An aircraft engine mount

Abstract

The utility model belongs to the technical field of aero-engine auxiliary components, and concretely is a kind of aircraft engine support, including cross bar;The both sides of cross bar are respectively fixedly connected with cabin wall mounting pad, and the both sides of the lower part of cross bar are fixedly connected with vertical pole in inclined shape, the surface of each vertical pole is respectively fixedly connected with coolant cooler mounting bracket, and one end of each vertical pole is respectively fixedly connected with support rod, and the other end between the opposite side of each support rod is fixedly connected with placing rod, the lower part of support rod is provided with reinforcing assembly, and the reinforcing assembly includes two V-shaped support rods. Through the collaborative design of cross bar, vertical pole, support rod and reinforcing assembly, a stable bearing structure mixed with multiple triangles and truss is constructed. The structure can effectively disperse and bear the weight of engine and complex load during operation, significantly improve the overall rigidity and structural stability of support, thereby improving flight safety.

Description

Technical Field

[0001] This utility model belongs to the technical field of aircraft engine auxiliary components, specifically an aircraft engine bracket. Background Technology

[0002] Aircraft engine mounts are key load-bearing and integrated components in aircraft power systems. They are used not only to support and fix the engine, but also often serve as a mounting platform for various auxiliary equipment such as coolers, shock absorbers, and actuators.

[0003] Current engine mount structures are relatively simple, with concentrated load-bearing points. When subjected to the enormous weight of the engine and the multidimensional impacts and vibrations under complex flight conditions, their overall rigidity and stability are insufficient. This may lead to structural fatigue, affecting the operational reliability of the auxiliary equipment mounted on it, and thus posing a potential threat to flight safety. Therefore, there is an urgent need for an aircraft engine mount that is structurally robust, highly integrated, and has excellent vibration resistance. Utility Model Content

[0004] In order to overcome the shortcomings of the existing technology and solve the technical problems of insufficient overall rigidity and stability mentioned in the background technology, this utility model proposes an aircraft engine bracket.

[0005] The technical solution adopted by this utility model to solve its technical problem is as follows: The aircraft engine bracket of this utility model includes a crossbar; bulkhead mounting pads are fixedly connected to both sides of the crossbar, and vertical bars are fixedly connected to both sides of the lower part of the crossbar in an inclined shape. Coolant cooler mounting brackets are fixedly connected to the surface of each vertical bar, a support rod is fixedly connected to one end of each vertical bar, and a placement rod is fixedly connected to the other end between opposite sides of each support rod. A reinforcement component is provided at the lower part of the support rod.

[0006] Preferably, the reinforcement component includes two V-shaped support rods, and each of the bent portions of the V-shaped support rods is fixedly connected to a mounting base.

[0007] Preferably, each of the mounting bases has a connecting rod fixedly connected to its upper part, each connecting rod is fixedly connected to the lower part of the support rod, a reinforcing rod is fixedly connected to the upper side of each mounting base that is close to each other, the upper part of each reinforcing rod has the same transverse reinforcing rib fixedly connected to it, and the two sides of the transverse reinforcing rib are fixedly connected to the support rod.

[0008] Preferably, a common combined rod is fixedly connected to one end of each of the two support rods, shock absorber mounting brackets are fixedly connected to both sides of the upper part of each combined rod, and an actuator mounting seat is fixedly connected to the other side of the lower part of the combined rod. One end of each of the V-shaped support rods is fixedly connected to the lower part of the combined rod, and a front shock absorber mounting seat is fixedly connected to the connection between the combined rod and the V-shaped support rod.

[0009] Preferably, a locking accessory is fixedly connected to one side of one end of the combined rod, a cabin heat exchanger mounting bracket is fixedly connected to one end of the crossbar, and a fan mounting bracket is fixedly connected to one side of one end of the crossbar.

[0010] Preferably, a positioning seat is fixedly connected to the other end of the V-shaped support rod, and a reinforcing rod is fixedly connected to the upper part of one end of the positioning seat, and the reinforcing rod is fixedly connected to the support rod.

[0011] The beneficial effects of this utility model are: 1. This utility model provides an aircraft engine bracket that, through the coordinated design of horizontal bars, vertical bars, support bars, and reinforcement components, constructs a stable load-bearing structure that combines multiple triangles and trusses. This structure effectively distributes and bears the weight of the engine and the complex loads during operation, significantly improving the overall rigidity and structural stability of the bracket, thereby enhancing flight safety.

