Aircraft landing gear self-powered monitoring device based on vibration energy collection

Abstract

The invention discloses an aircraft landing gear self-powered monitoring device based on vibration energy collection. The aircraft landing gear self-powered monitoring device comprises a sleeve and a sliding shaft which are installed in an aircraft landing gear. A lower end cover is arranged at the lower end of the sleeve and is connected with the sleeve through a screw; the inner wall of the sleeve is in support connection with the sliding shaft through small friction balls arranged in the circumferential direction; the sliding shaft and the upper end cover are fixed through a mortise and tenon joint structure, and the upper end cover and the sleeve are supported through a spring. Key shafts are inserted into key holes in the centers of the lower end cover and the sliding shaft; a power generation assembly and a sensing assembly are arranged in the sleeve, the power generation assembly comprises a friction power generation part and an electromagnetic power generation part, a groove in the sliding shaft is provided with a moving part of the power generation assembly, and the inner side of the sleeve is provided with a fixed part of the power generation assembly. The power generation assembly is driven to generate power to supply power to sensors around the undercarriage, and meanwhile the sensing assembly monitors vibration signals. According to the invention, the vibration energy of the aircraft during vibration falling can be effectively captured, and the vibration falling state can be monitored.

Description

Technical Field

[0001] The present invention belongs to a self-powered monitoring structure, and particularly relates to an aircraft landing gear self-powered monitoring device based on vibration energy harvesting. Background Art

[0002] With the continuous development of the world economy, the transportation industry has become increasingly mature. In the field of the aircraft industry with high timeliness, aircraft have moved from the original investment and construction stage to the operation and maintenance stage. Therefore, it is very important to detect the safety performance of transportation tools.

[0003] When an aircraft lands, a large amount of mechanical vibration energy is generated by the airframe in a short period of time. This energy can be collected as a power source to supply power to various sensors, or used as a monitoring signal for vibration. When an aircraft lands, the landing gear has to withstand a great deal of pressure in both the vertical and horizontal directions. For medium-sized airliners, the vertical overload of the landing gear reaches 2-3 during landing, which poses very high requirements for the performance of the landing gear. Due to the compactness of the assembly itself, it is difficult to directly inspect the landing gear of an aircraft from the outside. However, disassembling it and placing it on a testing platform for inspection will take a lot of time and cause waste of resources. Although the safety level of aircraft is relatively high, there are still deficiencies in the detection of some important components.

[0004] According to the search, there are currently aircraft landing gear detection and monitoring technologies available. For example, the "Aircraft Landing Gear Performance Detection Device" disclosed in Chinese Patent Application No. 202411260823.8 uses the cooperation of a hovering structure, an axial loading structure, and a vertical loading structure to detect its vertical load-bearing capacity, comprehensively evaluate its impact, lateral load, and torsional moment, and conduct repeated tests using the action of the vertical loading structure. Although this design can achieve a good detection effect on the landing gear, it cannot be installed on the aircraft to detect its real-time state during landing. It only detects the inherent properties of the landing gear. Summary of the Invention

[0005] To solve the problems existing in the above-mentioned prior art, the present invention provides an aircraft landing gear self-powered monitoring device based on vibration energy harvesting.

[0006] An aircraft landing gear self-powered monitoring device based on vibration energy harvesting of the present invention includes a sleeve and a sliding shaft installed inside the aircraft landing gear; a lower end cover is provided at the lower end of the sleeve, and the lower end cover is connected to the sleeve by screws; the inner wall of the sleeve and the sliding shaft are supported and connected by friction balls arranged circumferentially; the sliding shaft and the upper end cover are fixed by a mortise and tenon structure, and the upper end cover and the sleeve are supported by a spring; a key shaft is inserted into the key hole at the center of the lower end cover and the sliding shaft.

