Aircraft landing gear buffer control device and method based on damping control algorithm
Through the aircraft landing gear buffer control device based on the shock absorption control algorithm, the aircraft status data is collected and analyzed in real time, and the damping characteristics are dynamically adjusted, which solves the problems of low response speed and control accuracy of the traditional landing gear shock absorption system and improves the stability and safety of the system.
Patent Information
- Application Number
- CN202511124127.9
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-08-12
- Publication Date
- 2025-10-28
AI Technical Summary
The traditional landing gear shock absorption system cannot be dynamically adjusted according to the real-time status of the aircraft, and the electric mechanism has low response speed and control accuracy, resulting in insufficient system stability and safety and low integration.
The aircraft landing gear buffer control device based on the shock absorption control algorithm is adopted. The aircraft status data is collected in real time through the sensor module. The damping characteristics are dynamically adjusted by combining the data processing and communication module, the shock absorption control algorithm module and the damping characteristic optimization module. The electric mechanism and hydraulic servo valve are used to accurately control the damper and hydraulic system to achieve a high-precision shock absorption effect.
It achieves high-precision, fast-response shock absorption control of aircraft landing gear, adapts to complex working conditions, improves the stability and safety of the system, and ensures that the damping characteristics are always in the optimal state.
Smart Images
Figure CN120840859A_ABST
Abstract
Description
Technical Field
[0001] This invention belongs to the field of aircraft landing gear control technology, and particularly relates to an aircraft landing gear buffer control device and method based on a vibration reduction control algorithm. It is applicable to the manufacturing stage and the flight stage of the aircraft, and realizes data acquisition, status analysis and parameter optimization of the aircraft landing gear system through a vibration reduction control algorithm. Background Technology
[0002] Traditional landing gear damping systems typically employ fixed damping characteristics, making dynamic adjustments impossible based on the aircraft's real-time status. The electric mechanisms struggle to achieve precise control, failing to maintain optimal damping performance. Furthermore, the lack of integrated control systems results in insufficient stability and safety, low system integration, and room for improvement in the response speed and control precision of the electric mechanisms. Summary of the Invention
[0003] The technical problem this invention aims to solve is that the aircraft landing gear damping control device and method based on a vibration reduction control algorithm provides an improvement over the traditional fixed damping characteristics of landing gear vibration reduction landing systems. It allows for dynamic adjustment based on the aircraft's landing speed and load, and improves response speed and control accuracy based on the electronic control actuator. By integrating the vibration reduction control algorithm, damping characteristic optimization module, and electronic control actuator, the overall performance of the system is optimized, ensuring its stability and reliability under complex operating conditions.
[0004] The technical solution of this invention is: On one hand, the present invention provides an aircraft landing gear buffer control device based on a shock absorption control algorithm. The control device includes: a sensor module, a power management module, a data processing and communication module, a shock absorption control algorithm module, a damping characteristic optimization module, an electric mechanism, a damper, and a hydraulic servo valve. The sensor module is used to collect real-time aircraft operating status data, including wheel speed, tire pressure, and landing gear travel position, and transmits the collected sensor data to the data processing and communication module via the CAN bus. The data processing and communication module receives wheel speed, tire pressure, and landing gear displacement data sent by the sensor module, and performs filtering and noise reduction on these data. After noise reduction, the processed data is transmitted to the vibration control algorithm module via the 1553 bus. After receiving the aircraft operating status data from the data processing and communication module, the vibration reduction control algorithm module analyzes the different data, generates adjustment signals, and then sends the generated adjustment signals back to the data processing and communication module. The damping characteristic optimization module dynamically adjusts the damping characteristics of the damping system based on the adjustment signal generated by the damping control algorithm module, and sends the optimized control parameters to the electric mechanism. The electric mechanism controls the damper and hydraulic servo valve to precisely adjust the physical parameters of the damping system, including the damping force of the damper and the hydraulic pressure of the hydraulic system, based on the optimized control parameters.
[0005] Furthermore, The damper is installed at the bottom of the landing gear shock absorber strut. Its compression and tension are controlled according to the control parameters sent by the electric mechanism, and the damping characteristics are dynamically adjusted to achieve the shock absorption effect.
