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81. 发明授权

US5137353A Angular displacement measuring device 失效
标题翻译：角位移测量装置
公开(公告)号：US5137353A
公开(公告)日：1992-08-11
申请号：US774490
申请日：1991-10-10
申请人： H. Lee B. Seegmiller
发明人： H. Lee B. Seegmiller
IPC分类号： G01B11/16 , G01M9/06
CPC分类号： G01M9/06 , G01B11/168
摘要： A system for measuring the angular displacement of a point of interest on a structure, such as aircraft model within a wind tunnel, includes a source of polarized light located at the point of interest. A remote detector arrangement detects the orientation of the plane of the polarized light received from the source and compares this orientation with the initial orientation to determine the amount or rate of angular displacement of the point of interest. The detector arrangement comprises a rotating polarizing filter and a dual filter and light detector unit. The latter unit comprises an inner aligned filter and photodetector assembly which is disposed relative to the periphery of the polarizer so as to receive polarized light passing the polarizing filter and an outer aligned filter and photodetector assembly which recives the polarized light directly, i.e., without passing through the polarizing filter. The purpose of the unit is to compensate for the effects of dust, fog and the like. A polarization preserving optical fiber conducts polarized light from a remote laser source to the point of interest.
摘要翻译：用于测量诸如风洞内的飞行器模型的结构上的兴趣点的角位移的系统包括位于感兴趣点处的偏振光源。远程检测器装置检测从源接收的偏振光的平面的取向，并将该取向与初始取向进行比较，以确定感兴趣点的角位移量或速率。检测器装置包括旋转偏振滤光器和双滤光器和光检测器单元。后一单元包括内部对准的滤光器和光电检测器组件，其相对于偏振器的周边设置，以便接收通过偏振滤光器的偏振光和外部对准的滤光器和光电检测器组件，其直接接收偏振光，即不经过通过偏振滤光片。该单元的目的是补偿灰尘，雾等的影响。偏振保留光纤将来自远程激光源的偏振光传导到感兴趣点。

82. 发明授权

US5036480A Method and apparatus for simulating microburst windshears 失效
标题翻译：用于模拟微爆风切变风切变的方法和装置
公开(公告)号：US5036480A
公开(公告)日：1991-07-30
申请号：US492000
申请日：1990-03-12
申请人： Terry L. Zweifel , J. Rene Barrios
发明人： Terry L. Zweifel , J. Rene Barrios
IPC分类号： G01M9/06
CPC分类号： G01M9/06
摘要： A method and apparatus for simulating a windshear. A vortex is modelled in terms of a family of concentric streamlines and the position of an aircraft is defined with respect to the vortex as the aircraft traverses a reference plane. Four or more vortices are used to generate streamlines which match those encountered in an actual microburst. Each vortex placed above the simulated ground level is matched by a vortex of equal strength but opposite rotation placed below the simulated ground level at a distance equal but opposite to the height of the vortex above the ground. Strengths, distance from the vortex center, and height of the vortex may be programmed by the user. The high degree of flexibility permits accurate reproduction of the winds generated by actual microbursts for testing and developing microburst detection devices. The use of an algorithm which may be dynamically varied as a function of aircraft position obviates the need for simulating by discrete windshear magnitude as in conventional predetermined windshear tables and minimizes data storage requirements.
摘要翻译：一种用于模拟风切变的方法和装置。涡流以同心流线系列为模型，当飞行器穿过参考平面时，飞行器的位置相对于涡流来定义。使用四个或更多涡旋产生与实际微爆中遇到的流线相匹配的流线。放置在模拟地面以上的每个涡流通过相等强度的涡旋相匹配，但相反的旋转位于模拟地面下方，距离地面上方涡流高度相等但相反的距离处。强度，与涡流中心的距离以及涡流的高度可由用户编程。高灵活性允许精确再现由实际微爆发生的风，用于测试和开发微爆探测装置。使用可以作为飞机位置的函数而动态变化的算法消除了如常规预定风切变表中的离散风切变幅度的模拟的需要，并且使数据存储要求最小化。

