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Iced Aircraft Flight Data for Flight Simulator Validation

机译:用于飞行模拟器验证的冰机飞行数据

摘要

NASA is developing and validating technology to incorporate aircraft icing effects into a flight training device concept demonstrator. Flight simulation models of a DHC-6 Twin Otter were developed from wind tunnel data using a subscale, complete aircraft model with and without simulated ice, and from previously acquired flight data. The validation of the simulation models required additional aircraft response time histories of the airplane configured with simulated ice similar to the subscale model testing. Therefore, a flight test was conducted using the NASA Twin Otter Icing Research Aircraft. Over 500 maneuvers of various types were conducted in this flight test. The validation data consisted of aircraft state parameters, pilot inputs, propulsion, weight, center of gravity, and moments of inertia with the airplane configured with different amounts of simulated ice. Emphasis was made to acquire data at wing stall and tailplane stall since these events are of primary interest to model accurately in the flight training device. Analyses of several datasets are described regarding wing and tailplane stall. Key findings from these analyses are that the simulated wing ice shapes significantly reduced the C , max, while the simulated tail ice caused elevator control force anomalies and tailplane stall when flaps were deflected 30 deg or greater. This effectively reduced the safe operating margins between iced wing and iced tail stall as flap deflection and thrust were increased. This flight test demonstrated that the critical aspects to be modeled in the icing effects flight training device include: iced wing and tail stall speeds, flap and thrust effects, control forces, and control effectiveness.
机译:NASA正在开发和验证将飞机结冰效果纳入飞行训练设备概念演示器的技术。 DHC-6 Twin Otter的飞行模拟模型是根据风洞数据,使用具有和不具有模拟冰的完整规模飞机模型从风洞数据以及先前获取的飞行数据开发而来的。仿真模型的验证需要配置有模拟冰的飞机的额外飞机响应时间历史记录,类似于子尺度模型测试。因此,使用NASA双水獭结冰研究飞机进行了飞行测试。在此飞行测试中进行了500多次各种类型的演习。验证数据包括飞机状态参数,飞行员输入,推进力,重量,重心和惯性矩,其中飞机配置了不同数量的模拟冰。强调要在机翼失速和尾翼失速时获取数据,因为这些事件是在飞行训练设备中精确建模的主要兴趣所在。描述了有关机翼和尾翼失速的几个数据集的分析。这些分析的主要发现是,当机翼偏转30度或更大时,模拟的翼冰形状会显着降低C max,而模拟的尾冰会导致电梯控制力异常和尾翼失速。随着襟翼偏转和推力的增加,这有效地降低了冰翼和尾冰失速之间的安全运行裕度。这次飞行测试表明,要在结冰效果飞行训练装置中建模的关键方面包括:机翼和机尾失速速度,襟翼和推力效果,控制力和控制效果。

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