恶劣飞行环境中光纤光栅传感方法和技术研究
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摘要
航空飞行器作为国家综合实力和军事实力的体现，在现代战争中的地位越来越重要，它在预警、侦查、反坦克、防空、电子作战、空中指挥等系统中发挥着越来越大作用，飞行器己成为取得战争主动权的最重要的武器，对战争的进程和结局将产生重要乃至决定性的影响。但是由于飞行器的结构十分精密而复杂；经常工作在各种恶劣的环境中；以及高超声速的飞行等，导致其出现故障的机率增加。因此飞行器的结构安全监测问题成为一项非常必要和迫切的任务。
目前现役飞行器上的压力检测采用直读式压力表或通过压力传感器／信号器进行远距离测量和控制，温度检测和控制采用温包、热电偶、热电阻、双金属片等，这些传感器一般基于电阻或电感测量原理，它们感受温度和压力后通过电缆将电信号传递给对应的指示仪表或其他系统。这一类机电传感检测方法极易受到恶劣飞行环境的影响，导致温度和压力的检测精度低、测量误差大、可靠性差、易受电磁干扰等。
光纤光栅传感器具有传统机电传感器不可比拟的优点如重量轻、体积小、精度高、传感信号为数字、抗电磁干扰、防爆且易于引入综合处理器对信号进行集中处理等等，非常适合航空飞行器的结构安全监测。
本论文在国家自然科学基金(60537050)以及国防科工委预研项目的支持下，从基础理论、基本实验研究了光纤光栅传感技术及其在恶劣航空飞行环境中的应用。目的是研制出光纤光栅温度和压力等传感器及其所构成的健康监测系统，并实现其在航空飞行器中的应用。
本论文重点研究了裸光纤光栅、镍管镀金光纤光栅和细不锈钢管封装的三种不同形式的光纤光栅温度传感器的低温特性，前两种光纤光栅的波长在整个温度变化区间具有良好的线性，镍管镀金光纤光栅解决了航空飞行器在低温恶劣飞行环境中应用问题。同时对细不锈钢管封装的光纤光栅的中心波长突变温度点与其它温度点的反射光谱进行了研究，并详细阐述了突变的原因。航空发动机燃气温度可达到1400℃，现有的各种高温传感器自身存在许多缺点和不足，对光纤光栅高温特性提出了需求。本文对由通讯光纤、高掺硼和高掺锗光纤制备的三类光纤光栅镀金后的高温特性进行了研究，为光纤光栅在高温环境中的应用提供理论依据。实验发现升高到一定的温度时，光纤光栅被破坏即被擦除，并且不同类型的光纤刻写的光纤光栅其失效温度各不相同，同时对光纤光栅高温失效机理作了理论上的解释和分析。
本文还分析了各种结构的光纤光栅压力传感器受力状况和位移形变，通过优化设计确定了传感探头的几何形状和规格。提出了采用膜片制作光纤光栅压力传感器并对基于膜片的不同结构光纤光栅压力传感器进行了高低压性能试验，同时分析了它们各自的优缺点。讨论了强电磁场和剧烈振动等恶劣飞行环境下，光纤光栅敏感压力探头的设计以及关键问题的解决方法和途径。针对航空飞行器恶劣的飞行环境以及其自身结构特点，提出了采用适当的结构和材料以及与软件相结合的方法进行温度补偿，从而真正达到消除温度影响的目的。并研究了光纤光栅压力传感器的线性度、灵敏度、重复稳定性以及疲劳性能。
由于航空飞行器经常处于强振动、高冲击、高过载等十分恶劣工作环境，要求航空机载设备具有很高的可靠性、灵敏度以及卓越的性能。本文还探讨了采用基于DSP的解调方法解决了航空飞行器现有的电类振动传感器易受电磁干扰、无法测量高频信号等问题，提高解调系统可靠性、稳定性以及精度。特别是遇到紧急情况时飞行器能迅速作出反应，避免各种事故的发生。
Aero aircraft is an embodiment of the nation integration and military strength.Its roles become more and more important in the modern war, and function isgreater and more in the systems of the Early Warning, military surveillance,anti-tank, Air Defense System, communication command and so on. Aerocraft hasbeen the most important weapon to win the war initiative and caused the importantand even crucial influence to the course and sequel of the war. Aerocraft usuallygoes wrong because its structure is very precise and complicated; the workingenvironment is extremely harsh; hypersonic flying speed and so on. It is a greatlydispensable and exigent task for safety monitoring of aero aircraft structure.
