舰载机拦阻装置刚柔耦合系统建模及动态特性研究
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摘要
飞机拦阻系统是航空母舰上重要的辅助设备之一，是确保飞机安全着舰的关键设备。飞机在航空母舰上降落时，从飞机尾钩挂索到完全停止在甲板上仅需要3-4秒，拦阻系统在极短暂的时间内将飞机巨大的动能完全吸收并转化成热能释放掉。因此，拦阻系统的工作状态将直接影响到飞机着舰时的拦停距离、过载和拦阻索承受的拦阻力等与拦阻效果相关的性能指标。
目前，国外对拦阻系统的研究主要采用理论分析和实验数据对比的方法，已形成相对成熟的研究体系，但可供查询的资料极少；国内对拦阻系统的研究，已进入工程应用阶段，但由于目前该系统投入使用的时间较短，而拦阻系统结构的复杂性和工作过程的特殊性，实体机的数据采样过程较为困难，这就需要在研究其工作特性之前掌握其基本性能。目前对飞机拦阻系统动态特性的研究一般采用理论分析的方法，没有考虑钢索（包括拦阻索和传动索）的弹性性能、拦阻索与拦阻机构的耦合作用对拦阻系统动态特性的影响，从而导致拦阻系统的许多重要特性无法得到较准确的定量分析，以致其动态特性与实际存在较大差距。多体系统动力学为解决这种多维、时变、高度非线性的复杂动力学问题提供了一种有效的理论分析方法，因此，开展对飞机拦阻刚柔耦合系统动力学研究具有十分重要的理论意义和实际工程价值。
论文对刚柔耦合系统动力学相关理论进行了论述，提出用多柔体动力学方法建立飞机拦阻系统的刚柔耦合动力学模型的思路。考虑到飞机挂索时飞机尾钩对拦阻索的冲击作用以及钢索的振动对拦阻过程的影响，通过一种离散的梁单元建立具有弹性的钢索模型，在模型中不考虑梁单元的弯曲和扭转特性，仅考虑梁单元的拉伸性能；拦阻系统通过缠绕在各支撑和导向滑轮上的钢索传递飞机动能，模型中利用罚函数法解决钢索与滑轮体之间以及动滑轮组中滚柱与内/外滚道之间的接触/碰撞问题。
以美国海军正在使用的MK7-3型拦阻系统为例，通过有限元软件ANSYS/DYNA建立其的三维有限元实体模型，根据飞机对中挂索仿真试验，将相关参数的仿真数据与MIL-STD-2066试验数据对比，验证模型的正确性。基于仿真试验数据，对模型的动态特性进行分析，研究拦阻过程中飞机的拦停距离、过载、拦阻索拉力等相关参数之间的内在联系；将波动传载理论与仿真试验相结合，分析飞机尾钩挂索后应力波在拦阻索中的传播过程，以及应力波在甲板滑轮处的反射与传播。研究钢索的冲击作用对拦阻力的影响，以及在动滑轮组运动过程中，钢索松弛现象对拦阻系统工作状态的影响。
在飞机着舰拦阻过程中，由于飞机型号不同，飞机质量和着舰速度差异很大，为了确保飞机安全着舰，需要调整拦阻装置的拦阻能力，以适应不同着舰状态的飞机。文中详细分析了MK7-3型拦阻装置中定长冲跑系统的工作原理，从理论上推导了锥阀节流面积和凸轮型线联合控制方法，并分析了对于同种着舰状态下的飞机，调节重量选择器的值，定长冲跑系统对拦阻系统动态特性的影响；同时分析了甲板滑轮缓冲系统和尾端缓冲系统对拦阻系统动态特性的影响。
飞机对中拦阻是一种理想的拦阻情况，在实际的拦阻着舰过程中，飞机或多或少存在偏心偏航情况。本文基于拦阻系统的有限元模型，研究了飞机偏心偏航这类不对称着舰情况下拦阻系统主要机构的动态特性，包括飞机纵向和横向的动态特性，甲板滑轮缓冲系统的动态特性。
Aircraft arresting system is one of the important auxiliary equipment on the aircraftcarrier, and it is the key equipment of ship for ensures the aircraft landing safe. The aircraftlanding on the aircraft carrier, which from the aircraft tail hook hanging cable to completelystop on the deck only needs3-4seconds. Arresting system absorbed huge kinetic energy ofthe aircraft and converted into heat in a very short time. Therefore, the working state ofarresting system will directly affect the aircraft landing performance indicators, such asstopping distance, overload and arresting force.