[0012] 2. This utility model provides an aircraft engine bracket that highly integrates multiple functional interfaces such as coolant cooler mounting bracket, shock absorber mounting bracket, actuator mounting seat, cabin heat exchanger mounting bracket, and fan mounting bracket onto a single bracket body. This optimizes the layout of engine peripheral components, simplifies the assembly process, improves maintenance efficiency, and effectively utilizes space. Attached Figure Description

[0013] The accompanying drawings, which are included to provide a further understanding of the present invention and form part of this application, illustrate exemplary embodiments of the present invention and, together with the description thereof, serve to explain the present invention and do not constitute an undue limitation thereof. In the drawings: Figure 1 This is a three-dimensional view of the entire utility model.

[0014] Legend: 1. Horizontal bar; 2. Bulkhead mounting pad; 3. Vertical bar; 4. Coolant cooler mounting bracket; 5. Support rod; 6. Placement rod; 7. V-shaped support rod; 8. Mounting seat; 9. Connecting rod; 10. Reinforcing rod; 11. Transverse reinforcing rib; 12. Combination rod; 13. Shock absorber mounting bracket; 14. Actuator mounting seat; 15. Front shock absorber mounting seat; 16. Locking accessories; 17. Cabin heat exchanger mounting bracket; 18. Fan mounting bracket; 19. Positioning seat; 20. Reinforcing bar. Detailed Implementation

[0015] 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.

[0016] Specific implementation examples are given below.

[0017] Please see Figure 1 This utility model provides an aircraft engine bracket, including a crossbar 1 as the main supporting beam; during operation, the crossbar 1 is firmly connected to the aircraft body through the bulkhead mounting pads 2 on both sides, becoming the primary fixing point of the entire bracket device.

[0018] Furthermore, such as Figure 1 As shown, two vertical bars 3 extend obliquely from the lower part of the horizontal bar 1. A coolant cooler mounting bracket 4 is mounted on each vertical bar 3. Support bars 5 are connected to the ends of the vertical bars 3, and the two support bars 5 are connected by a placement rod 6. During operation, the oblique vertical bars 3 form a stable triangular support, effectively distributing the load borne by the horizontal bar 1. The support bars 5 and the placement rod 6 together form a bottom frame, providing a foundation for installing other components and enhancing the overall structural integrity.

[0019] Furthermore, such as Figure 1 As shown, the lower part of the support rod 5 is equipped with a reinforcing assembly consisting of two V-shaped support rods 7, and the curved part of the V-shaped support rod 7 is provided with a mounting seat 8. During operation, the V-shaped support rods 7, like two strong legs, support the entire bracket structure from below, effectively dispersing and absorbing the vertical pressure and longitudinal forces from the engine.

[0020] Furthermore, such as Figure 1 As shown, the mounting base 8 is fixed to the support rod 5 via the connecting rod 9, and the two mounting bases 8 are connected as a whole by the reinforcing rod 10 and the transverse reinforcing rib 11. During operation, the connecting rod 9 ensures the force transmission between the reinforcement component and the main frame; while the reinforcing rod 10 and the transverse reinforcing rib 11 form a robust transverse truss, which greatly suppresses the deformation and vibration that may occur in the support rod 5 under stress, and ensures the rigidity of the middle part of the bracket.

[0021] Furthermore, such as Figure 1As shown, the front ends of the two support rods 5 are connected by a combination rod 12. The combination rod 12 is equipped with a shock absorber mounting bracket 13 and an actuator mounting seat 14. The front end of the V-shaped support rod 7 is also fixed to the lower part of the combination rod 12, and a front shock absorber mounting seat 15 is provided at the connection point. During operation, the combination rod 12, as the core connecting component at the front of the bracket, gathers the forces of the support rods 5 and V-shaped support rods 7, and provides a direct and stable mounting point for the engine's front shock absorber and related actuators, resulting in better shock absorption and more precise control.

[0022] Furthermore, such as Figure 1 As shown, the combination rod 12 is equipped with a locking attachment 16, and one end of the crossbar 1 is fitted with a cabin heat exchanger mounting bracket 17 and a fan mounting bracket 18. During operation, the locking attachment 16 can be used to secure the engine or connect other system pipelines; the cabin heat exchanger mounting bracket 17 and the fan mounting bracket 18 allow these components to be installed close together, forming an efficient synergy with the engine system and simplifying the cabin layout.

