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A Novel Ultrasonic Method for Locating the Boundary Layer Transition Region on a Hypersonic Vehicle

机译:一种新型超声波方法,用于定位超声波车辆上的边界层过渡区域

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Knowledge of where air flowing across a body transitions from laminar flow to turbulent flow can provide numerous benefits to air vehicle design, thermal protection system design, and air vehicle in-flight control. We propose a novel measurement system that leverages the hypersonic body-surface heating profile to locate the boundary layer transition region. Ultrasonic sensing as the measurement strategy to detect localized changes in aeroshell temperature is suggested. For a localization system using ultrasonic transducers, the sensors would be located on the inside surface of the aeroshell away from the harsh external conditions. Consequently, the phenomenon that is being measured is not disturbed and the sensor is not exposed to deleterious environments. We hypothesize that incorporating state estimation to locate the transition region will require fewer sensors than otherwise possible. The proposed method involves a forward conduction solution and an inverse procedure based on the extended Kalman filter. Development of the proposed measurement method based on ultrasound and the extended Kalman filter is accomplished using simple, controlled experiments involving concentrated high heat flux sources on a large flat metal plate. In this work, the proposed heating source localization method is detailed, results are presented from forward conduction solution development and flat plate experimentation with a high heat flux point source, and extended Kalman filter convergence behavior is compared for heating source locations inside and outside a four-element ultrasonic transducer sensor array. The inverse procedure is able to converge to the correct heating source location if the heating source is located inside the sensor array but is unable to converge to the correct location if the heating source is located outside of the array. A key finding is the need to design a sensor array with numerous propagation paths and with paths near the heating source location.
机译:知识在流过流动流过流动流向湍流的情况下,可以为空气车辆设计,热保护系统设计和飞行飞行控制提供众多益处。我们提出了一种新的测量系统,其利用超声波体表面加热曲线来定位边界层过渡区域。提出了超声波感测,作为检测氧气室温度的局部变化的测量策略。对于使用超声换能器的本地化系统,传感器将位于雾气的内表面远离苛刻的外部条件。因此,测量的现象不会受到干扰,并且传感器不会暴露于有害环境。我们假设包含状态估计以定位过渡区域将需要比其他方式更少的传感器。该方法涉及前向传导解决方案和基于扩展卡尔曼滤波器的逆过程。基于超声波和扩展卡尔曼滤波器的所提出的测量方法的开发是使用涉及在大型扁平金属板上的浓缩高热通量源的简单,受控实验完成的。在这项工作中,详细说明了所提出的加热源定位方法,结果是通过前进导通溶液的开发和具有高热通量点源的平板实验,并将扩展的卡尔曼滤波器收敛行为进行了比较,以便在四个外部和外部加热源位置-Element超声波换能器传感器阵列。如果加热源位于传感器阵列内,则反向过程能够收敛到正确的加热源位置,但如果加热源位于阵列的外部,则无法收敛到正确的位置。一个关键发现是需要设计具有许多传播路径的传感器阵列,以及在加热源位置附近的路径。

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