Real-Time Stability and Control Derivative Extraction From F-15 Flight Data
Real-Time Stability and Control Derivative Extraction From F-15 Flight Data
复制标题
从 F-15 飞行数据中提取实时稳定性和控制导数
DOI：
10.2514/6.2003-5701
复制
发表时间：
2003
期刊：
影响因子：
--
通讯作者：
E. Morelli
中科院分区：
文献类型：
--
作者：
Mark S. Smith;T. Moes;E. Morelli
使用实时频域方程误差参数识别（PID）技术来估计飞行数据的稳定性和控制导数。正在研究这项技术，以支持 NASA（美国国家航空航天局）、学术界和工业界目前正在开发的自适应控制系统概念。本报告描述了本研究中使用的基本实时算法以及作为间接自适应控制系统一部分的船上使用的实施问题。讨论了自动评估 PID 结果的置信度测量系统。给出了使用改进的 F-15 飞机的飞行数据计算的结果。测试演习包括飞行员输入双联和多种飞行条件下的自动输入。将估计导数与空气动力学模型预测进行比较。数据表明，本研究中使用的实时 PID 性能良好，足以用于机载参数估计。对于合适的测试输入，参数估计迅速收敛到足够的准确度。所设计的信心措施取得了一定的成功。
A real-time, frequency-domain, equation-error parameter identification (PID) technique was used to estimate stability and control derivatives from flight data. This technique is being studied to support adaptive control system concepts currently being developed by NASA (National Aeronautics and Space Administration), academia, and industry. This report describes the basic real-time algorithm used for this study and implementation issues for onboard usage as part of an indirect-adaptive control system. A confidence measures system for automated evaluation of PID results is discussed. Results calculated using flight data from a modified F-15 aircraft are presented. Test maneuvers included pilot input doublets and automated inputs at several flight conditions. Estimated derivatives are compared to aerodynamic model predictions. Data indicate that the real-time PID used for this study performs well enough to be used for onboard parameter estimation. For suitable test inputs, the parameter estimates converged rapidly to sufficient levels of accuracy. The devised confidence measures used were moderately successful.