[0007] A power generation component and a sensing component are arranged inside the sleeve. The power generation component includes a triboelectric power generation part and an electromagnetic power generation part. The moving part of the power generation component is installed in the groove on the sliding shaft, and the fixed part of the power generation component is installed on the inner side of the sleeve. Through the linear vibration of the sliding shaft along the axial direction, the power generation component is driven to generate electricity to supply power to the sensors around the aircraft landing gear. At the same time, the sensing component monitors the vibration signal of the landing gear when the aircraft lands.

[0008] Furthermore, the triboelectric power generation part includes interdigital electrodes and friction balls. The interdigital electrodes are arranged on the inner wall of the sleeve, and the friction balls are circumferentially arranged in the arc-shaped grooves of the sliding shaft.

[0009] Furthermore, the interdigital electrodes are pasted on a plastic film, and the curled plastic film abuts against the stepped surface on the inner wall of the sleeve.

[0010] Furthermore, the electromagnetic power generation part includes a coil and a permanent magnet. The coil is fixed in the groove on the inner wall of the sleeve, and the permanent magnet is circumferentially installed in the cylindrical groove of the sliding shaft.

[0011] Furthermore, the coil is installed in the cylindrical groove of the sleeve, and a square through hole penetrates through the center of the cylindrical groove on the sleeve.

[0012] Furthermore, the permanent magnets are installed on the sliding shaft in two upper and lower rows, and the magnetization directions of the two rows of permanent magnets are opposite; four permanent magnets are circumferentially installed on the sliding shaft, and the magnetization directions are also staggered along the circumferential direction.

[0013] Furthermore, key holes are provided on the upper end cover, the sliding shaft and the lower end cover, key grooves are provided on the key shaft, a flat key is installed in the key groove, the key shaft is inserted into the key holes of the sliding shaft and the lower end cover, and the side surface of the flat key fits with the side surface of the key hole of the sliding shaft.

[0014] Furthermore, the lower end cover fits with the stepped surface of the key shaft, and the side surface of the flat key on the stepped surface of the key shaft fits with the side surface of the key hole of the lower end cover.

[0015] In a self-powered monitoring device for an aircraft landing gear based on vibration energy harvesting according to the present invention, the permanent magnet is driven by the sliding shaft to move up and down. Due to Faraday's law of electromagnetic induction, the coil generates regular alternating current. Four coils in the same row are connected in series and then rectified by a rectifier, and the rectified currents of the two rows are then connected in parallel to amplify the current and voltage to achieve a higher power output; at the same time, the friction balls and the interdigital electrodes rub against each other to form a voltage signal. Different waveforms represent specific amplitudes and frequencies. By reading the voltage waveform, the monitoring and identification of the vibration signal are realized.

[0016] The beneficial technical effects of the present invention are:

[0017] Through the linear vibration of the sliding shaft along the axial direction, the permanent magnet in the power generation component and the friction ball in the sensing component are driven to move, enabling the power generation component to supply power to the sensors around the aircraft landing gear and monitor the vibration of the landing gear during aircraft landing. The present invention can effectively capture the vibration energy during aircraft landing and monitor the landing vibration state. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 FIG. is a schematic diagram of the overall structure of the self-powered monitoring device for aircraft landing gear based on vibration energy collection according to the present invention.

[0019] Figure 2 FIG. is a schematic sectional view of the self-powered monitoring device for aircraft landing gear based on vibration energy collection according to the present invention.

[0020] Figure 3 FIG. is a schematic partial sectional view of the key shaft of the self-powered monitoring device for aircraft landing gear based on vibration energy collection according to the present invention.

[0021] Figure 4 FIG. is a schematic diagram of the structure when the present invention is installed inside the landing gear.

[0022] Figure 5 FIG. is a schematic diagram of the energy storage and power supply circuit structure of the power generation component of the present invention.

[0023] In the figure, 1, upper end cover; 2, spring; 3, sliding shaft; 4, permanent magnet; 5, sleeve; 6, lower end cover; 7, key shaft; 8, coil; 9, friction ball; 10, interdigital electrode; 11, flat key. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0024] The following further describes the present invention in detail with reference to the drawings and specific implementation methods.

