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1. 发明授权

US5628565A Multifunctional air data sensing probes 失效
标题翻译：多功能空气数据传感探头
公开(公告)号：US5628565A
公开(公告)日：1997-05-13
申请号：US460103
申请日：1995-06-02
申请人： Floyd W. Hagen , Gregg A. Hohenstein , John A. Severson , Pennelle J. Trongard
发明人： Floyd W. Hagen , Gregg A. Hohenstein , John A. Severson , Pennelle J. Trongard
IPC分类号： G01K13/02 , G01P5/165 , G01C21/00 , G01K1/14
CPC分类号： G01K13/028 , G01K13/02 , G01P5/165
摘要： An aerodynamic air data sensing probe adapted for mounting to an air vehicle and capable of generating signals related to a fluid flowing relative to the air vehicle. A fluid inlet positioned on a first end of the strut faces generally transverse to the fluid flow selectively admits fluid to an internal strut cavity due to a pressure differential thereacross. In operation, the pressure differential forms between the first end surface of the aerodynamically-shaped, forward-inclined strut and probe exhaust ports. A temperature sensing element disposed in the internal strut cavity registers the temperature of the fluid and the sensed fluid is expelled from the internal strut cavity through the exhaust ports. In another embodiment, a barrel-shaped probe head adapted to sense fluid pressure connects to a portion of the leading edge of the strut to form an aerodynamic multifunction air data sensing probe.
摘要翻译：一种空气动力学空气数据感测探头，其适于安装到空中车辆并且能够产生与相对于空中交通工具流动的流体相关的信号。位于支柱的第一端上的流体入口大致横向于流体流，由于其上的压力差，选择性地将流体引入内部支柱腔。在操作中，在空气动力学形状的前倾斜支柱和探头排气口的第一端面之间形成压差。设置在内部支柱空腔中的温度感测元件记录流体的温度，并且所检测的流体通过排气口从内部支柱腔排出。在另一个实施例中，适于感测流体压力的桶形探针头连接到支柱前缘的一部分，以形成空气动力学多功能空气数据传感探针。

2. 发明授权

US5466067A Multifunctional air data sensing probes 失效
标题翻译：多功能空气数据传感探头
公开(公告)号：US5466067A
公开(公告)日：1995-11-14
申请号：US122222
申请日：1993-09-17
申请人： Floyd W. Hagen , Gregg A. Hohenstein , John A. Severson , Pennelle J. Trongard
发明人： Floyd W. Hagen , Gregg A. Hohenstein , John A. Severson , Pennelle J. Trongard
IPC分类号： G01K13/02 , G01P5/165 , G01K1/14
CPC分类号： G01K13/028 , G01K13/02 , G01P5/165
摘要： An aerodynamic air data sensing probe adapted for mounting to an air vehicle and capable of generating signals related to a fluid flowing relative to the air vehicle. A fluid inlet positioned on a first end of the strut faces generally transverse to the fluid flow selectively admits fluid to an internal strut cavity due to a pressure differential thereacross. In operation, the pressure differential forms between the first end surface of the aerodynamically-shaped, forward-inclined strut and probe exhaust ports. A temperature sensing element disposed in the internal strut cavity registers the temperature of the fluid and the sensed fluid is expelled from the internal strut cavity through the exhaust ports. In another embodiment, a barrel-shaped probe head adapted to sense fluid pressure connects to a portion of the leading edge of the strut to form an aerodynamic multifunction air data sensing probe.
摘要翻译：一种空气动力学空气数据感测探头，其适于安装到空中车辆并且能够产生与相对于空中交通工具流动的流体相关的信号。位于支柱的第一端上的流体入口大致横向于流体流，由于其上的压力差，选择性地将流体引入内部支柱腔。在操作中，在空气动力学形状的前倾斜支柱和探头排气口的第一端面之间形成压差。设置在内部支柱空腔中的温度感测元件记录流体的温度，并且所检测的流体通过排气口从内部支柱腔排出。在另一个实施例中，适于感测流体压力的桶形探针头连接到支柱前缘的一部分，以形成空气动力学多功能空气数据传感探针。

3. 发明授权

US5731507A Integral airfoil total temperature sensor 失效
标题翻译：整体机翼总温度传感器
公开(公告)号：US5731507A
公开(公告)日：1998-03-24
申请号：US250342
申请日：1994-05-27
申请人： Floyd W. Hagen , Gregg A. Hohenstein , Pennelle J. Trongard
发明人： Floyd W. Hagen , Gregg A. Hohenstein , Pennelle J. Trongard
IPC分类号： B64D43/02 , G01K13/02 , G01M9/06 , G01P5/165 , G01C21/00
CPC分类号： G01K13/028 , G01K13/02 , G01P5/165
摘要： An air data sensing probe adapted for mounting to an aerodynamically-shaped airfoil or strut attached to an air vehicle. An inlet port located near the leading edge of the strut admits fluid, to a first cavity and then, in turn, to a second cavity, so that the total temperature of the fluid may be measured and a signal related thereto conveyed to suitable flight control gear. A first exhaust port located generally opposite the inlet port allows entrained particles to exit the probe and boundary layer fluid evacuation apertures formed through the strut across the interface between the two cavities permit only a substantially particle-free core sample of fluid on the temperature sensing element. The secondary cavity couples to the primary cavity at an angle so that inertial separation of entrained particles results. In a second embodiment, the air data sensing probe connects to a barrel-shaped probe head so that multiple parameters related to the fluid can be measured, such as total pressure, Pt, static pressure, Ps, and total temperature, Tt, of a fluid flowing relative to the air vehicle as well as angle-of-attack (AOA) of the air vehicle relative to the fluid.
摘要翻译：一种空气数据传感探头，其适于安装在附着于空中飞行器的空气动力学形状的翼型件或支柱上。位于支柱前缘附近的入口允许流体到达第一空腔，然后又进入第二空腔，从而可以测量流体的总温度，并将与之相关的信号传送到合适的飞行控制齿轮。位于大致与入口端相对的第一排气口允许夹带的颗粒离开探针，并且穿过跨过两个空腔之间的界面的支柱形成的边界层流体排出孔仅允许温度感测元件上的基本上无颗粒的流体样品。次级腔以一定角度耦合到主腔，从而导致夹带颗粒的惯性分离。在第二实施例中，空气数据感测探头连接到桶形探针头，使得可以测量与流体相关的多个参数，例如总压力，Pt，静压，Ps和总温度Tt 流体相对于飞行器流动的流体以及相对于流体的飞行器的攻角（AOA）。

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