[0023] Furthermore, such as Figure 1 As shown, a positioning seat 19 is connected to the rear end of the V-shaped support rod 7, and the positioning seat 19 is fixed to the support rod 5 by a reinforcing rod 20. During operation, the positioning seat 19 provides an additional positioning and fixing point for the V-shaped support rod 7, while the reinforcing rod 20 further locks the geometric relationship between the V-shaped support rod 7 and the main frame, preventing it from loosening under long-term vibration and ensuring the reliability of the entire reinforcement assembly in long-term operation.

[0024] Working principle: In operation, this utility model first securely mounts the main body of the support onto the aircraft fuselage via the bulkhead mounting pads 2 on both sides of the crossbar 1. The engine is then connected to the support via components such as the front shock absorber mounting bracket 13, the front shock absorber mounting seat 15, and the locking accessory 16. The weight of the engine and the vibration load generated during operation are transmitted and dissipated mainly through three paths: first, through the support rod 5 and the combined rod 12 to the reinforcement assembly composed of the V-shaped support rod 7; second, through the inclined vertical rod 3 to the crossbar 1; and third, through the connecting structures on each mounting seat. The truss-type reinforcement system, composed of the V-shaped support rod 7, the reinforcing rod 10, and the transverse reinforcing ribs 11, can effectively resist forces and moments in all directions and prevent structural deformation. At the same time, auxiliary equipment such as the cooler, heat exchanger, and fan integrated on the support are installed nearby via specialized mounting brackets (such as 4, 17, 18) to work in conjunction with the engine, forming a compact, functionally integrated, and stable and reliable engine support mechanism.

[0025] The foregoing has shown and described the basic principles, main features, and advantages of this utility model. Those skilled in the art should understand that this utility model is not limited to the above embodiments. The embodiments and descriptions in the specification are merely illustrative of the principles of this utility model. Various changes and modifications can be made to this utility model without departing from its spirit and scope, and all such changes and modifications fall within the scope of the claimed utility model.

Claims

1. An aircraft engine support, comprising a crossbar (1); characterized in that: The two sides of the crossbar (1) are respectively fixedly connected to the bulkhead mounting pads (2), and the two sides of the lower part of the crossbar (1) are fixedly connected to the vertical bars (3) in an inclined shape. The surfaces of each vertical bar (3) are respectively fixedly connected to the coolant cooler mounting brackets (4). One end of each vertical bar (3) is respectively fixedly connected to the support rod (5), and the other end between the opposite sides of each support rod (5) is fixedly connected to the placement rod (6). The lower part of the support rod (5) is provided with a reinforcement component.

2. The aircraft engine bracket according to claim 1, characterized in that: The reinforcement assembly includes two V-shaped support rods (7), and each of the bent portions of the V-shaped support rods (7) is fixedly connected to a mounting base (8).

3. The aircraft engine bracket according to claim 2, characterized in that: Each of the mounting bases (8) has a connecting rod (9) fixedly connected to its upper part. Each of the connecting rods (9) is fixedly connected to the lower part of the support rod (5). Each of the mounting bases (8) has a reinforcing rod (10) fixedly connected to one side of its upper part that is close to the other. Each of the reinforcing rods (10) has the same transverse reinforcing rib (11) fixedly connected to its upper part. Both sides of the transverse reinforcing rib (11) are fixedly connected to the support rod (5).

4. The aircraft engine bracket according to claim 3, characterized in that: The same combined rod (12) is fixedly connected to one end of the two support rods (5). Shock absorber mounting brackets (13) are fixedly connected to both sides of the upper part of each combined rod (12). An actuator mounting seat (14) is fixedly connected to the other side of the lower part of the combined rod (12). One end of each V-shaped support rod (7) is fixedly connected to the lower part of the combined rod (12). A front shock absorber mounting seat (15) is fixedly connected at the connection between the combined rod (12) and the V-shaped support rod (7).

5. The aircraft engine bracket according to claim 4, characterized in that: A locking accessory (16) is fixedly connected to one side of one end of the combined rod (12), a cabin heat exchanger mounting bracket (17) is fixedly connected to the other end of the crossbar (1), and a fan mounting bracket (18) is fixedly connected to one side of one end of the crossbar (1).

6. The aircraft engine bracket according to claim 5, characterized in that: The other end of the V-shaped support rod (7) is fixedly connected to a positioning seat (19), and a reinforcing rod (20) is fixedly connected to the upper part of one end of the positioning seat (19). The reinforcing rod (20) is fixedly connected to the support rod (5).

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