[0025] A self-powered monitoring device for aircraft landing gear based on vibration energy collection according to the present invention is as Figure 1 shown, including a sleeve 5 and a sliding shaft 3 installed inside the aircraft landing gear; a lower end cover 6 is provided at the lower end of the sleeve 5, and the lower end cover 6 is connected to the sleeve 5 by screws. As Figure 2 shown, the inner wall of the sleeve 5 and the sliding shaft 3 are supported and connected by circumferentially arranged friction balls 9; the sliding shaft 3 is fixed to the upper end cover 1 by a mortise and tenon structure, and the upper end cover 1 and the sleeve 5 are supported by a spring 2; a key shaft 7 is inserted into the key hole at the center of the lower end cover 6 and the sliding shaft 3.

[0026] A power generation component and a sensing component are arranged inside the sleeve 5. The power generation component includes a triboelectric power generation part and an electromagnetic power generation part. The moving part of the power generation component is installed in the groove on the sliding shaft 3, and the fixed part of the power generation component is installed on the inner side of the sleeve 5. Through the linear vibration of the sliding shaft 3 along the axial direction, the power generation component is driven to generate electricity to supply power to the sensors around the aircraft landing gear. At the same time, the sensing component monitors the vibration signal of the landing gear when the aircraft lands.

[0027] Further, the triboelectric power generation part includes interdigital electrodes 10 and friction balls 9. The interdigital electrodes 10 are arranged on the inner wall of the sleeve 5, and the friction balls 9 are circumferentially arranged in the arc-shaped grooves of the sliding shaft 3, effectively reducing the possibility of the friction balls 9 slipping and enhancing the output signal when the friction balls 9 move on the interdigital electrodes 10.

[0028] Further, the interdigital electrodes 10 are pasted on a plastic film, and the curled plastic film abuts against the stepped surface on the inner wall of the sleeve 5, enabling the friction balls 9 to roll within a low-damping cylindrical curved surface and improving the durability of the friction balls 9 and the interdigital electrodes.

[0029] Further, the electromagnetic power generation part includes a coil 8 and a permanent magnet 4. The coil 8 is fixed in the groove on the inner wall of the sleeve 5, and the permanent magnet 4 is circumferentially installed in the cylindrical groove of the sliding shaft 3. The sliding shaft 3 drives the permanent magnet 4 to move, causing the coil 8 to induce an electric current to generate electrical energy.

[0030] Further, the coil 8 is installed in the cylindrical groove of the sleeve 5. A square through-hole penetrates through the center of the cylindrical groove on the sleeve 5, and the lead wire of the coil 8 inside the sleeve 5 passes through the through-hole, facilitating the assembly and series-parallel wiring of the coil.

[0031] Further, the permanent magnet 4 is installed on the sliding shaft 3 in two upper and lower rows, and the magnetization directions of the two rows of permanent magnets 4 are opposite; four permanent magnets 4 are circumferentially installed on the sliding shaft 4, and the magnetization directions are also staggered along the circumferential direction, enhancing the combined magnetic field formed by the permanent magnets 4 and effectively improving the power generation efficiency of the power generation component.

[0032] Further, the upper end cover 1, the sliding shaft 3, and the lower end cover 6 are all provided with keyholes. As Figure 3 shown, a keyway is provided on the key shaft 7, a flat key 11 is installed in the keyway, the key shaft 7 is inserted into the keyholes of the sliding shaft 3 and the lower end cover 6, and the side surface of the flat key 11 fits with the side surface of the keyhole of the sliding shaft 3.

[0033] Further, the lower end cover 6 fits with the stepped surface of the key shaft 7, and the side surface of the flat key on the stepped surface of the key shaft 7 fits with the side surface of the keyhole of the lower end cover 6.

