An aircraft buffer with multiple layers of oil holes

Abstract

The present invention relates to the technical field of aircraft parts, and provides an aircraft buffer with multiple layers of oil holes, including a support outer tube and a support inner tube nested up and down, a damping rod is fixedly arranged in the support outer tube, the upper end of the damping rod is fixedly connected to the upper end of the support outer tube, and the lower end of the damping rod is in the support inner tube; an upper damping oil hole plug is fixedly arranged at the upper end of the support inner tube to slide in the support outer tube, and a lower damping oil hole plug is fixedly arranged at the lower end of the damping rod to slide in the support inner tube, and the upper damping oil hole plug and the lower damping oil hole plug divide the interior of the buffer into an upper cavity, a middle cavity and a lower cavity, and oil is arranged in the upper cavity, the middle cavity and the lower cavity. The beneficial effect of the present invention is that the interior of the buffer is divided into an upper cavity, a middle cavity and a lower cavity by arranging an upper damping oil hole plug and a lower damping oil hole plug, and when the aircraft lands, the space of the upper cavity and the lower cavity is compressed, and the fluid inside thereof flows to the middle cavity through the upper and lower unidirectional oil holes, generating damping forces at the upper and lower locations, greatly dissipating the impact energy.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft parts, in particular to an aircraft buffer with multiple layers of oil holes. Background Art

[0002] As a crucial component of the aircraft structure, the landing gear not only carries the entire weight of the aircraft, but also must withstand additional loads in various flight conditions, especially during takeoff and landing. Its performance and reliability are directly related to flight safety. The landing gear buffer system is designed to absorb the huge impact energy at the moment the aircraft touches the ground, reduce the impact on the fuselage structure, and ensure that the aircraft can land and take off smoothly and safely. Therefore, how to design and manufacture a high-efficiency, high-performance and high-comfort buffer system has become a core issue in the field of aeronautical engineering.

[0003] At present, the landing gear buffer system of most modern aircraft adopts an oil-gas design, which uses the combined effect of gas compression and oil flow to absorb and disperse energy. Depending on the specific application requirements, oil-gas buffers have a variety of structural forms, each of which has its specific advantages and application scenarios. However, although the oil-gas buffer system has been widely used, it still faces some challenges and problems to be solved. At the moment of aircraft landing, the landing gear will be subjected to great impact energy, which requires the buffer to absorb this energy quickly and smoothly. However, in actual situations, the damping force in the buffer often increases sharply due to the drastic change in energy, which not only puts higher requirements on the structural strength of the buffer, but may also cause passengers inside the aircraft to feel obvious turbulence, affecting ride comfort.

[0004] In addition, during the operation of the buffer system, a large amount of heat will be generated due to the friction between internal components and the rapid compression and release of the oil. The accumulation of this heat will not only affect the viscosity and fluidity of the oil, thereby reducing the buffer efficiency, but may also cause thermal stress damage to the surrounding structural materials and shorten their service life.

[0005] Therefore, actual use requires that the design and manufacture of the landing gear buffer system must not only ensure high efficiency and high performance, but also take into account the ability to adapt to various working conditions, effective thermal management measures and improved passenger comfort. These are key technical issues that need to be urgently resolved in the current and future development of aviation technology. Summary of the invention

[0006] The present invention provides an aircraft buffer with multiple layers of oil holes, comprising a support outer tube and a support inner tube nested up and down, wherein a damping rod is fixedly arranged in the support outer tube, the upper end of the damping rod is fixedly connected to the upper end of the support outer tube, and the lower end of the damping rod is in the support inner tube;

[0007] An upper damping oil hole plug is fixedly arranged at the upper end of the support inner tube and slides in the support outer tube. A lower damping oil hole plug is fixedly arranged at the lower end of the damping rod and slides in the support inner tube. The upper damping oil hole plug and the lower damping oil hole plug divide the interior of the buffer into an upper chamber, a middle chamber and a lower chamber. Oil is arranged in the upper chamber, the middle chamber and the lower chamber.

[0008] Furthermore, a thermoelectric conversion device is arranged outside the outer tube of the support to absorb the heat energy generated during the conversion and buffering process.

[0009] Furthermore, the oil is a magnetorheological fluid, and the thermoelectric conversion device is provided with an electromagnetic coil, so that the viscosity of the magnetorheological fluid increases as more heat energy is generated during the buffering process.

[0010] Furthermore, two buffer support ear holes are symmetrically arranged on the top of the support outer tube.

[0011] Furthermore, a tire axle hole is provided at the bottom end of the inner tube of the support.

[0012] As a preferred solution, the thermoelectric conversion device is provided with permanent magnet sheets to enhance magnetic properties.

