Large-swing-angle lubricating oil tank posture stabilizing structure

Abstract

The invention discloses a large-swing-angle lubricating oil tank posture stabilizing structure, and relates to the technical field of aero-engines, the large-swing-angle lubricating oil tank posture stabilizing structure comprises a mounting junction surface, a stable gyroscope assembly and a sleeve shock absorber assembly, the mounting junction surface is arranged at the front end of a lubricating oil tank, and a mounting support is arranged on the outer wall of the lubricating oil tank; the sleeve shock absorber assembly and the aviation aluminum alloy rigid clamping jaw are arranged on the side face of the lubricating oil tank on the basis of 120-degree circumferential uniform distribution, the connecting end of the sleeve shock absorber assembly is in rigid connection with the stable gyroscope assembly, and a load transmission chain of the mounting support, the aviation aluminum alloy rigid clamping jaw, the sleeve shock absorber assembly and the stable gyroscope assembly is formed. According to the device, the mounting bracket and a stable gyroscope assembly attitude constraint pair in the mounting junction surface are matched with the structural design of the sleeve shock absorber assembly, so that the lubricating oil tank is kept in a vertical state, and the lubricating oil storage and supply stability of an aero-engine lubricating system under the working condition of a large swing angle of an aircraft is guaranteed.

Description

Technical Field

[0001] This invention relates to the field of aero-engine technology, specifically to a large yaw angle lubricating oil tank attitude stabilization structure. Background Technology

[0002] The lubricating oil tank of an aircraft engine. Commonly known as the oil reservoir, it is one of the core components of the entire engine lubrication system. A typical aircraft engine oil reservoir typically includes the following parts: Tank body: usually made of high-strength, lightweight aluminum alloy or stainless steel, capable of withstanding engine vibration, pressure changes, and temperature variations. Filler neck and cap: equipped with locking devices and filters to prevent foreign objects from entering. The cap usually has a dipstick or sight glass for checking the oil level. Oil supply and return lines: Supply (pressure oil) line: located at the bottom of the tank, it delivers lubricating oil to the oil pump, which then pumps it to various parts of the engine requiring lubrication and cooling. Return (recovery) line: hot oil from lubricating engine components is returned to the oil reservoir via the return pump. Internal baffles and anti-vortex devices: Baffles / valve: Used to reduce the violent sloshing of lubricating oil during aircraft maneuvers (such as rolls and climbs), ensuring that the oil supply port is always covered with lubricating oil. Anti-vortex devices: Installed at the inlet of the oil supply line to prevent air from being drawn in during oil suction, avoiding "air lock" in the oil pump. Ventilation / breathing pipe connects the top of the oil tank to the engine venting line. Used to balance the pressure inside and outside the oil tank and expel the hot gases (containing air, water vapor, and oil mist) generated during oil operation. These gases are usually directed to the engine's oil-gas separator for treatment.

[0003] However, existing large-swing-angle lubricating oil tank attitude stabilization structures have the following problems during use: traditional methods cannot solve the problem of maintaining the attitude of the lubricating oil tank under large swing angles when the aircraft is flying at large angles, while also meeting the vibration reduction requirements of complex vibration environments. Summary of the Invention

[0004] The purpose of this invention is to provide a stabilizing structure for a lubricating oil tank with a large swing angle, so as to solve the related problems mentioned in the background art.

[0005] To solve the above-mentioned technical problems, the present invention provides the following technical solution: a large swing angle lubricating oil tank attitude stabilization structure, including a mounting mating surface, a stabilizing gyroscope assembly, and a sleeve shock absorber assembly. The lubricating oil tank has a mounting mating surface at its front end and a mounting bracket on its outer wall. The sleeve shock absorber assembly and aerospace aluminum alloy rigid claws are arranged on the side of the lubricating oil tank in a 120-degree circumferentially uniform layout. The connecting end of the sleeve shock absorber assembly is rigidly connected to the stabilizing gyroscope assembly, forming a load transmission chain of the mounting bracket, aerospace aluminum alloy rigid claws, sleeve shock absorber assembly, and stabilizing gyroscope assembly.

