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1. 发明申请

US20100014101A1 Optics Positioning Sensor System 有权
标题翻译：光学定位传感器系统
公开(公告)号：US20100014101A1
公开(公告)日：2010-01-21
申请号：US12568211
申请日：2009-09-28
申请人： Morgan Davidson , Steven R. Wassom
发明人： Morgan Davidson , Steven R. Wassom
IPC分类号： G01B11/14 , G01P21/00
CPC分类号： G01B21/16
摘要： A method and apparatus for determining the longitudinal position of a tapered displaceable element positioned between two substantially orthogonally laterally opposing displacement sensors. A change in the longitudinal position of the displaceable element causes the sensors to each measure their distance to the displaceable element which relates directly to the local thickness and thus the longitudinal position of the displaceable element. The system factors out errors in measured lateral proximity position of the displaceable element since an erroneous proximity to one sensor is equal and opposite to an erroneous proximity to the other.
摘要翻译：一种用于确定位于两个基本上正交横向相对的位移传感器之间的锥形可移位元件的纵向位置的方法和装置。可移动元件的纵向位置的改变使得传感器各自测量它们到可移位元件的距离，其直接与局部厚度相关，并且因此与可移位元件的纵向位置有关。该系统考虑了可移位元件的测量的横向接近位置中的错误，因为与一个传感器的错误接近度与错误接近另一个传感器相等并相反。

2. 发明申请

US20080043251A1 PROXIMITY SENSOR SYSTEM 有权
标题翻译：临近传感器系统
公开(公告)号：US20080043251A1
公开(公告)日：2008-02-21
申请号：US11770666
申请日：2007-06-28
申请人： Morgan Davidson , Steven R. Wassom
发明人： Morgan Davidson , Steven R. Wassom
IPC分类号： G01B11/14 , G01P21/00
CPC分类号： G01B21/16 , G02B7/1821
摘要： A system for determining the longitudinal position of a displaceable element positioned between two substantially orthogonally laterally opposing displacement sensors measures a distance from each displacement sensor to the displaceable element. The displaceable element has a tapered thickness along its length. A change in the longitudinal position of the displaceable element causes the proximity sensors to each detect their distance to the displaceable element, which distances then correspond directly to the local thickness and thus the longitudinal position of the displaceable element. The system calculates the position of the displaceable element. The system can easily factor out errors in measured lateral proximity position of the displaceable element, since an erroneous proximity to one sensor is equal and opposite to an erroneous proximity to the other.
摘要翻译：用于确定位于两个基本上正交横向相对的位移传感器之间的位移元件的纵向位置的系统测量从每个位移传感器到可移位元件的距离。可移动元件沿其长度具有锥形厚度。可移动元件的纵向位置的改变使得接近传感器各自检测到它们到可移位元件的距离，该距离然后直接对应于局部厚度，并因此对应于可移位元件的纵向位置。系统计算可移位元件的位置。由于与一个传感器的错误接近度与错误接近另一个传感器相等并且相反，所以系统可以容易地排除所测量的可移位元件的横向接近位置的误差。

3. 发明授权

US06705075B1 Digital solid rocket motor and gas generator 失效
标题翻译：数字固体火箭发动机和气体发生器
公开(公告)号：US06705075B1
公开(公告)日：2004-03-16
申请号：US09698472
申请日：2000-10-30
申请人： Thomas K. Highsmith , Michael D. Blair , Steven R. Wassom , William D. Starrett , Joel Dever
发明人： Thomas K. Highsmith , Michael D. Blair , Steven R. Wassom , William D. Starrett , Joel Dever
IPC分类号： F02K928
CPC分类号： F02K9/10 , F02K9/24 , F02K9/28
摘要： A method and device for producing a controlled combustion by placing a combustion chamber in communication with a feed chamber that contains a solid propellant/body, introducing at least a portion of the body into the combustion chamber, isolating the combustion chamber from the feed chamber, and igniting the solid propellant in the combustion chamber while the combustion chamber is isolated from the feed chamber.
摘要翻译：一种用于通过将燃烧室与包含固体推进剂/体的进料室连通来产生受控燃烧的方法和装置，将主体的至少一部分引入燃烧室，将燃烧室与进料室隔离，并且在燃烧室与进料室隔离的同时点燃燃烧室中的固体推进剂。