[0006] Furthermore, The hydraulic servo valve controls its hydraulic flow based on the control parameters sent by the electric mechanism, and achieves the shock absorption effect by changing the damping characteristics by changing the flow resistance.
[0007] Furthermore, Wheel speed is collected using speed sensors installed on the aircraft tires; Tire pressure is collected using pressure sensors installed on the aircraft tires; The landing gear travel position is collected using position sensors mounted on the landing gear struts.
[0008] Secondly, the present invention also provides an aircraft landing gear buffer control method based on a shock absorption control algorithm, the method being implemented based on the aforementioned control device, the method comprising: The sensor module collects real-time operational status data of the aircraft, including wheel speed, tire pressure, and landing gear travel position, and transmits the collected sensor data to the data processing and communication module via the CAN bus. The data processing and communication module receives wheel speed, tire pressure, and landing gear displacement data sent by the sensor module, and performs filtering and noise reduction on these data. After noise reduction, the processed data is transmitted to the vibration control algorithm module via the 1553 bus. After receiving the aircraft operating status data from the data processing and communication module, the vibration reduction control algorithm module analyzes the different data, generates adjustment signals, and then sends the generated adjustment signals back to the data processing and communication module. The damping characteristic optimization module dynamically adjusts the damping characteristics of the damping system based on the adjustment signal generated by the damping control algorithm module, and sends the optimized control parameters to the electric mechanism. The electric mechanism controls the damper and hydraulic servo valve to precisely adjust the physical parameters of the damping system, including the damping force of the damper and the hydraulic pressure of the hydraulic system, based on the optimized control parameters.
[0009] Furthermore, The shock absorption control algorithm module performs noise reduction processing on the received wheel speed, tire pressure, and landing gear travel position data through low-pass filtering. Then, it fuses the wheel speed, tire pressure, and landing gear travel position data to eliminate redundant information. Finally, it converts the data into a unified format and dimension to obtain the adjustment signal. Key features in the adjustment signal are extracted as input to the damping algorithm. These key features include impact load, rate of change of acceleration, and compression of the damping strut. The impact load at landing is calculated using pressure sensor data, the rate of change of acceleration during landing is calculated using velocity sensor data, and the compression of the landing gear damping strut is calculated using travel position sensor data. The vibration reduction control algorithm module then sends these key parameters to the data processing and communication module via the 1553 bus.
[0010] Furthermore, The damping characteristic optimization module receives the adjustment signal sent by the data processing and communication module, and the adjustment signal contains at least the key features; The first step is to blur the key features, dividing each extracted key feature into N levels based on the experimental data; Based on the key parameters divided into N levels, the optimal damping characteristics of the damper are determined through experimental data.
[0011] Furthermore, Based on the key parameters divided into N levels, the optimal damping characteristics of the damper were determined through experimental data, specifically: The N levels of each key parameter are derived and judged by fuzzy control rules, and the damping characteristics of the damper under this condition are determined based on experimental data. Then, the fuzziness is de-defined, and the required damping characteristics are converted into specific pressure values. The specific pressure values are achieved by controlling the damper and hydraulic valve.
[0012] Compared with the prior art, the present invention has the following characteristics: In existing technologies, aircraft landing gear dampers typically employ a passive design, with fixed damping characteristics or only supporting limited manual adjustment. This invention, however, introduces a damping characteristic optimization algorithm that can collect real-time data on the aircraft landing gear's operating status (such as landing speed, acceleration, and impact loads) and dynamically adjust the damping characteristics of the damper based on this information. This intelligent dynamic adjustment capability allows the damper to adapt to different landing conditions and aircraft states, providing optimal shock absorption.
[0013] This invention employs high-precision sensors (such as accelerometers, displacement sensors, and pressure sensors) and an advanced data acquisition system, enabling real-time acquisition of aircraft landing gear operating status and external environmental data. Through multi-sensor fusion technology, the system can comprehensively analyze multiple data sources, ensuring the accuracy and comprehensiveness of the data.
