Extracting Unmeasured Parameters Based on Quick Access Recorder Data Using Parameter-Estimation Method
Extracting Unmeasured Parameters Based on Quick Access Recorder Data Using Parameter-Estimation Method
复制标题
使用参数估计方法基于快速访问记录仪数据提取未测量参数
DOI：
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发表时间：
2013
期刊：
影响因子：
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通讯作者：
F. Holzapfel
中科院分区：
文献类型：
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作者：
J. Sembiring;L. Drees;F. Holzapfel
本文介绍了民用飞机快速访问记录仪数据参数估计方法的实现。使用的估计技术是基于最大似然原理的输出误差法和经典的最小二乘法。该算法的实施是通过执行数据兼容性检查或所谓的飞行路径重建来开始的，其目的是确定偏差/系统仪器误差并生成准确的飞机状态。研究发现，与未校正的测量数据相比，在参数估计过程中使用偏差校正的测量数据将提高参数的准确性。然后，数据兼容性检查的结果用于估计地球框架中未在数据记录器中测量或提供的风分量。该估计还通过计算基于时间历史的升力和阻力系数来完成，其中参数不是在数据记录器中测量的。还提出了进近飞行期间由于襟翼偏转而导致的升力和阻力系数增量的估计。本文参数估计方法的最后一次实现是在地面运行阶段进行的。在此阶段，还会估计并呈现升力系数、扰流板偏转引起的阻力系数、推力和摩擦系数等参数。进行匹配证明是为了验证估计的参数。发现本文使用的两种估计方法都成功地估计了足够的结果。本文使用的数据来自空客 340-600 的一次航班。
This paper presents the implementation of parameter-estimation method on civil aircraft Quick Access Recorder Data. The estimation techniques used are the output error method which works based on maximum likelihood principle and also the classical least square method. The implementation of the algorithm is started by performing data compatibility check or so called flight path reconstruction which aims at determining bias/systematic instrument errors and generating accurate aircraft states. It is found that using the bias corrected measurement data in the parameter estimation process will increase the accuracy of the parameters compare to that of uncorrected measurement data. The results from data compatibility check are then used to estimate the wind component in Earth frame which is not measured or provided in the data recorder. The estimation is also done by computing lift and drag coefficients time-history based in which the parameters are not measured in the data recorder. Estimation of lift and drag coefficients increment due to flap deflection during approach flight is also presented. The last implementation of parameter estimation method in this paper is conducted on the ground-run phase. In this phase, parameters such as lift coefficient, drag coefficient due to spoiler deflection, thrust and friction coefficient are estimated and presented as well. Proof of match is done in order to validate the estimated parameters. It is found that the two estimation methods which used in this paper have succeeded in estimating adequate results. The data used in this paper comes from a flight of Airbus 340-600.