductive strips, conductive bushings, and grounding design effectively prevent electromagnetic interference and lightning risks, ensuring the compatibility of avionics systems.

[0021] 4. Low cost and versatility: It utilizes the original mounting holes in situ without damage, eliminating the need to replace the entire panel and reducing costs; the mounting hole size is adjustable, making it suitable for instrument retrofitting of different aircraft models.

[0022] 5. Easy installation: The two-stage fixing method of "instrument-pad-panel" simplifies the installation process and improves replacement efficiency. Attached Figure Description

[0023] To more clearly illustrate the technical solution of this utility model, the drawings used in the description of the specific embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0024] Figure 1 This is a schematic diagram of the structure of the pad in an embodiment of this utility model;

[0025] Figure 2 This is a cross-sectional view of the pad AA position in an embodiment of this utility model;

[0026] Figure 3 This is a schematic diagram of a conventional installation in an embodiment of this utility model;

[0027] Figure 4 This is a schematic diagram of the installation of the pad in an embodiment of this utility model. Detailed Implementation

[0028] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those skilled in the art without creative effort are within the protection scope of the present utility model.

[0029] This utility model provides a pad for easy installation of instrument panels, including a pad body. The pad body has a double-layer composite structure, with a lower main base layer 1 made of aviation aluminum alloy and an upper inner ring structure 2 made of high-damping carbon fiber material. The main base layer 1 forms an embedded covering structure for the inner ring structure 2, and the thickness of the inner ring structure 2 is higher than the outer frame thickness of the main base layer 1, so that the display surface of the aviation instrument is flush with the aircraft instrument panel after installation. The inner ring structure 2 has three mounting holes 3 for fixing the aviation instrument, and the main base layer 1 has four mounting holes 4 for fixing the pad body to the aircraft instrument panel. The mounting holes are adapted to the original instrument mounting hole size, realizing in-situ non-destructive installation.

[0030] Furthermore, the pad body is also provided with a heat dissipation structure, which is a heat pipe embedded in the main base layer 1, or heat dissipation fins set on the four non-installation sides of the main base layer 1; the main base layer 1 is made of high thermal conductivity aviation aluminum alloy, and the heat generated by the aviation instrument is conducted to the surrounding air through the heat pipe or heat dissipation fins.

[0031] Furthermore, the pad body is also provided with an electromagnetic shielding structure, which includes a copper conductive strip laid inside the inner ring structure 2. The copper conductive strip forms an electrical connection with the main base layer 1. The mounting holes of the main base layer are provided with conductive bushings, and the screws used to fix the pad body are self-locking nuts that meet the shear strength requirements. The screws are also connected to the grounding post and connected to the aircraft fuselage.

[0032] Furthermore, the inner ring structure has a thickness of 5mm, and the outer frame of the main base layer has a thickness of 2mm; the size of the mounting holes is adapted to the mounting hole sizes of original instruments on different aircraft models, making the pad suitable for retrofitting and upgrading aircraft instruments on various aircraft.

[0033] The following will provide a detailed explanation in conjunction with the accompanying drawings:

[0034] as follows Figure 3 The diagram shown illustrates the conventional installation of the new instrument. The instrument is inserted from the rear of the instrument panel to the front, and secured with three screws from the front to the rear. The main problems with conventional installation are:

[0035] (1) The energy absorption and vibration reduction effect is not good. High-frequency vibration may be generated during flight, causing the instrument itself and its surrounding instruments to shake, affecting the operation and display stability of the aircraft instruments.

[0036] (2) The weight of the new instrument increases and the structural strength of the existing instrument panel cannot meet the airworthiness requirements. Under the load coefficients required by regulations in all directions, the installation will cause damage or permanent deformation to the aircraft instrument panel.

[0037] (3) The instrument is directly attached to the instrument panel. When the instrument panel is directly exposed to sunlight, it will affect the heat dissipation function of the instrument.

[0038] (4) Since the new instrument is an electromagnetically sensitive element, it has high requirements for electromagnetic shielding. The existing instrument panel is old and the insulation layer is damaged, resulting in a decline in insulation performance. Replacing the entire instrument panel directly will incur high costs and a large workload.

[0039] To meet the installation requirements of new instruments, auxiliary mounting plates are added as follows: Figure 4 As shown, the new instrument is fixed to the mounting plate with three screws, and the mounting plate is fixed to the instrument panel with four screws, thus completing the non-destructive, in-situ installation of the new instrument on the instrument panel. This mounting plate has strong versatility and can be used for retrofitting aircraft instruments on different aircraft models. The dimensions of the mounting plate can be flexibly adjusted according to the original instrument's mounting hole size, instrument fixing method, and structural thickness.

