公开(公告)号：US20090242702A1

公开(公告)日：2009-10-01

申请号：US12359064

申请日：2009-01-23

申请人： Alan B. Cain ,  Eric J. Jumper ,  Donald J. Wittich, III ,  Edward J. Kerschen ,  David Cavalieri ,  T. Terry Ng

发明人： Alan B. Cain ,  Eric J. Jumper ,  Donald J. Wittich, III ,  Edward J. Kerschen ,  David Cavalieri ,  T. Terry Ng

IPC分类号： B64C1/00 ,  B64D7/00 ,  B64C1/14 ,  G06F19/00 ,  B23P11/00

CPC分类号： B64C23/06 ,  B64C7/00 ,  B64D7/06 ,  F41H13/0043 ,  F41H13/005 ,  F41H13/0068 ,  Y02T50/162 ,  Y10T29/49826

摘要： An aircraft turret and fairing assembly for facilitating transmission of a directed energy beam from a directed energy device includes a turret section for directing an energy beam. The assembly also includes a fairing section aft of and adjacent to the turret section. Each of the turret section and the aft fairing section are coupled to an aircraft. The assembly also includes at least one sensor for detecting air speed of the aircraft and air pressure. The turret section and the aft fairing section are configured and positioned relative to one another to direct airflow for generating an aeroacoustic resonance within a desired frequency range in an area aft of the turret section.

摘要翻译： 用于促进定向能量装置的定向能量束的传输的飞机转台和整流罩组件包括用于引导能量束的转台部分。 组件还包括在转塔部分的后部和后部的整流罩。 每个转塔段和后整流装置联接到飞行器。 组件还包括用于检测飞行器的空气速度和空气压力的至少一个传感器。 转台部分和后整流装置相对于彼此构造和定位，以引导气流，以在转台部分的后部区域内的期望频率范围内产生气动共振。

公开(公告)号：US08096507B2

公开(公告)日：2012-01-17

申请号：US12359064

申请日：2009-01-23

申请人： Alan B. Cain ,  Eric J. Jumper ,  Donald J. Wittich, III ,  Edward J. Kerschen ,  David Cavalieri ,  T. Terry Ng

发明人： Alan B. Cain ,  Eric J. Jumper ,  Donald J. Wittich, III ,  Edward J. Kerschen ,  David Cavalieri ,  T. Terry Ng

IPC分类号： B64C1/38 ,  B64D7/00

CPC分类号： B64C23/06 ,  B64C7/00 ,  B64D7/06 ,  F41H13/0043 ,  F41H13/005 ,  F41H13/0068 ,  Y02T50/162 ,  Y10T29/49826

摘要： An aircraft turret and fairing assembly for facilitating transmission of a directed energy beam from a directed energy device includes a turret section for directing an energy beam. The assembly also includes a fairing section aft of and adjacent to the turret section. Each of the turret section and the aft fairing section are coupled to an aircraft. The assembly also includes at least one sensor for detecting air speed of the aircraft and air pressure. The turret section and the aft fairing section are configured and positioned relative to one another to direct airflow for generating an aeroacoustic resonance within a desired frequency range in an area aft of the turret section.

摘要翻译： 用于促进定向能量装置的定向能量束的传输的飞机转台和整流罩组件包括用于引导能量束的转台部分。 组件还包括在转塔部分的后部和后部的整流罩。 每个转塔段和后整流装置联接到飞行器。 组件还包括用于检测飞行器的空气速度和空气压力的至少一个传感器。 转台部分和后整流装置相对于彼此配置和定位，以引导气流，以在转台部分的后部区域内的期望频率范围内产生气动共振。

公开(公告)号：US07880125B1

公开(公告)日：2011-02-01

申请号：US12077447

申请日：2008-03-19

申请人： Mehul Patel ,  T. Terry Ng ,  Alan B. Cain ,  Zak Sowle ,  Jack DiCocco

发明人： Mehul Patel ,  T. Terry Ng ,  Alan B. Cain ,  Zak Sowle ,  Jack DiCocco

IPC分类号： F42B15/01

CPC分类号： F42B10/64 ,  F41G7/20 ,  F42B3/006 ,  F42B10/02 ,  F42B15/00 ,  F42B15/01 ,  F42B15/36 ,  F42B19/01

摘要： The present invention relates to an aircraft, missile, projectile, or underwater vehicle with an improved control system and an improved control system for maneuvering an aircraft, missile, projectile, or underwater vehicle. More particularly, the present invention relates to an aircraft, missile, underwater vehicle or projectile with removable control surfaces. The technical advantage of the removable control surface system (or “removable control surface”) over other systems is that the removable control surface system enables the aircraft, missile, underwater vehicle or projectile to have two or more design configurations, each configuration being tailored to the aircraft, missile, projectile, or underwater vehicle's specific stability or maneuverability requirements during a specific portion of the flight.