At present, research on arresting system abroad mainly adopting the method of theoryanalysis and empirical data, has formed a mature research system. The domestic study onarresting system is still in the initial stage, the research on the dynamic characteristics ofaircraft arresting system generally adopts the method of theoretical analysis, withoutconsidering the elastic properties of arresting cable (including arresting cable andtransmission cable), the arresting cables and arresting mechanism coupling on the dynamiccharacteristics of arresting system. Thus lead many important features of the arresting systemunable obtain a more precise quantitative analysis to its dynamic characteristics and there is abig gap with actually. Multibode system dynamics for solve the multi-dimensional,time-varying, nonlinear dynamics problem provides an effective theoretical analysis method;therefore, it has important theoretical and practical engineering value for study therigid-flexible coupling system dynamics of aircraft.
This paper discusses the rigid-flexible coupling dynamic theory, and put forward the ideato establish rigid-flexible coupling dynamics model of aircraft arresting system with flexiblemultibody dynamics method. Considering the influence of aircraft tail hook impact on cableand cable vibration on the process of arresting, the flexible cable model is constituted bydiscrete beam elements. The model does not consider the beam bending, torsion andcompression properties, only considering the tensile properties of beam element. Aircraftarresting system through the cable which winding in the support and guide pulley transferaircraft kinetic energy. The model using penalty function method to solve the contact betweenthe cable and pulley body, and between the movable pulley block rollers and inner/outerraceway contact/impact problems.
Taking MK7-3arresting system as an example, the three-dimensional finite elementmodel of arresting system is established. According to the simulation test of aircraft hanging on cable, comparing the simulation data of related parameters and the actual experimentaldata, verify the correctness of the model. Simulation based on test data to analyze thedynamic characteristics of the model, research aircraft stopping distance, overload and cableforce relationship in the parameters. The fluctuation of theory and simulation test combined,to analyse the wave propagation in the cable, and stress wave reflection and transmission onthe deck pulley. The process of moving block movement, and the influence of cable slack toarresting system working condition.
In aircraft arresting process, due to the different aircraft types, aircraft mass and landingspeed is great difference. In order to ensure the safety of aircraft landing, it is need to adjustthe arresting device blocking ability to adapt to different state of aircraft landing. In the paper,a detailed analysis of the working principle of fixed run out system of MK7-3arresting device,theoretically derived from the joint control of the cutting area of the poppet valve and camprofile, and analyzed for the same kind of landing state aircraft, adjust the weight value of theselector, the influence of fixed run out system on the arresting system dynamic characteristics.While analysis the influence of the deck pulley buffer system and the end buffer system toarresting system.
The aircraft landing on the centrality is an ideal arresting situation, but in actual processof arresting landing,the aircraft more or less off-center or yaw. This paper is based on thefinite element model of the arresting system, to analysis the dynamic characteristics ofarresting system in these conditions. Including the dynamic characteristics of the aircraftlongitudinal and transverse, and the deck pulley buffer system dynamic characteristics.
目前，国外对拦阻系统的研究主要采用理论分析和实验数据对比的方法，已形成相对成熟的研究体系，但可供查询的资料极少；国内对拦阻系统的研究，已进入工程应用阶段，但由于目前该系统投入使用的时间较短，而拦阻系统结构的复杂性和工作过程的特殊性，实体机的数据采样过程较为困难，这就需要在研究其工作特性之前掌握其基本性能。目前对飞机拦阻系统动态特性的研究一般采用理论分析的方法，没有考虑钢索（包括拦阻索和传动索）的弹性性能、拦阻索与拦阻机构的耦合作用对拦阻系统动态特性的影响，从而导致拦阻系统的许多重要特性无法得到较准确的定量分析，以致其动态特性与实际存在较大差距。多体系统动力学为解决这种多维、时变、高度非线性的复杂动力学问题提供了一种有效的理论分析方法，因此，开展对飞机拦阻刚柔耦合系统动力学研究具有十分重要的理论意义和实际工程价值。
论文对刚柔耦合系统动力学相关理论进行了论述，提出用多柔体动力学方法建立飞机拦阻系统的刚柔耦合动力学模型的思路。考虑到飞机挂索时飞机尾钩对拦阻索的冲击作用以及钢索的振动对拦阻过程的影响，通过一种离散的梁单元建立具有弹性的钢索模型，在模型中不考虑梁单元的弯曲和扭转特性，仅考虑梁单元的拉伸性能；拦阻系统通过缠绕在各支撑和导向滑轮上的钢索传递飞机动能，模型中利用罚函数法解决钢索与滑轮体之间以及动滑轮组中滚柱与内/外滚道之间的接触/碰撞问题。
以美国海军正在使用的MK7-3型拦阻系统为例，通过有限元软件ANSYS/DYNA建立其的三维有限元实体模型，根据飞机对中挂索仿真试验，将相关参数的仿真数据与MIL-STD-2066试验数据对比，验证模型的正确性。基于仿真试验数据，对模型的动态特性进行分析，研究拦阻过程中飞机的拦停距离、过载、拦阻索拉力等相关参数之间的内在联系；将波动传载理论与仿真试验相结合，分析飞机尾钩挂索后应力波在拦阻索中的传播过程，以及应力波在甲板滑轮处的反射与传播。研究钢索的冲击作用对拦阻力的影响，以及在动滑轮组运动过程中，钢索松弛现象对拦阻系统工作状态的影响。
