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Evaluation of flying helicopter simulator noseboom correction coefficients

机译：飞行直升机模拟器前臂校正系数的评估

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摘要

The EC135 flying helicopter simulator of DLR is equipped with noseboom-mounted sensors to enable measurements relatively unperturbed by rotor downwash effects. Remaining downwash disturbances on pressure and airflow angles measurements are compensated with correction coefficients, derived with the simultaneous calibration of aircraft data system (SCADS) technique. The purpose of this paper is to evaluate the quality of correction coefficients derived using estimated wind by comparing the difference in wind estimation from three different objective functions and two different optimization routines. The results obtained from the SCADS technique are also verified with accurate wind measurements close to the helicopter flight path from position error correction tower flyby maneuvers. The results show that the lower bound of the range in which airspeed can be detected via dynamic pressure measurements has been expanded from 30 to 16.2 kt.
机译：DLR的EC135飞行直升机模拟器配备了前吊臂传感器，可以使测量不受转子下冲效应的干扰。压力和气流角度测量中剩余的冲洗干扰会通过飞机数据系统（SCADS）技术的同时校准得出的校正系数进行补偿。本文的目的是通过比较来自三个不同目标函数和两个不同优化例程的风估算差异，来评估使用估算风得出的校正系数的质量。从SCADS技术获得的结果也通过位置误差校正塔架飞越操纵在接近直升机飞行路径的准确风速测量得到了验证。结果表明，通过动态压力测量可以检测到空速的范围的下限已从30 kt扩大到16.2 kt。

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