[0006] As a preferred embodiment of the large swing angle lubricating oil tank attitude stabilization structure of the present invention, the number of the sleeve shock absorber assembly and the aviation aluminum alloy rigid claw is set.

[0007] As a preferred embodiment of the large swing angle lubricating oil tank attitude stabilization structure of the present invention, the stabilizing gyroscope assembly consists of two sets of unidirectional gyroscopes.

[0008] As a preferred embodiment of the large swing angle lubricating oil tank attitude stabilization structure of the present invention, the sleeve shock absorber assembly is composed of a composite elastomer and a metal sandwich.

[0009] As a preferred embodiment of the large swing angle lubricating oil tank attitude stabilization structure of the present invention, the composite elastomer is made of composite rubber.

[0010] As a preferred embodiment of the large swing angle lubricating oil tank attitude stabilization structure of the present invention, the metal interlayer is composed of a stainless steel layer and an aluminum alloy layer, each with a thickness of 2mm.

[0011] The beneficial effects of the large swing angle lubricating oil tank attitude stabilization structure of the present invention are as follows: This invention addresses the issue that when an aircraft flies at a large angle, the oil tank experiences a large sway angle along with the aircraft. By using the attitude constraint pair of the stabilizing gyroscope component in the mounting bracket and mounting mating surface, along with the structural design of the sleeve shock absorber component, the oil tank is kept vertical. This ensures the stability of the oil storage and supply in the aircraft engine lubrication system under the condition of large sway angle, and improves the working accuracy and reliability of the stabilizing gyroscope component. Attached Figure Description

[0012] Figure 1 This is a three-dimensional structural diagram of the present invention; Figure 2 This is an enlarged structural schematic diagram of the present invention.

[0013] In the diagram: 1. Mounting mating surface; 2. Mounting bracket; 3. Stabilized gyroscope assembly; 4. Sleeve shock absorber assembly; 5. Aviation aluminum alloy rigid claw. Detailed Implementation

[0014] 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, and 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.

[0015] Example 1, such as Figure 1-2As shown, the present invention provides a technical solution: a large swing angle lubricating oil tank attitude stabilization structure, including a mounting mating surface 1, a stabilizing gyroscope assembly 3, and a sleeve shock absorber assembly 4. The mounting mating surface 1 is provided at the front end of the lubricating oil tank, and a mounting bracket 2 is provided on the outer wall of the lubricating oil tank. The sleeve shock absorber assembly 4 and aerospace aluminum alloy rigid claws 5 are arranged in a 120-degree circumferentially uniform layout on the side of the lubricating oil tank. The connecting end of the sleeve shock absorber assembly 4 is rigidly connected to the stabilizing gyroscope assembly 3, forming a load transmission chain of the mounting bracket 2, aerospace aluminum alloy rigid claws 5, sleeve shock absorber assembly 4, and stabilizing gyroscope assembly 3. The number of sleeve shock absorber assemblies 4 and aerospace aluminum alloy rigid claws 5 is 3 sets, and the stabilizing gyroscope assembly 3 consists of two sets of unidirectional gyroscopes. When the stabilized gyroscope assembly 3 is subjected to a small-amplitude shear deformation in the Z-axis lateral direction, the load will be evenly applied to the composite elastomer of the three sleeve damper assemblies 4. Due to the damping characteristics of the composite elastomer, the mechanical energy is converted into heat energy and dissipated. At the same time, the interlayer metal layer can limit the excessive deformation of the composite elastomer. Thus, the composite elastomer undergoes a small-amplitude shear deformation in the Z-axis lateral direction synchronously, realizing the buffering of the Z-axis lateral vibration. If subjected to axial stress in the X or Y axis, the force will be decomposed to the two sleeve damper assemblies 4 on both sides of the axis. The composite elastomer will be compressed or stretched along the axis, and the deformation will absorb the stress energy. At the same time, the 120-degree layout allows the remaining dampers to share the load, avoiding overload of a single sleeve damper assembly 4. This design meets the redundancy load design requirements of aerospace components.