The pressure in the active Aerocraft has been examined through the pressuremeter or pressure sensor/announciator to carry out distance measuring andcontrolling presently, the temperature has been examined and controlled by thetemperature wrap, the thermocouple, the thermoelectricity, the double sheet metaletc. The sensing theory of the sensors usually is based on the resistance orinductance. They pass the electricity signal to corresponding appearance and othersystem after they take the temperature and the pressure. The examining method ofthe machine-electron is influenced by the harsh flying environment to result in thetemperature and pressure to have low detection precision and reliability, measureerror, suffer from the electro-magnetic interference and so on.
It is very fit for the safety monitoring of aero aircraft structure because FiberBragg grating(FBG) sensors posses a series of merits such as light weigh, smallsize, high precision, the number sensing signal, anti-exploding and being easy toimport integrated processor to process signal which the conventional electrical-basedsensors could not match.
The basic theories and fundamental experiments of techniques of FBG and itsapplication in the harsh aviation environment financially supported by the NationalNatural Science Fund (60537050) and basic Pre-research Project of Committee ofDefense Science and Industry in this thesis,. The purpose is to develop the FBGtemperature and pressure sensors and their health monitoring system, and to usethem in aero aircraft construction.
The low temperature properties of three structures of FBG temperature sensors, which are the bare FBG, FBGs with thin stainless steel tube encapsulationand nickel tube after the fiber with plating gold package, have been researched.There is good linearity of the former two FBGs. FBG temperature sensor withplating full metal package has solved the application problem of the Aerocraft inthe harsh environment. The reflecting spectrogram of FBG with thin stainless steeltube package at the breaking temperature point and other temperature point hasbeen studied. Simultaneously the cause of the center wavelength breaking has beenexpounded in details. The temperature of the Aeroengine is up to 1400℃, there arelots of disadvantages and deficiency of all kinds of the high temperature sensor,and so there is demand for the high temperature properties of the FBG. The hightemperature properties of three types of FBGs which are made of thecommunication, high Boron and Germanium co-doped fiber have been studied inthe thesis, and it provides the theoretical basis for the use of FBG in the hightemperature environment. When the temperature has been heated to the criticaltemperature, FBG will be destroyed, and there are different destroyingtemperatures when FBGs are fabricated with different types fibers. The thermaldegradation of FBGs is carefully experimental explained and analyzed.
The force distributing and the displacement shift of all different structure FBGpressure sensors have been establishedin the thesis, and the geometry figure andspecification of the sensing probes have been confirmed by optimizing design andcontrasting. FBG pressure sensors with different structure based on the diaphragmhave been put forward and carried out an experiment in the high and low pressure,and the merits and demerits of theirs are analyzed. The design of the sensitivepressure probes of FBG pressure sensors and the solving methods and approachofthe key problem have been discussed in the harsh flying environment of the aeroaircraft such as strong electromagnetic fields and acutely vibration. The properstructures, materials and method related to the software have been brought forwardto compensate temperature in allusion to the harsh flying environment of the aeroaircraft and its structure characteristic. Consequently the temperature influence iseliminated really. The linearity, sensitivity, repletion, stability and fatigueperformance of FBG pressure sensors have been investigated.
