Nowadays,there is still a need for the development of a high-precision measurement system for aircraft structural elements vibrations,this is due to the fact that many aviation problems are associated with analyzing v...Nowadays,there is still a need for the development of a high-precision measurement system for aircraft structural elements vibrations,this is due to the fact that many aviation problems are associated with analyzing vibration characteristics of aircraft mechanical structures during its main modes of operation,including flight,particularly the airplane wing health monitoring.This paper presents preliminary results of research carried out toward building a promising system designed to measure vibration parameters of airplane wing.Comparing it with the existing analogues systems,the proposed system features the use of approaches that are traditional for solving orientation and navigation problems for vibration measurements.The article discusses the principles of building such system based on micromechanical inertialmeasurements units,displacement sensors,on-board aircraft navigation system and sensor data fusion technology.The paper provides a brief overview of the existing solutions in this field of research,and substantiates the relevance and feasibility of the proposed technical solution.The paper presents the basic hardware components of the proposed system,presents the fundamentals of its operation based on the data collected frommany sources,including displacement sensors,inertial units and the optimal Kalman estimation and correction algorithm.Besides,the paper presents the mathematical errors models of the system main components.The main algorithms of the system are shown,including algorithms for inertial measurements,estimation and correction in a closed-loop scheme for including optimal Kalman filter,and indirect calculations of vibration parameters.Finally,the initial simulation results of system operation are shown,demonstrating its operability and expected accuracy characteristics,which confirms the system effectiveness and the prospects of the chosen direction of research.展开更多
文摘Nowadays,there is still a need for the development of a high-precision measurement system for aircraft structural elements vibrations,this is due to the fact that many aviation problems are associated with analyzing vibration characteristics of aircraft mechanical structures during its main modes of operation,including flight,particularly the airplane wing health monitoring.This paper presents preliminary results of research carried out toward building a promising system designed to measure vibration parameters of airplane wing.Comparing it with the existing analogues systems,the proposed system features the use of approaches that are traditional for solving orientation and navigation problems for vibration measurements.The article discusses the principles of building such system based on micromechanical inertialmeasurements units,displacement sensors,on-board aircraft navigation system and sensor data fusion technology.The paper provides a brief overview of the existing solutions in this field of research,and substantiates the relevance and feasibility of the proposed technical solution.The paper presents the basic hardware components of the proposed system,presents the fundamentals of its operation based on the data collected frommany sources,including displacement sensors,inertial units and the optimal Kalman estimation and correction algorithm.Besides,the paper presents the mathematical errors models of the system main components.The main algorithms of the system are shown,including algorithms for inertial measurements,estimation and correction in a closed-loop scheme for including optimal Kalman filter,and indirect calculations of vibration parameters.Finally,the initial simulation results of system operation are shown,demonstrating its operability and expected accuracy characteristics,which confirms the system effectiveness and the prospects of the chosen direction of research.
