Lightweight aviation condenser housing

Abstract

The utility model discloses a kind of lightweight aviation condenser shell, belong to aviation condenser technical field, its technical scheme main points include main casing, the main casing is frame type structure, the front end and rear side of the main casing are respectively bolted with front cover and back cover, the main casing, front cover and back cover are enclosed and form the cavity for accommodating condenser core, by adopting the composite structure of surface layer, honeycomb structure reinforcing layer and edge strip, while reducing the amount of material, the overall torsional, impact resistance of mechanical properties of honeycomb structure is promoted, both meet the requirement of aviation environment to strength, realize shell lightweight, avoid the defect that traditional single material is thick then heavy, thin then weak, and the welding connection of surface layer and reinforcing layer, edge strip ensures that interlayer is combined closely, cooperate the reinforcing rib design of the four corners of main casing, further improve the overall rigidity of shell, reduce the deformation risk under vibration environment.

Description

Technical Field

[0001] This utility model relates to the field of aviation condenser technology, and in particular to a lightweight aviation condenser shell. Background Technology

[0002] Aircraft condensers are devices used in aircraft air conditioning systems to cool high-temperature gases. They convert gases into liquids and release heat through heat exchange. Aircraft condensers are key components of the refrigeration system, ensuring a suitable cabin air temperature by converting high-temperature gases or vapors into liquids and releasing heat.

[0003] Aircraft condensers are the core components of aviation air conditioning systems, responsible for condensing refrigerant vapor into liquid. Their outer shells serve as protective and support structures, directly affecting the condenser's working efficiency, equipment weight, and service life. However, existing aircraft condenser shells require increased wall thickness to meet the impact and torsional resistance requirements of aviation environments, resulting in increased weight, which does not conform to the "lightweight" development trend of aviation equipment. If a thin-walled design is adopted, deformation or cracking is likely to occur in vibration environments.

[0004] To address this, a lightweight aerospace condenser housing is proposed. Utility Model Content

[0005] The purpose of this utility model is to provide a lightweight aviation condenser shell, which can solve the problem that the existing aviation condenser shells need to increase the wall thickness to meet the impact and torsional resistance requirements in the aviation environment, resulting in increased weight, which does not conform to the trend of lightweight development of aviation equipment; if a thin-walled design is adopted, it is easy to deform or crack in the vibration environment.

[0006] To achieve the above objectives, the present invention provides the following technical solution: a lightweight aircraft condenser shell, including a main shell, the main shell being a frame structure, a front cover plate and a rear cover plate being bolted to the front and rear sides of the main shell respectively, the main shell, the front cover plate and the rear cover plate forming a cavity for accommodating the condenser core;

[0007] The main housing, front cover plate, and rear cover plate each include two covering layers, with a honeycomb structure reinforcement layer between the two covering layers, and an edge sealing strip around the perimeter between the two covering layers. The covering layers and the honeycomb structure reinforcement layer, as well as the covering layers and the edge sealing strip, are connected by welding.

[0008] Preferably, the covering layer is made of magnesium-aluminum alloy and has a ceramic heat-insulating coating sprayed on its surface.

[0009] Preferably, the honeycomb structure reinforcement layer is made of aluminum alloy and is distributed in a regular hexagonal array.

[0010] Preferably, two reinforcing ribs are welded at each of the four corners inside the main housing, and the reinforcing ribs are arranged circumferentially along the edge.

[0011] Preferably, the inner wall of the main housing is provided with a silicone cushioning pad, and the silicone cushioning pad has a rectangular frame structure, with an elastic metal skeleton embedded inside the silicone cushioning pad.

[0012] Preferably, the front cover has a ventilation plate embedded inside, and the ventilation plate has ventilation holes arranged in a ring array inside.

[0013] Preferably, a heat dissipation vent is provided in the middle of the rear cover plate, and a heat dissipation frame is bolted to the middle of the rear side of the rear cover plate. The heat dissipation frame is connected to the heat dissipation vent, and a louvered heat dissipation grille is provided between the heat dissipation frame and the heat dissipation vent.