[0040] Specifically, the shape of the pad is as follows: Figure 1 As shown, the inner ring thickness is 5mm, the outer frame thickness is 2mm, and the main material is aerospace-grade aluminum alloy, possessing the following characteristics:

[0041] (1) A double-layer composite structure is adopted. To meet the requirements of energy absorption and vibration reduction, the pad adopts a double-layer composite structure. The lower main base layer adopts a rigid layer (aluminum alloy) to ensure that the mounting surface is flat and has sufficient rigidity. The inner ring and the lower main base layer form a height difference. The inner ring is fixed to the inner ring surface with 3 screws. The lower main base layer is fixed to the pad and the new instrument as a whole with 4 screws. The thickness of the inner ring is higher than that of the lower outer ring, forming a thickness difference between them. The auxiliary device and the new instrument panel are fixed to the instrument panel in a non-destructive, in-situ manner using the original instrument mounting position and hole diameter, and it can ensure that the display surface of the new instrument is flush with the instrument panel after installation. The inner ring is made of high-damping carbon fiber material. The lower main base layer forms an embedded covering structure for the inner ring. When subjected to longitudinal, vertical or transverse vibration, the damping material will undergo elastic deformation and tightly wrap the fixing screws, playing a role in energy absorption and vibration reduction. The aluminum alloy and carbon fiber materials are sufficient to ensure the structural strength.

[0042] (2) Heat dissipation structure design. The pad body is made of high thermal conductivity material (aluminum alloy) and has heat pipes embedded inside or heat dissipation fins designed on the four sides (non-mounting surfaces). The pad becomes a heat dissipation base, which quickly conducts the heat generated by the instrument to the surrounding air.

[0043] (3) Electromagnetic shielding design. A composite copper conductive strip is laid inside the inner high-damping carbon fiber structure, and good electrical conductivity is formed with the aluminum alloy lower main base. The grounding post is connected to the aircraft fuselage by the mounting screw. Electromagnetic leakage is considered when designing the mounting hole. The mounting screw is a self-locking nut with good conductivity and shear strength, and the bottom contact is made by the conductive bushing.

[0044] In the description of this specification, references to terms such as "an embodiment," "example," "specific example," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0045] The preferred embodiments of this utility model disclosed above are merely illustrative of the present utility model. These preferred embodiments do not exhaustively describe all details, nor do they limit the utility model to the specific implementations described. Clearly, many modifications and variations can be made based on the content of this specification. This specification selects and specifically describes these embodiments to better explain the principles and practical applications of this utility model, thereby enabling those skilled in the art to better understand and utilize it. This utility model is limited only by the claims and their full scope and equivalents.

Claims

1. A pad for easy installation of instrument panels, characterized in that, The device includes a pad body, which is a double-layer composite structure. The lower layer is a main base layer (1) made of aviation aluminum alloy, and the upper layer is an inner ring structure (2). The inner ring structure (2) is made of high-damping carbon fiber material. The main base layer (1) forms an embedded covering structure for the inner ring structure (2), and the thickness of the inner ring structure (2) is higher than the outer frame thickness of the main base layer (1), so that the display surface of the aviation instrument is flush with the aircraft instrument panel after installation. The inner ring structure is provided with 3 mounting holes (3) for fixing the aviation instrument, and the main base layer is provided with 4 mounting holes (4) for fixing the pad body to the aircraft instrument panel. The mounting holes are adapted to the original instrument mounting hole size to achieve in-situ non-destructive installation.

2. The pad according to claim 1, characterized in that, The pad body is also provided with a heat dissipation structure, which is a heat pipe embedded in the main base (1) or heat dissipation fins set on the four non-installation sides of the main base (1); the main base is made of high thermal conductivity aviation aluminum alloy, and the heat generated by the aviation instrument is conducted to the surrounding air through the heat pipe or heat dissipation fins.

3. The pad according to claim 1, characterized in that, The pad body is also provided with an electromagnetic shielding structure, which includes a copper conductive strip laid inside the inner ring structure (2). The copper conductive strip forms an electrical connection with the main base layer. The mounting hole (4) of the main base layer is provided with a conductive bushing, and the screws used to fix the pad body are self-locking nuts that meet the shear strength requirements. The screws are also connected to the grounding post and connected to the aircraft fuselage.

4. The pad according to claim 1, characterized in that, The inner ring structure has a thickness of 5mm, and the outer frame of the main base layer has a thickness of 2mm; the size of the mounting hole is adapted to the mounting hole size of the original instruments of different aircraft models, so that the pad can be used for the modification of aircraft instruments of various aircraft.

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