[0034] When the landing gear squeezes the upper end cover 1 and moves downward, the sliding shaft 3 moves downward simultaneously due to the extrusion of the upper end cover 1, and the spring 2 generates a pre-return elastic force. When the landing gear starts to stretch, the spring 2 immediately pushes the upper end cover 1, and at the same time, the sliding shaft 3 is pulled upward through the upper end cover 1. The spring 2 can effectively provide buffering and rebound performance for the upper end cover 1 and the sliding shaft 3.

[0035] When installing the device of the present invention on the landing gear as Figure 4 shown, after pressing the spring 2 a certain distance in advance, it is installed in the landing gear. The spring 2 generates a pre-return elastic force, forcing the lower end cover 6 and the upper end cover 1 to always be in close contact with the landing gear. When the aircraft lands, the vibration of the landing gear is transmitted to the sliding shaft 3, and under the auxiliary action of the spring 2, the sliding shaft 3 moves up and down, and then drives the permanent magnet 4 and the friction ball 9 to move, so that the power generation component in the sleeve 5 outputs electrical energy and vibration signals.

[0036] A method for capturing the vibration energy and monitoring the landing state of an aircraft landing gear self-powered monitoring device based on vibration energy collection in the present invention is as follows: an alternating current is generated through the coil 8; the coils of the same layer are connected in series, and the alternating current is converted into direct current through a rectifier bridge, and the upper and lower two-layer coil groups are connected in parallel to generate electrical energy; the co-phase movement of the layer friction ball and the interdigital electrode enhances the output of the electrical signal, and the specific waveform can correspond to a specific amplitude and frequency, achieving the signal monitoring effect.

[0037] The principle of vibration energy capture and signal detection of an aircraft landing gear self-powered monitoring device based on vibration energy collection in the present invention is as Figure 5 shown. The specific method is as follows: the permanent magnet 4 is driven to move up and down by the sliding shaft 3. Due to Faraday's law of electromagnetic induction, the coil 8 generates a regular alternating current. The four coils in the same row are connected in series and rectified by a rectifier. After rectification, the two rows are connected in parallel to amplify the current and voltage, realizing a higher power output; at the same time, the friction ball 9 rubs against the interdigital electrode 10 to form a voltage signal. Different waveforms represent specific amplitudes and frequencies. By reading the voltage waveform, the monitoring and recognition of vibration signals are realized.

[0038] Working principle:

[0039] When the landing gear squeezes and the upper end cover 1 and the lower end cover 6 approach each other, a linear relative movement will occur between the sliding shaft 3 fixedly connected to the upper end cover 1 and the sleeve 5 fixedly connected to the lower end cover 6. The sliding shaft 3 drives the permanent magnet 4 and the friction ball 9 to move, and the coil 8 installed on the sleeve 5 generates an induced current to output electrical energy; the interdigital electrode 10 abutted on the stepped surface in the sleeve 5 generates a specific electrical signal under the action of the sliding friction of the friction ball 9.

[0040] The present invention is installed on the aircraft landing gear to monitor the vibration condition of the aircraft landing gear in real time, especially the vibration state during actual landing. It has excellent working applicability and is easy to detect.

[0041] The present invention can be perfectly matched with the landing gear size design and can be freely installed inside or outside the landing gear, with high integration and adaptability.

[0042] The above-described embodiments are only used to describe the preferred embodiments of the present invention and do not limit the scope of the present invention. Without departing from the design spirit of the present invention, various deformations and improvements made by those of ordinary skill in the art to the technical solution of the present invention shall fall within the protection scope determined by the claims of the present invention.