[0014] Compared with the prior art, the beneficial effects of this utility model are:

[0015] This application employs a composite structure consisting of a surface layer, a honeycomb reinforcement layer, and edge sealing strips. This reduces material usage while enhancing overall torsional and impact resistance through the mechanical properties of the honeycomb structure. It meets the strength requirements of the aerospace environment while achieving lightweight shell, avoiding the shortcomings of traditional single-material construction where thicker materials are heavy and thinner materials are weaker. Furthermore, the welded connection between the surface layer, reinforcement layer, and edge sealing strips ensures a tight bond between the layers. Combined with the reinforcing ribs at the four corners of the main shell, this further enhances the overall rigidity of the shell and reduces the risk of deformation under vibration. Attached Figure Description

[0016] Figure 1 This is an overall structural diagram of the lightweight aviation condenser shell of this utility model;

[0017] Figure 2 This is a schematic diagram showing the connection between the front cover plate, the rear cover plate, and the main housing of this utility model;

[0018] Figure 3 This is a schematic diagram of the main housing of this utility model;

[0019] Figure 4 This is a schematic diagram of the structure of the silicone cushioning pad of this utility model.

[0020] In the diagram, 1. Main shell; 2. Front cover plate; 3. Rear cover plate; 4. Covering layer; 5. Honeycomb structure reinforcement layer; 6. Edge sealing strip; 7. Reinforcing rib; 8. Silicone cushioning pad; 9. Elastic metal frame; 10. Ventilation plate; 11. Ventilation hole; 12. Heat dissipation vent; 13. Heat dissipation frame; 14. Louvered heat dissipation grille. Detailed Implementation

[0021] 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 of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0022] Please see Figure 1-4 The present invention provides the following technical solution:

[0023] A lightweight aircraft condenser housing includes a main housing 1, which has a frame structure. A front cover plate 2 and a rear cover plate 3 are respectively bolted to the front and rear sides of the main housing 1. The main housing 1, the front cover plate 2 and the rear cover plate 3 enclose a cavity for accommodating the condenser core.

[0024] The main shell 1, the front cover plate 2 and the rear cover plate 3 each include two covering layers 4, a honeycomb structure reinforcing layer 5 is provided between the two covering layers 4, and an edge sealing strip 6 is provided around the two covering layers 4. The covering layers 4 and the honeycomb structure reinforcing layer 5, as well as the covering layers 4 and the edge sealing strip 6 are connected by welding.

[0025] In this embodiment: the main housing 1 is a frame structure, and the front cover plate 2 and the rear cover plate 3 are bolted to the front and rear sides of the main housing 1, respectively. The three together form a cavity to accommodate the condenser core. Each component of the outer shell is composed of two covering layers 4, with a honeycomb structure reinforcing layer 5 sandwiched in the middle. The perimeter is sealed by edge sealing strips 6. The covering layer 4, the reinforcing layer, and the edge sealing strips 6 are welded together to form an integral whole. During operation, the covering layer 4 bears external impact, the honeycomb structure reinforcing layer 5 disperses stress, and the edge sealing strips 6 prevent interlayer peeling, thus ensuring the stability of the outer shell structure. This composite layered structure, through the synergistic effect of the covering bearing and the honeycomb reinforcement, reduces weight while increasing overall strength, solving the problem of the difficulty in balancing the weight and strength of traditional outer shells. The welded connection ensures a firm interlayer bond, and the frame structure adapts to the installation requirements of the condenser core, enhancing the compatibility between the outer shell and the equipment.

[0026] Specifically, such as Figure 3 As shown, the outer layer 4 is made of magnesium-aluminum alloy and is coated with a ceramic heat-insulating coating.

[0027] Specifically, such as Figure 3 As shown, the honeycomb structure reinforcement layer 5 is made of aluminum alloy and is distributed in a regular hexagonal array.