83. 发明授权

US4804154A Passive aerodynamic load mitigation system 失效
标题翻译：被动气动负荷减轻系统
公开(公告)号：US4804154A
公开(公告)日：1989-02-14
申请号：US165381
申请日：1988-02-29
申请人： James M. Davis
发明人： James M. Davis
IPC分类号： G01M9/06 , B64C1/36
CPC分类号： G01M9/06
摘要： A passive load mitigation system for supporting transducers on a body moving through a fluid stream is described. According to the invention, a streamlined aerodynamic surface for supporting the transducers is attached to the body via a pivot axis. The axis supports the surface in a torsionally unrestrained manner in at least one rotational degree of freedom about the pivot axis. Therefore, as the body moves through the fluid stream, the surface remains substantially parallel to the plane of the stream. Aerodynamic stability is ensured by forming the surface with substantially trapezoidal or parallelogram shaped sidewalls and by mounting the surface on the pivot axis such that the surface's aerodynamic center is located downstream of the pivot axis. Flutter is prevented or substantially reduced by increasing the surface's bending stiffness or by incorporating ballast weights on a tip pod attached to a portion of the surface.
摘要翻译：描述了用于在移动通过流体流的身体上支撑换能器的被动负载减轻系统。根据本发明，用于支撑换能器的流线型空气动力学表面通过枢转轴线附接到主体。该轴线以扭转无限制的方式以关于枢转轴线的至少一个旋转自由度的方式支撑表面。因此，当身体移动通过流体流时，表面基本平行于流平面。通过以基本上梯形或平行四边形形状的侧壁形成表面并且通过将表面安装在枢转轴线上使得表面的空气动力学中心位于枢转轴线的下游来确保空气动力学稳定性。通过增加表面的弯曲刚度或通过将附着在表面的一部分上的尖端容器上并入压载重量来防止或显着地减小振动。

84. 发明授权

US4750355A Wind-velocity controlling apparatus for simulating self-propelled vehicle velocity 失效
标题翻译：用于模拟自行车速度的风速控制装置
公开(公告)号：US4750355A
公开(公告)日：1988-06-14
申请号：US23459
申请日：1987-03-09
申请人： Sadayuki Urabe , Fumio Kakizaki
发明人： Sadayuki Urabe , Fumio Kakizaki
IPC分类号： G01M17/007 , G01M9/04 , G01M9/06 , G01M99/00 , G01M9/00
CPC分类号： G01M9/06 , G01M9/04
摘要： In conducting an environmental test of a vehicle, the vehicle is housed in the testing chamber and in which the vehicle is subjected to test simulating external environmental various conditions. In such test, it is often required to keep the vehicle stationary while varying a temperature and a humidity of the testing chamber. In such a case, the testing chamber provided with a by-pass air duct at a position near a ceiling portion of the testing chamber enables the vehicle being tested to be prevented from being subjected to an air flow caused by air-conditioning operation of the testing chamber, which improves a test in accuracy in case that the test must be conducted at a desired temperature/humidity condition.
摘要翻译：在进行车辆的环境试验时，车辆被容纳在测试室中，车辆经受模拟外部环境的各种条件的测试。在这种测试中，通常需要在改变测试室的温度和湿度的同时保持车辆静止。在这种情况下，在靠近测试室顶部的位置处设置有旁通空气管道的测试室使得能够防止被测试的车辆受到由空调操作引起的空气流动测试室，如果测试必须在所需的温度/湿度条件下进行，则可以提高测试精度。

85. 发明授权

US4532801A Method and apparatus for determining small magnitude fluid-dynamic drag resistance differentials between different structural configurations of a model 失效
标题翻译：用于确定模型的不同结构配置之间的小幅度流体 - 动力阻力差的方法和装置
公开(公告)号：US4532801A
公开(公告)日：1985-08-06
申请号：US611444
申请日：1984-05-17
申请人： David W. Coder , Benjamin B. Wisler, Jr. , Albert P. Clark , Raymond J. Ratcliffe
发明人： David W. Coder , Benjamin B. Wisler, Jr. , Albert P. Clark , Raymond J. Ratcliffe
IPC分类号： G01M9/06 , G01M9/08 , G01M9/00 , G01N33/00
CPC分类号： G01M9/06 , G01M9/08
摘要： A method and apparatus for determining small magnitude fluid-dynamic drag resistance differentials between different structural configurations of a variable model mounted in an environmental test facility. The variable model has disposed therein a configuration conversion mechanism to convert the variable model from a baseline configuration to a modified baseline configuration, i.e., the baseline configuration with a minor structural modification superimposed thereon, and vice versa, a nulling force mechanism to apply a nulling force to the variable model to null out the total fluid-dynamic drag resistance acting thereon, i.e., return the variable model to an undeflected position, and a system for measuring the deflections of the variable model caused by the small magnitude fluid-dynamic drag resistance differentials acting thereon. The variable model is mounted in the environmental test facility, and a predetermined fluid flow is initialized and stabilized. An initial deflection of the variable model due to the total fluid-dynamic drag resistance acting thereon is nulled out by applying the nulling force to the variable model through the nulling force mechanism. The variable model is then alternately converted to the baseline configuration and the modified baseline configuration by remote actuation of the configuration conversion mechanism, and the small magnitude fluid-dynamic drag resistance differentials acting thereon are determined by measuring the deflections of the variable model by the measuring system. The efficacy of the minor structural modification to the variable model may then be assessed by comparing the small magnitude fluid-dynamic drag resistance differentials of the different configurations.
摘要翻译：一种用于确定安装在环境测试设备中的可变模型的不同结构配置之间的小幅度流体 - 动态阻力差的方法和装置。变量模型在其中设置了配置转换机制，以将可变模型从基线配置转换为修改的基线配置，即，具有叠加在其上的次要结构修改的基线配置，反之亦然，归零力机制来应用零对可变模型施加力以消除作用在其上的总流体动力阻力，即将可变模型返回到未偏转位置，以及用于测量由小幅度流体动力阻力阻抗引起的可变模型的偏转的系统作用于其上的微分。可变模型安装在环境测试设备中，并且预定的流体流被初始化和稳定化。由于在其上作用的总流体动力阻力阻力，可变模型的初始挠度通过将零力施加到可变模型中而通过归零力机构而被消除。然后通过远程启动配置转换机制将可变模型交替地转换为基线配置和修改的基线配置，并且通过测量可变模型的偏差来测量作用在其上的小幅度流体 - 动力阻力差异系统。然后可以通过比较不同配置的小幅度流体 - 动力阻力差异来评估对可变模型的次要结构修改的功效。