[0014] This invention introduces a closed-loop control system and a real-time feedback mechanism, which can adjust the control strategy in real time based on the actual operating state of the damper and changes in the external environment through a vibration reduction control algorithm. Through closed-loop control, the system can ensure that the damping characteristics of the damper are always in an optimal state, adapting to the dynamic changes during aircraft landing. Attached Figure Description
[0015] Figure 1 This is a schematic diagram of an aircraft landing gear buffer control device based on a vibration reduction control algorithm. Detailed Implementation
[0016] The present application will be further described in detail below with reference to the accompanying drawings of the embodiments.
[0017] To address the issues of low system integration, insufficient safety and stability, and low response speed and control precision of traditional landing gear damping systems, this invention designs an aircraft landing gear damping control device and method based on a damping control algorithm. This device adjusts the damping characteristics of the aircraft landing gear damping landing system according to parameters such as aircraft landing speed, load, and runway conditions. This enables real-time monitoring of the aircraft's status, achieving high precision, high safety, and high responsiveness.
[0018] To meet the needs of aircraft production, this invention provides an aircraft landing gear buffer control device based on a vibration reduction control algorithm, comprising the following components: a sensor module 1, a power management module 2, a data processing and communication module 3, a vibration reduction control algorithm module 4, a damping characteristic optimization module 5, an electric mechanism 6, a damper 7, and a hydraulic servo valve 8. (Appendix) Figure 1 This is a diagram of the landing gear buffer control system.
[0019] a) Sensor module Sensor module 1 is used to collect real-time aircraft operating status data, including parameters such as wheel speed, tire pressure, and landing gear travel position, and transmits the collected sensor data to data processing and communication module 3 via CAN bus.
[0020] b) Power module Power module 2 provides the DC power required for the operation of the entire landing gear cushioning control system. Key parameters include: Output: DC12V 7.5A, voltage regulation accuracy ±5%; DC5V 2A voltage regulation accuracy ±3%; Overload protection: 105%~150% (rated load), self-recovering; Overvoltage protection: 115%~150% (rated output voltage).
[0021] c) Data Processing and Communication Module The data processing and communication module 3 receives parameters such as wheel speed, tire pressure, and landing gear displacement sent by the sensor module, and performs filtering and noise reduction on these data. After noise reduction, the processed data is transmitted to the vibration damping control algorithm module 4 via the 1553 bus.
[0022] d) Vibration reduction control algorithm module After receiving aircraft operating status data from the data processing and communication module 3, the vibration reduction control algorithm module 4 analyzes the different data, calculates the optimal vibration reduction control strategy, and generates an adjustment signal. The generated adjustment signal is then sent back to the data processing and communication module 3.
[0023] e) Damping characteristic optimization module The damping characteristic optimization module 5 can dynamically adjust the damping characteristics of the damping system according to the adjustment signal generated by the damping control algorithm module 4, and send the optimized control parameters to the electric mechanism 6.
[0024] f) Electric mechanism The electric mechanism 6 can precisely adjust the physical parameters of the damping system, including the damping force of the damper and the hydraulic pressure of the hydraulic system, through the damper 7 and the hydraulic servo valve 8, based on the adjustment signal generated by the damping characteristic optimization module 5.
[0025] g) Dampers The damper 7 is installed at the bottom of the landing gear shock absorber strut. It controls the compression and tension forces according to the electrical signal sent by the electric mechanism 6, and dynamically adjusts the damping characteristics to achieve the shock absorption effect.
[0026] h) Hydraulic servo valve The hydraulic servo valve 8 controls its hydraulic flow based on the electrical signal sent by the electric mechanism 6, and achieves the shock absorption effect by changing the damping characteristics by changing the flow resistance.
[0027] The specific implementation methods for the vibration reduction control algorithm and damping characteristic optimization are as follows: 1. Data Acquisition and Preprocessing The vibration damping control algorithm module 4 performs noise reduction processing on the received aircraft and landing gear status data using low-pass filtering to reduce sensor noise interference. Subsequently, it fuses data from the speed sensor, pressure sensor, and position sensor to eliminate redundant information. Finally, it converts the data into a unified format and dimension to obtain the adjustment signal.
[0028] 2. Data Input and Feature Extraction The preprocessed data undergoes further processing in the damping control algorithm module 4. First, key features from the adjustment signals are extracted as input to the damping algorithm. These key features include impact load, rate of change of acceleration, and damping strut compression. The impact load at landing is calculated using pressure sensor data, the rate of change of acceleration during landing is calculated using velocity sensor data, and the landing gear damping strut compression is calculated using travel position sensor data. Subsequently, the damping control algorithm module 4 transmits these key parameters to the data processing and communication module 3 via the 1553 bus.