[0028] In this embodiment: the outer layer 4 is made of magnesium-aluminum alloy, which reduces the overall weight of the outer shell due to its lightweight properties. The ceramic heat insulation coating sprayed on the surface forms a barrier to reduce the impact of high external environmental temperatures on the condenser core inside the cavity, while also preventing the heat generated by the condenser during operation from radiating outwards, thus avoiding excessively high outer shell temperatures that could affect surrounding components. The honeycomb structure reinforcement layer 5 is made of aluminum alloy, with hexagonal array honeycomb cells forming a uniform stress grid. When the outer shell is subjected to external impact or vibration, the honeycomb cells disperse stress through deformation, transforming concentrated loads into uniformly distributed forces, thus preventing local deformation or cracking. The aluminum alloy material ensures that the reinforcement layer itself has sufficient rigidity, working together with the outer layer 4 to bear the load.

[0029] Specifically, such as Figure 2 As shown, two reinforcing ribs 7 are welded at each of the four corners inside the main housing 1, and the reinforcing ribs 7 are arranged circumferentially along the edge.

[0030] Specifically, such as Figure 2 , Figure 4 As shown, the inner wall of the main housing 1 is provided with a silicone buffer pad 8, and the silicone buffer pad 8 has a rectangular frame structure. An elastic metal skeleton 9 is embedded inside the silicone buffer pad 8.

[0031] In this embodiment: the reinforcing ribs 7 welded to the four corners inside the main shell 1 are distributed circumferentially along the edge, forming local reinforcement of the four corners. When the shell is subjected to torsional force or corner collision, the reinforcing ribs 7 bear part of the stress, preventing the four corners from cracking due to stress concentration. The silicone buffer pad 8 on the inner side wall of the main shell 1 has a rectangular frame structure and fits the outer wall of the condenser core. When the aviation equipment vibrates, the silicone buffer pad 8 absorbs the vibration energy through its own elastic deformation, reducing the rigid collision between the core and the shell. The elastic metal skeleton 9 embedded inside limits the excessive deformation of the buffer pad, ensuring its support stability for the condenser core.

[0032] Specifically, such as Figure 2 As shown, a ventilation plate 10 is embedded inside the front cover 2, and ventilation holes 11 arranged in a ring array are opened inside the ventilation plate 10.

[0033] Specifically, such as Figure 2 As shown, a heat dissipation vent 12 is provided in the middle of the rear cover plate 3, and a heat dissipation frame 13 is bolted to the middle of the rear side of the rear cover plate 3. The heat dissipation frame 13 is connected to the heat dissipation vent 12, and a louvered heat dissipation grille 14 is provided between the heat dissipation frame 13 and the heat dissipation vent 12.

[0034] In this embodiment: the ventilation plate 10 embedded in the front cover plate 2 has a ring array of ventilation holes 11. The heat generated by the condenser during operation is exchanged with the outside air through the ventilation holes 11, forming convection heat dissipation. The ring array design ensures uniform ventilation and avoids local heat accumulation. At the same time, the ventilation plate 10 enhances the structural strength of the front cover plate 2 and prevents the rigidity from decreasing due to the opening. The heat dissipation port 12 of the rear cover plate 3 is connected to the heat dissipation frame 13. The louvered heat dissipation grille 14 is set between the two. When the condenser is working, the heat enters the heat dissipation frame 13 through the heat dissipation port 12. The grille blades open to dissipate the heat. When heat dissipation is not required, the grille blades close to prevent external dust and moisture from entering the cavity.