86. 发明授权

US4142410A Turner-transducer system 失效
标题翻译：特纳换能器系统
公开(公告)号：US4142410A
公开(公告)日：1979-03-06
申请号：US900789
申请日：1978-04-28
申请人： John S. Pedgonay
发明人： John S. Pedgonay
IPC分类号： G01L19/00 , G01M9/06 , G01M9/00
CPC分类号： G01L19/0007 , G01M9/06
摘要： An aerodynamic-pressure transducer system for directly indicating pressure distribution around the circumference of a body to be observed, such as an ogive spinning on a test stand which may be in a wind tunnel, includes a stationary transducer mounted axially at one end of a power-rotated hollow shaft which spins with the body to be observed, and having tubular communication through the spinning hollow-shaft to a tubing fixed transversely to the hollow shaft and extending radially to the surface of the body to be observed.
摘要翻译：用于直接指示待观察体的圆周周围的压力分布的空气动力学压力传感器系统，例如可能在风洞中的测试台上的原始旋转，包括在动力的一端轴向安装的固定换能器旋转的空心轴与待观察的身体旋转，并且通过纺丝中空轴与通过横向于中空轴固定并且径向延伸到待观察的身体表面的管的管状连通。

87. 发明授权

US3382712A Wind tunnel free flight test apparatus 失效
标题翻译：风洞自由飞行试验装置
公开(公告)号：US3382712A
公开(公告)日：1968-05-14
申请号：US41990064
申请日：1964-12-21
申请人： BOEING CO
发明人： CURRY TRUMAN M
IPC分类号： G01M9/06 , G01M9/08
CPC分类号： G01M9/06 , G01M9/08 , G01N13/00

88. 发明授权

US3267720A Accelerator 失效
公开(公告)号：US3267720A
公开(公告)日：1966-08-23
申请号：US28320263
申请日：1963-05-27
申请人： NORTH AMERICAN AVIATION INC
发明人： ESCALLIER EDWARD A , SCULLY CHARLES N
IPC分类号： G01M9/02 , G01M9/04 , G01M9/06
CPC分类号： G01M9/04 , G01M9/02 , G01M9/06

89. 发明授权

US3224265A Method for determining aerodynamic influence coefficients of a wing 失效
标题翻译：确定机翼的空气动力学影响系数的方法
公开(公告)号：US3224265A
公开(公告)日：1965-12-21
申请号：US19286362
申请日：1962-05-07
申请人： AEROJET GENERAL CO
发明人： BERNARD MAZELSKY , AMEY JR HARRY B
IPC分类号： G01M9/06
CPC分类号： G01M9/06

90. 发明授权

US2952776A Means and method for the measurement of local low gas densities 失效
标题翻译：用于测量局部低气体密度的方法和方法
公开(公告)号：US2952776A
公开(公告)日：1960-09-13
申请号：US75923958
申请日：1958-09-05
申请人： ONTARIO RESEARCH FOUNDATION
发明人： SCHUMACHER BERTHOLD W , GRUEN ARNOLD E
IPC分类号： G01M9/06 , G01N21/64 , G01N23/22 , H01J41/06
CPC分类号： G01N21/6456 , G01M9/06 , G01N23/22 , G01N2223/07 , G01N2223/102 , G01N2223/104 , G01N2223/638 , H01J41/06

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