摘要翻译： 本发明涉及具有改进的控制系统的飞机，导弹，射弹或水下航行器，以及用于操纵飞机，导弹，射弹或水下航行器的改进的控制系统。 更具体地，本发明涉及具有可移除控制表面的飞机，导弹，水下航行器或射弹。 可移动控制表面系统（或“可移除控制表面”）在其他系统上的技术优点是可移动控制表面系统使得飞机，导弹，水下航行器或射弹能够具有两个或多个设计配置，每个配置被定制为 飞机，导弹，射弹或水下航行器在特定部分飞行过程中的具体稳定性或机动性要求。

公开(公告)号：US07709772B1

公开(公告)日：2010-05-04

申请号：US11292972

申请日：2005-12-02

申请人： Mehul Patel ,  T. Terry Ng ,  Alan B. Cain ,  Zak Sowle ,  Jack DiCocco

发明人： Mehul Patel ,  T. Terry Ng ,  Alan B. Cain ,  Zak Sowle ,  Jack DiCocco

IPC分类号： F42B15/01

CPC分类号： F42B10/64 ,  F41G7/20 ,  F42B3/006 ,  F42B10/02 ,  F42B15/00 ,  F42B15/01 ,  F42B15/36 ,  F42B19/01

摘要： The present invention relates to an aircraft, missile, projectile, or underwater vehicle with an improved control system and an improved control system for maneuvering an aircraft, missile, projectile, or underwater vehicle. More particularly, the present invention relates to an aircraft, missile, underwater vehicle or projectile with removable control surfaces. The technical advantage of the removable control surface system (or “removable control surface”) over other systems is that the removable control surface system enables the aircraft, missile, underwater vehicle or projectile to have two or more design configurations, each configuration being tailored to the aircraft, missile, projectile, or underwater vehicle's specific stability or maneuverability requirements during a specific portion of the flight.

摘要翻译： 本发明涉及具有改进的控制系统的飞机，导弹，射弹或水下航行器，以及用于操纵飞机，导弹，射弹或水下航行器的改进的控制系统。 更具体地，本发明涉及具有可移除控制表面的飞机，导弹，水下航行器或射弹。 可移动控制表面系统（或“可移除控制表面”）在其他系统上的技术优点是可移动控制表面系统使得飞机，导弹，水下航行器或射弹能够具有两个或多个设计配置，每个配置被定制为 飞机，导弹，射弹或水下航行器在特定部分飞行过程中的具体稳定性或机动性要求。

公开(公告)号：US09541106B1

公开(公告)日：2017-01-10

申请号：US11710750

申请日：2007-02-26

申请人： Mehul Patel ,  Thomas Corke ,  Alan B. Cain

发明人： Mehul Patel ,  Thomas Corke ,  Alan B. Cain

IPC分类号： B64C29/00 ,  F15D1/00 ,  B64C21/00

CPC分类号： F15D1/0065 ,  B64C15/14 ,  B64C21/00 ,  B64C2230/12 ,  F15D1/0075 ,  Y02T50/166

摘要： The present invention relates to a method of designing or optimizing a control surface for use with plasma actuators for controlling an aircraft, missile, munition or automobile, and more particularly to controlling fluid flow across their surfaces or other surfaces using plasma actuators, which would benefit from such a method. The various embodiments provide the steps to increase the efficiency of aircraft, missiles, munitions and automobiles. The method of flow control also provides a means for reducing aircraft, missile's, munition's and automobile's power requirements. These methods also provide alternate means for aerodynamic control using low-power hingeless plasma actuator devices.

摘要翻译： 本发明涉及一种设计或优化用于控制飞机，导弹，弹药或汽车的等离子体致动器的控制表面的方法，更具体地涉及使用等离子致动器来控制流过其表面或其它表面的流体，这将有利于 从这样的方法。 各种实施例提供了增加飞机，导弹，弹药和汽车的效率的步骤。 流量控制方法还为减少飞机，导弹，弹药和汽车的电力需求提供了手段。 这些方法还提供了使用低功率无铰链等离子体致动器装置的空气动力学控制的替代方法。

公开(公告)号：US20160327448A1

公开(公告)日：2016-11-10

申请号：US15146805

申请日：2016-05-04

申请人： Alan B. Cain ,  Stanislav Gordeyev ,  R. Mark Rennie

发明人： Alan B. Cain ,  Stanislav Gordeyev ,  R. Mark Rennie

IPC分类号： G01M9/06 ,  G01F1/66

CPC分类号： G01F1/661 ,  G01M9/065 ,  G01M9/067

摘要： An “air-data probe” system measures at least one component of freestream velocity by tracking the motion of a laser-induced breakdown (“LIB”) spark created in a freestream flow. Neutral density filters are positioned or deployed so that the brightness of the initial LIB spark doesn't over saturate the LIB sensor system. This allows for more consistent tracking of the LIB spark throughout the duration of the LIB spark, including the later stages where the LIB spark is not nearly as bright as the initial LIB spark, thereby allowing all or substantially all of the light generated by the LIB spark to reach the sensors. This provides for enhanced visibility and more accurate detection of the LIB spark over time and as air density changes.

摘要翻译： “空气数据探测器”系统通过跟踪在自由流中产生的激光诱发击穿（“LIB”）火花的运动来测量自由流速度的至少一个分量。 中性密度过滤器定位或展开，使得初始LIB火花的亮度不会使LIB传感器系统饱和。 这允许在LIB火花的整个持续时间内对LIB火花进行更一致的跟踪，包括LIB火花不如初始LIB火花那样明亮的后期阶段，从而允许由LIB产生的全部或基本上全部的光 火花到达传感器。 这提供了随着时间的推移增加了LIB火花的可视性和更精确的检测，随着空气密度的变化。