[0035] Working Principle: In the use of an aircraft condenser, the main casing 1 forms a basic support through a frame structure. The front cover plate 2 and the rear cover plate 3 are bolted to the front and rear sides of the main casing 1, respectively. The three together form a closed cavity, in which the condenser core is stably placed. The composite layered structure of the outer casing components then comes into play: the magnesium-aluminum alloy cladding layer 4 directly bears external impact and friction, and its surface ceramic heat-insulating coating blocks the exchange of external high temperature with internal heat. The middle aluminum alloy honeycomb structure reinforcing layer 5, through the hexagonal array of honeycomb units, evenly distributes the external load to the entire structure, avoiding localized stress. The force is concentrated, and the sealing strips 6 around the perimeter are welded to the outer layer 4 and the reinforcing layer to prevent interlayer peeling, together forming a lightweight and high-strength protective system. The reinforcing ribs 7 at the four corners inside the main shell 1 further strengthen the corners and edges to resist torsional forces and impacts, ensuring the shell maintains structural stability under the complex stresses of the aviation environment. When the condenser is working, the silicone buffer pads 8 on the inner wall of the main shell 1 are tightly attached to the outer wall of the core. When the aviation equipment vibrates, the silicone material absorbs vibration energy through elastic deformation, reducing rigid collisions between the core and the shell. The embedded elastic metal skeleton 9 restricts the buffering. Excessive deformation of the pad ensures stable support for the core, preventing loosening of interfaces or wear of components due to shaking. Simultaneously, the heat dissipation system activates: the ventilation plate 10 embedded in the front cover 2 guides external airflow into the cavity through a ring-shaped array of ventilation holes 11, exchanging heat with the core surface; the louvered heat dissipation grille 14 of the rear cover 3 opens, allowing hot air from the cavity to enter the heat dissipation frame 13 through the heat dissipation vent 12 and be discharged. The heat dissipation frame 13 protects the grille from external debris, while the ceramic heat insulation coating continues to function throughout the process, preventing excessively high surface temperatures from affecting surrounding equipment. When the condenser needs to be inspected, it can be quickly disassembled by loosening the bolt connection between the front cover plate 2 and the rear cover plate 3, exposing the core inside the cavity and simplifying the maintenance process. If the shell is subjected to extreme loads, the honeycomb structure reinforcement layer 5 buffers the stress through local deformation, and the welding connection between the cover layer 4 and the reinforcement layer ensures that the overall structure does not collapse. The corrosion resistance of the aluminum alloy material reduces the erosion of the shell by water vapor and oil, extending the service life of the equipment. Throughout the entire operation, the shell always maintains its lightweight characteristics, and through the coordinated design of structure and function, it balances the requirements of strength, heat dissipation and protection, adapting to the working environment of aviation condensers.

[0036] The above are merely preferred embodiments of the present utility model and are not intended to limit the present utility model. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present utility model should be included within the protection scope of the present utility model.

Claims

1. A lightweight aircraft condenser housing, comprising a main housing (1), characterized in that: The main housing (1) is a frame structure. The front end and the rear end of the main housing (1) are respectively bolted with a front cover plate (2) and a rear cover plate (3). The main housing (1), the front cover plate (2) and the rear cover plate (3) enclose a cavity for accommodating the condenser core. The main shell (1), the front cover plate (2) and the rear cover plate (3) each include two covering layers (4), a honeycomb structure reinforcing layer (5) is provided between the two covering layers (4), and an edge sealing strip (6) is provided around the two covering layers (4). The covering layers (4) and the honeycomb structure reinforcing layer (5) and the covering layers (4) and the edge sealing strip (6) are connected by welding.

2. The lightweight aircraft condenser housing according to claim 1, characterized in that: The covering layer (4) is made of magnesium-aluminum alloy and has a ceramic heat insulation coating sprayed on its surface.

3. The lightweight aircraft condenser housing according to claim 1, characterized in that: The honeycomb structure reinforcement layer (5) is made of aluminum alloy and is distributed in a regular hexagonal array.

4. A lightweight aircraft condenser housing according to claim 1, characterized in that: Two reinforcing ribs (7) are welded at each of the four corners inside the main shell (1), and the reinforcing ribs (7) are arranged circumferentially along the edge.

5. A lightweight aircraft condenser housing according to claim 1, characterized in that: The inner wall of the main housing (1) is provided with a silicone buffer pad (8), and the silicone buffer pad (8) has a rectangular frame structure. An elastic metal skeleton (9) is embedded inside the silicone buffer pad (8).

6. A lightweight aircraft condenser housing according to claim 1, characterized in that: The front cover (2) has a ventilation plate (10) embedded inside, and the ventilation plate (10) has ventilation holes (11) arranged in a ring array inside.

7. A lightweight aircraft condenser housing according to claim 1, characterized in that: The rear cover plate (3) has a heat dissipation vent (12) in the middle, and a heat dissipation frame (13) is bolted to the middle of the rear side of the rear cover plate (3). The heat dissipation frame (13) is connected to the heat dissipation vent (12), and a louvered heat dissipation grille (14) is provided between the heat dissipation frame (13) and the heat dissipation vent (12).

Images