Claims

1. An aircraft landing gear self-powered monitoring device based on vibration energy harvesting, characterized in that, It includes a sleeve (5) and a sliding shaft (3) installed inside the aircraft landing gear; a lower end cover (6) is provided at the lower end of the sleeve (5), and the lower end cover (6) is connected to the sleeve (5) by screws; the inner wall of the sleeve (5) and the sliding shaft (3) are supported and connected by friction balls (9) arranged circumferentially; the sliding shaft (3) and the upper end cover (1) are fixed by a mortise and tenon structure, and a spring (2) is provided between the upper end cover (1) and the sleeve (5) for support; a key shaft (7) is inserted into the keyhole at the center of the lower end cover (6) and the sliding shaft (3). A power generation component and a sensing component are arranged inside the sleeve (5). The power generation component includes a triboelectric power generation part and an electromagnetic power generation part. The moving part of the power generation component is installed in the groove on the sliding shaft (3), and the fixed part of the power generation component is installed on the inner side of the sleeve (5). Through the linear vibration of the sliding shaft (3) along the axial direction, the power generation component generates electricity to supply power to the sensors around the aircraft landing gear. At the same time, the sensing component monitors the vibration signal of the landing gear when the aircraft lands.

2. The self-powered monitoring device for aircraft landing gear based on vibration energy harvesting according to claim 1, characterized in that The triboelectric power generation part includes interdigital electrodes (10) and friction balls (9). The interdigital electrodes (10) are arranged on the inner wall of the sleeve (5), and the friction balls (9) are arranged circumferentially in the arc-shaped groove of the sliding shaft (3).

3. The self-powered monitoring device for aircraft landing gear based on vibration energy harvesting according to claim 2, wherein The interdigital electrodes (10) are pasted on a plastic film, and the curled plastic film abuts against the stepped surface on the inner wall of the sleeve (5).

4. The self-powered monitoring device for aircraft landing gear based on vibration energy harvesting according to claim 1, characterized in that, The electromagnetic power generation part includes a coil (8) and a permanent magnet (4). The coil (8) is fixed in the groove on the inner wall of the sleeve (5), and the permanent magnet (4) is circumferentially installed in the cylindrical groove of the sliding shaft (3).

5. The self-powered monitoring device for aircraft landing gear based on vibration energy harvesting according to claim 4, characterized in that, The coil (8) is installed in the cylindrical groove of the sleeve (5), and a square through hole penetrates through the center of the cylindrical groove on the sleeve (5).

6. The self-powered monitoring device for aircraft landing gear based on vibration energy harvesting according to claim 4, wherein The permanent magnet (4) is installed on the sliding shaft (3) in two rows up and down, and the magnetization directions of the two rows of permanent magnets (4) are opposite; four permanent magnets (4) are circumferentially installed on the sliding shaft (4), and the magnetization directions are also staggered along the circumferential direction.

7. The self-powered monitoring device for aircraft landing gear based on vibration energy harvesting according to claim 1, characterized in that, The upper end cover (1), the sliding shaft (3) and the lower end cover (6) are all provided with keyholes. The key shaft (7) is provided with key grooves, and a flat key (11) is installed in the key grooves. The key shaft (7) is inserted into the keyholes of the sliding shaft (3) and the lower end cover (6), and the side surface of the flat key (11) fits against the side surface of the keyhole of the sliding shaft (3).

8. The self-powered monitoring device for aircraft landing gear based on vibration energy harvesting according to claim 7, wherein The lower end cover (6) fits against the stepped surface of the key shaft (7), and the side surface of the flat key on the stepped surface of the key shaft (7) fits against the side surface of the keyhole of the lower end cover (6).

9. A self-powered monitoring device for an aircraft landing gear based on vibration energy harvesting according to any one of claims 1-8, characterized in that, By driving the permanent magnet (4) to move up and down by the sliding shaft (3), the coil (8) generates regular alternating current due to Faraday's law of electromagnetic induction. The four coils in the same row are connected in series and rectified by a rectifier, and then the two rows are rectified and connected in parallel to amplify the current and voltage to achieve a higher power output; at the same time, the friction balls (9) and the interdigital electrodes (10) rub against each other to form a voltage signal. Different waveforms represent specific amplitudes and frequencies, and by reading the voltage waveform, the monitoring and identification of vibration signals are realized.

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