4. 发明授权

US5511745A Vectorable nozzle having jet vanes 失效
标题翻译：具有喷射叶片的可向量喷嘴
公开(公告)号：US5511745A
公开(公告)日：1996-04-30
申请号：US366848
申请日：1994-12-30
申请人： Lawrence C. Faupell , Steven R. Wassom , Joseph J. Kliger
发明人： Lawrence C. Faupell , Steven R. Wassom , Joseph J. Kliger
IPC分类号： F02K1/00 , F02K9/84 , F02K9/90 , F42B10/66
CPC分类号： F02K9/90 , F02K1/008 , F02K9/84 , F42B10/665
摘要： A system for providing pitch, yaw, and roll control during the flight of a rocket-propelled vehicle combines a vectorable nozzle with jet vanes. The vectorable nozzle provides yaw and pitch control, while the jet vanes provide roll control. Anti-rotation pins extend from the vehicle housing into longitudinal slots within the vectorable nozzle to allow vectoring movements and prevent rotation of the nozzle. The jet vanes are rotatably mounted on shafts within the nozzle exit cone to receive and guide combustion products passing through the nozzle. The jet vanes may be jettisoned after an initial high-angle-of-attack maneuver is completed and the vehicle gains speed, after which roll control is provided by aerodynamic fins. The jet vanes may also be formed of material which erodes after the initial maneuver, thereby reducing the loss of thrust caused by the jet vanes.
摘要翻译：在火箭推进车辆的飞行期间提供俯仰，偏航和滚动控制的系统将可向量喷嘴与喷射叶片组合。矢量喷嘴提供偏航和俯仰控制，而喷气叶片提供滚动控制。防旋转销从车辆壳体延伸到可向量喷嘴内的纵向槽中，以允许矢量运动并防止喷嘴旋转。喷射叶片可旋转地安装在喷嘴出口锥体内的轴上，以接收和引导通过喷嘴的燃烧产物。在最初的高角度攻击机动完成之后，喷射叶片可以被抛弃，并且车辆获得速度，之后由空气动力学翅片提供滚动控制。喷射叶片也可以由在初始操纵之后腐蚀的材料形成，从而减少由喷射叶片引起的推力损失。

5. 发明授权

US08223346B2 Optics positioning sensor system 有权
标题翻译：光学定位传感器系统
公开(公告)号：US08223346B2
公开(公告)日：2012-07-17
申请号：US12568211
申请日：2009-09-28
申请人： Morgan Davidson , Steven R. Wassom
发明人： Morgan Davidson , Steven R. Wassom
IPC分类号： G01B11/14 , G01B11/26 , G01C1/00
CPC分类号： G01B21/16
摘要： A method and apparatus for determining the longitudinal position of a tapered displaceable element positioned between two substantially orthogonally laterally opposing displacement sensors. A change in the longitudinal position of the displaceable element causes the sensors to each measure their distance to the displaceable element which relates directly to the local thickness and thus the longitudinal position of the displaceable element. The system factors out errors in measured lateral proximity position of the displaceable element since an erroneous proximity to one sensor is equal and opposite to an erroneous proximity to the other.
摘要翻译：一种用于确定位于两个基本上正交横向相对的位移传感器之间的锥形可移位元件的纵向位置的方法和装置。可移动元件的纵向位置的改变使得传感器各自测量它们到可移位元件的距离，其直接与局部厚度相关，并且因此与可移位元件的纵向位置有关。该系统考虑了可移位元件的测量的横向接近位置中的错误，因为与一个传感器的错误接近度与错误接近另一个传感器相等并相反。

6. 发明授权

US07616326B2 Proximity-leveraging, transverse displacement sensor apparatus and method 有权
标题翻译：近似力，横向位移传感器装置及方法
公开(公告)号：US07616326B2
公开(公告)日：2009-11-10
申请号：US11770666
申请日：2007-06-28
申请人： Morgan Davidson , Steven R. Wassom
发明人： Morgan Davidson , Steven R. Wassom
IPC分类号： G01B11/14 , G01B11/26 , G01C1/00
CPC分类号： G01B21/16 , G02B7/1821
摘要： A system for determining the longitudinal position of a displaceable element positioned between two substantially orthogonally laterally opposing displacement sensors measures a distance from each displacement sensor to the displaceable element. The displaceable element has a tapered thickness along its length. A change in the longitudinal position of the displaceable element causes the proximity sensors to each detect their distance to the displaceable element, which distances then correspond directly to the local thickness and thus the longitudinal position of the displaceable element. The system calculates the position of the displaceable element. The system can easily factor out errors in measured lateral proximity position of the displaceable element, since an erroneous proximity to one sensor is equal and opposite to an erroneous proximity to the other.
摘要翻译：用于确定位于两个基本上正交横向相对的位移传感器之间的位移元件的纵向位置的系统测量从每个位移传感器到可移位元件的距离。可移动元件沿其长度具有锥形厚度。可移动元件的纵向位置的改变使得接近传感器各自检测到它们到可移位元件的距离，该距离然后直接对应于局部厚度，并因此对应于可移位元件的纵向位置。系统计算可移位元件的位置。由于与一个传感器的错误接近度与错误接近另一个传感器相等并且相反，所以系统可以容易地排除所测量的可移位元件的横向接近位置的误差。