[0013] Furthermore, one-way valves are arranged in the oil holes of the upper damping oil hole plug and the lower damping oil hole plug, and both the upper damping oil hole plug and the lower damping oil hole plug are provided with an upward one-way valve and a downward one-way valve.

[0014] As a preferred solution, the number of oil holes in the upper damping oil hole plug and the lower damping oil hole plug are both 8 to 10, and half of the one-way valves in the oil holes are directed upward and the other half are directed downward.

[0015] The beneficial effects of the present invention are:

[0016] 1. The present invention divides the interior of the buffer into an upper chamber, a middle chamber and a lower chamber by arranging an upper damping oil hole plug and a lower damping oil hole plug. When the aircraft lands, the outer cylinder and the inner cylinder of the buffer move relative to each other, and the damping rod moves downward with the outer cylinder, compressing the space between the upper chamber and the lower chamber. The fluid inside flows to the middle chamber through the upper and lower unidirectional oil holes, generating damping forces at the upper and lower locations, greatly dissipating the impact energy.

[0017] 2. The present invention sets a thermoelectric conversion device on the outside of the buffer, and sets the oil in the cavity to magnetorheological fluid, collects the heat generated when the aircraft lands, and converts the thermal energy into electrical energy, which is further converted into the magnetic force of the magnet through the winding coil, thereby increasing the viscosity of the magnetorheological fluid and adaptively improving the buffering performance of the buffer. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to make the content of the present invention more clearly understood, the present invention is further described in detail below based on specific embodiments and in conjunction with the accompanying drawings, wherein:

[0019] Figure 1 It is a structural schematic diagram of the present invention.

[0020] Figure 2 It is a schematic diagram of the internal structure of the present invention.

[0021] Figure 3 It is a schematic structural diagram of the damping oil hole plug of the present invention.

[0022] The reference numerals in the accompanying drawings are:

[0023] 1. Buffer support ear hole; 2. Thermoelectric conversion device; 3. Support outer tube; 4. Support inner tube; 5. Tire axle hole; 6. Damping rod; 7. Upper damping oil hole plug; 8. Lower damping oil hole plug; 9. Upper cavity; 10. Middle cavity; 11. Lower cavity. DETAILED DESCRIPTION

[0024] To illustrate the features of the present invention, the present invention is further described below in conjunction with the accompanying drawings and embodiments.

[0025] Example:

[0026] See also Figures 1 to 3 This embodiment provides an aircraft buffer with multiple layers of oil holes, including a support outer tube 3 and a support inner tube 4 nested up and down, two buffer support ear holes 1 are symmetrically arranged at the top of the support outer tube 3, and a tire shaft hole 5 is arranged at the bottom of the support inner tube 4. The landing gear is connected to the aircraft body through the buffer support ear holes 1 to support the weight of the aircraft; and is connected to the tire through the tire shaft hole 5 to establish a contact relationship with the ground. When the aircraft lands, the tire touches the ground, and the landing gear bears the impact energy transmitted through the tire shaft hole 5 on the one hand, and bears the weight of the aircraft on the other hand, so that the support outer tube 3 and the support outer tube 4 of the aircraft buffer system move relative to each other, quickly absorb the impact energy, and achieve safe landing of the aircraft.

[0027] In this embodiment, a damping rod 6 is fixedly arranged in the pillar outer tube 3, the upper end of the damping rod 6 is fixedly connected to the upper end of the pillar outer tube 3, and the lower end of the damping rod 6 is in the pillar inner tube 4; an upper damping oil hole plug 7 is fixedly arranged at the upper end of the pillar inner tube 4 to slide in the pillar outer tube 3, and a lower damping oil hole plug 8 is fixedly arranged at the lower end of the damping rod 6 to slide in the pillar inner tube 4. The upper damping oil hole plug 7 and the lower damping oil hole plug 8 divide the interior of the buffer into an upper chamber 9, a middle chamber 10 and a lower chamber 11, and oil is arranged in the upper chamber 9, the middle chamber 10 and the lower chamber 11. Check valves are arranged in the oil holes of the upper damping oil hole plug 7 and the lower damping oil hole plug 8, and the upper damping oil hole plug 7 and the lower damping oil hole plug 8 are both provided with four check valves in the upward direction and four check valves in the downward direction.