在飞机着舰拦阻过程中，由于飞机型号不同，飞机质量和着舰速度差异很大，为了确保飞机安全着舰，需要调整拦阻装置的拦阻能力，以适应不同着舰状态的飞机。文中详细分析了MK7-3型拦阻装置中定长冲跑系统的工作原理，从理论上推导了锥阀节流面积和凸轮型线联合控制方法，并分析了对于同种着舰状态下的飞机，调节重量选择器的值，定长冲跑系统对拦阻系统动态特性的影响；同时分析了甲板滑轮缓冲系统和尾端缓冲系统对拦阻系统动态特性的影响。
飞机对中拦阻是一种理想的拦阻情况，在实际的拦阻着舰过程中，飞机或多或少存在偏心偏航情况。本文基于拦阻系统的有限元模型，研究了飞机偏心偏航这类不对称着舰情况下拦阻系统主要机构的动态特性，包括飞机纵向和横向的动态特性，甲板滑轮缓冲系统的动态特性。
Aircraft arresting system is one of the important auxiliary equipment on the aircraftcarrier, and it is the key equipment of ship for ensures the aircraft landing safe. The aircraftlanding on the aircraft carrier, which from the aircraft tail hook hanging cable to completelystop on the deck only needs3-4seconds. Arresting system absorbed huge kinetic energy ofthe aircraft and converted into heat in a very short time. Therefore, the working state ofarresting system will directly affect the aircraft landing performance indicators, such asstopping distance, overload and arresting force.
At present, research on arresting system abroad mainly adopting the method of theoryanalysis and empirical data, has formed a mature research system. The domestic study onarresting system is still in the initial stage, the research on the dynamic characteristics ofaircraft arresting system generally adopts the method of theoretical analysis, withoutconsidering the elastic properties of arresting cable (including arresting cable andtransmission cable), the arresting cables and arresting mechanism coupling on the dynamiccharacteristics of arresting system. Thus lead many important features of the arresting systemunable obtain a more precise quantitative analysis to its dynamic characteristics and there is abig gap with actually. Multibode system dynamics for solve the multi-dimensional,time-varying, nonlinear dynamics problem provides an effective theoretical analysis method;therefore, it has important theoretical and practical engineering value for study therigid-flexible coupling system dynamics of aircraft.
This paper discusses the rigid-flexible coupling dynamic theory, and put forward the ideato establish rigid-flexible coupling dynamics model of aircraft arresting system with flexiblemultibody dynamics method. Considering the influence of aircraft tail hook impact on cableand cable vibration on the process of arresting, the flexible cable model is constituted bydiscrete beam elements. The model does not consider the beam bending, torsion andcompression properties, only considering the tensile properties of beam element. Aircraftarresting system through the cable which winding in the support and guide pulley transferaircraft kinetic energy. The model using penalty function method to solve the contact betweenthe cable and pulley body, and between the movable pulley block rollers and inner/outerraceway contact/impact problems.
Taking MK7-3arresting system as an example, the three-dimensional finite elementmodel of arresting system is established. According to the simulation test of aircraft hanging on cable, comparing the simulation data of related parameters and the actual experimentaldata, verify the correctness of the model. Simulation based on test data to analyze thedynamic characteristics of the model, research aircraft stopping distance, overload and cableforce relationship in the parameters. The fluctuation of theory and simulation test combined,to analyse the wave propagation in the cable, and stress wave reflection and transmission onthe deck pulley. The process of moving block movement, and the influence of cable slack toarresting system working condition.
In aircraft arresting process, due to the different aircraft types, aircraft mass and landingspeed is great difference. In order to ensure the safety of aircraft landing, it is need to adjustthe arresting device blocking ability to adapt to different state of aircraft landing. In the paper,a detailed analysis of the working principle of fixed run out system of MK7-3arresting device,theoretically derived from the joint control of the cutting area of the poppet valve and camprofile, and analyzed for the same kind of landing state aircraft, adjust the weight value of theselector, the influence of fixed run out system on the arresting system dynamic characteristics.While analysis the influence of the deck pulley buffer system and the end buffer system toarresting system.
The aircraft landing on the centrality is an ideal arresting situation, but in actual processof arresting landing,the aircraft more or less off-center or yaw. This paper is based on thefinite element model of the arresting system, to analysis the dynamic characteristics ofarresting system in these conditions. Including the dynamic characteristics of the aircraftlongitudinal and transverse, and the deck pulley buffer system dynamic characteristics.
引文
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