7. 发明授权

US5398887A Finless aerodynamic control system 失效
标题翻译：无限空气动力学控制系统
公开(公告)号：US5398887A
公开(公告)日：1995-03-21
申请号：US134911
申请日：1993-10-12
申请人： Steven R. Wassom , Girard H. Rapp , Robert B. Smalley
发明人： Steven R. Wassom , Girard H. Rapp , Robert B. Smalley
IPC分类号： B64C19/00 , F02K1/00 , F02K9/90 , F42B10/14 , F42B10/00
CPC分类号： F02K9/90 , B64C19/00 , F02K1/008 , F42B10/14
摘要： A control system for use in missiles and other projectiles which provides pitch, yaw and roll control. The control system includes two opposing pairs of flaps configured in the aft end of the missile case. Each flap is attached for rotation about its leading edge. Prior to actuation, the flaps conform to the exterior surface of the missile. Upon actuation, the flaps extend into the airstream to induce aerodynamic forces. The axis of rotation of each flap is positioned at an oblique angle to the radial plane of the missile.
摘要翻译：用于导弹和其他射弹的控制系统，提供俯仰，偏航和滚转控制。控制系统包括配置在导弹箱的后端的两对相对的襟翼。每个翼片连接以围绕其前缘旋转。在致动之前，翼片符合导弹的外表面。在致动时，翼片延伸到气流中以引起空气动力。每个翼片的旋转轴线定位成与导弹的径向平面成倾斜的角度。

8. 发明申请

US20130036801A1 APPARATUS AND METHOD FOR MEASURING MOMENT OF INERTIA 审中-公开
标题翻译：用于测量动力学的装置和方法
公开(公告)号：US20130036801A1
公开(公告)日：2013-02-14
申请号：US13357336
申请日：2012-01-24
申请人： Bryan Bingham , Michael S. Watson , Steven R. Wassom
发明人： Bryan Bingham , Michael S. Watson , Steven R. Wassom
IPC分类号： G01M1/00
CPC分类号： G01M1/10
摘要： A method and apparatus for determining the mass moment of inertia of a given object is disclosed, The apparatus is a mass moment of inertia platform whereon objects to be measured can be placed. The platform uses flex pivots as torsional springs and the method ensures the flex pivots are procured and assembled in such a way so as to limit flex pivot misalignment systemic errors thereby resulting in a highly accurate and low-cost apparatus for measuring the mass moment of inertia.
摘要翻译：公开了一种用于确定给定物体的质量惯性矩的方法和装置。该装置是能够放置被测物体的质量惯性平台。该平台使用弯曲枢轴作为扭转弹簧，并且该方法确保弯曲枢轴以这种方式被采购和组装，以便限制挠性枢轴不对准系统误差，由此导致用于测量质量惯性矩的高精度和低成本的装置。

9. 发明授权

US4867393A Reduced fin span thrust vector controlled pulsed tactical missile 失效
标题翻译：减少的翅片跨度推力矢量控制脉冲战术导弹
公开(公告)号：US4867393A
公开(公告)日：1989-09-19
申请号：US233069
申请日：1988-08-17
申请人： Lawrence C. Faupell , Steven R. Wassom
发明人： Lawrence C. Faupell , Steven R. Wassom
IPC分类号： F42B10/64 , B64C39/02 , B64D7/08 , B64G1/00 , F42B10/60
CPC分类号： F42B10/60
摘要： A tactical pulsed missile with a movable nozzle for thrust vector control and movable aerofins to provide greater maneuverability and flexibility. The first pulse is fired at launch and the later pulses are fired as needed whereby steerage may be provided by thrust vector control during the firing of the pulses. When none of the pulses are firing, steerage may be provided by the movable aerofins. The missile is provided with separate small electromechanical actuators for each of the aerofins and each of the movable nozzle axes which are preferably placed closely adjacent the respective aerofins and nozzle so that the weight and space of various linkages may be eliminated. The motors are provided with a source of high voltage so that their size may be reduced whereby they burn up when the high voltage is applied for a short period of time but not before their task has been achieved. The fin span is reduced to less than about four inches to enable the packaging of a greater number of such tactical missiles in the payload bay of an airplane. A flexible bearing may be provided between the nozzle and nozzle housing. An elastomeric material may be provided between and bonded to the nozzle and nozzle housing to prevent the ingestion of exhaust and debris into the space therebetween.

10. 发明申请

US20090159377A1 Magnetic, Launch Lock Apparatus and Method 审中-公开
标题翻译：磁性，启动锁定装置和方法
公开(公告)号：US20090159377A1
公开(公告)日：2009-06-25
申请号：US12337919
申请日：2008-12-18
申请人： Steven R. Wassom , Morgan Davidson , Richard Sanders
发明人： Steven R. Wassom , Morgan Davidson , Richard Sanders
IPC分类号： B60L7/00
CPC分类号： B64G1/283 , B64G1/22 , B64G1/285 , B64G1/286
摘要： An apparatus for securing movable elements of a multiple-axis drive mechanism with respect to the fixed base thereof during launch to prevent damage while unpowered. Mating surfaces of the lock secure the mechanism about all three axes of motion. Thus, the drives need to be only sufficiently designed to break free one element of the launch lock from the other element. Tapered or other guiding surfaces of the two elements of the launch lock make it self-aligning, such that mating surfaces are guided together once placed in sufficiently close proximity.
摘要翻译：一种用于在发射期间相对于其固定基座固定多轴驱动机构的可移动元件的装置，以防止损坏而无动力。锁的接合表面固定所有三个运动轴的机构。因此，驱动器仅需要被充分地设计成将启动锁的一个元件与另一个元件断开。发射锁的两个元件的锥形或其他引导表面使其自对准，使得一旦放置在足够接近的位置，配合表面被引导在一起。

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