[0029] 3. Damping characteristics calculation and optimization The data processing and communication module 3 sends the adjustment signal to the damping characteristic optimization module 5. The damping characteristic optimization algorithm includes two aspects: fuzzy control rules and damping characteristic calculation and optimization. Among them, the definition of fuzzy rules is the core of this algorithm, which requires a large amount of experimental data to define different state levels.
[0030] Fuzzy rule definition is a control method based on fuzzy logic, capable of handling complex nonlinear systems in this process and making reasonable control decisions. The first step is to fuzzify key parameters. For example, the extracted key parameters, such as vertical impact force, are divided into levels one to N based on experimental data for different magnitudes of vertical impact force. Similarly, the rate of change of acceleration and the compression of the damper strut are divided into N levels. These data are then transmitted to the damping characteristic calculation and optimization logic.
[0031] The damping characteristic calculation and optimization logic calculates the optimal damping characteristics of the damper based on the key parameters currently received by the system, which are divided into N levels. The calculation process includes fuzzy inference and defuzzification. Fuzzy inference involves using fuzzy control rules to deduce and judge the N levels of each key parameter, calculating the damping characteristics that the damper should have under these conditions. Subsequently, defuzzification converts the required damping characteristics into specific pressure values. These specific pressure values are achieved by controlling the damper 7 and the hydraulic valve 8.
[0032] 4. Damper Execution and Real-time Feedback The calculated damping characteristics are sent to the landing gear damper 7 and hydraulic valve 8, and dynamic damping of the landing gear is achieved by adjusting the damping characteristics and hydraulic pressure. Simultaneously, the system collects real-time data on the damper's operating status and the aircraft's operational status to achieve closed-loop control. Through a real-time feedback mechanism, the control strategy is continuously adjusted to ensure the damper is always in optimal condition.
[0033] This invention designs a method for aircraft landing gear damping control based on a vibration reduction control algorithm. It includes an intelligent variable damping control algorithm that analyzes the landing gear's operating status in conjunction with environmental data to dynamically adjust the damping characteristics of the damper in real time. The sensor module is a multi-sensor integrated module containing speed, pressure, displacement, and acceleration sensors, capable of collecting various landing gear status information in real time. It includes a dynamic damping adjustment mechanism that uses an electric mechanism to control the damper and servo hydraulic valves to achieve precise control of the damping force. It features a closed-loop control system that achieves real-time dynamic control of the damping characteristics through the issuance of adjustment signals and sensor-acquired signals. It has a multi-environmental adaptability design, capable of adapting to different runway conditions and different aircraft landing states, providing optimal vibration reduction performance. It is highly integrated, combining data processing and communication modules, vibration reduction control algorithm modules, damping characteristic optimization modules, and electric mechanisms, resulting in fast response speed and high control accuracy.
Claims
1. An aircraft landing gear damping control device based on a vibration reduction control algorithm, characterized in that, The control device includes: a sensor module (1), a power management module (2), a data processing and communication module (3), a shock absorption control algorithm module (4), a damping characteristic optimization module (5), an electric mechanism (6), a damper (7), and a hydraulic servo valve (8). The sensor module (1) is used to collect real-time aircraft operating status data, including wheel speed, tire pressure, and landing gear travel position, and transmit the collected sensor data to the data processing and communication module (3) via the CAN bus. The data processing and communication module (3) receives wheel speed, tire pressure and landing gear displacement sent by the sensor module, and performs filtering and noise reduction on these data. After noise reduction, the processed data is transmitted to the vibration control algorithm module (4) via the 1553 bus. After receiving the aircraft operating status data from the data processing and communication module (3), the shock absorption control algorithm module (4) analyzes the different data, generates adjustment signals, and then sends the generated adjustment signals back to the data processing and communication module (3). The damping characteristic optimization module (5) dynamically adjusts the damping characteristics of the damping system according to the adjustment signal generated by the damping control algorithm module (4), and sends the optimized control parameters to the electric mechanism (6). The electric mechanism (6) controls the damper (7) and the hydraulic servo valve (8) according to the optimized control parameters to precisely adjust the physical parameters of the damping system, including the damping force of the damper and the hydraulic pressure of the hydraulic system.