There must be high reliability and sensitivity, eximious performance for theaircraft airborne equipment. Because the aero aircraft usually suffers from the terribly harsh environment such as the intensively virbration, high impulsion, andhigh over loading and so on, the demodulating methods based on DSP have solvedthe problems of being liable to electro-magnetic interference and unable tomeasuring high frequency signals of the electric vibration sensor in the aeroaircraft.The reliability, stability and precision of the demodulating system havebeen improved. Especially it could respond in the urgent instance so all kinds ofaccidents is avoided to happen.
目前现役飞行器上的压力检测采用直读式压力表或通过压力传感器／信号器进行远距离测量和控制，温度检测和控制采用温包、热电偶、热电阻、双金属片等，这些传感器一般基于电阻或电感测量原理，它们感受温度和压力后通过电缆将电信号传递给对应的指示仪表或其他系统。这一类机电传感检测方法极易受到恶劣飞行环境的影响，导致温度和压力的检测精度低、测量误差大、可靠性差、易受电磁干扰等。
光纤光栅传感器具有传统机电传感器不可比拟的优点如重量轻、体积小、精度高、传感信号为数字、抗电磁干扰、防爆且易于引入综合处理器对信号进行集中处理等等，非常适合航空飞行器的结构安全监测。
本论文在国家自然科学基金(60537050)以及国防科工委预研项目的支持下，从基础理论、基本实验研究了光纤光栅传感技术及其在恶劣航空飞行环境中的应用。目的是研制出光纤光栅温度和压力等传感器及其所构成的健康监测系统，并实现其在航空飞行器中的应用。
本论文重点研究了裸光纤光栅、镍管镀金光纤光栅和细不锈钢管封装的三种不同形式的光纤光栅温度传感器的低温特性，前两种光纤光栅的波长在整个温度变化区间具有良好的线性，镍管镀金光纤光栅解决了航空飞行器在低温恶劣飞行环境中应用问题。同时对细不锈钢管封装的光纤光栅的中心波长突变温度点与其它温度点的反射光谱进行了研究，并详细阐述了突变的原因。航空发动机燃气温度可达到1400℃，现有的各种高温传感器自身存在许多缺点和不足，对光纤光栅高温特性提出了需求。本文对由通讯光纤、高掺硼和高掺锗光纤制备的三类光纤光栅镀金后的高温特性进行了研究，为光纤光栅在高温环境中的应用提供理论依据。实验发现升高到一定的温度时，光纤光栅被破坏即被擦除，并且不同类型的光纤刻写的光纤光栅其失效温度各不相同，同时对光纤光栅高温失效机理作了理论上的解释和分析。
本文还分析了各种结构的光纤光栅压力传感器受力状况和位移形变，通过优化设计确定了传感探头的几何形状和规格。提出了采用膜片制作光纤光栅压力传感器并对基于膜片的不同结构光纤光栅压力传感器进行了高低压性能试验，同时分析了它们各自的优缺点。讨论了强电磁场和剧烈振动等恶劣飞行环境下，光纤光栅敏感压力探头的设计以及关键问题的解决方法和途径。针对航空飞行器恶劣的飞行环境以及其自身结构特点，提出了采用适当的结构和材料以及与软件相结合的方法进行温度补偿，从而真正达到消除温度影响的目的。并研究了光纤光栅压力传感器的线性度、灵敏度、重复稳定性以及疲劳性能。
由于航空飞行器经常处于强振动、高冲击、高过载等十分恶劣工作环境，要求航空机载设备具有很高的可靠性、灵敏度以及卓越的性能。本文还探讨了采用基于DSP的解调方法解决了航空飞行器现有的电类振动传感器易受电磁干扰、无法测量高频信号等问题，提高解调系统可靠性、稳定性以及精度。特别是遇到紧急情况时飞行器能迅速作出反应，避免各种事故的发生。
Aero aircraft is an embodiment of the nation integration and military strength.Its roles become more and more important in the modern war, and function isgreater and more in the systems of the Early Warning, military surveillance,anti-tank, Air Defense System, communication command and so on. Aerocraft hasbeen the most important weapon to win the war initiative and caused the importantand even crucial influence to the course and sequel of the war. Aerocraft usuallygoes wrong because its structure is very precise and complicated; the workingenvironment is extremely harsh; hypersonic flying speed and so on. It is a greatlydispensable and exigent task for safety monitoring of aero aircraft structure.