[0028] When the buffer system is working, the damping rod 6 moves downward with the support outer tube 3, the upper chamber 9 is compressed, and the oil in the upper chamber 9 is ejected from the oil hole into the middle chamber 10, generating oil damping force, accompanied by the generation of heat. Similarly, the support inner tube 4 moves upward, the lower chamber 11 is also compressed, and the oil in the lower chamber 11 is ejected into the middle chamber 10, generating oil resistance. The oil damping forces at the upper and lower locations can be generated simultaneously or successively, depending on the preset pressure value of the oil hole one-way valve. The oil damping forces generated at the upper and lower locations jointly dissipate the impact energy and play a buffering effect. The oil damping forces generated at the upper and lower locations are in opposite directions, which suppresses the amplitude of the internal force of the buffer and reduces its own vibration.

[0029] In this embodiment, the oil is a magnetorheological fluid, and the thermoelectric conversion device 2 includes a p-type thermoelectric conversion element and an n-type thermoelectric conversion element. By setting an electromagnetic coil, the viscosity of the magnetorheological fluid increases as more heat energy is generated during the buffering process. The thermoelectric conversion device 2 is set on the outside of the support outer tube 3 to absorb the heat energy generated during the conversion buffering process, and a permanent magnet sheet is set in the thermoelectric conversion device 2 to enhance the magnetism.

[0030] The heat generated is converted into electrical energy through the thermoelectric conversion device 2, and further converted into the magnetic force of the magnet through the winding coil, thereby improving the viscosity of the fluid in the cavity and adaptively improving the buffering performance of the buffer system.

[0031] Similarly, when the outer cylinder of the buffer moves upward and the inner cylinder moves downward, the volume of the upper chamber 9 and the lower chamber 11 increases, and the pressure in the chamber decreases. The damping rod 6 moves upward with the outer cylinder, and the volume of the middle chamber 10 decreases. The fluid inside it flows to the upper chamber 9 and the lower chamber 11 through the upper and lower one-way oil holes, generating damping forces at the upper and lower locations to dissipate the impact energy. This process repeats until the impact energy is exhausted and the buffer stops working.

[0032] The above embodiments and drawings are only used to illustrate the technical solutions of the present invention, and are not intended to limit the present invention. The present invention is described in detail with reference to the preferred embodiments. It should be understood by those skilled in the art that any changes, modifications, additions or substitutions made by those skilled in the art within the essential scope of the present invention do not deviate from the purpose of the present invention and should also fall within the scope of protection of the claims of the present invention. Other related technical structures not fully disclosed in the present invention are prior art in the art.

Claims

1. An aircraft buffer with multiple layers of oil holes, comprising a support outer cylinder (3) and a support inner cylinder (4) nested in an upper and lower manner, characterized in that: A damping rod (6) is fixedly arranged inside the pillar outer tube (3), the upper end of the damping rod (6) is fixedly connected to the upper end of the pillar outer tube (3), and the lower end of the damping rod (6) is inside the pillar inner tube (4); An upper damping oil hole plug (7) is fixedly provided at the upper end of the pillar inner tube (4) and slides in the pillar outer tube (3); a lower damping oil hole plug (8) is fixedly provided at the lower end of the damping rod (6) and slides in the pillar inner tube (4); the upper damping oil hole plug (7) and the lower damping oil hole plug (8) divide the interior of the buffer into an upper chamber (9), a middle chamber (10) and a lower chamber (11); Oil is provided in the upper chamber (9), the middle chamber (10) and the lower chamber (11); a thermoelectric conversion device (2) is provided outside the support outer tube (3) to absorb heat energy generated during the conversion buffering process; the oil is a magnetorheological fluid; the thermoelectric conversion device (2) is provided with an electromagnetic coil to convert heat energy into electric energy through the thermoelectric conversion device; and the thermoelectric conversion device (2) is provided with a permanent magnet sheet to enhance magnetism; One-way valves are arranged in the oil holes of the upper damping oil hole plug (7) and the lower damping oil hole plug (8), and both the upper damping oil hole plug (7) and the lower damping oil hole plug (8) are provided with an upward one-way valve and a downward one-way valve; the magnetorheological fluid is further converted into magnetic force of the magnet after being further converted into magnetic force of the magnet through the electromagnetic coil, so that the more heat energy is generated in the buffering process, the greater the viscosity of the magnetorheological fluid.

2. The aircraft buffer with multiple layers of oil holes according to claim 1, characterized in that: Two buffer support ear holes (1) are symmetrically arranged at the top end of the support outer tube (3).

3. The aircraft buffer with multiple layers of oil holes according to claim 1, characterized in that: A tire axle hole (5) is provided at the bottom end of the support inner tube (4).

4. The aircraft buffer with multiple layers of oil holes according to claim 1, characterized in that: The number of oil holes of the upper damping oil hole plug (7) and the lower damping oil hole plug (8) are both 8 to 10, and half of the one-way valves in the oil holes are oriented upwards and the other half are oriented downwards.

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