2. The aircraft landing gear buffer control device based on a vibration reduction control algorithm according to claim 1, characterized in that, The damper (7) is installed at the bottom of the landing gear shock absorber strut. Its compression and tension are controlled according to the control parameters sent by the electric mechanism (6), and the damping characteristics are dynamically adjusted to achieve the shock absorption effect.
3. The aircraft landing gear buffer control device based on a vibration reduction control algorithm according to claim 1, characterized in that, The hydraulic servo valve (8) controls its hydraulic flow according to the control parameters sent by the electric mechanism (6), and changes the damping characteristics by changing the flow resistance to achieve the shock absorption effect.
4. The aircraft landing gear buffer control device based on a vibration reduction control algorithm according to claim 1, characterized in that, Wheel speed is collected using speed sensors installed on the aircraft tires; Tire pressure is collected using pressure sensors installed on the aircraft tires; The landing gear travel position is collected using position sensors mounted on the landing gear struts.
5. A method for aircraft landing gear buffer control based on a vibration reduction control algorithm, characterized in that, The method is implemented based on the control device as described in any one of claims 1-4, and the method includes: The sensor module (1) collects real-time data on the aircraft's operating status, including wheel speed, tire pressure, and landing gear travel position, and transmits the collected sensor data to the data processing and communication module (3) via the CAN bus. The data processing and communication module (3) receives wheel speed, tire pressure and landing gear displacement sent by the sensor module, and performs filtering and noise reduction on these data. After noise reduction, the processed data is transmitted to the vibration control algorithm module (4) via the 1553 bus. After receiving the aircraft operating status data from the data processing and communication module (3), the shock absorption control algorithm module (4) analyzes the different data, generates adjustment signals, and then sends the generated adjustment signals back to the data processing and communication module (3). The damping characteristic optimization module (5) dynamically adjusts the damping characteristics of the damping system according to the adjustment signal generated by the damping control algorithm module (4), and sends the optimized control parameters to the electric mechanism (6). The electric mechanism (6) controls the damper (7) and the hydraulic servo valve (8) according to the optimized control parameters to precisely adjust the physical parameters of the damping system, including the damping force of the damper and the hydraulic pressure of the hydraulic system.
6. The aircraft landing gear buffer control method based on a vibration reduction control algorithm according to claim 5, characterized in that, The shock absorption control algorithm module (4) performs noise reduction processing on the received wheel speed, tire pressure and landing gear travel position data by low-pass filtering, then fuses the wheel speed, tire pressure and landing gear travel position data to eliminate redundant information, and finally converts the data into a unified format and dimension to obtain the adjustment signal. Key features are extracted from the adjustment signal and used as input to the damping algorithm. These key features include impact load, rate of change of acceleration, and compression of the damping strut. The impact load during landing is calculated using pressure sensor data, the rate of change of acceleration during landing is calculated using velocity sensor data, and the compression of the landing gear shock absorber strut is calculated using stroke position sensor data. Subsequently, the vibration reduction control algorithm module (4) sends these key parameters to the data processing and communication module (3) via the 1553 bus.
7. The aircraft landing gear buffer control method based on a vibration reduction control algorithm according to claim 6, characterized in that, The damping characteristic optimization module (5) receives the adjustment signal sent by the data processing and communication module (3), and the adjustment signal contains at least the key features; The first step is to blur the key features, dividing each extracted key feature into N levels based on the experimental data; Based on the key parameters divided into N levels, the optimal damping characteristics of the damper are determined through experimental data.
8. The aircraft landing gear buffer control method based on a vibration reduction control algorithm according to claim 7, characterized in that, Based on the key parameters divided into N levels, the optimal damping characteristics of the damper were determined through experimental data, specifically: The N levels of each key parameter are derived and judged by fuzzy control rules, and the damping characteristics of the damper under this condition are determined based on experimental data. Then, the fuzziness is de-defined, and the required damping characteristics are converted into specific pressure values. The specific pressure values are achieved by controlling the damper (7) and the hydraulic valve (8).