The pressure in the active Aerocraft has been examined through the pressuremeter or pressure sensor/announciator to carry out distance measuring andcontrolling presently, the temperature has been examined and controlled by thetemperature wrap, the thermocouple, the thermoelectricity, the double sheet metaletc. The sensing theory of the sensors usually is based on the resistance orinductance. They pass the electricity signal to corresponding appearance and othersystem after they take the temperature and the pressure. The examining method ofthe machine-electron is influenced by the harsh flying environment to result in thetemperature and pressure to have low detection precision and reliability, measureerror, suffer from the electro-magnetic interference and so on.
It is very fit for the safety monitoring of aero aircraft structure because FiberBragg grating(FBG) sensors posses a series of merits such as light weigh, smallsize, high precision, the number sensing signal, anti-exploding and being easy toimport integrated processor to process signal which the conventional electrical-basedsensors could not match.
The basic theories and fundamental experiments of techniques of FBG and itsapplication in the harsh aviation environment financially supported by the NationalNatural Science Fund (60537050) and basic Pre-research Project of Committee ofDefense Science and Industry in this thesis,. The purpose is to develop the FBGtemperature and pressure sensors and their health monitoring system, and to usethem in aero aircraft construction.
The low temperature properties of three structures of FBG temperature sensors, which are the bare FBG, FBGs with thin stainless steel tube encapsulationand nickel tube after the fiber with plating gold package, have been researched.There is good linearity of the former two FBGs. FBG temperature sensor withplating full metal package has solved the application problem of the Aerocraft inthe harsh environment. The reflecting spectrogram of FBG with thin stainless steeltube package at the breaking temperature point and other temperature point hasbeen studied. Simultaneously the cause of the center wavelength breaking has beenexpounded in details. The temperature of the Aeroengine is up to 1400℃, there arelots of disadvantages and deficiency of all kinds of the high temperature sensor,and so there is demand for the high temperature properties of the FBG. The hightemperature properties of three types of FBGs which are made of thecommunication, high Boron and Germanium co-doped fiber have been studied inthe thesis, and it provides the theoretical basis for the use of FBG in the hightemperature environment. When the temperature has been heated to the criticaltemperature, FBG will be destroyed, and there are different destroyingtemperatures when FBGs are fabricated with different types fibers. The thermaldegradation of FBGs is carefully experimental explained and analyzed.
The force distributing and the displacement shift of all different structure FBGpressure sensors have been establishedin the thesis, and the geometry figure andspecification of the sensing probes have been confirmed by optimizing design andcontrasting. FBG pressure sensors with different structure based on the diaphragmhave been put forward and carried out an experiment in the high and low pressure,and the merits and demerits of theirs are analyzed. The design of the sensitivepressure probes of FBG pressure sensors and the solving methods and approachofthe key problem have been discussed in the harsh flying environment of the aeroaircraft such as strong electromagnetic fields and acutely vibration. The properstructures, materials and method related to the software have been brought forwardto compensate temperature in allusion to the harsh flying environment of the aeroaircraft and its structure characteristic. Consequently the temperature influence iseliminated really. The linearity, sensitivity, repletion, stability and fatigueperformance of FBG pressure sensors have been investigated.
There must be high reliability and sensitivity, eximious performance for theaircraft airborne equipment. Because the aero aircraft usually suffers from the terribly harsh environment such as the intensively virbration, high impulsion, andhigh over loading and so on, the demodulating methods based on DSP have solvedthe problems of being liable to electro-magnetic interference and unable tomeasuring high frequency signals of the electric vibration sensor in the aeroaircraft.The reliability, stability and precision of the demodulating system havebeen improved. Especially it could respond in the urgent instance so all kinds ofaccidents is avoided to happen.
引文
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