[0016] Example 2, as Figure 1-2 As shown, the present invention provides a technical solution: a large swing angle lubricating oil tank attitude stabilization structure, including the sleeve shock absorber assembly 4 which is composed of a composite elastomer and a metal sandwich. The composite elastomer is made of composite rubber, and the metal sandwich is composed of stainless steel layer and aluminum alloy layer, each with a thickness of 2mm. Unlike ordinary rubber shock absorbers, this structure can independently adjust the lateral and axial stiffness of each shock absorber elastomer. For example, by adapting the rubber hardness and the metal sandwich thickness, the lateral stiffness of the Z-axis and the axial stiffness of the X / Y axes can avoid the vibration frequency of the engine in the corresponding direction, thereby achieving directional stiffness adaptation to avoid resonance risk.

[0017] Working principle: First, when the aircraft flies at a large angle, the oil tank will generate a large sway angle with the aircraft. Through the attitude constraint pair of the stabilizing gyroscope component 3 in the mounting bracket 2 and the mounting mating surface 1, and with the structural design of the sleeve shock absorber component 4, the oil tank is kept in a vertical state. Vibration stress buffering: The stable gyroscope component 3 is mainly subjected to the transverse forced vibration stress of the Z-axis and the axial stress of the X / Y axes. The 3-claw type sleeve shock absorber component 4 is adapted to multi-directional stress characteristics, avoiding the problem of "resonance caused by fixed stiffness" in ordinary rubber shock absorbers.

[0018] Finally, it should be noted that the above content is only used to illustrate the technical solution of the present invention, and is not intended to limit the scope of protection of the present invention. Simple modifications or equivalent substitutions made by those skilled in the art to the technical solution of the present invention do not depart from the essence and scope of the technical solution of the present invention.

Claims

1. A large swing angle oil tank posture stabilizing structure, comprising a mounting joint surface (1), a stabilizing gyroscope assembly (3) and a sleeve damper assembly (4), characterized in that: The front end of the lubricating oil tank is provided with a mounting joint surface (1), the outer wall of the lubricating oil tank is provided with a mounting support (2), the sleeve shock absorber assembly (4) and the aviation aluminum alloy rigid clamping jaw (5) are arranged on the side of the lubricating oil tank in a 120-degree circumferential uniform distribution mode, the connecting end of the sleeve shock absorber assembly (4) is rigidly connected with the stable gyroscope assembly (3), and the load transmission chain of the mounting support (2), the aviation aluminum alloy rigid clamping jaw (5), the sleeve shock absorber assembly (4) and the stable gyroscope assembly (3) is formed.

2. The attitude stabilizing structure for a large-swing-angle oil tank according to claim 1, characterized by: The number of the sleeve shock absorber assembly (4) and the aviation aluminum alloy rigid clamping jaw (5) is three groups.

3. The attitude stabilizing structure for a large-swing-angle oil tank according to claim 1, characterized by: The stable gyroscope assembly (3) is composed of two groups of one-way gyroscopes.

4. The attitude stabilizing structure for a large-swing-angle oil tank according to claim 1, characterized by: The sleeve shock absorber assembly (4) is composed of a composite elastomer and a metal interlayer.

5. The attitude stabilizing structure for a large-swing-angle oil tank according to claim 4, characterized by: The composite elastomer is made of composite rubber.

6. The attitude stabilizing structure for a large-swing-angle oil tank according to claim 4, characterized by: The metal interlayer is composed of a stainless steel layer and an aluminum alloy layer, and the thickness of each layer is 2 mm.

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